STPSat-1

AeroAstro is the prime contractor on STPSat-1. STPSat-1 is a highly capable three-axis stabilized space platform. AeroAstro is responsible for spacecraft design and fabrication, integration of all experiments, space vehicle testing, launch integration support, launch and early orbit operations support, and post-launch mission operations support. This spacecraft, which hosts three different DoD experiments, is complete and expected to launch in March 2007.

STPSat-1 continues STP's mission to provide access to space for DoD-sponsored experiments. This spacecraft hosts three experiments: Spatial Heterodyne Imager for Atmospheric Radicals (SHIMMER), Computerized Ionospheric Tomography Receiver in Space (CITRIS), and Micro-Electric-Mechanical System (MEMS)-based PICOSAT Inspector (MEPSI). Consistent with STP's mission, these experiments will demonstrate new technologies for future space applications.

The STPSat-1 design is a function of both the mission requirements and the optimization parameters. Stated generally, two considerations drive the STPSat-1 design: 1) satisfying the requirements of the selected payloads (e.g., pointing, thermal, power, etc.); and 2) developing a system that is compatible with the existing interfaces (launch vehicle, communications, mission operations, etc.). Two optimization parameters complete this definition process: 1) staying within the cost envelope; and 2) minimizing technical risk.

For more information on AeroAstro’s STPSat-1 spacecraft, please download our product data sheet. [download PDF]

STP-SIV

The Standard Interface Vehicle (SIV) provides Multi-Mission high reliability and performance. The innovative SIV design includes a separable Payload Standard Interface Module that may be integrated in parallel with the bus to support accelerated launch schedules and reduce technical risk.

The SIV bus utilizes a standard payload interface to accommodate a variety of payload configuration in low earth orbits from 400 - 850km. The spacecraft supports, without design change, a wide range of inclinations with a minimum one-year lifetime. SIV features high mass and power margins, flight-proven heritage components, and a highly integrated mechanical and thermal design. It incorporates a flexible zero-momentum ACS, fixed and articulated solar arrays, integrated C&DH and power avionics, and a high-reliability SGLS transponder. AeroAstro is under contract to design and build up to six spacecraft buses under the SIV contract, and to provide integration, launch and mission operations support.

AeroAstro is prime contractor for STPSat-1, from which the STP-SIV spacecraft bus is largely derived. The STP-SIV spacecraft will simplify and accelerate access to space for critical new technologies.

For more information on AeroAstro’s STP-SIV spacecraft, please download our product data sheet. [download PDF]

ESPA Ring Interface

The Evolved Expendable Launch Vehicle (EELV) Secondary Payload Adapter, or ESPA, is a ring placed under an EELV primary payload that supports up to six 180-kg secondary spacecraft. By utilizing excess EELV capacity, ESPA increases the launch availability and reduces the launch cost for secondary payloads. ESPA rings are transparent to the EELV primary payload, so ESPA satellites are protected from primary payload manifest changes. The ESPA ring is shown here with the SIV spacecraft attached.