Version 1.0 Outline Preliminary Design Review (PDR) · PDF filePreliminary Design Review (PDR) Outline Version 1.0 IPN ... Mission Operations Manual • SOE - Sequence of Events

CanSat 2017 PDR: Team #6621 Cuauhtémoc 1

CanSat 2017 Preliminary Design Review (PDR)

Outline Version 1.0

IPNCuauhtémoc


Presentation Outline

– Systems Overview [##] - Sebastián López– Sensor Subsystem Design [##] - Alejandro Muñoz– Descent Control System - Sebsatián López– Mechanical Subsystem Design - Javier Sánchez– Communication and Data Handling - Alejandro Muñoz– Electrical Power Subsystem Design - Gabriel C.– Flight Software Design - Gabriel Carrasquero– Ground Control System - Tomás Guerrero– Cansat Integration and Test - Javier Sánchez– Mission Operations and Analysis - Sebastián López– Requirements Compliance - Sebastián López– Management - Sebastián López

Presenter: Sebastián López

CanSat 2017 PDR: Team #6621 Cuauhtémoc

Team Organization

3

Team Lead:Sebastián López

Sophomore

Faculty Advisor:MSc Héctor Díaz

Cansat Mentor:Alessandro Geist

Irving LópezSenior

Mechanical Team:

Bruno MartínezSenior

Javier SánchezJunior

Cecilia PrimeroSophomore

Gabriel C.Sophomore

Alejandro MuñózFreshman

Electrical Team:

Tomás GuerreroFreshman

Martín MarcelinoSophomore

Alexis GallegosFreshman



Acronyms

• CDH - Command and Data Handling (also C&DH)• EPS - Electrical Power Subsystem• FSW - Flight Software• GCS - Ground Control Station• GS - Ground Station• GUI - Graphical User Interface• SBO - Selectable Bonus Objective• A - Analysis• D - Demonstration• I - Inspection• T - Tests• M1 - First Mechanical Division (Mechanical Subsystem)• M2 - Second Mechanical Division (Descent Control)• E1 - First Electrical Division (CDH GCS FSW & Sensors)• E2 - Second Electrical Division (EPS)• VM - Verification Method• MOM - Mission Operations Manual• SOE - Sequence of Events• RP&T - Retrieve, process and trasmit



Systems Overview

Sebastián López


Mission Summary

• Sample the atmosphere using a cansat which consists of a container and a solar powered sensor payload glider.

• The container is meant to protect the glider from the violent deployment and provide a more stable and less forceful release environment.

• The glide shall be in a circular pattern with a diameter of no more than 1000 meters.

• Data of heading, altitude and speed, among others, shall be transmitted to the GS via XBEE through one packet each second.

• When the science vehicle lands, transmission shall automatically stop and an audio beacon shall be activated automatically for recovery

• The SBO of adding a color camera with a minimum resolution of 640x480 pixels to take images of the ground as often as possible is going to be attempted.



# Requirement Rationale Priority ChildrenVM

A I T D

System Requirements Summary

7

1Total mass of the CanSat (container and payload) shall be 500 grams +/- 10 grams.

Competition Requirement - High impact on FRR Score

HIGH M1 x x

2

The glider shall be completely contained in the container. No part of the glider may extend beyond the container. One circular end of the cylindrical container may be open (no door enclosure is required); however, the glider may not extend outside the container.


HIGH M1 x x

3

Container shall fit in a cylindrical envelope of 125 mm diameter x 310 mm length including the container passive descent control system. Tolerances are to be included to facilitate container deployment from the rocket fairing.

Competition Requirement - PASS/FAIL Requirement

HIGH M1 x x

4The container shall use a passive descent control system. It cannot free fall. A parachute is allowed and highly recommended. Include a spill hole to reduce swaying.

Competition Requirement - Mission Integrity

HIGH M2 x

7The rocket airframe shall not be used to restrain any deployable parts of the CanSat.

Competition Requirement HIGH M1 x x




A I T D

8


8The rocket airframe shall not be used as part of the CanSat operations.

Competition Requirement HIGH M1 x x

9The CanSat (container and glider) shall deploy from the rocket payloadsection.

Competition Requirement HIGH M1 x

10The glider must be released from the container at 400 meters +/- 10 m.

Competition Requirement - High impact on Launch Ops

ScoreHIGH M1 E1 x x

11

The glider shall not be remotely steered or autonomously steered. It must be fixed to glide in a preset circular pattern of no greater than 1000 meter diameter. No active control surfaces are allowed.

Competition Requirement - High impact on Launch Ops

ScoreHIGH M2 x x

12All descent control device attachment components shall survive 30 Gs of shock.

Competition Requirement - High impact on FRR Score &

Mission IntegrityHIGH M1 x x

13 All descent control devices shall survive 30 Gs of shock.Competition Requirement -

High impact on FRR Score & Mission Integrity

HIGH M1 x x

15 All structures shall be built to survive 15 Gs acceleration.Competition Requirement -


HIGH M1 x x

16 All structures shall be built to survive 30 Gs of shock.Competition Requirement -


HIGH M1 x x




A I T D


9

17All electronics shall be hard mounted using proper mounts such as standoffs, screws, or high performance adhesives.


Mission IntegrityHIGH M1 E2 x x

18All mechanisms shall be capable of maintaining their configuration or states under all forces.


Mission IntegrityHIGH M1 x x

21

During descent, the glider shall collect air pressure, outside air temperature, compass direction, air speed and solar power voltage once per second and time tag the data with mission time.

Competition Requirement - High impact in scores

HIGH E1 x x

22During descent, the glider shall transmit all telemetry. Telemetry can be transmitted continuously or in bursts.


HIGH E1 x x

27

The glider electronics must be all solar powered except for the time keeping device which may use a coin cell battery. No batteries are allowed. Supercapacitors are allowed and must be fully discharged at launch.

Competition Requirement - PASS/FAIL Requirement

HIGH E1 E2 x x

30 All telemetry shall be displayed in real time during descent.Competition Requirement -

High impact on Launch Ops & PFR Score

HIGH E1 x x x




A I T D


10

32

Teams shall plot each telemetry data field in real time during flight. In addition, the ground system shall display a two dimensional map of estimated glider position based on speed and heading telemetry data.

Competition Requirement - High impact on Launch Ops &

PFR ScoreHIGH E1 x x x

36

The flight software shall maintain a count of packets transmitted, which shall increment with each packet transmission throughout the mission. The value shall be maintained through processor resets.

Competition Requirement HIGH E1 x x x

38

The glider must include an easily accessible power switch which does not require removal from the container for access. Access hole or panel in the container is allowed.


HIGH M1 E1 E2

x x

39The container shall contain electronics and mechanisms to release the glider at the required altitude.

Competition Requirement - Mission Integrity

HIGH M1 E1 E2

x x x

40The container electronics shall be powered by only alkaline batteries.


HIGH E2 x x

41 The glide duration shall be as close to 2 minutes as possible. Competition Requirement - High impact on FRR Score

HIGH M2 x x




A I T D


11

42

The CanSat container shall have a payload release override command to force the release of the payload in case the autonomous release fails.


HIGH M1 E1 x x

44

The glider shall use a timekeeping device to maintain mission time. The time keeping device can use a small coin cell battery.

Competition Requirement HIGH E1 x x

46

The container shall transmit telemetry from the time being turned on and placed on the launch pad until 2 seconds after releasing the glider.

Competition Requirement HIGH E1 E2 x x

47The container telemetry shall be transmitted once per second.


48

The container telemetry shall include team number, indication of container telemetry, altitude, temperature and software state


51 A camera to take images of the ground as often as possible. SBO - High impact in Launch Ops score

HIGH E1 E2 M1

x x




A I T D


12

52A count of the number of pictures must be kept and included in the telemetry. Images do not get transmitted.

SBO - High impact in Launch Ops score

HIGH E1 x

53The camera must be powered by the same solar source as the glider electronics.


HIGH E2 x x

57 C&DH Startup time management.Packet transmission time

opening and pictures taken are crucial

HIGH E2 x x

58 Power budget. Competition Requirement - Mission Integrity

HIGH L E2 x

59 The range of the transmitter shall be optimal. Mission Inegrity HIGH E1 x x

61 The altitude sensor should have one meter resolution. Competition Requirement - Mission Integrity R# 10

HIGH E1 x x

64 At least 20 Images should be taken during flight SBO - High impact in Launch Ops score

HIGH E1 E2 x x



System Level CanSat Configuration Trade & Selection

High wing conventional glider

Delta wing glider

● Hight lift and minimal drag● Relatively easy to design ● Large available surface for

solar power● Little Stability ● High complexity construction

and deployment considering solar cells.

● Good Stability and lift.● Regular complexity of

construction and design.● Optimal surface for solar power.● Lots of design references.


CanSat 2017 PDR: Team #6621 Cuauhtémoc 14Presenter: Sebastián López

System Level CanSat Configuration Trade & Selection

* In the end we opted for a Arduino Nano in the Glider and a MS5803 and BMP180 as Pressure sensors in container.


Physical Layout

15

CanSat Launch & Container Configuration:

- At every step the dimensions of the rocket fairing and the volume available were taken into consideration, clearances are included.

- In the container, the electronics volume is represented by a brown box.

- The semi-spherical parachute can be appreciated.

- Container and glider will be labeled with the team contact information including email address.



Physical Layout

16

Glider lateral dimensions (mm):


*Preliminary dimensions


Physical Layout

17

Deployed glider from top:

● Solar panels are placed on the wings and on top of the horizontal stabilizers extrados as well.

● Electronics are placed in the fuselage. A pressure sensor is placed at the front and another on the side, both protected from the sun’s radiation. The C&DH components are enclosed in the fuselage.

● The camera will be placed on the bottom of the fuselage, facing down and close to the center of gravity.


