Optimization adjustment method for intersatellite separation near field security

Abstract

The application discloses an optimization adjustment method for intersatellite separation near-field safety, which comprises the following steps: firstly, fuzzy parameter identification is carried out to identify key engineering parameters so as to carry out early control, and meanwhile, minor fuzzy engineering parameters are removed to determine initial engineering parameters for iterative optimization; and then, a Monte Carlo targeting method is used to establish the initial engineering parameters and the deviation range after control in a dynamic simulation model, and a simulation software is used to carry out dynamic simulation calculation of all combinations to obtain the worst result of the near-field distance under all conditions, and if the safety requirement is not met, the adjustment of the nominal value, the deviation and the nearest distance layout is carried out and the next round of iteration is carried out until the requirement is met. The method realizes the rapid identification and iterative optimization of the fuzzy engineering parameters, saves the calculation resources, the time cost and the labor cost, and shortens the product development cycle.

Description

Technical Field

[0001] This invention belongs to the field of spacecraft control and relates to a method for near-field safety analysis of inter-satellite separation of multiple spacecraft, and in particular a method for near-field safety assessment and control of inter-satellite separation under multiple fuzzy parameter constraints. Background Technology

[0002] Inter-satellite separation of multiple spacecraft is typically achieved through connection and separation mechanisms. After the connection device unlocks, separation springs provide the energy for successful separation of the primary and secondary satellites. During separation, if protruding equipment, cables, or multi-layer structures on the primary and secondary satellites interfere with or become entangled, it can lead to abnormal spacecraft attitudes or even mission failure. Due to the influence of ground gravity, the multibody motion of inter-satellite separation in microgravity environments cannot be accurately reproduced in ground tests, making it impossible to determine near-field separation safety under extreme conditions. Therefore, conducting near-field safety calculations for inter-satellite separation during the mission design phase is a prerequisite for mission success.

[0003] Currently, near-field safety analysis for inter-satellite separation faces two main engineering challenges. Firstly, there are numerous engineering parameters that may affect near-field safety, each with its own nominal value and deviation. Previous near-field simulation methods only focus on parameter deviations, employing ergonomic calculation strategies. This leads to an exponential increase in computational scale with the number of parameters, incurring enormous computational costs without quantitatively assessing the rationality of the nominal values ​​of the engineering parameters. Secondly, during the mission design phase, the nominal values ​​and deviations of these engineering parameters are often ambiguous. The engineering parameters exhibit complex coupling effects on near-field safety, where a change in one affects the entire system. This leaves designers feeling powerless when iterating or optimizing design schemes. Summary of the Invention

[0004] The technical problem solved by this invention is to overcome the shortcomings of the prior art and provide a method for near-field safety optimization and adjustment of inter-satellite separation that integrates fuzzy parameter identification and Monte Carlo target shooting. This method enables rapid identification and iterative optimization of fuzzy engineering parameters, saves computing resources, time costs and manpower costs, and shortens the development cycle.

[0005] The technical solution of this invention is: an optimized adjustment method for near-field safety during inter-satellite separation, comprising the following steps:

[0006] (1) According to the design scheme, establish a multibody dynamics simulation model of multiple spacecraft with inter-satellite separation;

[0007] (2) List all engineering parameters that may affect the near-field safety of inter-satellite separation, determine the nominal values ​​and corresponding deviation ranges of each engineering parameter according to the design scheme, and further determine the minimum spacing D of the motion process under ideal conditions. min And the expected value of separation safety Dexp ;

[0008] (3) For all engineering parameters, only one engineering parameter is selected as the adjustment item each time. While keeping the nominal values ​​of other engineering parameters unchanged, the adjustment item is taken as the limit value of the deviation in two directions through simulation to obtain the corresponding minimum inter-satellite spacing change. After calculating the minimum inter-satellite spacing change corresponding to each of all engineering parameters, they are sorted according to the magnitude of the minimum inter-satellite spacing change.

[0009] (4) Sort the key engineering parameters according to the numerical sorting of the minimum inter-satellite spacing change, and select the key engineering parameters based on the threshold of the minimum inter-satellite spacing change; the rest are secondary engineering parameters.

