AbstractOrbital maneuvering of microsatellite and nanosatellite requirements can be efficiently addressed by planar nozzles, in which real-time thrust control is gained actuating on the nozzle throat area. In the present work, the method of characteristics is used to design a hypersonic contour; then, the resulting profile is laser cut, assembled, and built into a propulsion system to finally perform tests in a vacuum chamber under several working conditions. Results are used to validate the profile and modeling assumptions and investigate overall behavior. Tests showed that thrust-inlet pressure ratio is a linear function of separation between nozzle contours and that no additional losses are introduced in the system. The corresponding design/manufacture/assembly tools can be used to a provide low-cost/low-weight controllable propulsion systems to the small-satellite industry with no efficiency loss.
Planar Nozzles for Controllable Microthrusters
Journal of aerospace engineering ; 30 , 3
2017
Aufsatz (Zeitschrift)
Englisch
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