Spacecraft inter-stage separation design evaluation method, electronic device and storage medium

Abstract

The present application relates to a kind of spacecraft interstage separation design evaluation method, electronic equipment and storage medium, comprising the following steps: step S10, utilize the kinetic model to calculate output parameter, whether there is near-field separation safety risk according to output parameter, if there is no near-field separation safety risk, then carry out far-field separation safety analysis;Step S20, utilize spacecraft two-stage orbit model, calculate the relative distance after two-stage separation, judge whether there is collision risk.The present application effectively avoids the problem that variable is not identified sufficiently when independent analysis occurs, not only can the spacecraft separation safety under specific conditions be evaluated, but also the input parameter feasible solution without separation safety risk can be obtained by iterative calculation, and the separation design characteristic parameter is optimized in feasible solution, correct design data envelope line is obtained, which can effectively guide spacecraft optimization design work.

Description

TECHNICAL FIELD

[0001] The present application relates to a spacecraft inter-stage separation design evaluation method, an electronic device and a storage medium. BACKGROUND

[0002] Spacecrafts are generally separated in orbit to meet the advanced technical requirements of multi-mission, high energy efficiency and low weight cost. For example, the Shenzhou spacecraft separates the return capsule from the orbital capsule, the Tianzhou cargo spacecraft separates from the space station after rendezvous and docking, the satellite separates the cube satellite, the Chang'e-5 orbiter separates from the lander, and so on. During the separation process of the spacecrafts, there are problems affecting the safety of the separation, such as the interference of the structural shape dynamic envelope caused by the attitude change of the spacecraft after separation, and the pursuit of the two spacecrafts after separation due to orbital perturbation, light pressure and atmospheric resistance. Therefore, it is crucial to establish a spacecraft separation dynamics model, analyze the environmental boundary conditions, and evaluate the safety of the separation design under given input conditions. The existing spacecraft inter-stage separation safety evaluation method generally separates the near-field separation safety and the far-field separation safety. The rigid-elastic coupling dynamics model is generally used to solve the motion of the two spacecrafts after separation, thereby verifying the near-field separation safety. The far-field separation safety is generally considered to have no attitude change during the separation process, and the separation velocity is solved by the parallel energy conservation formula and the momentum conservation formula, as shown in the following formula:

[0003]

[0004] m1v1=m2v2 (2)

[0005] where m1 and m2 are the weights of the two spacecrafts after separation, V1 and V2 are the changes in the relative separation velocities of the two spacecrafts after separation, k and Δx are the equivalent stiffness and equivalent elastic displacement of the separation elastic force (the spacecraft inter-stage separation generally selects a separation spring), and V1 and V2 obtained by solving are used for orbit calculation to analyze whether the two spacecrafts after separation will have a pursuit problem. The above two works are completed, and a conclusion is drawn that the spacecraft separation is safe. This independent analysis method has the following disadvantages:

[0006] 1) The evaluation of whether the two spacecrafts after in-orbit separation will have a pursuit collision risk is called far-field separation safety analysis. The angular velocity of the two spacecrafts after separation is not considered during the far-field separation safety analysis, and the separation velocity obtained is greater than the actual state, so that the far-field separation safety result does not cover all working conditions;

[0007] 2) whether the two-stage spacecraft will produce a dynamic envelope interference risk during separation is called near-field separation safety analysis, when performing the near-field separation safety analysis, the motion state before the spacecraft separation is not considered, and the variable is generally obtained by orbit calculation and will affect the near-field separation safety analysis result.

[0008] In summary, breaking the separation safety of the spacecraft near-field and far-field analysis is mutually exclusive, and a comprehensive evaluation of the spacecraft separation design scheme is urgently needed. SUMMARY

[0009] In view of the above technical problems, the present application provides a spacecraft interstage separation design evaluation method based on multi-teacher knowledge distillation, an electronic device and a storage medium, to realize comprehensive evaluation of the spacecraft separation near-field and far-field safety.

[0010] The technical solution for achieving the object of the present application is: a spacecraft interstage separation design evaluation method, comprising the following steps:

[0011] Step S10, the output parameters are calculated by using the dynamic model, whether there is a near-field separation safety risk is judged according to the output parameters, if there is no near-field separation safety risk, the far-field separation safety analysis is carried out;

[0012] Step S20, the relative distance after two-stage separation is calculated by using the two-stage orbit model of the spacecraft, and whether there is a collision risk is judged.

