A Time Optimization Method for Spacecraft Online Reconfiguration
An optimization method and spacecraft technology, applied in the overall field of spacecraft, can solve problems such as low system reconfiguration performance, high reconfiguration difficulty, waste of limited resources, etc., to improve long-life autonomous and safe operation capabilities, completeness and system performance, and the effect of improving utilization efficiency
Active Publication Date: 2020-12-18
BEIJING INST OF SPACECRAFT SYST ENG
View PDF4 Cites 0 Cited by
- Summary
- Abstract
- Description
- Claims
- Application Information
AI Technical Summary
Problems solved by technology
If this "delay" is too short, the diagnostic module does not have enough time to provide accurate fault information for the reconfiguration controller, resulting in poor system reconfiguration performance; on the contrary, if this "delay" is too long, the It will cause a waste of limited resources and cause the spread of fault deviations, making the subsequent reconstruction cost too high
In addition, many specific tasks need to be completed within a specified time window. The smaller the window, the smaller the time redundancy of the system, and the greater the difficulty of reconstruction.
[0005] (2) Most of the failures of actuators are considered, and there is a lack of discussion on fast-changing deviation faults
In fact, the time-varying characteristics of faults can seriously affect the diagnostic accuracy and thus the system reconfiguration performance, especially when the diagnostic results are directly applied in the reconfiguration control loop
Method used
the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
View moreImage
Smart Image Click on the blue labels to locate them in the text.
Smart ImageViewing Examples
Examples
Experimental program
Comparison scheme
Effect test
Embodiment 1
[0048] A method for optimizing the timing of spacecraft online reconfiguration, comprising the steps of:
[0049] (1) Establish a spacecraft system failure model, which includes multiplicative failures and additive failures.
[0050] First, the spacecraft control system is linearized to obtain the following model:
[0051]
[0052]
[0053]
[0054] Among them, I x , I y , I z are the moments of inertia of the x-axis, y-axis, and z-axis of the satellite; x∈R n , u∈R m , y∈R q are the state vector, control input vector and output vector of the system respectively; A∈R n×n ,B∈R n×m ,C∈R p×n They are the state matrix, control input matrix, and output matrix; α, β are the installation angles of the control mechanism to the x-axis and y-axis, respectively, and Φ(α, β) is the moment distribution matrix, which depends on the installation configuration of the control mechanism. ω o is the orbital angular velocity, I 3×3 and I 6×6 Both are unit matrices, and t is t...
Embodiment 3
[0115] A computer-readable storage medium, on which a computer program is stored. When the program is executed by a processor, the steps of the method described in Embodiment 1 are realized.
the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More PUM
Login to View More Abstract
The invention relates to a spacecraft online reconstruction opportunity optimization method and belongs to the spacecraft overall technical field. The method comprises steps of S1, building a spacecraft system fault model, and the faults comprising multiplicative faults and additive faults; S2, on the basis of an expected control target and the spacecraft system fault model in the step S1; obtaining a closed-loop model of the spacecraft system; S3, setting an allowable threshold value of the performance reduction degree after the fault, solving Lyapunov equations in different time periods according to the closed-loop model of the spacecraft system, and obtaining a spacecraft system reconfigurable parameter value containing a reconstruction opportunity; and S4, repeating the steps S2 to S4by taking the maximum reconfigurable parameter value of the spacecraft system in the step S3 as a target function and taking the spacecraft system fault detection time, the spacecraft system task completion time and control input as constraints to obtain the online optimal reconstruction opportunity of the spacecraft.
Description
technical field [0001] The invention relates to an online reconfiguration timing optimization method of a spacecraft, which belongs to the general technical field of spacecraft. Background technique [0002] With the increasing cost and complexity of spacecraft, people have higher and higher requirements for its reliability and safety. Therefore, it is urgent to improve the ability of spacecraft to autonomously respond to failures. In the case of severely limited resources on the planet, the reconfigurability optimization design of the spacecraft system is an effective way to improve the system's autonomous fault handling capability and improve the system's operating quality. [0003] At present, the research on reconfigurability has made some progress, but there are still the following deficiencies: [0004] (1) Most of them focus on the optimization of space resources (for example: configuration, configuration, algorithm), while ignoring the planning of time resources. I...
Claims
the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More Application Information
Patent Timeline
Login to View More Patent Type & Authority Patents(China)
IPC IPC(8): G05B13/04
CPCG05B13/042
Inventor 王大轶李文博屠园园刘成瑞左子瑾赵小宇
Owner BEIJING INST OF SPACECRAFT SYST ENG