Location
Utah State University
Start Date
5-11-2011 9:30 AM
Description
This project proposes the demonstration of a novel, compact propulsion system, scaled for CubeSat-sized spacecraft. The tests will demonstrate a system that will provide the ability to precisely position CubeSats to form a large constellation whose members work collectively to accomplish a meaningful tactical objective. The distributed nature of this “swarm” offers distinct advantages not achievable by a single, large-scale spacecraft. Because of their small sizes, CubeSats must be constructed using the most efficient packaging possible. Thus the design challenges associated with creating CubeSat-scale propulsion systems are greater than those associated with designing thrusters for conventional spacecraft. Deploying conventional propulsion systems with gimbaled bell-nozzles for attitude control is infeasible in such small form factors. The proposed design, based on the aerospike nozzle concept, overcomes this difficulty. While the aerospike nozzle has long been known for its altitude compensation capability during endo-atmospheric flight, the aerospike also presents significant advantages for purely in-space applications.
Attitude Control Using Aerodynamic Vectoring on an Aerospike Nozzle
Utah State University
This project proposes the demonstration of a novel, compact propulsion system, scaled for CubeSat-sized spacecraft. The tests will demonstrate a system that will provide the ability to precisely position CubeSats to form a large constellation whose members work collectively to accomplish a meaningful tactical objective. The distributed nature of this “swarm” offers distinct advantages not achievable by a single, large-scale spacecraft. Because of their small sizes, CubeSats must be constructed using the most efficient packaging possible. Thus the design challenges associated with creating CubeSat-scale propulsion systems are greater than those associated with designing thrusters for conventional spacecraft. Deploying conventional propulsion systems with gimbaled bell-nozzles for attitude control is infeasible in such small form factors. The proposed design, based on the aerospike nozzle concept, overcomes this difficulty. While the aerospike nozzle has long been known for its altitude compensation capability during endo-atmospheric flight, the aerospike also presents significant advantages for purely in-space applications.