Rocket Sat 8 Conceptual Design Review University of

Rocket. Sat 8 Conceptual Design Review University of Colorado Boulder 10/4/11 2012 Co. DR

Mission Statements • Rocket. Sat 8 shall integrate and validate the Roll Out De-Orbiting Device (RODEO) developed by Composite Technology Development (CTD). This shall provide a means to de-orbit future small satellites. • Rocket. Sat 8 shall validate an attitude determination system for future Rock. Sat missions 2012 Co. DR

Theory and Background • 23 small satellites (10 kg-500 kg) launched every year by the United States • Growth of small satellites in space exponentially increases the likelihood of collisions • The rise in the number of satellites in orbit has led to an increasing need for a cost effective and lightweight means to de-orbit small satellites. • The Rocket. Sat VII attitude determination system was successful, but the accuracy of the system couldn’t be verified since there was no known solution for the attitude of the rocket. 2012 Co. DR

Requirements Project Requirements Parent Requirement O 1 Shall deploy the RODEO device Mission Objective O 2 Shall validate the deployment of the RODEO device Mission Objective O 3 Shall validate the ability of RODEO to de-orbit small satellites Mission Objective O 4 Shall comply with all Rock. Sat-X requirements Mission Objective O 5 Shall determine the orientation of the payload Mission Objective 2012 Co. DR

Requirements (cont. ) System Requirements Parent Requirement S 1 Shall deploy the RODEO device on the RTS (RODEO Test Structure) O 1 S 2 Shall capture image of deployed RODEO sail O 2 S 3 Shall detach the RTS from the rocket canister O 3 S 4 Shall confirm that RTS experiences deceleration O 3 S 5 Shall meet all structural requirements as defined in the Rock. Sat-X user guide O 4 S 6 Shall meet all electrical requirements as defined in the Rock. Sat-X user guide O 4 S 7 Shall determine the orientation of the payload within ten degrees of accuracy O 5 S 8 The orientation of the payload shall be known on all three axis O 5 2012 Co. DR

Requirements (cont. ) System Level 2 Requirements Parent Requirement S 1. 1 Shall deploy in a time sufficient for the needs of the mission S 1 S 2. 1 Shall capture an image of RODEO while it is in the field of view of the camera S 2. 2 Shall set a image frame rate and quality that confirms RODEO deployment S 2. 3 Shall store the image data S 2 S 3. 1 Shall detach from rocket at the determined time S 3. 2 Shall detach from rocket without damaging equipment S 3. 3 Shall generate acceleration upon detachment S 3 S 4. 1 Shall measure deceleration of the RTS S 4. 2 Shall transmit deceleration data from RTS to the rocket S 4 2012 Co. DR

Requirements (cont. ) System Level 2 Requirements (continued) Parent Requirement S 6. 1 Shall have sufficient power to perform all required operations S 6 S 7. 1 Shall use attitude sensors that are within five degrees of accuracy S 7. 2 Shall incorporate an attitude determination algorithm that is accurate to within ten degrees of accuracy S 7 S 8. 1 Shall employ attitude sensors that can determine the attitude on all three axes S 8 2012 Co. DR

Minimum Success Criteria • Mission success depends on the image capture of the deployed RODEO device. • Secondary mission success is determined by the validation of the Rocket. Sat 8 attitude determination system 2012 Co. DR

Mission overview: Concept of Operations Deploy RTS data collection Apogee Continue Telemetry Send Data from RTS to payload Altitude: ≈160 km Initialize Camera Begin Rodeo Deployment Splash Down Pre-Launch Chute Deployment -Begin Telemetry Continue Telemetry -Begin attitude data collection 2012 Co. DR End Telemetry

Mission overview: Expected Results We expect: • the RODEO system to be fully extended while attached to the rocket • to capture an image of the extended RODEO system • the RTS to detatch from the rocket canister • to measure deceleration from the RTS • to transmit the deceleration data from the RTS • We expect to characterize the rockets attitude and verify it with a known solution 2012 Co. DR 10

Design Overview 2012 Co. DR 11

User Guide Compliance: Structures • The payload shall fit into the allotted 12 in diameter base and 11 in height and weigh less than 30 +- 1 lb. • The center of gravity shall be within 1 square inch of the Rock. Sat-X deck. • Materials with a high resistance to stress corrosion and cracking, and a low outgassing index will be used. • The deployable shall conform to all standards to safely eject from the canister. 2012 Co. DR 12

Payload Layout: Structures • The structure thus far will be composed of two plates. • The bottom plate will include the RTS containing the deployable given to us by Composite Technology Development, as well as the ejection system. • The electronics boards and the ADS(Attitude Determination System) will all be utilized on the top plate with the cameras. 2012 Co. DR 13

Payload Layout: Structures Top Plate Camera on bottom of top plate ADS Deployable Ejection System Bottom Plate Electronics Board Keep Out Zone 2012 Co. DR 14

RODEO Test Structure (RTS) Layout: rough diagram RTS RODEO Note: Drawing not drawn to scale 2012 Co. DR 15

