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Spacecraft rendezvous fault diagnosis and filter design method based on event driving

A filter design and event-driven technology, which is applied in the fields of instrumentation, computing, and electrical digital data processing, etc., can solve the problems of high energy consumption in data transmission and high bus bandwidth occupancy

Active Publication Date: 2019-11-05
HARBIN INST OF TECH
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  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to solve the problem of large bus bandwidth occupancy rate and large energy consumption in data transmission in the existing spacecraft rendezvous system, and propose an event-driven spacecraft rendezvous fault diagnosis and filter design method

Method used

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  • Spacecraft rendezvous fault diagnosis and filter design method based on event driving
  • Spacecraft rendezvous fault diagnosis and filter design method based on event driving
  • Spacecraft rendezvous fault diagnosis and filter design method based on event driving

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specific Embodiment approach 1

[0032] Specific implementation mode 1: The specific process of the event-driven spacecraft rendezvous fault diagnosis and filter design method in this implementation mode is as follows:

[0033] Step 1. The orbital coordinate system of the tracker and the target spacecraft is as follows: figure 1 As shown, according to Newton's dynamics theory, the C-W equation is established, and the state-space model of the spacecraft rendezvous system is established according to the kinematic equation;

[0034] Step 2, designing a weighted fault function to improve fault diagnosis performance;

[0035] Step 3. Based on the state space model of the spacecraft rendezvous system established in step 1, design a gain matrix based on dynamic event-driven FDF, and establish an augmented residual system under event-driven conditions;

[0036] Step 4. According to the gain matrix of FDF, get and x(t), then according to And u(t)=Kx(t), get residual signal r(t) and control input u(t);

[0037] ...

specific Embodiment approach 2

[0042] Specific embodiment 2: The difference between this embodiment and specific embodiment 1 is that the orbital coordinate system between the tracker and the target spacecraft in the step 1 is as follows figure 1 As shown, according to the Newtonian dynamics theory, the C-W equation is established, and the state-space model of the spacecraft rendezvous system is established according to the kinematic equation; the specific process is:

[0043] According to Newton's dynamics theorem, the relative dynamics model of the spacecraft is as follows:

[0044]

[0045]

[0046]

[0047] Among them, x, y, z are the relative position components in the satellite orbit coordinate system; Respectively, the relative velocity components of the x-axis, y-axis, and z-axis of the satellite orbit coordinate system; r 0 is the center distance of the target aircraft; μ e is the gravitational constant of the earth; n is the orbital angular velocity of the target aircraft, equal to ...

specific Embodiment approach 3

[0058] Specific embodiment three: the difference between this embodiment and specific embodiment one or two is that the spacecraft rendezvous system matrix A 0 , B 0 , B 1 , the C expression is as follows:

[0059]

[0060]

[0061] Other steps and parameters are the same as those in Embodiment 1 or 2.

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Abstract

The invention discloses a spacecraft rendezvous fault diagnosis and filter design method based on event driving, and relates to the spacecraft rendezvous fault diagnosis and filter design method. Theinvention aims to solve the problems of high bus bandwidth occupancy rate and high data transmission energy consumption in the conventional spacecraft rendezvous system. The method comprises the following steps: 1, establishing a state space model of a spacecraft rendezvous system; 2, designing a weighted fault function; 3, designing an FDF gain matrix based on dynamic event driving, and establishing an augmented residual error system under the event driving condition; 4, obtaining a residual signal and control input according to the gain matrix of the FDF; 5, designing a dynamic event drivingmechanism to enable the gain matrix obtained in the step 3 to be established; 6, designing a residual evaluation function according to the residual signal; and 7, designing a residual evaluation function threshold, and completing fault diagnosis of the spacecraft rendezvous system according to the residual evaluation function. The method is applied to the field of spacecraft rendezvous fault diagnosis and filter design.

Description

technical field [0001] The invention relates to a spacecraft rendezvous fault diagnosis and filter design method. Background technique [0002] Autonomous rendezvous and docking of space spacecraft is an important issue in many space missions. The cost of spacecraft is generally very expensive, and the success of its rendezvous and docking is often of great significance. In the rendezvous and docking process of the master-slave spacecraft, reliability is an important indicator of it. However, components of the spacecraft, especially the measurement sensors that measure the distance between the master and slave spacecraft, are highly likely to fail during the rendezvous. Therefore, in order to improve the robustness and reliability of the spacecraft rendezvous, we designed a fault diagnosis filter (FDF) to detect possible faults in the spacecraft rendezvous system in time. [0003] In the spacecraft rendezvous system, the data measured by the sensor needs to be transmitted...

Claims

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Application Information

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IPC IPC(8): G06F17/50
Inventor 费中阳杨柳王旭东吴宝林关朝旭陈伟重
Owner HARBIN INST OF TECH
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