*Wing measurements changed


System Concept of Operations

Pre Launch:• FRR • Cansat is turned on• Cansat is placed in the

rocket• Cansat is taken to Launch

Site• GCS is turned on

18

Launch:• Data collected is analyzed

to detect deployment• Near Apogee Deployment• SW state: Launch

Container Deployment:

• Container descent strategy active

• SW state: Deployed• Container continues to

send telemetry data.




Glider Deployment:• Release mechanism

activates in order to deploy at 400m

• The glider unfolds and starts stable flight

• The container continues to transmit telemetry for 2 seconds

19

Glider Flight:• Glider powers on from

solar energy and starts transmission and taking pictures

• Glider flies on a helical pattern with a radius of no more than 500 meters for about 2 minutes

Recovery• Glider and container stop

transmission and activate buzzer

• Team locates the CanSat with binoculars

• Images from the CanSat are retrieved




400m

800mE



Launch Vehicle Compatibility

• The container will be introduced faced down in the rocket’s payload section to guarantee an easier deployment.

• The descent control mechanism consists of the parachute, strings to attach the parachute to the container, tubes to fill the container with air in the stipulated height and release the parachute.

• The container dimensions are 121 mm of diameter and 310 mm of height.

• The clearance between the container and the rocket’s walls is of 2mm.

• No part of the cansat system extends beyond this volume.

• There will be an accessible power switch in the tail of the glider.

21


Sensor Subsystem Design

Alejandro Muñoz


Sensor Subsystem Overview

23Presenter: Alejandro Muñóz


Sensor Subsystem Requirements

# Requirements Rationale Priority ChildrenVM

A I T D

37 No lasers allowed Competition Requirement LOW E1 x

61 The altitude sensor should have one meter resolution.Competition Requirement - Mission Integrity R# 10

HIGH E1 x x

62The sensed temperature should be in degrees C with one degree resolution

Competition Requirement MEDIUM E1 x x

64 At least 20 Images should be taken during flightSBO - High impact in

Launch Ops scoreHIGH E1 x x

Presenter: Alejandro Muñóz


Magnetometer Trade & Selection

Magnetometer Operating Voltage (V)

Current Working

(mA)Interface Dimensions

(mm)Resolution

(milli-gauss)Cost

($dlls)

IM120710016 3.5 - 5 0.043 Grove (24, 21, 1.6) 2.6 2.90

HMC5883L 2.16 - 3.6 0.1 12C (3, 3, 0.9) 5 3.49

BMX055 2.4 - 3.6 0.13 I2C / SPI (3, 4.5, 0.95) 3 3.75

MagnetometerChosen Rationale

HMC5883L

◘ Small Size for Highly Integrated Product◘ Low Voltage Operations and Low Power Consumption◘ Popular Two-Wire Serial Data Interface for Consumer Electronics◘ Easy to get and compatible with Arduino◘ Can Be Used in Strong Magnetic Field Environments with a 1° to 2° Degree Compass Heading Accuracy HMC5883L



Payload Air Pressure Sensor Trade & Selection

Air Pressure Sensor

Operating Voltage (V)

Current Working

(µA)Interface Dimensions

(mm)Pressure Range

(kPa) Cost ($dlls)

Pololu AltImu 2.2 - 5.5 6 I2C 25,13,2 1.3 - 8.1 22.311

BMP180 1.8 - 3.6 5 I2C 3.6, 3.8, 0.93 0.3 - 1.1 9.95

MPXV7002 4.75 - 5.25 10 I2C 0.7, 0.6, 0.2 -2.0 - 2.0 16

SensorChosen Rationale

BMP180

◘ Low weight and small size ◘ Increased sampling rate ◘ Very Low Voltage Operations and Low Power Consumption ◘ Low noise in measurements◘ Low price◘ High altitude accuracy◘ Includes temperature sensor and altimeter that will be used as well

BMP180



Container Air Pressure Sensor Trade & Selection

Air Pressure Sensor


Current Working

(µA)Interface Cost ($dlls) Dimensions (mm) Pressure Range

(kPa)

BMP180 1.8 - 3.6 5 I2C 9.95 3.6, 3.8, 0.93 0.3 - 1.1

MPXV7002 4.75 - 5.25 10 I2C 16 0.7, 0.6, 0.2 -2.0 - 2.0

MS5803 1.8 - 3.6 0.0125 SPI / I2C 24.83 6.4,6.2,2.88 0.1 - 1.3


BMP180 & MS5803

◘ Low weight and small size ◘ Increased sampling rate ◘ Very Low Voltage Operations and Low Power Consumption ◘ Low noise in measurements◘ Low price◘ Includes temperature sensor and altimeter that will be used as well◘ Two different temperture / pressure sensors will be used to have a better accuracy

BMP180


MS5803


Payload Pitot Tube Trade & Selection

Pitot Tube Model


Current Working


(mm) Resolution (Pa) Cost ($dlls)

Airspeed Kit with MPXV7002DP 0.5 - 4.5 10 I2C 0.7, 0.6, 0.2 3,920 26.56

BMP180 1.8 - 3.6 5 I2C 3.6, 3.8, 0.93 30,000-110,000 9.95


BMP180Putting two BMP180 sensors (one in the front and one on the side) we can calculate the air speed with the difference of the sensed pressures, simulating the pitot tube and achieving a better management and thrift of electrical power, costs and weight.

BMP180



Payload Air Temperature Sensor Trade & Selection

Air Temperature

Sensor


Current Working


(mm)

Operating Temperature (°

C)

Temperature Resolution (°

C)Cost ($dlls)

BMP180 1.8 - 3.6 5 I2C 3.6, 3.8, 0.93 -40 - 80 0.01 9.95

LM35 4 - 30 10 I2C 4.7, 4.9, 3.65 -55 - 15 0.5 2

SHT21 3 0.2 I2C 3.0, 3.0, 1.1 -40 - 1250.01 (14 bit) 0.04 (12bit)

3.5


BMP180

◘ Low weight and small size ◘ Increased sampling rate ◘ Very Low Voltage Operations and Low Power Consumption ◘ Low noise measurements◘ Reasonable price◘ High accuracy (temperature resolution)◘ Includes barometric pressure sensor and altimeter that will be used aswell

BMP180



Container Air Temperature Sensor Trade & Selection

Air Temperature

Sensor


Current Working


(mm)

Operating Temperature (°

C)

Temperature Resolution (°

C)Cost ($dlls)

BMP180 1.8 - 3.6 5 I2C 3.6, 3.8, 0.93 -40 - 80 0.01 9.95

MS5803 1.8 - 3.6 0.0125 SPI / I2C 6.4,6.2,2.88 -40 - 85 <0.01 24.83

SHT21 3 0.2 I2C 3.0, 3.0, 1.1 -40 - 1250.01 (14 bit) 0.04 (12bit)

3.5

Presenter: Alejandro Muñóz 30


BMP180 & MS5803

◘ Low weight and small size ◘ Increased sampling rate ◘ Very Low Voltage Operations and Low Power Consumption ◘ Low noise in measurements◘ Low price◘ Includes temperature sensor and altimeter that will be used as well◘ Two different temperture / pressure sensors will be used to have a better accuracy

BMP180

MS5803


Payload Solar Power Voltage Sensor Trade & Selection

Voltage Sensor Operating Voltage (V)

Current Working (mA) Interface Dimensions

(mm) Cost ($dlls)

Arduino Nano - voltage divider

5 20 per pin UART

SPII2C

JTAG

18,48 19.19

ZMPT101B 3.3 - 5 2 I2C 19.5, 17, 19.5 5.08



◘ Does not require extra space since it is integrated in Arduino◘ Less voltage and power consumption◘ Low cost◘ Good accuracy◘ Simple implementation from the circuit

Circuit



Container Battery Voltage Sensor Trade & Selection

Voltage Sensor Operating Voltage (V)

Current Working (mA) Interface Dimensions

(mm) Cost ($dlls)


5 20 per pinUART SPII2C

JTAG

18,45 36.61

ZMPT101B 3.3 - 5 2 I2C 19.5, 17, 19.5 5.08

Circuit



◘ Does not require extra space since it is integrated in Arduino◘ Less voltage and power consumed◘ Low cost◘ Good accuracy◘ Simple implementation from the circuit



Bonus Camera Trade & Selection

Camera Model

Operating Voltage

(V)

Current Working

(mA)

Dimensions (mm)

Output formats

Pixel Size (μm)

Image size (Resolution)

Cost ($dlls)

Adafruit TTL serial JPEG

camera ID: 397

5 75 32 x 32Standard

JPEG5.6 x 5.6 VGA (640 x 480) 39.95

Omnivision OV7670

2.45 - 3 10 37 x 42

YUV/YCRGBGRB

Raw RGB

3.6 x 3.6 VGA (640 x 480) 16.25

CameraChosen Rationale

Omnivision OV7670

◘ Low operating voltage and current working◘ Standard SCCB interface compatible with I2C interface◘ Supports VGA, CIF and resolution lower than CIF for RGB that will help to manage power consumption◘ Includes automatic image control functions◘ Low price◘ Easy to get

Omnivision OV7670



Descent Control Design

Sebastián López


Descent Control Overview

Container• Uses an octogonal parachute of nylon with a surface

of 0.345m^2 with a spill hole of 0.129m of diameter. • The container will be of fiberglass and will have the

dimensions that stipulate the requirements minus the clearance ( 310mm of length and 121mm diameter).

Glider• The glider will be released in free fall at 811 meters

absolute altitude (400 meters over the ground) from the container.

• It will glide for approximately 2 minutes in a helical path with a diameter smaller than 1000m.

• It will have a fixed high wing configuration with common empennage (vertical and horizontal stabilizer).


