RAPTR SAT-XConceptual Design Review

University of Northern ColoradoShiely, Woods, Aken, Adamson

10/4/2011

Mission Overview - Mission Statement

The RAPTR SAT-X team intends to develop a highly reliable, deploy-able, capsule and accompanying deployment mechanism capable of accomplishing multiple mission objectives. The capsule objective for this iteration of RockSat-X is to better characterize the forces involved in the re-entry process as well as report physical behavior of the vessel as it passes through the changing atmosphere.

Mission Overview - Objective Breakdown

The system shall relay information to the ground for post processing.

The system should record visual data for post analysis.

The system shall be designed with ease of assembly and integration in mind.

Mission Overview - Objective Breakdown

Mission Objective1: Successfully deploy capsule from CarRoLL rocket section and initialize radio transmission of data.Mission Objective 2: Collect meaningful data from probe during the re-entry process, and store to secure digital(SD) card.Mission Objective 3: Transmit system information throughout duration of flight via telemetry to be used as an indicator of points of failure during post-processing of data.Mission Objective 4: Recreate probe re-entry utilizing visual and numerical data and compare to mathematical model of expected behavior

Mission Overview - Expected Results

● The RAPTR SAT-X team fully expects successful probe deployment and successful data acquisition and logging from all probe and base station sensors for, at least, the first half of the re-entry process.

● The team expects to retrieve a working SD card from a successfully recovered rocket.

● The team does not anticipate recovering deployed components and thus all data generated and collected by probes must be relayed back to the rocket for storage.

Mission Overview - Theory and Concepts

● Mathematical models developed through testing and theory prior to launch will be compared to in flight behavior to better analyze the re-entry process.

● It is anticipated that flight behavior will not align with model during sections of the re-entry process. These deviations will be interpreted as variance of actual atmospheric density from the theoretical density.

Mission Overview - Theory and Concepts

Reentry Experiment SAT-X (2010/11 RS-X)○ Results:

■ Successful Deployment from Rocket Body■ Successful Capsule PowerOn/Initialization■ Data connection via 900MHz Radio

less-than-nominal■ No useful returned data (just pretty pictures)■ Design Process revealed issues that

prevented development of full-systemsfunctionality

1. Launch Telemetry/GPS begins2. Launch to Apogee Telemetry/GPS continues3. Apogee Nose cone separation Skin separation De-spin to TBD rate Option to align with B Field Telemetry/GPS continues Capsule Ejection4. Descent Telemetry/GPS continues5. Landing Telemetry/GPS terminates Payloads recovered

Mission Overview - ConOps

Design Overview

● RAPTR SAT-X will utilize a similar electronics configuration within each of the probes deployed as used in the prior mission. Physical payload configuration will change drastically to ensure machine-ability and take full advantage of lessons learned from prior mission failures.

○ Similar sensor capabilities will be attempted as were attempted in prior mission.(9 DOF IMU and temperature sensors.)

○ Primary data storage and on-rocket processing will be done with a Gumstix computer.

Major Technology Dependencies:

900MHz XBees will be used for comunication between probes and rocket.

Gumstix computers (700MHz ARM architecture), to remain attached to the rocket, will be used to manage all payload functions and store all data.

RoboVero expansion boards for the Gumstix will provide power management as well as co-processors (120MHz ARM) and 9 DOF IMUs.

Arduino Pro Minis will be used as data handlers on the probes and will handle establishing communication with rocket-based components

9 DOF Sensor Sticks will be used on the probes to generate attitude assessment data.

A commitment to battery types for probe and rocket has not yet been made

Mission Overview - FBD; Electrical (rough diagram)

Design heavily influenced by ReX

Fundamental design

Base station will now be controlled by a

Gumstix COM

Design Overview - Payload Layout; Capsule

Drag Fins Deployed

Drag Fins Folded

(Flight Config)

(Launch Config)

Design Overview - Payload Layout; Capsule

Design Overview - Payload Layout; Capsule (Exploded)

Drag Fins EjectionSpring

Electronics Decks

Design Overview - Payload Layout; Capsule (Cross Sec)

Drag Fins

EjectionSpring

Electronics Decks

Design Overview - Payload Layout; Launcher

With Lid Without Lid

Design Overview - Payload Layout; Launcher

Linear Actuator

Capsule Launch Chute

Securing Latch

Capsule Spring Receiver

Design Overview - Payload Layout; Launcher (Electronics)

With Lid Without Lid

Design Overview - Payload Layout; Launcher (Electronics)

RoboVero

Design Overview - Payload Layout; Camera

With Lid Without Lid

Design Overview - Payload Layout; Full Assembly

Management

Industry Cooperation:● Contour Cameras● Club Workshop, Denver, CO

Management

● Payload development will be broken down into three phases. These three phases will align with both school semesters and a summer period respectively. -First phase: Complete main hardware design and fabrication. -Second phase: Software development and hardware testing to ensure proper payload behavioral characterization. -Third phase: Ensure all system components are in a state that should achieve overall mission success.

● Monetary budget: ~$4,000

Design Overview - RockSat-X 2011 User’s Guide Compliance

● Rough Order of Magnitude (ROM) mass estimate: 30lbs● Estimate on payload dimensions: Shall fit in payload envelope● Deployables/booms? Yes (Deployables)● None of the ADC lines will be utilized● The rocket-based system will use asynchronous communication

for post flight analysis purposes.● Parallel use:

○ The 16 bit parallel line will be used to relay system state information to the ground.

● Power lines and timer use?○ A timer event to indicate launch and a timer event to indicate

apogee are both absolutely necessary. A pre-launch event will also be required to indicate actual launch, the time of which is TBD.

● CG requirement: Shall comply● Are you utilizing high voltage? No

● This year's RAPTR SAT-X is the second iteration of the DINA-SAUR (Deploy-able INtegumentary Atmospheric System for Applied Undergrad Research) development project which seeks to design a base system for RockSat-X upon which future research may be conducted.

● Main Concern: Physical component fabrication may take longer than expected and hinder other aspects of system development.

● Future Plans:○ Develop testing procedure to ensure high probability of

overall mission success.○ Begin making finalized decisions on components and

timing of Wallop's events

Conclusion