The DoD Space Test Program Standard Interface Vehicle (ESPA) Class Program

Transcription

1 The DoD Space Test Program Standard Interface Vehicle (ESPA) Class Program Mr. Mike Marlow STP-SIV Program Manager Co-Authors Lt Col Randy Ripley Capt Chris Badgett Ms. Hallie Walden 20 th Annual AIAA/USU Conference on Small Satellites

2 Space Test Program Mission STP serves as the primary provider of spaceflight for the entire DoD space science and technology community STP is a DoD Program; USAF is the Executive Agent TEX MSTRS POAM III CORIOLIS RADCAL STPSat 1 TSX-5 CLOUDSAT th Annual AIAA/USU conference on Small Satellites 20th XSS-11 C/NOFS 2

3 SERB Experiment Analysis Launch only Sounding Rocket Shuttle 20% 6% ISS KC-135 Build a SC 54% 1% 3% 16% * SERB Lists Performed design trade studies to accommodate majority of SERB experiments requiring a bus acquisition ESPA-Class 63% 7% 30% Med/Lg (>400 lb) Small (<=400 lb) Nano 20 th Annual AIAA/USU conference on Small Satellites 3

4 Standardization Concepts Terms Standard interfaces Pre-specified boundary and limits for interaction across boundary Standard parts Units with identical form and function that form a distinct portion of different systems Standard architectures (fixed, scalable, modular/reconfigurable) Defined ways of configuring and connecting parts of system Missions STEP CNES 20 th Annual AIAA/USU conference on Small Satellites 4

5 STP-SIV Goals Develop an agile, repeatable, ESPA-Class space- flight capability for DoD space technology demonstrations with a targeted launch readiness date of Develop a non-proprietary standard payload to spacecraft interface (mechanical, thermal, data and power) for use by all experiments hosted on STP-SIV (ESPA Class) program spacecraft. Develop flexible capability to launch on a Minotaur-I, Minotaur-IV, other commercial vehicles, or attached to an Evolved Expendable Launch Vehicle (EELV) Secondary Payload Adaptor (ESPA). Reduce non-recurring costs through the life of the program through the use of a repeatable space-flight capability, a standard payload interface and overall mission costs through launch vehicle flexibility. 20 th Annual AIAA/USU conference on Small Satellites 5

6 Acquisition Approach Flexible contract for rapid acquisition of satellites Uses low risk technologies to lower spacecraft cost Incorporates lessons learned Generates a capability to purchase and integrate space hardware (e.g,. separation system, adapter) Permits payload integration from non-serb customers Options for multiple spacecraft procurements 20 th Annual AIAA/USU conference on Small Satellites 6

7 Spacecraft Capability Orbit Altitude km Orbit Inclination Launch Mass 180 kg SV Volume (cm) 60.9 x 71.1 x 96.5 SV Lifetime 1 year Reliability (at 7 months) 0.90 Stabilization Method 3-axis Pointing Modes Nadir, Sun Pointing, Safe Attitude Knowledge σ (goal σ) Attitude Control 0.1 3σ (goal σ) Bus Voltage 28 V Comm Frequency SGLS Command Rate 2 kbps uplink Telemetry Rate 2 Mbps downlink Data Storage 8 Gbits 20 th Annual AIAA/USU conference on Small Satellites 7

8 Payload Interface Specifications Payload mass 60 kg (goal 85 kg) Payload OAP 100 Watts Payload Volume 0.12 m3 (goal 0.16 m3) PL Field of Regard Unobstructed hemispherical FOV Number of Payloads Payload Data Handling Up to Four 460 kbps / payload PL Digital Cmd & Data Interface RS-422 Serial Tlm and Cmd, Bi-Level Discreet Output PL Analog Data Interface NLT 8 analog channels / payload for PL H&S Payload Heat Rejection 100 Watts Interface Temperature -9 C to +39 C th Annual AIAA/USU conference on Small Satellites 20th 8

9 Launch Vehicle Compatibility Falcon 1 Pegasus/Raptor Minotaur I Minotaur IV EELV Secondary Payload Adaptor (ESPA) [Atlas and Delta] 20 th Annual AIAA/USU conference on Small Satellites 9

10 Benefits Provides cost-effective platform to mature technologies and meet design challenges Non-recurring costs reduced/eliminated for follow-on vehicles Reduces spacecraft risk Demos utility of standards for experiment-tospacecraft integration Leverages evolving low-cost launch capabilities with streamlined spacecraft development process Supports more responsive access-to-space for both SERB and non-serb payloads Increases launch opportunities for small spacecraft 20 th Annual AIAA/USU conference on Small Satellites 10

