Responsive Access to Space: Space Test Program Mission S26 Capt Holly Borowski, Mr
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Responsive Access to Space: Space Test Program Mission S26 Capt Holly Borowski, Mr. Kenneth Reese DOD Space Test Program, Space and Missile Systems Center, Space Development and Test Wing 3548 Aberdeen Avenue SE, Kirtland AFB, NM 87117; (505) 846-2530 [email protected] [email protected] Mr. Mike Motola Orbital Sciences Corp. 3380 South Price Road Chandler, AZ 85248-3534 [email protected] Abstract— Space Test Program Mission S26 (STP-S26) is the twenty sixth dedicated small launch vehicle mission of 1. INTRODUCTION the Department of Defense Space Test Program.*† STP-S26 extends previous standard interface development efforts, The mission of the Department of Defense (DOD) Space implementing a number of capabilities aimed at enabling Test Program (STP) is to provide access to space for responsive access to space for small experimental satellites experiments from the DOD Space Experiment Review and payloads. The STP-S26 Minotaur-IV launch vehicle is Board (SERB). STP-S26 is the twenty sixth dedicated configured in a Multi-Payload Adaptor configuration which small launch vehicle mission for STP. In total, STP-S26 includes the following features: will launch 14 experiments on seven separate spacecraft, • The Multi-Payload Adaptor (MPA), which was one of the most for a single launch in the 40-year history of developed by Orbital Sciences Corporation for STP to STP. STP-S26 will be launched on a Minotaur-IV launch launch up to four ESPA-class satellites on the vehicle being developed by Orbital Sciences Corporation Minotaur-IV. (OSC) from the Kodiak Launch Complex under a contract • Provisions for the inclusion of up to four Poly-Picosat with the Alaska Aerospace Corporation (AAC). The Orbital Deployers (P/PODs) to be mounted on the current launch is expected late spring to summer 2010. Stage 4 avionics cylinder. • A dual orbit capability provided by the Hydrazine Auxiliary Propulsion System (HAPS). The design provides volume and mass for four additional payloads attached to the HAPS avionics cylinder. The actual payload manifest of STP-S26 includes four ESPA-class satellites manifested on the MPA and three cubesats. One of the four ESPA-class satellites is STPSat- 2, the first Standard Interface Vehicle. STP implemented a flexible, responsive “dual path” process for a late satellite manifest change. The goal was to delay the final manifest decision as late as possible while minimizing risk. STP-S26 is a complex multi-payload mission and incorporates many innovative capabilities enabling responsive access to space. TABLE OF CONTENTS Figure 1 – Fully Loaded ESPA Stack TABLE OF CONTENTS...........................................................1 on EELV Illustration 1. INTRODUCTION.................................................................1 2. MINOTAUR-IV MULTIPAYLOAD ADAPTOR DESIGN The STP-S26 mission extends previous standard interface REFERENCE MISSION...........................................................3 development efforts intended to maximize access to space 3. DESIGN REFERENCE MISSION ON STP-S26 ...................5 for experimental satellites and payloads. One such effort 4. RESPONSIVE LATE MANIFEST PROCESS.........................6 initiated by STP is the Evolved Expendable Launch Vehicle 5. CONCLUSION ....................................................................8 (EELV) Secondary Payload Adapter (ESPA). Many large REFERENCES ........................................................................8 EELV missions launch with unused mass and volume BIOGRAPHY ..........................................................................8 margin. The ESPA ring was developed to accommodate up to six satellites as secondary payloads on an EELV mission. 1 Figure 1 illustrates the ESPA ring and secondary payloads * 978-1-4244-3888-4/10/$25.00 ©2010 IEEE † IEEEAC paper # 1220, Updated January 4, 2009 on a notional EELV mission. 1 The Planner’s Guide also details the mechanical and electrical interface standards, environmental testing standards, and mission integration and documentation requirements. Satellites compliant with the ESPA standards greatly increase their probability of gaining access to space. Like ESPA, the STP Standard Interface Vehicle (SIV) was developed to improve access to space for SERB payloads. Itself an ESPA-class satellite, the SIV additionally defines a standard interface for payloads. Described in the STP-SIV Payload Users Guide (reference 2), adherence to these standard interfaces makes a payload compatible with SIV and increase the probability of manifest. The SIV is designed to operate over a range of low earth orbit altitudes and inclinations and meet the power, data, attitude and thermal requirements