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Vehicle Dimensions, Materials, and Justifications
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FAMU PDR Presentation
Table of Contents• Vehicle dimensions, materials, and justifications
• Static stability margin
• Plan for vehicle safety verification and testing
• Baseline motor selection and justification
• Thrust-to-weight ratio and rail exit velocity
• Launch vehicle verification and test plan overview
• Drawing/Discussion of each major component and subsystem, especially the recovery subsystem
• Baseline payload design
• Payload verification and test plan overview
• Questions
Vehicle Dimensions, Materials, and Justifications
Vehicle dimensions, materials, and justifications
• Airframe: Always Ready Rocketry - BT20-139A - 5.5 in Blue Tube 2.0
• Fins: 3/16 Aircraft Plywood
• Length: 123 in.
• Mass: 718.92 ounces (44.932 lbs.)
• Outside Diameter: 5.50 in.• Inside Diameter: 5.35 in.
Vehicle dimensions, materials, and justifications
Static Stability Margin
Static Stability Margin
Concept used to characterize the static stability and controllability of aircraft and missiles
Stability Margin: 1.71 cal
Vehicle Safety verification and testing
Vehicle Safety/Failure Mitigation
Potential Failure Mode Effects of Potential Failure Prevention
Electronics package is too large to fit inside rocket
Payload cannot be integratedinto rocket
Redesign payload to fit proper body tube size
Nose section too heavy Rocket may not have enough power for stable flight
Redesign rocket to reduce weight
The fins fail during flight due to shear forces or inadequate use of adhesive.
The rocket will experience anunstable and unpredictable flight trajectory.
The team shall use suitable building materials, through-the-wall fin mounting, and ample application of epoxy adhesive and fillets
Vehicle Safety/Failure Mitigation
The interior of the rocket catches on fire due to internal heat.
The interior of the rocket is destroyed.
The team shall use proper spacing and bulkheads to prevent the transfer of heat.
The rocket experiences drag separation during flight.
The rocket will prematurely separate, leading to early parachute deployment and a mission failure.
The team shall ensure that all joints are secure and shall drill a hole in the body tube to equalize pressure between the interior of the rocket and the atmosphere.
A bulkhead detaches from the interior of the body tube.
Shock cords become no longer attached, causing a ballistic recovery.
The team shall apply ample amounts of adhesive, such as epoxy.
Rocket components are lost or damaged during transport to launch site.
The team risks not launching the rocket unless repairs can be made.
The team shall pack components safely and securely for transport and have replacement components and needed tools available at the launch site.
Vehicle Safety/Failure Mitigation
Fin(s) break off during flight/landing
Unstable flight; possible damage of engine mount
Adequate materials and construction techniques
Fin-can failure due to high temperatures
Unstable flight; Fin-can separation during flight
Proper mounting material and hardware
Centering ring failure Unstable shift in stability margin; Damage to all subsystems; separation of fin can
Proper centering ring diameter; proper construction techniques
Bulkhead failure Unstable flight; damage to subsystems; unstable shift in stability margin
Proper bulkhead diameter; proper construction techniques
Vehicle Safety/Failure Mitigation
The center of pressure is too high or too low.
The rocket will be unstable orover stable.
The team shall adjust fin sizing and position so that the center of pressure is 1-2 calibers behind the center of gravity.
The center of gravity is too high or too low.
The rocket will be unstable orover stable.
The team shall adjust weight so that center of gravity is 1-2 calibers ahead of center ofpressure.
Motor Selection and Justification
Motor
• Loki L930
• Motor Type: reloadable
• Total Weight: 3538.0200 g
• Peak Thrust: 1136.70 N
• Total Impulse: 3587.2 Ns
• Justification: We currently have the motor house for the L930. Our rocket design is
similar to last years and based on the weight of the rocket we chose the L930. Lead
plates will be added to the rocket to keep the rocket from exceeding a 10240 ft.
Thrust-to-Weight Ratio and Rail Exit Velocity
Thrust to weight /Rail Exit Velocity
• Rail Size: 1.5 in.
• Rail Exit Length: 96 in.
• Rail Exit Velocity : 67.99 ft/s
• Thrust to Weight Ratio: 5.62 N
Launch Vehicle Verification and Test Plan
Vehicle VerificationRequirement Design Feature Verification by
The launch vehicle shall carry the SMD and/or a scientific payload
Visual Hazard Analysis payload Inspection and testing
The launch vehicle shall deliver the payload to 10,240ft.
Correct selection of motor, Rocksim simulations.