CanSat 2017 PDR: Team #6621 Cuauhtémoc IPN 36

Descent Control Requirements


Container requirements :Description Requirement number of

the competition guide

The container has the following dimensions: 125mm in diameter and 310 in length

3

Use a parachute like passive descent method after separation from rocket

4

The edges of the container will be smoothed to prevent it from being hit by the rocket

5

The color of the container must be fluorescent for easy viewing, it can be orange or pink.

6

The structure of the cansat, as well as its mechanisms of liberation and operation completely independent of the rocket 7,8

Made to withstand 30G impact 12,13,15,16



Glider requirements:Description Requirement number of

the competition guide

The dimensions will be designed with the purpose of generating the necessary support with the least drag possible to counter the weight of the glider, this weight added to that of the container should not exceed 500g.

1

In addition the glider must be able to be stored inside the container without leaving it, it is considered to use a folding mechanism for this purpose.

2

The glider will be launched at 400 meters from the launch site. 10

The glider will be designed so that throughout its descent its surfaces remain static. DO NOT use any control surface.

11

The structure of the canMade to withstand 30G impactsat, as well as its mechanisms of liberation and operation completely independent of the rocket

12,13,15,16





CanSat 2017 PDR: Team #6621 Cuauhtémoc IPN

Container Descent Control Strategy Selection and Trade

•Parachute shape selection

39

Options advantages and disadvantages

Chosen Reason Preview

Square ❑ Easy construction

❑ High Drag

Octagon

These forms were considered because they are the most common among parachutes. The octagonal form is the one that provides the least resistance so it was chosen, The circle was not considered because of the large number of threads needed to maintain its shape, which may cause them to get entangled

Hexagon ❑ Easy Construction

❑ Less Drag

Ocatgon ❑ Easy Construction

❑ Considerable reduction of drag




Chosen Reason Example

Cardboard Is the cheapest option and has a great lightness, but is very fragile

NylonProvides the best mechanical resistance, and its cost isn´t high.

Nylon Great lightness, good mechanical resistance and its cost is not so high. Is the most used option in rocketry

Plastic Great lighteness,its cost isn´t so high, but is very elastic, it can cause a problem and change with the temperature.

Container Descent Control Strategy Selection and Trade (Continue)

•Parachute materials




•Color

41

Options Advantages and Disadvantages

Chosen Reason Preview

Orange Provides good visibility from far

Pink

By offering both options the same advantages by means of a vote among the team members, the color was determined.

Pink Provides good visibility from far





Acrylic ❑ Density of 1.18 gm / cm3 ❑ High impact resistance ❑ It can be given various forms

Fiberglass

Provides the best strength to weight ratio and its construction is the easiest.

Carbon Fiber ❑ Excellent mechanical properties.

❑ Extremely light❑ Expensive ❑ Difficult manufacture

Fiber glass ❑ High impact resistance❑ Lighter❑ Structural elaboration is

more complex.


•Shock Force Endurance




43

Preflight review testability



DCS connections

● Kevlar cord will be used to support the container during descent, with a separation of about 60cm, which will be attached to a ring or knot to achieve a better vertical stability and pendulum length.

● The container holes attached to the parachute will be reinforced if deemed necessary.


*Testing will be done to demonstrate compliance with resistance requirements.



Payload Descent Control Strategy Selection and Trade

Configuration Type

•Shock force Survival

45



Flying wing ❑ Hight lift and negligible drag❑ Easy Design and

Construction❑ Bad Stability

Conventional Glider

It provides us with the necessary characteristics to meet the requirements without involving more complexity

Canard ❑ Hight stability at slow velocities and good lift

❑ Complexity of construction: Medium

❑ High complexity of design

Conventional Glider

❏ Good Stability and lift❏ Complexity of construction

and design: Medium




Wing Dimensions

Two designs were made, the first with a weight of 300g and the second with a weight of 180g and a proposed Aspect ratio of 14.5. In both cases, the same methodology was followed. The common wing load for a glider is 10-15 kg / m2 and knowing the weight we calculate the wing surface. In the first case we had an estimate of the chord according to the solar cells(2.5c that would be placed in the wing, after calculating the wingspan and then the Aspect Ratio. In the second case with an Aspect Ratio of 14.5 the wing span was determined and finally the chord.

46Presenter: Sebastián López


First glider prototypes and proof of concept:

47





Shock Force Endurance

48



Fiberglass ❑ High impact resistance

❑ Greater lightness.❑ Structural elaboration

complexity is medium.

Fiberglass and Balsa

The fiberglass provides a great strength and weight ratio, however its construction for complex forms like an airfoil is very difficult, reason for using balsa in the wing.

Balsa ❑ Greater ease in construction

❑ Low cost. ❑ Its mechanical

properties are lower

Carbon Fiber ❑ Excellent mechanical properties.

❑ Extremely light❑ More expensive ❑ Difficulty building




Airfoil Selection

49

NASA/Langley LS(01) 0413-MOD Naca 25112 FX 63-137

With the help of several iterations we decided the optimal speed to be 20m/s. Given the wing dimensions and velocity we get an optimal Cl of 0.46. With this and the reynolds number in mind we chose the NACA 25112 due to its high stability, good aerodynamic efficiency and optimal lift generation.



Container Descent Rate Estimates

50

It is considered that the container, after releasing the glider, should have a lower descent speed than the glider. So it was proposed the mass of the container plus the mass of glider" (m_(C+G))=500g (320g+180g)

It is proposed that the parachute falls with a constant velocity (V) of 3 m/s

The drag coefficient (CD) is 0.75

Density (ρ) 1.077 kg / ^3

It is considered that the parachute can not have a completely circular shape. So we chose an octogonal shape that is the easiest to build and has a good aerodynamic quality because of its similarity to the circle. According to design recommendations, it is suggested that the spill hole diameter (SHD) be 20% of the diameter.

Calculations

The required diameter will be calculated for an area that provides a constant speed with the required weight, then the descent rate (VC) is calculated after the glider has been released, with a mass (mC)=200g

Ap =(2*g*m_(C+G))/(ρ*Cd *V^2 )=0.345 m^2 VC=√((2*mC*g)/(ρ*CD*AP ))=4.6m/s

d=√(4*Ap/(n*tan(180/8)))=0.645 m SHD=0.2*1.2527m=0.129m



Payload Descent Rate Estimates

Wing Assumptions• As mentioned in the previous slide, the total mass of the final glider (MG) will be 180 g.• The Wing load (WL) is 10-15Kg / m2. So the calculations with different values of wing load

were made until we chose one.• In order to comply with the 2 minutes in the descent, the glider must have a vertical Speed

(VS) =3.3 m / s• For the first proposal we had the chord ©, we calculated the wingspan (b) and the aspect

ratio (AR), and for the second we proposed an aspect ratio=14.5.


Formulas A=W/WL; A=b*C; AR=b^2/A ; Wing Estimation


Descent Rate Estimates Glider

52

• It is considered that the glider will be released at 400m.• To calculate the speed of the glider first we needed the total distance (TD) that the glider

would travel, so it was assumed that the glider would make circular turns, so we calculated the perimeter, multiplied by the number of turns and approximated the distance.

• The helical pattern will be obtained with the slight deviation of a surface such as the horizontal or vertical stabilizer.

• And in order to estimate the turning diameter and the spins, several iterations of the resulting velocity were made, taking into account that it must have a vertical Speed = 3.3m / s and a varying horizontal speed, finally with the resulting velocity the required CL was estimated.

• And to be able to calculate it, it was necessary to obtain the angle of descent with the following formula Ø= Arctan (1 / (TD / 400)), and for the next velocities :

Operations Assumptions




53

Turning diameter=500m


Estimations



54






As we can observe with a diameter = 100m we obtain acceptable conditions, from the same table we can also observe that with an approximate speed of 20 m / s the CL required is =0.46.



Summary

56


Component Descent Rate Estimate

Glider and Container 6 m/s

Glider 3.3m/s (20.27 m/s wind speed)

Container 4.6 m/s



Mechanical Subsystem Design

Javier Sánchez


Cansat Configuration:• The top cover is the parachute attached

to drilled holes with kevlar cord; the bottom cover is a panel.

• The glider is designed to keep its wings folded while it is in the container.

• We did an n^2 form chart visualizing component interfaces.

• Components are mostly made of carbon fiber due to its low weight and high strength.

58

Mechanical Subsystem Overview

Launch Configuration

Presenter: Javier Sánchez


Number Requirement Sub-system Fulfillment

1 Total mass of the CanSat (container and payload) shall be 500 grams +/- 10 grams.

All All mechanical design were made with a mass control to ensure a weight lesser than 500 grams at most.

2 The glider shall be completely contained in the container. No part of the glider may extend beyond the container. One circular end of the cylindrical container may be open (no door enclosure is required); however, the glider may not extend outside the container.

Container Clearances were considered throughout all the design process.

3 Container shall fit in a cylindrical envelope of 125 mm diameter x 310 mm length including the container passive descent control system. Tolerances are to be included to facilitate container deployment from the rocket fairing.

Container The container was designed with a clearance of 2mm in mind.

Mechanical Sub-System Requirements



5 The container shall not have any sharp edges to cause it to get stuck in the rocket payload section.

Container All container edges were rounded mitigating any stuck risk.

6 The container shall be a florescent color, pink or orange.

Container The container will be painted with a fluorescent orange color.

7 The rocket airframe shall not be used to restrain any deployable parts of the CanSat.

Container The rocket airframe was not considered to restrain any deployable parts of the CanSat.

8 The rocket airframe shall not be used as part of the CanSat operations.

Container The CanSat operation will start from its deployment. An instant later from the separation.

9* The CanSat (container and glider) shall deploy from the rocket payload section.

Container Clearances are considered.