[0013] According to one aspect of the present application, before step S10 is performed, it further comprises:

[0014] Step S1, the input conditions for carrying out near-field dynamic analysis are determined;

[0015] Step S2, a three-dimensional spacecraft separation model is established, and a dynamic model is constructed to determine the geometric shape, constitutive relationship and motion parameters;

[0016] Step S3, preset the dynamic calculation step, the dynamic calculation step is not less than 2000 frames / s.

[0017] According to one aspect of the present application, before step S20 is performed, it further comprises:

[0018] Step S11, the two-stage orbit model of the spacecraft is established, and orbit analysis is carried out, the initial characteristic parameters of the separation point are inputted;

[0019] Step S12, the output parameters obtained in step S1 are inputted into the orbit model to input the separation characteristic parameters, the separation process is regarded as the two stages flying together at the same position before separation, and the separation is regarded as a change of orbit for the two stages.

[0020] According to one aspect of the present application, the initial characteristic parameters at least include orbital elements, atmospheric model, planetary perturbation model, light pressure parameters, and surface area.

[0021] According to one aspect of the present application, in step S10, specifically comprising:

[0022] Step S101, calculating the output parameters by using the dynamic calculation step and the dynamic model.

[0023] Step S102, judging whether there is interference according to the distance change of the two-stage spacecraft during the separation process.

[0024] Step S103, when the minimum distance L is less than the preset distance tolerance L0, then modifying the input conditions and executing step S1.

[0025] Step S104, when the minimum distance L is greater than or equal to the preset distance tolerance L0, then executing step S11.

[0026] According to one aspect of the present application, in step S2, a three-dimensional spacecraft separation model is established, specifically comprising:

[0027] Step S21, importing or newly creating a spacecraft structure model in the modeling software, and setting the relative position relationship and the relative position relationship of the two-stage mode.

[0028] Step S22, establishing an inter-stage separation mechanism model based on the spacecraft separation simulation analysis structure model, arranging the separation mechanism model in the spacecraft structure model, defining the contact relationship between the separation mechanism and the two-stage spacecraft structure model, fixing one end of the separation mechanism and contacting the other end with the separated spacecraft structure, setting the contact characteristics according to the material of the contacted object, and simultaneously giving the motion constraint, elastic coefficient and damping characteristics of the separation mechanism.

[0029] Step S23, setting the initial values of the two-stage spacecraft structure in the docking coordinate system, and giving the motion parameters such as the velocity, acceleration, angular velocity and angular acceleration of the combined body formed by the two-stage spacecraft at the separation starting time.

[0030] Step S24, completing the modeling work of the spacecraft separation model.

[0031] According to one aspect of the present application, the distance tolerance L0 ranges from 0.5m.

[0032] According to one aspect of the present application, the output parameters at least further include the time-domain responses of the velocity, acceleration, attitude angular velocity, angular acceleration of the two-stage spacecraft during the separation process, and the working state of the inter-stage separation mechanism.

[0033] According to one aspect of the present application, in step S20, specifically comprising:

[0034] Step S201, calculating the relative distance after two-stage separation;

[0035] Step S202, judging whether there is a far-field safety risk according to the change trend of the relative distance over time;

[0036] Step S203, when the relative distance changes closer and closer over time, confirming that there is a risk, then modifying the input conditions and executing step S1;

[0037] Step S204, when the relative distance changes first decreases and then increases over time, taking the minimum relative distance between the two spacecraft as the judgment point, if the minimum relative distance is greater than 10m, confirming that there is no risk, otherwise confirming that there is a risk, then modifying the input conditions and executing step S1;

[0038] Step S205, when the relative distance continuously increases over time, confirming that the spacecraft has no separation safety risk.

[0039] According to one aspect of the present application, an electronic device is provided, comprising: one or more processors, one or more memories, and one or more computer programs; wherein the processor is connected with the memory, and the one or more computer programs are stored in the memory, and when the electronic device is running, the processor executes the one or more computer programs stored in the memory, so that the electronic device executes a spacecraft inter-stage separation design evaluation method according to any one of the above technical solutions.