[0010] (5) For all engineering parameters, their nominal values ​​are taken, and the corresponding minimum inter-satellite spacing change Δd is obtained through simulation. It is determined that Δd ≤ β(D min -D exp If the condition is true, proceed to the next step; otherwise, readjust the nominal values ​​of the key engineering parameters or the design scheme until Δd ≤ β(D). min -D exp After its establishment, proceed to the next step, where β is the safety factor;

[0011] (6) For key engineering parameters, select their adjusted nominal values ​​and corresponding deviation ranges. For minor engineering parameters, select their nominal values ​​as initial parameter settings for Monte Carlo target simulation. By performing traversal simulation calculations on the upper and lower limit combinations of key engineering parameters, obtain the minimum inter-satellite spacing change corresponding to each working condition. The maximum value of the minimum inter-satellite spacing change is denoted as Δd. max ;

[0012] (7) If Δd max ≤β(D min -D exp If the design scheme and the nominal values ​​of each engineering parameter, and the corresponding deviations meet the near-field safety requirements for inter-satellite separation, then the deviation ranges are adjusted sequentially according to the key engineering parameters until the adjusted Δd is achieved. max The requirements are met; if the final Δd max If the requirements are still not met, return to step (5) to readjust the nominal values ​​of the key engineering parameters or the design scheme until Δd is reached. max Continue until the requirements are met.

[0013] Furthermore, the ideal state described above is that the inter-satellite separation process only has linear velocities along the theoretical separation direction.

[0014] Furthermore, the process of sorting key engineering parameters based on the numerical values ​​of the minimum inter-satellite spacing variation and then filtering them using a threshold value for the minimum inter-satellite spacing variation specifically involves defining an engineering parameter sensitivity S. i , When S i When ≥α, the corresponding engineering parameter is the critical engineering parameter; X1, X2, X3... are all engineering parameters, and α is the given sensitivity threshold.

[0015] Preferably, the value of α is 5%, and the value of the safety factor β is 80%.

[0016] Furthermore, in step (5), the nominal values ​​or design schemes of key engineering parameters are readjusted. The adjustment method is as follows: first, the layout scheme is adjusted to increase D. min If the layout scheme is limited and the adjusted Δd still does not meet the requirements, the nominal values ​​of the key engineering parameters will be adjusted. Specifically, the nominal values ​​will be adjusted in order of priority according to the key engineering parameters. If the adjusted nominal value of the first key engineering parameter still does not meet the requirements, the nominal value of the next key engineering parameter will be adjusted until the adjusted Δd meets the requirements.

[0017] Furthermore, the traversal simulation was performed using ADAMS software, and a total of 2 calculations were performed. n There are 10 working conditions, where n is the number of key engineering parameters.

[0018] The advantages of this invention compared with the prior art are as follows: This invention integrates fuzzy parameter identification and Monte Carlo target shooting method, and solves the problem of safety optimization of inter-satellite near-field separation under the combined effect of multiple fuzzy engineering parameters. It achieves rapid identification and iterative optimization of fuzzy engineering parameters by first adjusting a single parameter, then adjusting the nominal value of the parameter accordingly, and finally adjusting the parameter deviation. This saves manpower and resources and shortens the development cycle. Attached Figure Description

[0019] Figure 1 This is a flowchart of the method of the present invention;

[0020] Figure 2 This is a list of all engineering parameters that may affect the near-field safety of inter-satellite separation in the embodiments of the present invention;

[0021] Figure 3 This is a schematic diagram of the multibody dynamics simulation model of the primary star and the secondary star in an embodiment of the present invention;

[0022] Figure 4 This is a list of key engineering parameters identified by deviation sensitivity analysis in the embodiments of the present invention;

[0023] Figure 5 This refers to the minimum spacing in the separation process for the nominal value rationality analysis in this embodiment of the invention;

[0024] Figure 6 This represents the minimum spacing distribution for all working conditions in the Monte Carlo target analysis of this invention. Detailed Implementation