12 All descent control device attachment components shall survive 30 Gs of shock.

Glider All structures and joints are designed to survive 30Gs of shock

13 All descent control devices shall survive 30 Gs of shock.

Glider All structures and joints are designed to survive 30Gs of shock




14 All electronic components shall be enclosed and shielded from the environment with the exception of sensors.

ContainerGlider

The glider will serve as a great enclosure for all electronic components in flight and a membrane will protect any electronic component inside the container.

15 All structures shall be built to survive 15 Gs acceleration.

Glider All structures and joints are designed to survive 15 Gs acceleration

16 All structures shall be built to survive 30 Gs of shock.

ContainerGlider

All structures and joints are designed to survive 30Gs of shock

17 All electronics shall be hard mounted using proper mounts such as standoffs, screws, or high performance adhesives.

ContainerGlider

All electronics will be mounted over hard panels joined to main structures.

18 All mechanisms shall be capable of maintaining their configuration or states under all forces.

Glider All mechanisms were designed with a system to ensure a rigid configuration under expected forces.

19 Mechanisms shall not use pyrotechnics or chemicals.

ContainerGlider

All mechanism turn on or start to work with an electrical signal and its functions are completely mechanical.

20 Mechanisms that use heat (e.g., nichrome wire) shall not be exposed to the outside environment to reduce potential risk of setting vegetation on fire.

ContainerGlider

Our glider’s deploy starts with a signal to burn a nichrome wire releasing it to start descent. The wire will remain inside the container.




28 Cost of the CanSat shall be under $1000. Ground support and analysis tools are not included in the cost.

All All teams made a price control of all components and materials..

35 Both the container and glider shall be labeled with team contact information including email address.

ContainerGlider

They will be labeled with team contact information over a visible surface.

38 The glider must include an easily accessible power switch which does not require removal from the container for access. Access hole or panel in the container is allowed

ContainerGlider

A power switch will be located behind glider’s tail in line with a hole in the middle of parachute.

39 The container shall contain electronics and mechanisms to release the glider at the required altitude.

Container Down the glider will be sited our mechanism to release the glider, it will be constituted for a electronical control to burn a nichrome wire.

42 The CanSat container shall have a payload release override command to force the release of the payload in case the autonomous release fails.

Container Just in case the autonomous release fail a timer will provide a emergency signal to burn nichrome wire after a considered time

54 No foam based beads or other similar bits of foam material that can be dropped and lost on the ground. This material is dangerous to the livestock that occupy the competitions area.

ContainerGlider

All mechanical sub-systems were designed for not being dangerous or risky to the biosphere.




Payload Mechanical Layout of Components Trade & Selection

a) Mid wing, electronics inside the fuselage and glider won’t have attaching points it just rests inside the container.

b) High wing and electronics below the fuselage and glider won’t have attaching points it just rests inside the container



Glider configuration.Glider configuration option a: mid wing and mid tail. Glider configuration option b: low wing and mid tail.

Criteria for selection Option a Option b

Stability Low High

Control High Low

Construction difficulty Low Low

Container volume advantage High Low



Chosen Glider Configuration: The team chose a combination of the two because it presented better overall characteristics. The high wing glider provides higher stability. Finally the team decided to place the electronics inside the fuselage because it saves space and gives more clearance to the glider’s deployment. This will help to develop a fuselage that can be easily dismounted to have a simple way to replace damaged electronics.


Material Selection

66

Payload Deployment Configuration Trade & Selection

Payload Material Density Young ModulusElectromagnetic

Waves Attenuation

Manufacturing Skills Required Cost

E Glass Fiber 1.90 g/cm^3 40 GPa Low Medium Medium

Carbon Fiber 1.60 g/cm^3 70 GPa High High High

Balsa wood 0.163 g/cm^3 3.71 GPa Low Low Low

Polystyrene0.96 -1.04

g/cm^33.3 GPa Low Low Low



67

MaterialChosen for

WingsRationale

Balsa wood

● Light weight● Most favorable resistance● Easiness of manufacturing● Accessible● Low attenuation on EM Waves● Affordable

MaterialChosen for Fuselage

Rationale

E Glass Fiber

● Optimal Resistance● Good density● Easiness of manufacturing● Accessible● Low attenuation on EM Waves


Payload Pre DeploymentConfiguration Trade & Selection

B Changing sweep and dihedral angles.A Changing only sweep angle.

Criteria for selection A B

Time of deployment Short long

Number of movements to deploy one two

Container volume advantage good great

Our main criteria are the number of movements; less deployment

movements translates into a faster deployment which requires less

mechanical components that would represent an extra weight.




B Gear mechanism to roll a wireA Torsion spring and gear blocking

Criteria for selection A B

Simplicity Good Middling

Weight Light Heavy

Resistant Great Great

Our main criteria are the number of components as well as its easiness of

integration and fabrication.Testing will be done to demonstrate

compliance with resistance requirements.



First prototypes and proof of concept

70




Container Mechanical Layout of Components Trade & Selection

– Electrical components will be placed on a hard mounted PCB on the container walls.

– Container’s major attachment points are the reinforced holes made in the top for the attachment of the parachute’s kevlar cord lines.

– Major mechanical parts include the bottom lead and the split mechanism.

– The parachute will be made of nylon sheets and the electronics will be enclosed with a thermoformed plastic.



Material Selection

72

Container Mechanical Layout of Components Trade & Selection

Container Material Density Young Modulus

Electromagnetic Waves

Attenuation

Manufacturing Skills Required Cost

E Glass Fiber 1.90 g/cm^3 40 GPa Low Medium Medium

Carbon Fiber 1.60 g/cm^3 70 GPa High High High

PVC 1.37-1.42 g/m^3 30,000 kg/cm^2 Low Low Low

MaterialChosen Rationale

E Glass Fiber

● Optimal Resistance● Good density● Easiness of manufacturing● Accessible● Low attenuation on EM Waves

E Glass FIber


Payload Release Mechanism


• The Payload will be resting inside the container with the ballast, nichrome wire will be enclosed.

• No chord will be used, the only mechanical interface is the one of the walls and the lead.

• The wings are stranded by the walls, loaded and folded waiting for its deployment.

• The container splits in two aided by the parachute chords force and stays stranded do to plastic threads.


Operation Description:• The FSW will start the release

mechanism at the required altitude.

• The nichrome wire will burn the plastic threads securing the lid and preventing the container to split.

• The container and lead will open due to their weight letting the ballast (seeds) and glider fall by their own weight.

74

Payload Release Mechanism

*Testing will be done to demonstrate compliance with resistance requirements.



Electronics Structural Integrity

Container electronic structural integrity:

• All electronic components will be mounted in one module, fixed directly to the container with a high strength adhesive.

• A battery and all electronic components apart from the sensors and the audio beacon will be enclosed in a case of polypropylene inside the container.

• Pressure sensor will be seated in a pipe inside the container to measure static pressure.

• Nichrome wire will be placed over a small base of quartz fixed to the container between the glider and the electronic components case.

• All connections will be secured with a protective coating based on acrylic resins (Plastik 70).

75Presenter: Javier Sánchez


Electronics Structural Integrity

Glider electronic structural integrity

• All electronic components will be mounted on PCBs, fixed mechanically in modules to the main structure. This main structure will go from the front to the tail of the glider.

• All the modules except for the sensors will have a membrane of low density polyethylene to be protected.

• All sensors will be mounted over the body of the glider and reinforced in that area to bear all strain concentrations.

• All connections will be secured with a protective coating based on acrylic resins (Plastik 70).



Mass Budget

77

Components Mass (g) SourceBosch BMP180 0.6 Measured

GY-87 (BMP180 & HMC5803) 2 Measured

Camera Omnivision 12.7 Measured

Arduino nano 5.2 Measured

Xbee Zigbee 3 Datasheet

RTC DS3232M 6.6 Measured

Solar panels 5 Datasheet

PCBs 10 +-1.5 Average weight

Regulating circuit 13.5 +-1.5 Average weight

Buzzer 0.1 Measured weight

Payload Electronics



Components Mass (g) Source

Fuselage 31 CAD Estimate

Wing 27 Estimate

Stabilizers 15 CAD Estimate

Wing deployment 22 Estimate

Electronics 58.6 +-3

Ballast* 26.7 +- 3

Total Mass 180

Mass Budget

*The ballast is used as a margin and to adjust the glider’s center of gravity and to adjust to descent calculations.

Payload Mass Total



Mass Budget


Arduino Nano 5.2 Measurement

BMP180 & MS5803 2 Estimate

XBee Zigbee 3 Datasheet

RTC DS3232M 6.6 Measurement

Battery 45.3 Reference Measurement

PCBs 10 Average weight

Switch 2 Datasheet

Audio Beacon 0.1 Datasheet

Container Mass Electronics




Structure 67 CAD Estimate

Electronics 74.2

Parachute 10 Estimate

Parachute Thread 4 Estimate

Gate 12.5 CAD Estimate

Ballast & Margin* 152.3

Total Mass 320

Container Mass Budget

Container Mass Total


*The ballast is used as a margin and to adjust the glider’s center of gravity and to adjust to descent calculations. The electrical ground is considered as part of the container ballast.


Mass Budget

81

System Mass (g)Payload 180

Container 320

Cansat 500

Summary



Communication and Data Handling (CDH) Subsystem Design

Alejandro Muñoz


CDH Overview


Part Type Device Function

MIcrocontroller Arduino Nano - RP&T container data.- Realize deployment

Radio XBEE zigbee (S2C)- Receive data packets from MCU- Submit data to GS

Antenna Wire antenna integrated in XBEE - Increase radio signals

Real Time Clock DS3232M - Keep track of the current mission time

Memory M25PE80-VMN6TP- Encode, store and retrieve sensed information


CDH Overview

84

Glider Container

Ground Station

Sensors Sensors

RTC RTCMCU - Nano MCU - Nano

Radio XBEE Radio XBEEAntennaUART UART

I2C

I2C

I2C

I2C



CDH Requirements


A I T D

21During descent, the glider shall collect air pressure, outside air temperature, compass direction, air speed and solar power voltage once per second and time tag the data with mission time.