[0040] According to one aspect of the present application, a computer readable storage medium is provided for storing computer instructions, and when the computer instructions are executed by a processor, a spacecraft inter-stage separation design evaluation method according to any one of the above technical solutions is realized.

[0041] According to the concept of the present application, a spacecraft inter-stage separation design evaluation method, electronic equipment and computer program are provided, by using a dynamics model to calculate output parameters, determining whether there is a near-field separation safety risk according to the output parameters, if there is no near-field separation safety risk, performing a far-field separation safety analysis, using a spacecraft two-stage orbit model to calculate the relative distance after two-stage separation, and determining whether there is a collision risk, breaking the original near-field and far-field separation safety evaluation methods which are mutually fragmented, logically serializing and organically unifying the two analysis modes, effectively avoiding the problem of incomplete simulation coverage due to insufficient variable identification in independent analysis, not only can the spacecraft separation safety under specific conditions be evaluated, but also the feasible solution of input parameters without separation safety risk can be obtained through iterative calculation, and the separation design characteristic parameters can be optimized in the feasible solution to obtain the correct design data envelope, which can effectively guide the spacecraft optimization design work. BRIEF DESCRIPTION OF DRAWINGS

[0042] Figure 1 A flowchart schematically showing a spacecraft inter-stage separation design evaluation method according to an embodiment of the present application is shown in the figure.

[0043] Figure 2 A modeling flowchart schematically showing a spacecraft separation model according to an embodiment of the present application is shown in the figure.

[0044] Figure 3 A flowchart schematically showing a spacecraft inter-stage separation design evaluation method according to another embodiment of the present application is shown in the figure. DETAILED DESCRIPTION

[0045] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments. Obviously, the drawings in the following description only represent some embodiments of the present application, and other drawings can also be obtained by those skilled in the art without any creative effort based on these drawings.

[0046] The present application will be described in detail below in combination with the drawings and specific embodiments. The embodiments cannot be described one by one here, but the embodiments of the present application are not limited to the following embodiments.

[0047] As shown in the figure, a spacecraft inter-stage separation design evaluation method of the present application includes the following steps: Figures 1 to 3

[0048] Step S10, using a dynamics model to calculate output parameters, determining whether there is a near-field separation safety risk according to the output parameters, if there is no near-field separation safety risk, performing a far-field separation safety analysis;

[0049] ​Step S20, using a two-stage orbit model of the spacecraft, calculating the relative distance after two-stage separation, judging whether there is a collision risk.

[0050] In this embodiment, by calculating the output parameters by using the dynamic model, judging whether there is a near-field separation safety risk according to the output parameters, if there is no near-field separation safety risk, performing far-field separation safety analysis, using a two-stage orbit model of the spacecraft, calculating the relative distance after two-stage separation, judging whether there is a collision risk, breaking the original near-field and far-field separation safety evaluation methods which are mutually disjoint, realizing logical series and organic unification of the two analysis modes, effectively avoiding the problem of incomplete simulation coverage caused by insufficient variable identification in independent analysis, not only can the spacecraft separation safety under specific conditions be evaluated, but also the feasible solution of the input parameters without separation safety risk can be obtained by iterative calculation, and the separation design characteristic parameters can be optimized in the feasible solution, so that the correct design data envelope line can be obtained, which can effectively guide the optimization design of the spacecraft.

[0051] In one embodiment of the present application, preferably, before step S10 is performed, it further comprises:

[0052] Step S1, determining the input conditions for carrying out near-field dynamic analysis;

[0053] Step S2, establishing a three-dimensional spacecraft separation model, and constructing a dynamic model to clearly define geometric shape, constitutive relationship and motion parameters;

[0054] Step S3, presetting a dynamic calculation step, the dynamic calculation step is not less than 2000 frames / s, and the dynamic calculation step is accurate to the extent that the dynamic model calculation converges.

[0055] In one embodiment of the present application, preferably, before step S20 is performed, it further comprises:

[0056] Step S11, establishing a two-stage orbit model of the spacecraft, and performing orbit analysis, inputting initial characteristic parameters of the separation point;

[0057] Step S12, inputting the separation characteristic parameters in the orbit model by using the output parameters obtained in step S1, regarding the separation process as co-flying of the two stages before separation at the same position, and regarding the separation as a change of orbit of the two stages.

