RAPTR SAT-X. University of Northern Colorado. Conceptual Design Review. Shiely, Woods, Aken, Adamson 10/4/2011

Transcription

1 RAPTR SAT-X Conceptual Design Review University of Northern Colorado Shiely, Woods, Aken, Adamson 10/4/2011

2 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 reentry process as well as report physical behavior of the vessel as it passes through the changing atmosphere.

3 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.

4 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 reentry 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 postprocessing of data. Mission Objective 4: Recreate probe re-entry utilizing visual and numerical data and compare to mathematical model of expected behavior

5 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.

6 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.

7 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-systems functionality

8 Mission Overview - ConOps 1. Launch Telemetry/GPS begins 2. Launch to Apogee Telemetry/GPS continues 3. Apogee Nose cone separation Skin separation De-spin to TBD rate Option to align with B Field Telemetry/GPS continues Capsule Ejection 4. Descent Telemetry/GPS continues 5. Landing Telemetry/GPS terminates Payloads recovered

9 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 machineability 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.

10 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

11 Mission Overview - FBD; Electrical (rough diagram) Design heavily influenced by ReX Fundamental design Base station will now be controlled by a Gumstix COM

12 Design Overview - Payload Layout; Capsule Drag Fins Folded (Launch Config) Drag Fins Deployed (Flight Config)

13 Design Overview - Payload Layout; Capsule

14 Design Overview - Payload Layout; Capsule (Exploded) Drag Fins Ejection Spring Electronics Decks

15 Design Overview - Payload Layout; Capsule (Cross Sec) Ejection Spring Drag Fins Electronics Decks

16 Design Overview - Payload Layout; Launcher With Lid Without Lid

17 Design Overview - Payload Layout; Launcher Capsule Spring Receiver Securing Latch Linear Actuator Capsule Launch Chute

18 Design Overview - Payload Layout; Launcher (Electronics) With Lid Without Lid

19 Design Overview - Payload Layout; Launcher (Electronics) RoboVero

20 Design Overview - Payload Layout; Camera With Lid Without Lid

21 Design Overview - Payload Layout; Full Assembly

22 Management Industry Cooperation: Contour Cameras Club Workshop, Denver, CO

23 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

24 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

25 Conclusion 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