Spacecraft propulsion system and method

A propellant and propellant technology, which is applied in the power supply system of space navigation vehicle, space navigation vehicle, and space navigation vehicle guidance device, etc., can solve the problems of less resource sharing, limited specific impulse of cold gas thruster, and complex system.

Active Publication Date: 2017-04-19
SAFRAN AIRCRAFT ENGINES SAS
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, due to the very limited specific impulse of cold-gas thrusters, they consume a large amount of propellant fluid for high-thrust maneuvers, and moreover, in this system, there is little resource sharing among multiple types of thrusters, lead to a rather complex system

Method used

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  • Spacecraft propulsion system and method
  • Spacecraft propulsion system and method
  • Spacecraft propulsion system and method

Examples

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Embodiment Construction

[0022] figure 1 Illustrated is a spacecraft 10, more specifically a satellite, equipped with an attitude and trajectory control system for maintaining the orbit and attitude of the spacecraft relative to a body about which the spacecraft orbits. To this end, the attitude and trajectory control system not only includes at least one sensor 11 for determining the true attitude and trajectory of the spacecraft, but also a control unit 12 connected to the sensor 11 and used to determine the desired attitude and trajectory together with the operations that need to be performed , so that the true attitude and trajectory determined by at least one sensor 11 achieve the desired attitude and trajectory, and includes a manipulation device connected to the control unit 12 and capable of exerting forces and torques on the spacecraft 10 to perform said manipulation. In the example shown, maneuvering devices notably include the space propulsion system 100 , although in addition to this space...

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PUM

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Abstract

The invention relates to the field of spacecraft propulsion, and more specifically to electrically powered spacecraft propulsion. A spacecraft propulsion system (100) according to the invention includes at least one electrostatic thruster (101) with at least one first electricity consumer, a resistojet (102), a circuit (104) for supplying a propellant fluid, and a circuit (103) for supplying electricity comprising at least one first electricity supply line (131) and a first switch (114-1, 114'-1, 114"-1) making it possible to choose between connecting said first electricity supply line (131) to the resistojet (102) and connecting said first electricity supply line (131) to said first electricity consumer of the electrostatic thruster (101). This system thus allows the application of a spacecraft propulsion method including a switching step for selecting a first propulsion mode, in which the resistojet (102) is activated, or a second propulsion mode, in which the electrostatic thruster (101) is activated.

Description

Background technique [0001] The invention relates to the field of space propulsion. [0002] In this field, electric thrusters are becoming more and more common, especially for controlling the attitude and orbit of spacecraft. Specifically, the many types of electric thrusters available offer specific impulses that are generally greater than conventional chemical or cold gas thrusters, thus reducing propellant fluid consumption for the same maneuver, thereby increasing spacecraft life and / or payload. [0003] Among the various types of electric propulsion, two classes are particularly known: the so-called thermoelectric propulsion, in which the propellant fluid is heated electrically prior to expansion in the thrust nozzle, and the so-called electrostatic propulsion, in which the propellant fluid is directly Ionized and accelerated by an electric field. Among thermoelectric thrusters there are in particular those known as "resistance engines", in which heat is transferred t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F03H1/00
CPCF03H1/0018B64G1/405B64G1/428B64G1/402B64G1/415B64G1/42F03H1/00B64G1/26B64G1/443F03H1/0012F03H1/0075
Inventor 弗雷德里克·马尔尚迪斯
Owner SAFRAN AIRCRAFT ENGINES SAS
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