[0058] In one embodiment of the present application, preferably, the initial characteristic parameters at least include orbit six elements, an atmospheric model, a planet perturbation model, light pressure parameters and surface area.

[0059] In one embodiment of the present application, preferably, in step S10, it specifically comprises:

[0060] Step S101: Calculate the output parameters using the dynamic calculation step size and dynamic model;

[0061] Step S102: Determine whether interference exists based on the distance change of the dynamic envelope motion of the two stages of the spacecraft during the separation process;

[0062] Step S103: When the minimum distance L is less than the preset distance tolerance L0, modify the input conditions and then execute step S1.

[0063] Step S104: When the minimum distance L is greater than or equal to the preset distance tolerance L0, then execute step S11.

[0064] like Figure 3 As shown, in one embodiment of the present invention, preferably, in step S2, a three-dimensional spacecraft separation model is established, specifically including:

[0065] Step S21: Import or create a new spacecraft structure model in the modeling software, and set the relative positional relationship between the two-level modes;

[0066] Step S22: Based on the spacecraft separation simulation analysis structural model, establish an interstage separation mechanism model, place the separation mechanism model on the spacecraft structural model, define the contact relationship between the separation mechanism and the two-stage spacecraft structural model, fix one end of the separation mechanism and contact the spacecraft structure to be separated at the other end, set the contact characteristics according to the material of the contact object, and at the same time give the motion constraints, elastic coefficient and damping characteristics of the separation mechanism.

[0067] Step S23: Set initial values ​​for the two-stage spacecraft structure in the docking coordinate system, and give motion parameters such as velocity, acceleration, angular velocity and angular acceleration of the combined body formed by the two-stage spacecraft at the start of separation.

[0068] Step S24: Complete the modeling of the spacecraft separation model.

[0069] In one embodiment of the present invention, preferably, the range of the distance tolerance L0 satisfies: L0≥0.5m.

[0070] In one embodiment of the present invention, preferably, the output parameters include at least the velocity, acceleration, attitude angular velocity, time-domain response of angular acceleration, and working status of the interstage separation mechanism of the two stages of the spacecraft during the separation process.

[0071] In one embodiment of the present invention, preferably, step S20 specifically includes:

[0072] Step S201: Calculate the relative distance after the two-stage separation;

[0073] Step S202: Determine whether there is a far-field security risk based on the trend of relative distance changing over time;

[0074] Step S203: When the relative distance decreases over time and a risk is confirmed, modify the input conditions and then execute step S1.

[0075] Step S204: When the relative distance decreases and then increases over time, the minimum relative distance between the two aircraft is used as the evaluation point. If the minimum relative distance is greater than 10m, it is confirmed that there is no risk; otherwise, it is confirmed that there is a risk. Then, after modifying the input conditions, step S1 is executed.

[0076] Step S205: When the relative distance increases continuously over time, it is confirmed that there is no risk to the spacecraft's separation safety.

[0077] According to one aspect of the present invention, an electronic device is provided, comprising: one or more processors, one or more memories, and one or more computer programs; wherein the processor is connected to the memory, and the one or more computer programs are stored in the memory; when the electronic device is running, the processor executes the one or more computer programs stored in the memory to cause the electronic device to perform a spacecraft inter-stage separation design evaluation method as described in any of the above technical solutions.

[0078] According to one aspect of the present invention, a computer-readable storage medium is provided for storing computer instructions, which, when executed by a processor, implement a spacecraft inter-stage separation design evaluation method as described in any of the above technical solutions.

[0079] like Figure 3 As shown, according to an embodiment of the present invention, the specific implementation method of the spacecraft inter-stage separation design evaluation method is as follows:

[0080] Step S100: Determine the input conditions for conducting near-field dynamics analysis, including:

[0081] 1a. Two-level separated coordinate system, generally a docking coordinate system is used, and the center of the separation surface is usually set as the origin of the coordinate system.

