ADAMASat CDR (Introduction/Overview)

1. ADAMASat CDR (Introduction/Overview) www.kentuckyspace.com James Lumpp

2. SOCEM • Sub- • Orbital • CubeSat • Experimental • Mission

3. Wallops Sounding Rocket Launch Vehicles

4. Altitude versus Payload Weight Performance

5. Terrier-Malemute The Terrier-Malamute is a two-stage, solid fuel rocket consisting of a Terrier 1st stage and a Malamute 2nd stage. It is capable of lifting a 200 lb payload to an apogee of approximately 700 km or a 500 lb payload to approximately 400 km.

6. Payload Section

7. SOCEM Experiment Concept

8. Trajectory Estimate

9. SOCEM Purpose • The purpose of this mission is to demonstrate the feasibility of launching CubeSats from the Wallops 17” sounding rocket form-factor. • Once ejected, the CubeSats will carry out experiments and return data via telemetry to mobile ground stations deployed at Wallops and existing ground stations in Kentucky.

10. Partners • Cal Poly partnering to provide Poly CubeSat Launcher (PCL) and a CubeSat Experiment • Kentucky Space: CubeSat, Sounding Rocket, High-Altitude Balloon Programs • NASA Wallops Flight Facility Sounding Rockets Program

11. SOCEM Success Criteria • Minimum Success Criteria • Integration of PCL in Malemute payload section • Delivery and Integration of CubeSats into PCL • Acceptance testing of complete payload • Comprehensive Success Criteria • Successful ejection of CubeSats • Reception of telemetry data from CubeSats on portable ground stations at Wallops and stations in Kentucky • Successful reception of experiment results from monofilament cutter system

12. Mechanical Interface:PCL to Bulkhead Pedestal between PCL and payload deck, elevates PCL 1”, centering it on the 6” x 6” door opening. Pedestal top interfaces with PCL bolt pattern Pedestal designed to interface with payload deck.

13. Mechanical Interface:Blow-off door and CubeSats 2U KY Space Payload will interface directly with the inner surface of the rocket door (Ultem Material) 1U Cal Poly payload directly behind the KY Space Payload

14. ADAMASat • Antenna • Deployment • and • Mono-filament • Actuator • Satellite

15. ADAMASat Payload • Nichrome and mono-filament actuator experiment • 22 turn coil of 36 Ga Nichrome wire • ~5.5 Ohms • Housed in a glass tube

16. ADAMASat ConOps • T+74 s (125km): Door Open/Satellite Ejection • Antennas Deployed (held passively by PCL) • Foot switch energizes satellite power rail(s) • T + 80 s: Beacon Begins (3 second interval) • T + 85 s: Telemetry Begins (5 second interval) • T + 350 s: Cutter Experiment Initiated • T + 360 s: Telemetry includes experiment results • T + 600 s (Sea Level): Impact

17. CubeSat Form-Factor • CubeSat and P-POD Standard minimize risk • Poly CubeSat Deployer (PCL) based on MK III P-POD with Flight Heritage

18. CubeSat Standard Developed in 1999 by Cal Poly and Stanford “High risk” missions, student innovation, leverage COTS technology, shorter development cycles Less expensive access to space International standard 1 U – 10cm cube, 1 Kg 2 U – 10cm x 10cm x 20cm, 2 Kg 3U – 10cm x 10cm x 30cm, 3 Kg

19. CubeSat Form Factor

20. P-POD Standard Poly Picosatellite Orbital Deployer (P-POD) Flight heritage and qualification for a variety of launch vehicles, third generation Robust rail and spring system that assures Operation in space environment Anodized 7075-T73 Aluminum with Teflon impregnation.

21. P-POD Mechanical Detail

22. Poly CubeSat Launcher (PCL) Modified MK III P-POD Door, QuickNut assembly, and connectors removed No cover plates Rail System of PCL

23. California Polytechnic UniversityPolySat Program Four Orbital Satellites CP1, 2, 3, and 4 CP1 and 2 were lost due to Dnepr launch vehicle failure CP3 and CP4 on-orbit SOCEM Payload is based on CP4 Mission to test the C&DH board

24. www.kentuckyspace.com