of a broad spectrum of potential payloads. It additionally is designed to integrate onto multiple launch vehicles, including the Minotaur I, Minotaur IV, Minotaur V, and an ESPA ring. The SIV can accommodate up to four payloads weighing 132 lbs (60 kg) and requiring 100 Watts of power on orbit in total. STPSat- 2 (described later in this paper) is the first SIV satellite and is manifested on STP-S26. The second SIV, STPSat-3, is Figure 2 – STP-SIV provides a currently under development. standard payload interface The Minotaur-IV family of launch vehicles is developed by The ESPA Payload Planner’s Guide (reference 1) defines Orbital Sciences Corporation under the Orbital/Suborbital standards for satellites planning to be compatible with the Program 2 (OSP-2) managed by the Space Development ESPA ring. Some of the key standards: and Test Wing. It builds upon previous low cost launch • Mass not-to-exceed (NTE) 400 lb (181 kg) with the initiatives such as Taurus and Minotaur-1. The first three center of gravity CG not more than 20 in (51 cm) from stages of the Minotaur IV consist of refurbished the interface plane government furnished equipment (GFE) Peacekeeper Stages • Volume NTE 24”x28”x38” (61 cm x 71 cm x 97 cm) 1, 2 and 3. The Stage 4 solid motor is the same Orion 38 Figure 3 – Minotaur IV Space Launch Vehicle 2 design used on Minotaur I, Pegasus, Taurus, and other Orbital Sciences Corporation between June – October 2007. Orbital launch vehicles. An optional Star 48V motor is The prioritized government goals for the study were: available for additional performance. Figure 3 depicts the 1. Provide access to space for STPSat-2 Minotaur-IV launch vehicle. Figure 4 shows the Minotaur- 2. Demonstrate dual-orbit capability of the Minotaur IV IV mass capacity to circular low earth orbit for a number of with Hydrazine Auxiliary Propulsion System (HAPS); inclinations from Kodiak, AK. same inclination, different altitude 3. Demonstrate multi-payload capability on Minotaur IV to fly additional ESPA-class SVs 4. Provide access to space for additional SERB rideshare experiments The primary orbit was specified to be 650 km at 72 degrees inclination driven by the primary payload, STPSat-2. The secondary orbit had the same inclination and was to be circular as high as possible to demonstrate HAPS performance. In conducting the MPA study Orbital also had some corporate objectives. These included meeting or exceeding all the study objectives, incorporating design flexibility so it could meet future mission needs and not be a single point solution, and maximizing commonality by building on existing Minotaur IV design and incorporating Minotaur-V conceptual design concepts. Figure 4 – Minotaur IV Performance from Kodiak Some of the deliverables of the study included: • Configuration layout for the standard fairing for the Minotaur IV launch vehicle including payload envelopes and the proposed adapters 2. MINOTAUR-IV MULTIPAYLOAD ADAPTOR • Trajectory data with margins specified DESIGN REFERENCE MISSION • Draft interface control document (ICD) for Minotaur IV MPA Design Reference Mission, including The Minotaur-IV Multiple Payload Adaptor (MPA) study mechanical and electrical Interfaces was sponsored by the Space Test Program and conducted by • Results of preliminary coupled loads analysis Figure 5 – Minotaur-IV MPA3 Design Reference Mission • Execution plan for Minotaur IV multi-payload missions including schedules and funding profile The result of the study was the Minotaur-IV MPA design reference mission. The results met all the Air Force objectives and incorporated commonality and reuse wherever possible. Figure 5 depicts the configuration layout for the MPA design reference mission. In this configuration the HAPS with its avionics cylinder sits atop a RUAG separation system on the HAPS interstage cone. On top of the HAPS cylinder is the non-separating multi- payload adaptor (MPA). Figure 6 shows an upper view of the MPA. Figure 7 – Arrangement of four ESPA-class satellites on the MPA fairing dynamic envelope. The Minotaur-IV MPA design reference mission also provides volume and mass for deploying space vehicles from the sides of the HAPS avionics cylinder. Figure 8 shows the configuration of the HAPS auxiliary payload space. There are locations for four payloads each having a Figure 6 – Minotaur-IV Multi-Payload Adaptor volume not to exceed 20” x 20” x 48” (51 cm x 51 cm x 122 cm). The HAPS cylinder can either accommodate a The MPA has the capacity to accommodate four ESPA class configuration of two payloads each up to 130 lb (59 kg), or satellites, each weighing up to 400 lbs (181 kg) and four payloads each up to 65 lb (30 kg). Future MPA measuring 24”x28”x38” (61 cm x 71 cm x 97 cm). Figure 7 missions could utilize this capability to deploy spacecraft depicts an arrangement