Session
Session III: Where We're Going Section 2
Abstract
The continuous increase in the number of small satellites under development today is in direct contrast to the number of launch opportunities available for that payload class. The NASA Goddard Space Flight Center, Wallops Flight Facility (WFF) recognized this problem and in 2004 started an effort to reform the system supporting small satellites. The Multi Payload Ejector (MPE) is a fundamental part of this new pathway. The MPE is an orbital carrier that uses common interfaces. It is capable of accommodating a flexible set of small, stand-alone spacecraft, ranging from cubesats to ESPA-class satellites with masses ranging from 2 to 400 pounds. The MPE offers the flexibility to trade mass, volume and orbital altitude, along with the quantity of individual spacecraft, through the modular addition or removal of mechanical sections. Being developed in parallel with the DARPA Falcon Low Cost Launch Vehicle Program, the MPE does meet the vehicle requirements of that program, but it has also been designed to be compatible with more traditional vehicles such as Minotaur I, Minotaur IV, Pegasus, Taurus and Delta, flying as a primary or secondary payload. This mission flexibility allows the MPE to take advantage of a variety of available launch opportunities in the industry. The MPE is an instrumental part of a WFF strategic plan called, ”Small Launch Vehicles Research Project” (SLVR). The goal of the SLVR project is to provide end-to-end mission support for the payloads and selected vehicles on a recurring basis, depending upon demand and available launch opportunities.
Presentation Slides
Multi Payload Ejector (MPE), Bridging the Gap in Recurring Space Access
The continuous increase in the number of small satellites under development today is in direct contrast to the number of launch opportunities available for that payload class. The NASA Goddard Space Flight Center, Wallops Flight Facility (WFF) recognized this problem and in 2004 started an effort to reform the system supporting small satellites. The Multi Payload Ejector (MPE) is a fundamental part of this new pathway. The MPE is an orbital carrier that uses common interfaces. It is capable of accommodating a flexible set of small, stand-alone spacecraft, ranging from cubesats to ESPA-class satellites with masses ranging from 2 to 400 pounds. The MPE offers the flexibility to trade mass, volume and orbital altitude, along with the quantity of individual spacecraft, through the modular addition or removal of mechanical sections. Being developed in parallel with the DARPA Falcon Low Cost Launch Vehicle Program, the MPE does meet the vehicle requirements of that program, but it has also been designed to be compatible with more traditional vehicles such as Minotaur I, Minotaur IV, Pegasus, Taurus and Delta, flying as a primary or secondary payload. This mission flexibility allows the MPE to take advantage of a variety of available launch opportunities in the industry. The MPE is an instrumental part of a WFF strategic plan called, ”Small Launch Vehicles Research Project” (SLVR). The goal of the SLVR project is to provide end-to-end mission support for the payloads and selected vehicles on a recurring basis, depending upon demand and available launch opportunities.