HIGH E1 x x



HIGH E1 x x

23

Telemetry shall include mission time with one second or better resolution, which begins when the glider is powered on. Mission time shall be maintained in the event of a processor reset during the launch and mission.

Competition Requirement - Telemetry format and

correct associationMEDIUM E1 x x

24XBEE radios shall be used for telemetry. 2.4 GHz Series 1 and 2 radios are allowed. 900 MHz XBEE Pro radios are also allowed.

Competition Requirement - Telemetry format and

correct associationMEDIUM E1 x x

25 XBEE radios shall have their NETID/PANID set to their team number.Competition Requirement

- Low impact on FRR score

LOW E1 x x

26 XBEE radios shall not use broadcast mode.Competition Requirement

- Low impact on FRR score

LOW E1 x

31All telemetry shall be displayed in engineering units (meters, meters/sec, Celsius, etc.)

Competition Requirement LOW E1 x



CDH Requirements


A I T D

44The glider shall use a timekeeping device to maintain mission time. The time keeping device can use a small coin cell battery.


46The container shall transmit telemetry from the time being turned on and placed on the launch pad until 2 seconds after releasing the glider.


47 The container telemetry shall be transmitted once per second. Competition Requirement HIGH E1 x x

48The container telemetry shall include team number, indication of container telemetry, altitude, temperature and software state.


52A count of the number of pictures must be kept and included in the telemetry. Images do not get transmitted.


HIGH E1 x

59 The range of the transmitter shall be optimal. Mission Inegrity HIGH E1 x x



Payload Processor & Memory Trade & Selection

87

ProcessorOperating

Voltage (V)

Input Voltage

(V)

DC Current per I/O

Pin (mA)

Digital I/O Pin (mA)

Analog Input Pins

Operating Power Supply

per Pin (W)

Clock Speed (MHz)

MemoryInterface

Flash (kB)

SRAM (kB)

EEPROM (kB)

ATmega328 (Arduino Pro

MIni)5 3.3-5 40 14 6 0.13 16 32 2 1

UARTSPII2C

ATmega32U4 (Arduino

Micro)5 7-12 20 20 12 0.1 16 32 2.5 1

UART SPII2C

JTAGATmega328

(Arduino Nano)

5 5-12 40 14 8 0.2 16 32 2 1UART

SPII2C

Processor Chosen Rationale

ATmega328 (Arduino Nano)

◘ Arduino has an extensive set of support libraries and hardwares which makes it easier to program◘ It’s ideal because it complies with the requirements.◘ Small size, low weight and easy to integrate◘ Low power and current consumption Arduino Nano



Container Processor & Memory Trade & Selection

ProcessorOperating

Voltage (V)

Input Voltage

(V)

DC Current per I/O

Pin (mA)

Digital I/O Pin (mA)

Analog Input Pins

Operating Power Supply

per Pin (W)

Clock Speed (MHz)

MemoryInterface

Flash (kB)

SRAM (kB)

EEPROM (kB)

ATmega328 (Arduino Pro

MIni)5 3.3-5 40 14 6 0.13 16 32 2 1

UARTSPII2C

ATmega32U4 (Arduino

Micro)5 7-12 20 20 12 0.1 16 32 2.5 1

UART SPII2C

JTAGATmega328

(Arduino Nano)

5 5-12 40 14 8 0.2 16 32 2 1UART

SPII2C

Processor Chosen Rationale

ATmega328 (Arduino Nano)

◘ Arduino has an extensive set of support libraries and hardwares which makes it easier to program◘ It’s ideal because it complies with the requirements.◘ Small size, low weight and easy to integrate◘ Low power and current consumption Arduino Nano

88Presenter: Alejandro Muñóz


Processor & Memory Trade & Selection (Decision Table)

89

The decision table compares the 5 most important attributes, giving them a different level of prioritization to achieve a more reliable decision. (All trades and selections were performed using this method)


Payload Real-Time Clock

90

RTC Voltage Supply (V)

Time Keeping Current (mA) Interface Memory type Memory Size

(bytes)Integrated Resonator

DS3232M 2.3 - 4.5 1.8 I2C NV/SRAM 236 MEMs

DS3234 2.0 - 5.5 1.5 SPI NV/SRAM 356 XTAL

DS3231 2.3 - 5.5 0.84 I2C none none XTAL

RTC Chosen Rationale

DS3232M

◘ It has a Microelectromechanical system oscillator (MEMs), this mechanism is better in relation to the disturbances of the descent and impact of the glider because it doesn't suffer alterations at the moment of impact◘ Has an I2C interface◘ Its battery is a coin cell battery with a capacity limit of 240 mAh and with no more than a 1 ma discharge rate◘ High memory capacities (o size) RTC - DS3232M



Container Real-Time Clock

91

RTC Voltage Supply (V)

Time Keeping Current (mA) Interface Memory type Memory Size

(bytes)Integrated Resonator

DS3232M 2.3 - 4.5 1.8 I2C NV/SRAM 236 MEMs

DS3234 2.0 - 5.5 1.5 SPI NV/SRAM 356 XTAL

DS3231 2.3 - 5.5 0.84 I2C none none XTAL

RTC - DS3232M


RTC Chosen Rationale

DS3232M

◘ It has a Microelectromechanical system oscillator (MEMs), this mechanism is better in relation to the disturbances of the descent and impact of the glider because it doesn't suffer alterations at the moment of impact◘ Has an I2C interface◘ Its battery is a coin cell battery with a capacity limit of 240 mAh and with no more than a 1 ma discharge rate◘ High memory capacities (o size)


Payload Antenna Trade & Selection

Antenna Gain (dBi) Length (cm) Outdoor line-of-sight range (km) Frequency (MHz)

900MHz Duck Antenna RP-SMA

2 10.5 10 900-1800

Integrated Wire SMT: U.FL Connector

XBEE (S2C) ZigBee5 1.5 3.2 2400-2500

Antenna Chosen Rationale


XBEE (S2C) ZigBee

◘ It has sufficient range to complete the data transmission◘ Low power and current consumption◘ It is integrated into the XBee

Antenna



Container Antenna Trade & Selection

Antenna Gain (dBi) Length (cm) Outdoor line-of-sight range (km) Frequency (MHz)

900MHz Duck Antenna RP-SMA

2 10.5 10 900-1800


XBEE (S2C) ZigBee5 1.5 3.2 2400-2500

Antenna Chosen Rationale


XBEE (S2C) ZigBee

◘ It has sufficient range to complete the data transmission◘ Low power and current consumption◘ It is integrated into the XBee

Antenna



Payload Radio Configuration

Xbee S2C Zigbee selected due to lower power consumption and sufficient range.• In compliance with the requirement it’s NETID/PANID

will be set to the team number 6621.• Xbees will be configured and paired via DH-SH &

DL-SL using XCTU.• Transmission will be managed by the FSW and will be

in bursts at 1 Hz.• No broadcast mode allowed, Xbee will be an endpoint.


Radio Operating Voltage (V) Transmit Power (mA) Outdoor line-of-sight range (m) Frequency (GHz)

Xbee-Pro S2C Zigbee

3.3 120 3200 2.4

Xbee S2C Zigbee 3.3 33 1200 2.4

XBEE Pro 802.15.4 3.3 215 1600 2.4


Container Radio Configuration


Xbee S2C-PRO Zigbee was selected due to its adequate performance.• In compliance with the requirement it’s NETID/PANID

will be set to the team number 6621.• Xbees will be configured and paired via DH-SH &

DL-SL using XCTU.• Transmission will be managed by the FSW and will be

in bursts at 1 Hz.• No broadcast mode allowed, Xbee will be an endpoint.

Radio Operating Voltage (V) Transmit Power (mA) Outdoor line-of-sight range (m) Frequency (GHz)

Xbee-Pro S2C Zigbee

3.3 120 3200 2.4

Xbee S2C Zigbee 3.3 33 1200 2.4

XBEE Pro 802.15.4 3.3 215 1600 2.4


Payload Telemetry Format

Data Packets includes

<TEAM ID> <”GLIDER”> <MISSION TIME> <PACKET COUNT> <ALT SENSOR> <PRESSURE> <SPEED> <TEMP> <VOLTAGE> <HEADING> <SOFTWARE STATE> [<BONUS>]

Team Identification Number“Glider” printed to specify the source of the packageTime since power up in secondsNumber of packets that have been transmittedAltitude sensed with one meter resolutionMeasurement of atmospheric pressureMeasurement from the pitot tube (meters/second).Sensed temperature in degrees C with one degree resolutionVoltage of the CanSat power busCanSat glider heading measured by magnetometerOperating state of the software. (boot, idle, launch detect, deploy, etc.).Color images taken and a count of the number of pictures that have been taken

Telemetry Format

<TEAM ID>,GLIDER,<MISSION TIME>,<PACKET COUNT>,<ALT SENSOR>,<PRESSURE>,<SPEED>,<TEMP>,<VOLTAGE>,<HEADING>,<SOFTWARE STATE>,[<BONUS>]

E.G.: 6621,GLIDER,13:11,50,330,100,20,30,5,120,90,35,DEPLOYED,20



Container Telemetry Format

Data Packets includes

<TEAM ID> <”CONTAINER”> <MISSION TIME> <PACKET COUNT> <ALT SENSOR> <TEMP> <SOFTWARE STATE>

Team Identification Number“Container” printed to specify the source of the packageTime since power up in secondsNumber of packets that have been transmittedAltitude sensed with one meter resolutionSensed temperature in degrees C with one degree resolutionOperating state of the software. (boot, idle, launch detect, deploy, etc.).

