Autonomous thrust system and method for safety of separation of Mars exploration surrounding device

A thrust direction, Mars technology, which is applied to the propulsion system devices of space navigation vehicles, aircraft, and space navigation vehicles, etc., can solve problems such as inability to measure in time, and achieve the effect of improving reliability

Pending Publication Date: 2020-06-23
SHANGHAI AEROSPACE CONTROL TECH INST
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Problems solved by technology

Due to the particularity of the track control with the separation of the device and

Method used

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  • Autonomous thrust system and method for safety of separation of Mars exploration surrounding device
  • Autonomous thrust system and method for safety of separation of Mars exploration surrounding device
  • Autonomous thrust system and method for safety of separation of Mars exploration surrounding device

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Embodiment Construction

[0054] The present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0055] Such as figure 1 As shown, the present invention provides a specific embodiment of a separate safe autonomous thrust system for a Mars exploration orbiter, which includes a large thrust system, a small thrust system, a small thrust system in a non-thrust direction, a backup large thrust system, and a backup small thrust system. system, backup non-thrust direction small thrust system; where:

[0056] The large thrust system includes 4 large thrusters, marked as: A3, A5, A7, A9 in the figure. These 4 units are installed on a plane perpendicular to the X-axis of the Mars exploration orbiter system, of which, two are installed on the Z-axis and are installed symmetrically with respect to the Y-axis, and the other two are installed on the Y-axis and are installed symmetrically with respect to the Z-axis , the thrust direction of the four ...

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Abstract

The invention relates to an autonomous thrust system and method for the safety of the separation of a Mars exploration surrounding device. The system comprises a large thrust system, a small thrust system, and a non-thrust direction small thrust system, and can work in three working modes; under the first air injection mode, the large thrust system is used for the orbit control of the Mars exploration surrounding device; the small thrust system is adopted to control the Y-axis and Z-axis attitudes of a Mars detection surrounding device body coordinate system; in the first air injection mode, when the thruster in the small thruster system breaks down, the first air injection mode is switched to the second air injection mode; the large thrust system is adopted to control the Y-axis and Z-axis attitudes of the track of the Mars exploration surrounding device and the body coordinate system; in the first air injection mode, when the large thruster breaks down, the first air injection mode is switched to the third air injection mode; the large thrust system is adopted to control the Y-axis and Z-axis attitudes of the track of the Mars detection surrounding device and the body coordinatesystem; and in the three modes, the non-thrust direction small thrust system is adopted to control the X-axis attitude of the Mars detection surround device body coordinate system.

Description

technical field [0001] The invention relates to a Mars exploration orbiter separation safety autonomous thrust system and method, which are used for the fault diagnosis and reconstruction of the propulsion system during the Mars probe separation orbit control period, and belong to the field of deep space detection fault diagnosis and reconstruction. Background technique [0002] The Mars exploration orbiter carries the lander to capture and brake Mars and then enters the ring-fire orbit. A Mars exploration orbiter is used to carry the lander to change orbit and enter the fire-impact orbit. The method of the fire track is used for the separation of the device and the device. After the detector separates and descends into orbit, it enters an orbit that will hit Mars. If the orbit control thruster of the Mars exploration orbiter fails during the orbit ascent and cannot be raised in time, the probe will face the risk of hitting Mars. Due to the long distance between the fire an...

Claims

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Application Information

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IPC IPC(8): B64G1/24B64G1/26B64G1/40
CPCB64G1/24B64G1/242B64G1/26B64G1/40B64G1/245Y02T90/00
Inventor 冯建军刘斌吴梦璇李立斌朱庆华蔡雄
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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