[0025] To address the fuzzy nature of engineering parameters during the design phase, this invention integrates fuzzy parameter identification and Monte Carlo simulation methods. First, the fuzzy parameter identification method identifies key engineering parameters during the design phase for early, stringent control, while simultaneously eliminating secondary fuzzy engineering parameters to determine the initial engineering parameters for iterative optimization. Next, the Monte Carlo simulation method establishes the initial engineering parameters and their corresponding controlled deviation ranges within a dynamic simulation model. Simulation software is used to perform traversal and combined dynamic simulation calculations to obtain the worst-case near-field spacing results under all operating conditions. If safety requirements are not met, the nominal values, deviations, and nearest-field spacing layout are adjusted, and the next iteration is initiated.

[0026] The calculation process is attached. Figure 1 The specific method is as follows:

[0027] (1) Establish a multibody dynamics simulation model for multiple spacecraft (such as the primary satellite and the secondary satellite). It is necessary to ensure that the mass characteristics of the spacecraft, the main modal frequencies of flexible large components (such as antennas and solar panels), the force and position of the separation spring, the force and position of the separation plug, and the layout of equipment near the inter-satellite separation surface (especially equipment with the smallest spacing) are consistent with the above inputs and the design or implementation status.

[0028] (2) List all fuzzy engineering parameters that may affect near-field safety.

[0029] Determine the nominal values ​​and corresponding deviation ranges of each engineering parameter based on the preliminary design scheme. Determine the minimum spacing D of the ideal analytical motion process for the initial design scheme. min And the expected value of separation safety D exp (e.g. D) exp =20mm means that the minimum near-field distance during the separation process is not less than 20mm. Here, the ideal motion, i.e. the inter-satellite separation process, only has linear velocity along the theoretical separation direction.

[0030] There are m assumed engineering parameters, with nominal values ​​X1, X2, ..., X... m The superscript "+" indicates a positive deviation, and a1, b1, c1, ... are the maximum allowable deviation values. Similarly, the subscript "-" indicates a negative deviation, and a2, b2, c2, ... are the maximum allowable deviation values. The above parameters are initially set based on the spacecraft design scheme and manufacturing capabilities.

[0031] (3) Identify key engineering parameters.

[0032] Select a single engineering parameter (e.g., X1), and while keeping the nominal values ​​of other engineering parameters unchanged, perform limit stretching simulation calculations on the positive and negative deviations (e.g., +a1, -a2) of this single engineering parameter in multibody dynamics simulation software to obtain the minimum inter-satellite spacing change (e.g., Δd) after stretching this engineering parameter. X1 Following the above steps, the positive and negative deviations of all engineering parameters are calculated sequentially to obtain the minimum inter-satellite spacing change Δd after adjusting each engineering parameter. i Let i = X1, X2, X3, ... and sort their values.

[0033] Define the sensitivity of engineering parameters as When S i When S ≥ α (α is a given sensitivity threshold, with a suggested value of 5%), this engineering parameter is considered to have a significant impact on near-field separation safety and is listed as a key engineering parameter (A1 A2 A3 …) [n×1] (sorted from largest to smallest according to the corresponding sensitivity value). i <α, indicating that the overall impact of this engineering parameter is of a different order of magnitude compared to other engineering parameters, it is listed as a secondary engineering parameter (B1 B2 B3 …)[(mn)×1] (sorted from largest to smallest according to the corresponding sensitivity value). That is, the number of key engineering parameters is n, and the number of secondary engineering parameters is mn.

[0034] (4) Rationality analysis of nominal values ​​of engineering parameters: All engineering parameters are set according to their respective nominal values ​​(H1 H2 H3…) [m×1], and the minimum inter-satellite spacing change Δd is calculated using multibody dynamics simulation software. If Δd>β(D min -D exp (β is the safety factor, with a recommended value of 80%), then the nominal values ​​and deviations of the engineering parameters of the design scheme need to be adjusted.