Telemetry Format

<TEAM ID>,CONTAINER,<MISSION TIME>,<PACKET COUNT>,<ALTITUDE>,<TEMP>,<SOFTWARE STATE>

E.G.: 6621,CONTAINER,13:11,130,500,30,5,STABILIZE


* Telemetry will be sent in ASCII as required for both glider and container.


Electrical Power Subsystem (EPS) Design

Gabriel Carrasquero


EPS Overview

Presenter: Gabriel Carrasquero

Component Function Subsystem

Solar Cells It is a used as a power source for the glider section for the purpose of data collection.

Glider

Battery It is used as a power source of the re-entry container. Container

Microcontroller Controller on which the code resides to interface or drive sensor, camera, buzzer, XBEE and Pitot tube.

Glider & Container

Sensors Used to collect information regarding the temperature, pressure, and others. Glider & Container

XBEE Wireless communication module that will send the data to the ground control station.

Glider & Container

Camera Transmit images during glider descent path. Glider

Buzzer Helps the recovery of the glider at the moment of the impact, it emits a sound to facilitate the location of the glider.

Glider & Container

Real time clock Records real time at dispatch time to impact. Glider & Container


EPS Requirements# Requirement Rationale Priority Children VM

A I T D

17 All electronics shall be hard mounted using proper mounts such as standoffs, screws, or high performance adhesives.

Competition Requirement - High

impact on FRR Score & Mission Integrity

HIGH M1 E2 x x

21 During descent, the glider shall collect air pressure, outside air temperature, compass direction, air speed and solar power voltage once per second and time tag the data with mission time.


impact in scores

HIGH E1 x x

27 The glider electronics must be all solar powered except for the time keeping device which may use a coin cell battery. No batteries are allowed. Supercapacitors are allowed and must be fully discharged at launch.

Competition Requirement -

PASS/FAIL Requirement

HIGH E1 E2 x x

38 The glider must include an easily accessible power switch which does not require removal from the container for access. Access hole or panel in the container is allowed.


impact on FRR Score

HIGH M1 E1 E2 x x

39 The container shall contain electronics and mechanisms to release the glider at the required altitude.

Competition Requirement - Mission

Integrity

HIGH M1 E1 E2 x x x

40 The container electronics shall be powered by only alkaline batteries.


impact on FRR Score

HIGH E2 x x

45 The timekeeping device battery shall be a coin cell battery with a capacity limit of 240 mAh and with no more than a 1 ma discharge rate

Competition Requirement

MEDIUM E1 E2 x



EPS Requirements

# Requirement Rationale Priority Children VM

A I T D

45 The timekeeping device battery shall be a coin cell battery with a capacity limit of 240 mAh and with no more than a 1 ma discharge rate

Competition Requirement MEDIUM E1 E2 x

46 The container shall transmit telemetry from the time being turned on and placed on the launch pad until 2 seconds after releasing the glider.

Competition Requirement HIGH E1 E2 x x

49 An audio beacon for the glider shall be included and powered off of the solar power.

Competition Requirement MEDIUM E1 E2 x x

51 A camera to take images of the ground as often as possible. SBO - High impact in Launch Ops score

HIGH E1 E2 M1 x x

53 The camera must be powered by the same solar source as the glider electronics.


HIGH E2 x x

55 No lithium polymer batteries. The battery is relatively easy to damage and a fire hazard. We want to avoid setting any parts of the field on fire.

Competition Requirement LOW E2 x

57 C&DH Startup time management. Packet transmission time opening and pictures taken are crucial

HIGH E2 x x

58 Power budget. Competition Requirement - Mission Integrity

HIGH L E2 x

63 System Startup power should be supplied with a security factor of 20% Mission Inegrity MEDIUM E2 x x

64 At least 20 Images should be taken during flight SBO - High impact in Launch Ops score

HIGH E1 E2 x x



Payload Electrical Block Diagram


*RTC is fed by its own battery


Container Electrical Block Diagram



Payload Solar PowerTrade & Selection

104

Solar cell Electrical properties Physical characteristics Price

Pmpp(W) Voltage (V) Current (A) Efficiency (%) Dimensions(mm*mm)

Thickness(mm)

±.0.020mm

THE SUN POWER C60 3.34 0.574 5.83 21.8 125*125 .145 € 4,31

SUNPOWER MAXEON FLEXABLE

1.67 0.574 2.915 21.8 63*125 .145 US $1.34

16-TBPJW-40 ECO-WORTHY .56 0.5 1.1 16.4 26*156 .2 US $0.8

5238-TBP-40 ECO-WORTHY 0.28 0.5 0.56 17.6 52*38 .2 US $0.4375

5276-TBP-40 ECO-WORTHY 0.62 0.5 1.2 16.4 52*76 .2 US $0.5875

26-TBP-40 1.3 0.5 2.6 16.4 52*156 .2 US $.8125

L0126M-TBP-40 1.8 0.55 3.54 17 156*58.5 .2 € 0,85

MP3-25 0.093 3 0.0025 12.5 114X25 .22 US $5.15

Solar Cell DIY 0.225 0.5 0.45 17 52x26 .2



Horizontal Stabilizer:

105

Selected Solar Panel

Rationale

MP3-25 •Flexible and fits the Aerodynamic profile•Is on the range of measures suitable for the glider•Offers to us an excellent range of power

Other free surfaces:

Selected Solar Cell

Rationale

Solar Cell DIY Pol

•Is on the range of measures suitable for the glider•Offers to us an excellent range of power


Selected Solar Cell

Rationale

16-TBPJW-40 ECO-WORTHY

•Offers to us an excellent range of power•Is on the range of measures suitable for the glider•Can cover an excellent part of the fuselage and the wing surface as well•Relatively inexpensive

Wing Extrados, major power contribution:




Selected Solar Cel

Rationale

MP3-25 •Offers to us an excellent range of power•Is on the range of measures suitable for the glider•Can cover an excellent part of the container surface.•Relatively inexpensive

Container Surface: We will use solar cells on the surface of the container so that we can charge the supercapacitors integrated in the regulator circuit before the glider is deployed from the container. So that we can obtain an immediate response from the glider data. The required accessible switch will ensure fully discharged capacitors at launch.



Payload Energy Management Strategy Trade Study

107Presenter: Gabriel Carrasquero

Regulator Circuit

Storage Capacity

Current Capacity Power Management

Inverter Charger Circuit for Solar Panels

12 V 450 mAUses an adjustable regulator to stabilize the voltage and a transistor in his Darlington configuration to amplify the current of the circuit.

Solar Panel Voltage Regulator

9 V 300 mAUses an operational amplifier in his comparative configuration to manage the voltage changes. Also, it has transistors in a Darlington position for a current amplification.

Inverter Charger Circuit for Solar Panels Solar Panel Voltage Regulator


Selection

108

Selected Circuit Rationale

Solar Panel Voltage Regulator

•Offers us an excellent range of power•It has a voltage divider section connected with operational amplifier to provide an accurate voltage measure.•Low current consumption.

Payload Energy Management Strategy Trade Study

Supercapacitors are positioned in parallel with the output capacitor of the circuit so we can charge them with the cells. They will be used as an emergency battery for the processor circuit in case that we may not obtain energy from the solar cells.


Container Battery Trade & Selection

109

Battery Chemistry Cell Voltage(V)

Number of Cells (For 9V)

Capacity(mA)

Size(cm)

Price(USD)

CYLINDER 4LR44

ALKALINE 6 2 105 2.5 x 1.3 1.9

TYPE "N“ BATTERY

ALKALINA 1,5 4 250 3 x 1.2 3.6

RADOX 660-720

Ni-MH 9 1 300 4.8 x 1.7 4.6

Battery chosen Rationale:

RADOX 660-720

-Sufficient current rating-Low Weight-Low cost-One battery can power all electronic components



Payload Power Budget

Component Current Voltage

Power Duty Cycle Source

Arduino Nano 19 mA 5 V 0.095 W 100% Datasheet

XBee S2C Zigbee (Transmit) 33 mA 3.3 V 108.9 mW 10% Datasheet

XBee S2C Zigbee (IDLE) 1 μA 3.3 V 3.3 μW 90% Datasheet

RTC DS3232M 4.5 mA 1.8 V 8.1 mW 0% Datasheet

Bosch BMP180 (2) 3 μA 2.5 V 10.8 μW*2 100% Datasheet

Magnetometer HMC5883L 0.1 mA 2.5 V 250 μW 100% Datasheet

Buzzer QSI-1410 8 mA 2 V 0.016 W 0% Datasheet

OV7670 (IDLE) 20 μA 1.8 V 1.8 μW 95% Datasheet

OV7670 (Active) 10 mA 3 V 60 mW 5% Datasheet

TOTAL 102 mW


*Sensors Duty cycles are not analyzed because their current is negligible anyway.



We have designed a robust EPS for the payload that will provide us with sufficient energy.We will make two arrangements of solar cells for the payload energy requirements. The first one is on the surface of the container that is going to be dealing with the charge of the supercapacitors with a voltage of 6 V average. The purpose of those cells is to shorten the time of charge of the supercapacitors and get an immediate feedback data at the moment when the glider deploys from the container.The second arrangement will be on the fuselage, wing and stabilizer of the glider, and will supply 9 V and 300 mA average to the regulator circuit; the regulator circuit will manage the energy variations and protect the rest of the circuit.

Selected Supercapacitors Specifications

SCMR14C474MRBA0

•5 volts.•0.47 F.•300 mOhms 20% vert.