11 Opportunities Provides cost-effective platform to demo payloads and systems to support production programs Enables sys production & operational communities to leverage S&T spaceflight opportunities Share SIV payload space Rideshare S&T launch opportunities ESPA on every EELV, payload adaptors on Minotaurs I & IV Offers contractual mechanism for ACTDs, or other ops demos, on cost-reimbursable basis Once successful, basis for follow-on programs Larger spacecraft class Use of internal interfaces 20 th Annual AIAA/USU conference on Small Satellites 11

12 FY09 Rideshare Proposal STP is designing a mission around a single ESPA-class spacecraft Orbit: 600 km at 65 inclination ILC: FY09 S/C mass: 180 kg SLV is TBD No excess spacelift capability is expected With partnership, STP could re-design the mission around a Minotaur IV Same orbit, same ILC, but with 4 times more capability ~1117 kg capability Multi-payload adapter mass: 230 kg Available Payload Mass: 887 kg STP-SIV mass: 180 kg 3 ESPA-Class 180 kg each or 1 larger 540 kg that fits Margin: 167 kg 20 th Annual AIAA/USU conference on Small Satellites 12

13 STP Rideshare Opportunities FY09 SLV PL Selection Development Mission Integr Launch DMSP F-19 SPL Selection Special Studies* Mission Unique Mission Integr Launch STP-2 SPL Selection Special Studies* Mission Unique Mission Integr Launch FY11 SLV PL Selection Mission Integr Launch DMSP F-20 SPL Selection Special Studies* Mission Unique Mission Integr Launch FY13 SLV PL Selection Mission Integr Launch FY06 FY07 FY08 FY09 FY10 FY11 FY12 FY13 1Q 2Q 3Q 4Q 1Q 2Q 3Q 4Q 1Q 2Q 3Q 4Q 1Q 2Q 3Q 4Q 1Q 2Q 3Q 4Q 1Q 2Q 3Q 4Q 1Q 2Q 3Q 4Q 1Q 2Q 3Q 4Q There are potentially 30 ESPA-class spacecraft rideshare opportunities between FY09 FY13 20 th Annual AIAA/USU conference on Small Satellites 13

14 Summary SIV is a change from past STP business practices Moving away from one-of-a-kind spacecraft to gain benefits of successive spacecraft builds More responsive IDIQ contract, fits with other Space Development & Test Wing IDIQs Planned to provide improved access to space for SERB S&T payloads Potential benefits for broader space community Operational users must contend with Class C spacecraft design and lack of support infrastructure SIV is a Transformational Capability for STP 20 th Annual AIAA/USU conference on Small Satellites 14

15 The DoD Space Test Program Standard Interface Vehicle (ESPA) Class Program Mr. Mike Marlow STP-SIV Program Manager th Annual 20th AIAA/USU Conference on Small Satellites 20 Annual AIAA/USU conference on Small Satellites 15 th th

16 Backup Slides 20 th Annual AIAA/USU conference on Small Satellites 16

17 Outline Space Test Program Mission Standardization Concepts STP-SIV Goals Acquisition Approach Spacecraft Capability Payload Interface Specifications Launch Vehicle Compatibility Benefits Opportunities Summary 20 th Annual AIAA/USU conference on Small Satellites 17

18 SIV: What it is not Not intended as end-all solution for S&T or operational communities Not STP s only spaceflight mode Not pushing spacecraft subsystem state-of-the-art Doesn t require a standard bus Not in competition with other initiatives Complements Operational Responsive Space, et al 20 th Annual AIAA/USU conference on Small Satellites 18

19 Standard Payload to Spacecraft Interfaces Spacecraft Payload 2 Mechanical Fasten payload hardware to spacecraft structure Align payload hardware to spacecraft reference Thermal M T P D Payload 1 Sense temperature at payload to spacecraft interface Control temperature at payload to spacecraft interface by affecting spacecraft side Power Supply primary main electrical power to payload Supply redundant main payload power Supply power for payload heaters Data Supply bilevel discrete signal from spacecraft to payload for reset or other switching functions Provide command data from spacecraft to payload Provide data transfer from spacecraft to payload (code upload, time synch, attitude, GPS) Provide digital telemetry data from payload to spacecraft Provide analog data from payload to spacecraft (state of health monitoring) 20 th Annual AIAA/USU conference on Small Satellites 19