[0035] Based on the principle of starting with the easy tasks and then moving to the difficult ones, the following engineering adjustment strategy was formulated: ① The layout scheme was appropriately adjusted to increase D. min If the layout scheme is limited and the adjusted Δd still does not meet the requirements, then consider adjusting the nominal value of the design; ② According to the key engineering parameters (sorted from largest to smallest according to the corresponding sensitivity value), adjust the nominal value of the parameters in turn. If the adjusted nominal value of the first key engineering parameter still does not meet the requirements, then adjust the nominal value of the next key engineering parameter until the adjusted Δd meets the requirements.

[0036] After the nominal value or layout scheme is adjusted, a sensitivity analysis is performed again to determine the ranking of the key engineering parameters of the new scheme (ranked from largest to smallest according to the corresponding sensitivity values).

[0037] (5) Monte Carlo calculation of deviations of key engineering parameters.

[0038] Under this assumption, the deviation range of the key engineering parameters after adjustment is... Secondary engineering parameters are set using only nominal values ​​(B1 B2 B3 …)[(mn)×1] as initial parameters for Monte Carlo shooting simulation.

[0039] Using ADAMS software, a total of 2 simulation calculations are required to perform traversal simulations on the upper and lower limit combinations of key engineering parameters. n For each operating condition, obtain the minimum inter-satellite spacing change Δd corresponding to each operating condition. j j = 1,...,2 n Its maximum value is denoted as Δd. max .

[0040] (6) If Δd max >β(D min -D exp If the deviation range of the critical engineering parameter is adjusted sequentially according to its ranking, the adjustment should be within the design, process, and operational capabilities. If the deviation range of the first-ranked critical engineering parameter is adjusted, then Δd max If the requirements are still not met, then adjust the deviation range of the next critical engineering parameter until the adjusted Δd is achieved. max The requirement is met, that is, Δd max ≤β(D min -D exp ).

[0041] If the final Δd max If the requirements are still not met, it is necessary to return to step (4) to adjust the layout scheme or nominal value until Δd is reached. max Continue until the requirements are met.

[0042] Example

[0043] (1) A multibody dynamics simulation model of the primary star and the secondary star was established using ADAMS software. (See Appendix) Figure 3 .

[0044] (2) List all fuzzy engineering parameters that may affect near-field safety: (see appendix) Figure 2 (Number of parameters m = 21). The minimum distance for the ideal inter-satellite separation motion is D. min =25mm, the expected value for separation safety is D exp =10mm.

[0045] (3) Sensitivity analysis of engineering parameter deviations: Keeping the nominal values ​​of other engineering parameters unchanged, limit pull simulation calculations were carried out on the positive and negative deviations of a single engineering parameter in ADAMS software to determine n=8 key engineering parameters, and the rest were secondary engineering parameters (see appendix). Figure 4 ).

[0046] (4) Rationality analysis of nominal values ​​of engineering parameters: All engineering parameters were set according to their respective nominal values, and the simulation calculation showed that the change in the closest distance between satellites was Δd = 3.5mm (see Appendix). Figure 5 ), satisfying Δd≤80% (D min -D exp =12mm, no adjustment is needed to the nominal values ​​and layout of key engineering parameters.

[0047] (5) Monte Carlo calculation of deviations for key engineering parameters: Deviation ranges are set for key engineering parameters, while nominal values ​​are used for secondary engineering parameters as initial parameter settings for Monte Carlo target practice. The ADAMS software is used to perform traversal simulation calculations on the upper and lower limit combinations of key engineering parameters, requiring a total of 2 calculations. n =256 working conditions, the maximum change in minimum spacing under all working conditions is Δd max = 5.6mm (see appendix) Figure 6 ), satisfying Δd max ≤80% (D) min -D exp The accuracy is 12mm, meaning the near-field safety for inter-satellite separation in this mission meets the requirements. Therefore, based on the current layout and the control of separation-related engineering parameters, near-field safety for inter-satellite separation can be guaranteed. It should be noted that fuzzy parameter identification can quickly determine the engineering parameters that need to be adjusted first in the iterative scheme, a feature not present in previous Monte Carlo methods. Secondly, when dealing with calculations involving many engineering parameters, previous Monte Carlo methods required enormous computational resources and time, which was detrimental to scheme iteration.

