Liquid filling spacecraft posture dynamics physical simulation test system and method

A technology of attitude dynamics and liquid-filled spacecraft, which is applied in the direction of attitude control, space navigation aircraft, aircraft, etc., can solve the problems affecting the control of the air-floor platform and the collapse of the platform, so as to avoid the collapse of the air-floor platform, high precision, and equipment Create simple and easy effects

Inactive Publication Date: 2018-11-23
SHANGHAI SATELLITE ENG INST
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  • Description
  • Claims
  • Application Information

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Problems solved by technology

The three-axis air flotation table has strict requirements on the control of the center of mass of the table body. If a liquid storage tank is installed on the air flotat

Method used

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  • Liquid filling spacecraft posture dynamics physical simulation test system and method
  • Liquid filling spacecraft posture dynamics physical simulation test system and method
  • Liquid filling spacecraft posture dynamics physical simulation test system and method

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Embodiment

[0084] Using the present invention to simulate the liquid sloshing disturbance moment of a certain spacecraft, specifically:

[0085] The spacecraft adopts dual-component propulsion technology, with four 1020L spherical crown storage tanks, the middle column section is 300mm long, and the hemisphere diameter at both ends is Ф1116mm. The combustion agent is monomethylhydrazine (MMH), the oxidant is green dinitrogen tetroxide (MON-1), and it is filled diagonally. When the liquid filling ratio is 65%, the acceleration of the whole star is 0.117m / s 2 When , the parameters of the liquid sloshing model are:

[0086] (1) Parameters of the liquid sloshing model in the tank filled with combustion agent: rest mass 163.9kg, rest mass position (0,0,0.66)m, sloshing mass 210.6kg, pendulum length 0.305m, pendulum suspension point position (0,0,0.66)m 0,-0.14)m, and the shaking directions are (0.8760,-0.4823,0)m and (0.4823,0.8760,0)m respectively;

[0087] (2) Parameters of the liquid sl...

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Abstract

The present invention discloses a liquid filling spacecraft posture dynamics physical simulation test system and method. The system comprises a set of liquid slosh moment simulation systems. The liquid slosh moment simulation system comprises: a liquid slosh moment generator formed by a plurality of single-frame control moment gyroscopes, wherein the liquid slosh moment generator is installed on the body of an air bearing table and performs angular momentum exchange with a triaxial air bearing table to simulate the interference of the liquid slosh on the attitude of a satellite; a liquid sloshcalculation communication module used for moment calculation and telemeasuring data forwarding; a ground monitoring module used for system state monitoring and parameter lettering; and a power moduleconfigured to control the control moment gyroscope set and calculate the power supply of the communication module. The system and the method are suitable for the physical simulation test of the triaxial air bearing table to analyze the influence of the liquid slosh on the attitude of the spacecraft so as to more really and effectively check and verify the control system, and the simulation methodcan avoid the downfall phenomenon of the air bearing table.

Description

technical field [0001] The invention relates to a full physical simulation test method of a three-axis air bearing platform, in particular to a full physical simulation system and method for attitude dynamics of a liquid-filled spacecraft. Background technique [0002] In order to have the ability to break away from the gravity of the earth, enter the GEO transfer orbit or the inter-satellite transfer orbit, re-enter the planet, and fly around the star, the spacecraft is generally equipped with a large liquid-filled storage tank. The ratio is as high as 50% to 60%, or even higher. Therefore, the coupling effect of liquid fuel sloshing and global control is greatly strengthened, which poses a serious challenge to the stability design of the control system. Especially in the maneuvering section of orbit change, due to the ignition of the engine and the eccentric thrust direction, or the jetting of the attitude control thruster, it may cause small or even large sway of the liq...

Claims

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Application Information

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IPC IPC(8): G05D1/08
CPCB64G1/244
Inventor 吕旺邓泓信思博方宝东宋效正朱新波
Owner SHANGHAI SATELLITE ENG INST
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