Session
Technical Session X: Mission Enabling Technologies II
Abstract
Cold gas propulsion systems offer today’s CubeSats a relatively simple propulsion solution, but with often limited V capability. Various mission and desired CubeSat capabilities have been identified which would be enhanced or enabled if additional V were available in conjunction with preserving the control authority typically associated with current cold gas propulsion systems. These include large scale orbit transfer for constellation deployment, de-orbit, orbit maintenance, attitude control, and momentum management. To expand the overall utility of the CubeSat form-factor with respect to these objectives, Aerojet is developing a 1U blow-down CubeSat Hydrazine Adaptable Monopropellant Propulsion System (CHAMPS) which will deliver a more than five-fold increase in total impulse compared to similarly-packaged cold gas systems. A four-thruster array, providing three-axis attitude control as well as single-axis V, is integrated into a monolithic piston propellant tank doubling as the primary structure. To satisfy varied mission specific propulsion system requirements, the CHAMPS design supports adjustment of the thrust level and minimum impulse via easily changeable fluid resistors and system operating pressure. Thrust vector orientation can also be tailored through simple modifications of the thruster nozzles. The final flight system design will be fully compliant with Air Force Space Command Manual 91-710.
Presentation Slides
Hydrazine Propulsion Module for CubeSats
Cold gas propulsion systems offer today’s CubeSats a relatively simple propulsion solution, but with often limited V capability. Various mission and desired CubeSat capabilities have been identified which would be enhanced or enabled if additional V were available in conjunction with preserving the control authority typically associated with current cold gas propulsion systems. These include large scale orbit transfer for constellation deployment, de-orbit, orbit maintenance, attitude control, and momentum management. To expand the overall utility of the CubeSat form-factor with respect to these objectives, Aerojet is developing a 1U blow-down CubeSat Hydrazine Adaptable Monopropellant Propulsion System (CHAMPS) which will deliver a more than five-fold increase in total impulse compared to similarly-packaged cold gas systems. A four-thruster array, providing three-axis attitude control as well as single-axis V, is integrated into a monolithic piston propellant tank doubling as the primary structure. To satisfy varied mission specific propulsion system requirements, the CHAMPS design supports adjustment of the thrust level and minimum impulse via easily changeable fluid resistors and system operating pressure. Thrust vector orientation can also be tailored through simple modifications of the thruster nozzles. The final flight system design will be fully compliant with Air Force Space Command Manual 91-710.
