A Method for Estimating the Position of Spacecraft's Center of Mass in Orbit

A spacecraft and center of mass technology, applied in the field of on-orbit rapid estimation of the position of the spacecraft center of mass, can solve the problems of large impact and thrust errors, achieve the effects of reducing measurement accuracy, avoiding calculation errors, and simple algorithms
CN108401561BInactive Publication Date: 2013-07-24NORTHWESTERN POLYTECHNICAL UNIV
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Patent Information

Authority / Receiving Office
CN Β· China
Patent Type
Patents(China)
Current Assignee / Owner
NORTHWESTERN POLYTECHNICAL UNIV
Publication Date
2013-07-24
Estimated Expiration
Not applicable Β· inactive patent

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Abstract

The invention relates to a method for estimating the position of the center of mass of a spacecraft, in particular to a method for quickly estimating the position of the center of mass of the spacecraft. The technical feature is that: based on attitude kinematics equations, the center of mass position estimation equation is established by using the least square method. Two accelerometers are installed in the three-axis direction of the spacecraft body, combined with the gyro information, the angular acceleration at each time is calculated, which avoids the calculation error caused by the direct differentiation of the angular velocity to obtain the angular acceleration, and greatly reduces the estimation algorithm. measurement accuracy requirements. The new method for estimating the center of mass of the spacecraft does not need to know the information of the moment of inertia and control moment of the spacecraft, and the algorithm is simple, which can ensure that the absolute error of the estimation of the center of mass of the spacecraft is less than 10 mm.
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Description

technical field The invention relates to a method for estimating the position of the center of mass of a spacecraft, in particular to a method for quickly estimating the position of the center of mass of the spacecraft. Background technique At present, the methods for on-orbit estimation of the position of the spacecraft center of mass are mainly researched from two aspects: the dynamic equation and the kinematic equation of the spacecraft. A kind of A method for estimating the position of the center of mass based on spacecraft attitude dynamics. This method utilizes three gyroscopes to measure the three-axis angular velocity, combined with the thruster output to estimate the center of mass position. This method needs to know the rotational inertia of the spacecraft, and the thrust error seriously affects the estimation accuracy of the center of mass position. E.Bergmann (E.Bergmann, J.Dzielski, Spacecraft Mass Property Identification with Torque-Generating Control[J], Jo...

Claims

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