[0048] The contents not described in detail in this specification are common knowledge to those skilled in the art.

Claims

1. An optimized adjustment method for near-field safety during inter-satellite separation, characterized in that: (1) According to the design scheme, establish a multibody dynamics simulation model of multiple spacecraft with inter-satellite separation; (2) List the engineering parameters that affect the near-field safety of inter-satellite separation, determine the nominal values ​​and corresponding deviation ranges of each engineering parameter according to the design scheme, and further determine the minimum spacing of the motion process of the design scheme under ideal conditions. and separation safety expectation value ; (3) For all engineering parameters, only one engineering parameter is selected as the adjustment item each time. While keeping the nominal values ​​of other engineering parameters unchanged, the adjustment item is taken as the limit value of the deviation in two directions through simulation to obtain the corresponding minimum inter-satellite spacing change. After calculating the minimum inter-satellite spacing change corresponding to each of all engineering parameters, they are sorted according to the magnitude of the minimum inter-satellite spacing change. (4) Based on the numerical sorting of the minimum inter-satellite spacing change, and combined with the threshold of the minimum inter-satellite spacing change, the key engineering parameters are selected, and the rest are secondary engineering parameters; (5) For all engineering parameters, their nominal values ​​are taken, and the corresponding minimum inter-satellite spacing variation is obtained through simulation. ,judge If the condition is met, proceed to the next step; otherwise, readjust the nominal values ​​of the key engineering parameters or the design scheme until... After its establishment, it will proceed to the next step, in which... For safety factor; (6) For key engineering parameters, select their adjusted nominal values ​​and corresponding deviation ranges. For secondary engineering parameters, select their nominal values ​​as initial parameter settings for Monte Carlo target simulation. By performing traversal simulation calculations on the upper and lower limit combinations of key engineering parameters, obtain the minimum inter-satellite spacing change corresponding to each working condition. The maximum value of the minimum inter-satellite spacing change is denoted as... ; (7) If If the design scheme and the nominal values ​​of each engineering parameter, and the corresponding deviations, meet the near-field safety requirements for inter-satellite separation, then the deviation ranges are adjusted sequentially according to the key engineering parameters until the adjustment is satisfactory. The requirements are met; if ultimately If the requirements are still not met, return to step (5) to readjust the nominal values ​​of the key engineering parameters or the design scheme until... Until the requirements are met; The ideal state described is that the inter-satellite separation process only has linear velocity along the theoretical separation direction.

2. The optimized adjustment method for near-field safety of inter-satellite separation according to claim 1, characterized in that: The process of sorting key engineering parameters based on the numerical changes in minimum inter-satellite spacing, and then filtering them using a threshold value for the minimum inter-satellite spacing change, specifically involves defining the sensitivity of engineering parameters. , ,when At that time, the corresponding engineering parameters are the key engineering parameters; X1, X2, X 3… For all project parameters, For a given sensitivity threshold.

3. The optimized adjustment method for near-field safety of inter-satellite separation according to claim 2, characterized in that: The aforementioned The value is 5%.

4. The optimized adjustment method for near-field safety of inter-satellite separation according to claim 1, characterized in that: The aforementioned safety factor The value is 80%.

5. The optimized adjustment method for near-field safety of inter-satellite separation according to claim 1, characterized in that: In step (5), the nominal values ​​or design schemes of key engineering parameters are readjusted. The adjustment method is as follows: first, the layout scheme is adjusted to increase... ; If the layout scheme is limited and adjustments are necessary... If the requirements are still not met, the nominal values ​​of the key engineering parameters will be adjusted. Specifically, the nominal values ​​will be adjusted sequentially according to the ranking of the key engineering parameters. If adjusting the nominal value of the first-ranked key engineering parameter results in a satisfactory result... If the requirements are still not met, then adjust the nominal value of the next critical engineering parameter until the adjustment is successful. The requirements are met.

6. The optimized adjustment method for near-field safety of inter-satellite separation according to claim 1, characterized in that: The traversal simulation was performed using ADAMS software, and a total of [number] calculations were performed. There are 10 working conditions, where n is the number of key engineering parameters.

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