-
公开(公告)号：US20200024003A1
公开(公告)日：2020-01-23
申请号：US16266520
申请日：2019-02-04
Applicant: Raytheon Company
Inventor： Frederick B. Koehler , Jeremy C. Danforth , Ward D. Lyman , Mark T. Langhenry , Matt H. Summers , Paul E. Pontius , Brian M. Pape , Jared D. Stallings , James K. Villarreal , Thomas Villarreal
Abstract: A satellite has thrusters that are integral parts of its frame. The frame defines cavities therein where thrusters are located. The thrusters may include an electrically-operated propellant and electrodes to activate combustion in the electrically-operated propellant. The frame may be additively manufactured, and the propellant and/or the electrodes may also be additively manufactured, with the frame and the propellant and/or the electrodes also being manufactured in a single process. In addition the thrusters may have nozzle portions through which combustion gases exit the thrusters. The thrusters may be located at corners and/or along edges of the frame, and may be used to accomplish any of a variety of maneuvers for the satellite. The satellite may be a small satellite, such as a CubeSat satellite, for instance having a volume of about 1 liter, and a mass of no more than about 1.33 kg.
-
公开(公告)号：US20180128207A1
公开(公告)日：2018-05-10
申请号：US15274669
申请日：2016-09-23
Applicant: Raytheon Company
Inventor： James K. Villarreal , Mark T. Langhenry , Matt H. Summers
CPC classification number: F02K9/24 , B64G1/403 , F02K9/08 , F02K9/12 , F02K9/26 , F02K9/28 , F02K9/34 , F02K9/82 , F02K9/86 , F02K9/94 , F02K9/95 , F02K9/97 , F05D2220/80 , F05D2240/35
Abstract: Electrically operated propellant is used to supplement the thrust provided by solid rocket motor (SRM) propellant to manage thrust produced by a SRM. The gas produced by burning the electrically operated propellant may be injected upstream of the nozzle to add mass and increase chamber pressure Pc, injected at the throat of the nozzle to reduce the effect throat area At to increase chamber pressure Pc or injected downstream of the throat to provide thrust vector control or a combination thereof. Certain types of electrically operated propellants can be turned on and off provided the chamber pressure Pc does not exceed a self-sustaining threshold pressure eliminating the requirement for physical control valves.
-
公开(公告)号：US20180003130A1
公开(公告)日：2018-01-04
申请号：US15197421
申请日：2016-06-29
Applicant: Raytheon Company
Inventor： Matt H. Summers , James K. Villarreal , Mark T. Langhenry , Jeremy C. Danforth , John W. Walter
IPC: F02K9/26 , B60R21/264 , F02K9/95 , B60R21/26
CPC classification number: F02K9/26 , B60R21/264 , B60R2021/26029 , F02K9/94 , F02K9/95 , F42C19/0819
Abstract: Electrical ignition of electrically operated propellant in a gas generation system provides an ignition condition at an ignition surface between a pair of electrodes that satisfies three criteria of a current density J that exhibits a decreasing gradient along an axis normal to an ignition surface, is substantially constant across the ignition surface and exceeds an ignition threshold at the ignition surface. These criteria may be satisfied by one or more of an angled electrode configuration, a segmented electrode configuration or an additive to the electrically operated propellant that modifies its conductivity. These configurations improve burn rate control and consumption of the available propellant and are scalable to greater propellant mass to support larger gas generation systems.
-
-
Search Results
23
records
(took 0.013 seconds)