Mission Requirements • The payload shall conform to the requirements set forth in the 2011 Rock. Sat-X User Guide • The system shall successfully deploy the hardware manufactured by Composite Technology Development. • The structure will interface with Rock. Sat-X through provided mounting surfaces. 2012 Co. DR 16

Mission Requirements: Electronics Integration • All electronic interfaces will be held in place throughout the duration of the flight with the exception of the deployable. • The structure will withstand the forces of launch and protect the scientific and electrical systems. • The structure will thermally protect the electronics for as long as reasonable data can be collected. • The system shall successfully take at least one photo of the deployable as it leaves the canister, and house the cameras securely during launch. 2012 Co. DR 17

Mission Requirements: Ejection System • The ejection system shall be durable enough to survive the forces of launch. • The structure shall allow exposure to an open air environment while still protecting electronics and instruments from harm. 2012 Co. DR 18

Electrical Subsystems: - Power - Memory - Radio Communications (Comm) - Mechatronics - Imaging 2012 Co. DR 19

Conceptual Electrical Configuration Main Structure Power line Digital line Analog Line Power Radio Comm RTS Comm MCU Memory Imaging ADS Charging (before deploy) MCU Sail Deploy Sensors Power RTS Deploy Note: Not actual layout 2012 Co. DR 20

User Guide Compliance: Electrical • The GSE Controlled power lines shall carry a total current of less than 1. 85 A. • The Timer Controlled power lines shall carry a total current of less than 3. 75 A. • All telemetry lines shall operate in the range of 0 – 5 V. • All components shall operate at 28 V or less. Higher voltages shall be used only with express written permission. • All components shall be conformal coated to protect from the space environment. 2012 Co. DR 21

State Chart: Software State 1 Pre-Launch State 2 Launch State 3 Apogee State 4 Post-Apogee Code • Initialize Camera • Delay 30 seconds Telemetry State 5 Splash Down Power On Telemetry G Switch Initial Code • Initialize Devices • Check G Switch Main Code • Store Data • Check Timed Sequence One Telemetry Yes Deploy Code • Deploy RTS • Get Data RTS Camera Yes No RTS 2012 Co. DR Final Code • Check Time Sequence Two • Stop Recording

Design Overview: Rock. Sat-X 2012 User’s Guide Compliance Rough Order of Magnitude (ROM) mass estimate Plates and launcher ~ 10 lbs Rts ~ 2 -3 lbs Estimate on payload dimensions RTS~ 1 U cube sat configuration Deployables/booms? Yes-Deployable How many ADC lines? Exact amount not confirmed Asynchronous use? Yes Parallel use? Yes Power lines and timer use? Yes- will need timer for RTS deployment CG requirement Understood Are you utilizing high voltage? No 2012 Co. DR

Management Andrew Broucek Project Manager Wheeler Gans Systems Lead Nate Keyek. Franssen Structures Lead Emma Young Science Lead Andrew Thomas Electrical Lead Ethan Long Software Lead Devin Mackenzie Structures Eric Lobato Science Shreyank Amartya Electrical Long Tat Software Kameron Medina Structures Aram Podolski Science Brendan Lee Electrical 2012 Co. DR

Preliminary Schedule- Important Dates Task Date Conceptual Design Review (Co. DR) 10/4/11 Online Progress Report 1 Due 10/21/11 Preliminary design Review (PDR) 10/25/11 Online Progress Report 2 Due 11/11/11 Critical Design Review (CDR) 11/29/11 Order Hardware and Begin Fabrication 12/5/11 2012 Co. DR

Preliminary Schedule- Weekly Schedule Day Time/Description Monday 1 -3 pm Software Team meeting Tuesday 2 -3 pm Structures Team meeting 5 -7 pm Science Team meeting Wednesday 2 -3 pm Executive Meeting Thursday 4 -6 pm Electrical Team meeting Mon-Fri 5 -8 pm Common working hours 2012 Co. DR

Budget Source of Funding Amount Composite Technology Development $24, 000 UROP (Not Confirmed) ~$3, 000 EEF(Not Confirmed) ~$2, 000 Total: $29, 000 2012 Co. DR

Additional Support • We will be working in conjunction with Composite Technology Development (CTD). Our main advisors from CTD are still to be determined 2012 Co. DR 28

Conclusions Mission Statement To integrate and validate the Roll Out De-Orbiting Device (RODEO) developed by Composite Technology Development (CTD) and test the attitude determination system from Rocket. Sat VII Next Steps • Prepare for PDR • Finalize Design 2012 Co. DR 29

Questions 2012 Co. DR 30

Refrences 1"The Bright Future of Small Satellite Technology : : Via Satellite. " Guest Edition : : Satellite Today. Web. 04 Oct. 2011. <http: //www. satellitetoday. com/via/features/37150. html>. 2 Carroll, Shawn, and Chris Koehler. Rocksat-X User Guide. 8 Feb. 2011. PDF. 2012 Co. DR 31