Analysis and testing
The launch vehicle shall carry one PerfectFlite altimeter
Electronics bay includes a PerfectFlite Inspection and testing
The recovery system electronics shall be designed to be armed on the pad
Push button switches are accessible from the outside of the vehicle by holes
Testing
Launch Vehicle
Vehicle VerificationRequirement Design Feature Verification by
The recovery system electronics shall be completely independent of the payload electronics
The recovery electronics and payload electronics will be in separate bays.
Inspection and design
The recovery system electronics shall contain redundant altimeters
There are two separate altimeters in the electronics bay. They are powered by two separate batteries for complete redundancy
Inspection and testing
Vehicle Verification
Requirement Design Feature Verification by
The recovery system electronics shall have each altimeter armed by a dedicated arming switch
Each altimeter has a separate switch Inspection
The recovery system electronics shall have a dedicated battery for each altimeter
Each altimeter has a separate battery Inspection
The recovery system electronics shall have each arming switch accessible from the exterior of the rocket frame
There are holes in the frame of the rocket that reaches the push button switches
Inspection
Drawings/Discussion
Drawings/Discussion
Upper Chute Housing(b)
Retainer Ring
Dispersion Insert/Chute support
(d)
To Scientific payload in nosecone
To Scientific payload in body
(a)
Scientific Payload(c)
Retainer Ring(s)
Black powder wells
External Center Ring
Internal layout of scientific payload TBD by dimensions of equipment.
Equipment
Camera (s)
Sensor board
Transmitter
GPS
Batteries
Altimeter (s)
Secondary Stage(d)
v v
Parachute connector ring
(e)To drogue chute
Motor Mounts
(g)
(g) is inserted in base of (f) secondary stage
Mounting of secondary will be recessed from the bottom of the tube to insert engine ignition system to ensure stability of rocket and proper ignition .
v
120ᵒ
Fins
Stage Two Rocket Engine Ignition System(e)
Hollow Tube
Electrical wiring
for ignition cap
Altimeters for ignition and parachute
Solid Tube
Ignition cap and Flammable material
Black powder and cap
Parachute connector
Position of Altimeter (s) are TBD do to battery size (not shown). Also, the length of the ignition tube will depend on the depth of engine and material used for ignition.
Altimeter for Ignition will be set to ignite engine when altitude of rocket is still straight and adequate velocity TBD.
(h)
First Stage(f)
v v
120ᵒ
Fins
Motor Mounts
Engine Retainer
Parachute connector ring
(h)To First stage recovery chute
Parachutes
Parachutes (CONT.)
Parachutes (CONT.)
Payload Design
Payload Design
Electronics used in payload:
Payload Design
• Raven 3 altimeter
→ Flight Counter
• Fit-PC2 miniature computer
→ Data acquisition
• HackHD Camera
→ Video & still frames – faces tail of rocket
• 5.8G 8ch 2w Wireless Camera Video AV Audio Transmitter & Receiver
→ Provides USB interface between computer and video devices with component outputs
Payload Design
• The team aim to implement and test a Hazard classification system with its
scientific payload.
• Two computers mounted in the electronics bay, one connected to altimeter,
will determine altitude intervals on which video will be analyzed
• Analysis tasks shared between the 2 payload computers
Payload Integration/Test Plans
Payload Integration
• Mounted on 5.5”x9.25” Board in electronics bay above motor mount
• 2 - Fit-PC2, powered by LiPo s
• 2 – 5.8G 8ch 2w Wireless Camera Video AV Audio Transmitter &
Receiver
• 3 - Raven 3 altimeter, powered by built-in 9v battery
• In separate bay adjacent to motor mount
• HackHD camera, powered by LiPo battery
Payload Test Plan
• Hardware and Software Integrationo Check Camera's compatibility with software.
• Ground Testingo Software tested for performance in completed its needed tasks
• Computer Based Testingo Testing data transmission between payload electronics and a computer
based device(s).• Full-Scale launch
o Encapsulates every previous test; all systems tested in context of a rocket launch
Payload Experiment Criteria
• The team aim to implement and test a Hazard classification system with its scientific payload. Hazard
classification is a general term for methods used to derive descriptions of the physical characteristics
of an area that is in harmful distance from the rocket, such as whether the Hazard in question is
people, cars, or other heavy machinery Determining the nature of an area’s Hazard is useful in the
area of autonomous robotics.
• Florida A&M University’s scientific we will Execute Hazard Detections, be recoverable, and execute
triple deployment.
• Also, the electronics bay is required to be reusable and recoverable in order for the mission to
succeed.
Questions