Graph of charge of the capacitor at 6V and 240 seconds of time using a resistor of 100 ohms




Graph of discharge of the capacitor at 6V and 240 seconds of time using a resistor of 100 ohms







Power requirements

Specification XBee ZigBee S2C

Supply voltage 2.1 - 3.6 V 2.2 - 3.6 V for programmable version

Operating Current(transmit)

45 mA (+8 dBm, boost mode) 33 mA (+5 dBm, normal mode)

Operating Current(receive)

31 mA (boost mode) 28 mA (normal mode)

Power-downcurrent

< 1 µA @ 25°C




RTC DS3232M

Voltage Range on Any Pin Relative to GND

-0.3V to +6.0V

Operating Temperature Range

-40°C to +85°C

Storage Temperature Range -55°C to +125°C

Junction Temperature +150°C

Lead Temperature (soldering, 10s)

+300°C

Soldering Temperature (reflow)

+260°C



Container Power Budget

Component Current (mA)

Voltage (V)

Power (mW)

Duty Cycle Source

Arduino Nano 19 5 95 100% Datasheet

Bosch BMP180 0.032 2.5 0.08 100% Datasheet

MS5803 1.4 3.6 5.04 100% Datasheet

XBee Zigbee S2C (Transmit) 33 3.3 148.5 10% Datasheet

XBee Zigbee S2C (Receive) 28 3.3 92.4 90% Datasheet

Buzzer QSI-1410 8 2 125 0% Datasheet

RTC DS3232M 1.8 4.5 8.1 0% Datasheet

TOTAL 22.02 9 198.2



Flight Software (FSW) Design

Gabriel Carrasquero


FSW Overview

– Basic FSW architecture and environment•The FSW will consist of Arduino Code both for the container and the glider.•We will use the Arduino IDE.•FSW will transmit data at 1Hz and will keep a packet count that will be stored in the arduino EEPROM along with the software state.

– Brief summary FSW tasks:•Identifying certain strategies for guaranteeing a successful release in compliance with the requirements.

– Altimeter redundancy: Weight assignment to the reading of each sensor.

–Deployment time.•Tests with sensors are to be made to identify their sensibility to environmental conditions.



FSW Requirements


A I T D

10 The glider must be released from the container at 400 meters +/- 10 m.Competition Requirement - High impact on Launch

Ops ScoreHIGH E1 x x

30 All telemetry shall be displayed in real time during descent.Competition Requirement - High impact on Launch

Ops & PFR ScoreHIGH E1 x x x

36The flight software shall maintain a count of packets transmitted, which shall increment with each packet transmission throughout the mission. The value shall be maintained through processor resets.

Competition Requirement HIGH E1 x x x

42The CanSat container shall have a payload release override command to force the release of the payload in case the autonomous release fails.

Competition Requirement - High impact on FRR

ScoreHIGH E1 x x



Payload FSW State Diagram



Container FSW State Diagram



Software Development Plan

– Prototyping and prototyping environments•The FSW will be continually functionally tested in an iterative manner through the semester. Its development will start in the following weeks.

– Software subsystem development sequence and tests•The FSW will be modularly developed by the electrical team while testing sensors and components.•Environmental tests will be performed.



Ground Control System (GCS) Design

Tomás Guerrero


GCS Overview

Overview:◘ Signal from both Xbees (Container & Payload) is received by the GS Antenna.◘ GS Xbee receives, decodes and sends the information from the GS Antenna to the USB converter◘ The USB serial converter gathers the information to make it able to be visualized on the monitor◘ Matlab displays data in hexadecimal system units and saves it into the CSV file.◘ The software collects the saved data and graphs it for a better handling

Presenter: Tomás Guerrero


GCS Requirements


A I T D

29 Each team shall develop their own ground station. Competition Requirement LOW E1 x

32Teams shall plot each telemetry data field in real time during flight. In addition, the ground system shall display a two dimensional map of estimated glider position based on speed and heading telemetry data.

Competition Requirement - High impact on Launch

Ops & PFR ScoreHIGH E1 x x x

33The ground station shall include one laptop computer with a minimum of two hours of battery operation, XBEE radio and a hand held antenna.

Competition Requirement MEDIUM E1 x

34The ground station must be portable so the team can be positioned at the ground station operation site along the flight line. AC power will not be available at the ground station operation site.

Competition Requirement MEDIUM E1 x x



GCS Design

127

Specifications- Operating time: 6 hours with

portable battery - Overheating mitigation: PC fan- Auto update mitigation: - All components will be assembled

in a rigid case for damage protection



GCS Antenna Trade & Selection

Antenna Option Type Frequency (GHz)

Peak Gain (dBi) Height Wave Type Cost

($dlls)

Through-Hole DA-24-04 RPSMA 2.4 2.1 4.5" Half wave Dipole 6.95

MT U.FL 2.4 2.1 " Quarter wave Monopole 4

Mounting Selection

Selected mounting design: Table TopRationale: Better steadiness

Selected Antenna

Rationale

RPSMA◘ Acceptable radiation pattern◘ Good portability◘ Compatible with the selected xbee

Antenna Pattern



GCS Software

- We will use python and its scientific libraries for data capturing, saving and plotting.

- We will use python lists loaded from a CSV and plotted in a GUI using engineering units with the help of Matlab.

129

Python parser script

Comport

CSV File

Matlab Logic and GUI

- The python script will load the data from the Comport and save it to a CSV file, the computer plotting interface will work loading the CSV every second.

Python scripts at desktop*

*Eg. override mechanism

- We will program the proper calculations in Matlab to estimate the glider’s position in a 2D plot.



GCS Graphical User Interface first prototype

130

GCS Software



CanSat Integration and Test

Javier Sánchez


CanSat Integration and TestOverview

The CanSat subsystems consist in: Mechanical Subsystem (Container and Glider), Descent Control Subsystem, Sensor Subsystem, EPS, CDH, Radio Communications, and FSW.

● Subsystem level tests will focus on components working separately, from sensors to structures all parts of the CanSat will be evaluated to check if they meet the working standards proposed by the team.



• In the integrated level tests the team will be evaluating how the two main systems (Glider and Container) work. Aspects being tested: aerodynamic performance of the glider, mounted electronics transmitting data, and deployment mechanisms working correctly.

133




• Environmental tests will be carried out to see how the Cansat will do in the tests made by the competition, the final performance of the Cansat and to look for failures of any subsystem during a mission simulation.

134






● Sensor Subsystem:• Each sensor will be verified to work precisely and it will be analyzed to know if the sensed results fit in the correct margins.

136

Subsystems Level Testing Plan




● Mechanical Subsystem testing plans:

➢ Glider:• The Glider will be tested in a wind tunnel to check flow patterns and the aerodynamic behavior.• Wing deployment mechanism will be tested to check if it’s correctly assembled to the fuselage. • Impact tests will be done to see the amount of energy the glider can resist before fracture.




➢ Container:• The release mechanism will be evaluated to detect any failures which could prevent a successful release.• The Container will be tested in a wind tunnel to check flow patterns and the aerodynamic behavior.• To fulfill the fit test the Container will be put into a tube of approximately the diameter stipulated and the length will be measured with a Vernier Caliper.• Impact tests will be done to see the amount of energy the container can resist before fracture.



● Parachute (Descent Control Subsystem):•The parachute will be examined in the wind tunnel to observe if it meets the aerodynamic properties needed.

139




● Radio Communications:• The radios will be inspected to verify if the information is being transmitted between the radios of the CanSat and the Ground Station.

140




● CDH:•The circuit and microprocessor will be tested to recognize if the electrical components are meeting the system requirements.

141




● FSW:• The microprocessors will be checked to analyze if the program compiles and reads correctly the data read by the sensors.

142





● EPS:• Solar cells will be tested to check if they meet the power required by the electronics in the Glider.



Integrated Level Functional Test Plan

Integration of CanSat:After all subsystems are fully tested the team will proceed to assemble the sensor subsystem with mechanical subsystem, the descent control subsystem to the container and proceed to the integrated tests.Integrated tests:● Glider:❏ The Glider will be tested in the wind tunnel to check if its

performance is modified by the insertion of the electronics.❏ The Glider and Container electronics will be evaluated to

secure they work in the distances and weather conditions the team thinks will be found during the competition.




● Mechanisms:The wing deployment mechanism will be checked in the wind tunnel to confirm if the mechanism can endure the force produced by the wind and evaluate if the mechanism has the strength to sustain the structure during the time of the mission.



Deployment:● The glider deployment mechanism will be tested to see if

the space between the glider and the container is enough to secure a correct deployment, it will also be tested in the wind tunnel to assure it can undergo the force of the wind before deployment and after deployment.

146




Drop Test:• The glider and container will be elevated to approximately the height stipulated by the competition with drones and weather balloons and released to see their performance.

147

Environmental Test Plan



Thermal Test:• Thermal tests will be conducted on the glider and container separately and together in a thermal vacuum chamber to evaluate the amount of heat the structures and electronics can endure and still work properly.

148




Vibration Tests:• Vibration tests will be carried out on the glider and container separately and as a system in a vibration table with random patterns to check if they work properly under this circumstances.

149





Mission Simulation Test:• Final tests will be taken with a third party’s rocket to simulate the conditions of the competition, in this tests the team will evaluate if the Cansat and ground station are working as expected with the results shown in prior tests.



Mission Operations & Analysis

Sebastián López


Overview of Mission Sequence of Events


Time Event Crews Involved

Pre-LaunchArrive at launch site ALL

Prepare CanSat for turn in. Make it flight ready and perform any tests. CanSat Crew GCS Crew MCO

Launch

Turn in CanSat at the check-in table by noon. It will be weighed and fit checked and stored in the off state until rocket preparation time.

CanSat Crew GCS Crew MCO

Upon the team round, the team will collect their CanSat and load it into a rocket. CanSat Crew

Verify the CanSat is communicating with the ground station. GCS Crew MCO

Take the rocket with the ground station to the assigned launch pad. A staff member will install the rocket on the launch pad.

CanSat Crew MCO

When it is time to launch, a judge will come by the ground station to monitor the ground station operation.

MCO

The team mission control officer will go to the launch control table and execute the launch procedures with the flight coordinator providing oversight.

