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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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 tra

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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Example Embodiment

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

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

[0034] Step 2: Design a weighted failure function to improve the performance of fault diagnosis;

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

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

Example Embodiment

[0042] Specific embodiment two: this embodiment is different from specific embodiment one in that the orbital coordinate system of the tracker and the target spacecraft in the step one 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 kinematics 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; Are the relative velocity components of the x-axis, y-axis, and z-axis of the satellite orbit coordinate system; r 0 Is the distance to the center of the target aircraft; μ e Is the earth's gravitational constant; n is the orbital angular velocity of the target aircraft, equal to α x , Α y , Α z It is the control...

Example Embodiment

[0058] Specific embodiment three: This embodiment is different from specific embodiment one or two in that the spacecraft rendezvous system matrix A 0 , B 0 , B 1 , The C expression is as follows:

[0059]

[0060]

[0061] The other steps and parameters are the same as in the first or second embodiment.

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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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