MCO

Ground station crew will perform all required flight operations. GCS Crew

Post-Launch

After all CanSats have launched for the current half hour round, team recovery personnel can head out to recover.

Recovery Crew

Ground station crew must clear out of the ground station area to allow the next round ground stations to set up.

GCS Crew

Ground station crew must turn in the thumb drive with any ground station data and or photos if desired to the check-in judge.

GCS Crew

Recovery crew must return to the check-in for any final judging requirements. Recovery Crew


Mission Operations Manual Development Plan

• The MOM is going to be developed in detail when the final design of CanSat is presented and shall be completed by May.

• The MOM will include five check lists/operations:–Configuring the ground station–Preparing and integrating the CanSat into the rocket. –The launch preparation procedures and operations.

• It will also include crew roles and plans for action as well as the SOE.

• The MOM will be available for download and modification.



CanSat Location and Recovery

Container Recovery:• Container will be pink fluorescent color and with an orange parachute.• Container will have a buzzer.• Container will be seen with the aid of binoculars by a designated

recovery crew member.Glider Recovery:• Glider chasi will be orange fluorescent color• Glider will have a solar powered buzzer.• Glider will be seen with the aid of binoculars by a designated recovery

crew member.Container and Glider will be legibly labeled with team leader’s address, contact information and e-mail in order to avoid permanent loss.



Requirements Compliance

Sebastián López


Requirements Compliance Overview

• Currently the design complies with most of the requirements.

• The requirements with partial compliance ought to be tested in order to assure compliance.

• In the following slides we demonstrate the compliance with the requirements via the reference to the slide.

• Tests are to be made in most of the areas to clearly demonstrate the design behaves as expected.

156Presenter: Sebastian López



157

# Requirement Status X-Ref Slide

Team comments

1Total mass of the CanSat (container and payload) shall be 500 grams +/- 10 grams.

Comply 81

2

The glider shall be completely contained in the container. No part of the glider may extend beyond the container. One circular end of the cylindrical container may be open (no door enclosure is required); however, the glider may not extend outside the container.

Comply 21

3

Container shall fit in a cylindrical envelope of 125 mm diameter x 310 mm length including the container passive descent control system. Tolerances are to be included to facilitate container deployment from the rocket fairing.

Comply 21

4The container shall use a passive descent control system. It cannot free fall. A parachute is allowed and highly recommended. Include a spill hole to reduce swaying.

Comply 35, 39, 50

5The container shall not have any sharp edges to cause it to get stuck in the rocket payload section.

Comply 21

Presenter: Sebastian López



6 The container shall be a florescent color, pink or orange. Comply 41

7The rocket airframe shall not be used to restrain any deployable parts of the CanSat.

Comply 21

8The rocket airframe shall not be used as part of the CanSat operations.

Comply 21

9The CanSat (container and glider) shall deploy from the rocket payload section.

Comply 21

10The glider must be released from the container at 400 meters +/- 10 m.

Comply 73 74 122

11

The glider shall not be remotely steered or autonomously steered. It must be fixed to glide in a preset circular pattern of no greater than 1000 meter diameter. No active control surfaces are allowed.

Comply 52

12All descent control device attachment components shall survive 30 Gs of shock.

Partial 66 71 72Testing required

13 All descent control devices shall survive 30 Gs of shock. Partial 66 71 72 Testing required

14All electronic components shall be enclosed and shielded from the environment with the exception of sensors.

Comply 75 76

15 All structures shall be built to survive 15 Gs acceleration. Partial 66 68 69 71 72 Testing required




16 All structures shall be built to survive 30 Gs of shock. Partial 66 68 69 71 72 Testing required

17All electronics shall be hard mounted using proper mounts such as standoffs, screws, or high performance adhesives.

Comply 75 76

18All mechanisms shall be capable of maintaining their configuration or states under all forces.

Comply 65 69

19 Mechanisms shall not use pyrotechnics or chemicals. Comply 67 64

20Mechanisms that use heat (e.g., nichrome wire) shall not be exposed to the outside environment to reduce potential risk of setting vegetation on fire.

Comply 74

21

During descent, the glider shall collect air pressure, outside air temperature, compass direction, air speed and solar power voltage once per second and time tag the data with mission time.

Comply 121


Comply 94 121 119

23

Telemetry shall include mission time with one second or better resolution, which begins when the glider is powered on. Mission time shall be maintained in the event of a processor reset during the launch and mission.

Comply 96 97 119




24XBEE radios shall be used for telemetry. 2.4 GHz Series 1 and 2 radios are allowed. 900 MHz XBEE Pro radios are also allowed.

Comply 94 95

25XBEE radios shall have their NETID/PANID set to their team number.

Comply 94 95

26 XBEE radios shall not use broadcast mode. Comply 94 95

27

The glider electronics must be all solar powered except for the time keeping device which may use a coin cell battery. No batteries are allowed. Supercapacitors are allowed and must be fully discharged at launch.

Comply 102

28Cost of the CanSat shall be under $1000. Ground support and analysis tools are not included in the cost.

Comply 165

29 Each team shall develop their own ground station. Comply 124 - 130

30All telemetry shall be displayed in real time during descent.

Comply 124 - 130

31All telemetry shall be displayed in engineering units (meters, meters/sec, Celsius, etc.)

Comply 129




32

Teams shall plot each telemetry data field in real time during flight. In addition, the ground system shall display a two dimensional map of estimated glider position based on speed and heading telemetry data.

Comply 129 130

33The ground station shall include one laptop computer with a minimum of two hours of battery operation, XBEE radio and a hand held antenna.

Comply 125

34

The ground station must be portable so the team can be positioned at the ground station operation site along the flight line. AC power will not be available at the ground station operation site.

Comply 125

35Both the container and glider shall be labeled with team contact information including email address.

Comply 15

36

The flight software shall maintain a count of packets transmitted, which shall increment with each packet transmission throughout the mission. The value shall be maintained through processor resets.

Comply 119

37 No lasers allowed Comply 14




38The glider must include an easily accessible power switch which does not require removal from the container for access. Access hole or panel in the container is allowed.

Comply 21

39The container shall contain electronics and mechanisms to release the glider at the required altitude.

Comply 73 74

40The container electronics shall be powered by only alkaline batteries.

Comply 103 109

41 The glide duration shall be as close to 2 minutes as possible. Comply 56

42The CanSat container shall have a payload release override command to force the release of the payload in case the autonomous release fails.

Comply 129A python script that sends a command to the container

43

Glider shall be a fixed wing glider. No parachutes, no parasails, no parafoils, no autogyro, no propellers. Hang glider design where the electronics section has a hard attachment point is allowed.

Comply 13 45

44The glider shall use a timekeeping device to maintain mission time. The time keeping device can use a small coin cell battery.

Comply 102 103




45The timekeeping device battery shall be a coin cell battery with a capacity limit of 240 mAh and with no more than a 1 ma discharge rate

Comply 102 103

46The container shall transmit telemetry from the time being turned on and placed on the launch pad until 2 seconds after releasing the glider.

Comply 122

47 The container telemetry shall be transmitted once per second. Comply 95 122

48The container telemetry shall include team number, indication of container telemetry, altitude, temperature and software state

Comply 96 97

49An audio beacon for the glider shall be included and powered off of the solar power.

Comply 102

50 An audio beacon is required for the container. Comply 103

51 A camera to take images of the ground as often as possible. Comply 33 102



Management

Presenter Name(s) Go Here


CanSat Budget – Hardware


Concept Cost (USD 20 MXN) Status

GM-Structure $90.00 EstimatedGM-Wing Deployment Mechanism $5.00 EstimatedGE-Bosch BMP 180 $5.00 RealXbee Pro SC2 x 3 $200.00 RealGE-Magnetometer $12.50 RealGE-Camera $3.00 RealGE-RTC DS3232M $3.54 RealGE-Solar Panels $55.00 EstimatedGE-PCBs $1.00 EstimatedGE-Regulating Circuit $2.00 EstimatedGE-Audio Beacon $1.00 EstimatedCM-Structure $85.00 Estimated

CM-Payload Deployment Mechanism $5.00 EstimatedCM-Parachute $2.00 EstimatedArduino Nano x 2 $43.95 RealCE-Bosch BMP 180 x 2 $10.00 RealCE-RTC DS3232M $3.54 RealCE-Battery $2.50 RealCE-PCBs $1.00 EstimatedCE-Switch $0.10 RealCE-Audio Beacon $1.00 Estimated

Total $532.08


Cansat Budget - Other Costs

166

Component Costs (USD)

GCS Computer Not available

GCS Antenna 7

CS Xbee 37.05

GCS Battery Not Available

Transportation 500

Lodging and Food 900

Tests 250

Sponsorship & Funds:To the day the project has been self-funded but in the last week we have been looking for sponsors and help. The results are several entities interested in the sponsorship that include: Superior School of Mechanical and Electrical Engineering P.F. Ticoman, Grupo Interacciones, CCEEA, Ay Güey!, HetPro. The imminent support of this entities will result in a complete financing of the project and it is expected to be confirmed before the CDR deadline.



Program Schedule


Program Schedule


Program Schedule

*MOM will be done in the Manufacturing Integfration and Full system tests phase


Conclusions

• Major accomplishments•First iteration prototypes in GCS, gliders, and mechanisms.•Sensors have been bought.•Two sponsors secured and several others tempting.•Comprehensive design according to mission requirements.•New working team.

• Future work•Important testing is to be made•Due to funding Xbees haven’t been acquired•FSW hasn’t been started

• Why you are ready to proceed to next stage of development•We have a complete design ready to be tested and iterated.


Documents

Version 1.0 Outline Preliminary Design Review (PDR) · PDF filePreliminary Design Review (PDR) Outline Version 1.0 IPN ... Mission Operations Manual • SOE - Sequence of Events