[0082] 1b. Two-stage structural model of the spacecraft. The geometric model needs to be able to represent the maximum outline of the spacecraft separation surface structure. For locations where there is a risk of dynamic envelope interference during separation, the geometric shape needs to be refined, while other geometric shapes can be simplified. According to the structural mechanism scheme, the kinematic pairs of each mechanism in the separation model should be correctly set, including the kinematic pairs connecting the main structure on both sides of the separation surface with other structures. The two parts of the structure to be separated can be regarded as rigid body analysis models, and the mass characteristics (including center of mass, moment of inertia and deviation) of the structures on both sides of the separation surface need to be correctly described.

[0083] 1c. The interstage separation mechanism model needs to include the geometric model of the interstage separation structure, which should be able to describe its outer envelope and the mechanical connection points of the structures on both sides of the separation. According to the separation mechanism scheme, set the kinematic pairs of each mechanism in the model correctly. According to the current scheme, set the correct mechanical parameters of the kinematic pairs such as friction coefficient, contact coefficient, etc. The physical model of the interstage separation mechanism depends on the type of the model. According to the scheme, set the mass properties of the rigid body part (including centroid, moment of inertia, and deviation) and the mechanical constitutive related parameters of the flexible body part such as elasticity, damping, etc.

[0084] 1d. According to the orbit calculation, the initial motion state of the spacecraft before separation is obtained, such as velocity, acceleration, angular velocity, angular acceleration, etc.

[0085] Step S200, after the input conditions are determined, select appropriate dynamic simulation software for modeling. The geometric model, constitutive relationship and motion parameters can be established directly through simulation software. For complex structures, the geometric model can be established first through CAD software (PROE, AutoCAD, CATIA) and then imported into simulation software (ADAMS, DYTRAN) for CAE analysis. The specific modeling method is as follows:

[0086] 2a. Establish a spacecraft separation simulation analysis structure model. Import or create a spacecraft structure model in the modeling software, and set the relative position relationship and relative position relationship of the two-stage model;

[0087] 2b. Based on the spacecraft separation simulation analysis structure model, establish an interstage separation mechanism model. Place the separation mechanism model in the spacecraft structure model, define the contact relationship between the separation mechanism and the two-stage spacecraft structure model. Generally, one end of the separation mechanism is fixed and the other end is in contact with the spacecraft structure to be separated. According to the material of the contact object, set the contact characteristics, and at the same time, give the motion constraints, elastic coefficient and damping characteristics of the separation mechanism;

[0088] 2c. Set the initial values of the two-stage spacecraft structure in the docking coordinate system. Give the motion parameters such as velocity, acceleration, angular velocity and angular acceleration of the combined body formed by the two-stage spacecraft at the separation starting time. If you want to perform a shooting analysis, you need to select the parameter distribution characteristics in the dynamic simulation software;

[0089] 2d. Complete the modeling of the spacecraft separation model.

[0090] Step S300, preset the appropriate dynamic calculation step. The preset dynamic calculation step needs to be able to make the dynamic model calculation converge. Generally, the calculation step is not less than 2000 frames per second. It can be adjusted according to the actual operation situation;

[0091] Step S400, based on the spacecraft separation model and dynamic calculation step size, the output parameters are calculated. In the case of considering the deviation, the following calculation results are concerned:

[0092] 4a. The time domain response of velocity, acceleration, attitude angular velocity, and angular acceleration of the two-stage spacecraft during separation;

[0093] 4b. The dynamic envelope motion of the two-stage spacecraft during separation, to determine whether there is interference and the change of the closest distance;

[0094] 4c. The working state of the interstage separation mechanism (force, stroke, etc.);

[0095] 4d. Other parameters of interest, etc.

[0096] According to the output parameters, it is determined whether there is a near-field separation safety risk. The output values of steps 4a and 4c are used to confirm the correctness of the calculation process, and the output structure in step 4b is used to determine whether there is a near-field safety risk. Generally, a distance tolerance L0 is set, which can be 0.5 m without other constraint conditions. If the closest distance L is calculated to be less than L0, return to step S100 to adjust the input conditions of step 1; if the closest distance L is calculated to be greater than or equal to L0, perform far-field separation safety analysis;

[0097] Step S500, the spacecraft two-stage orbit model is established using orbit dynamics calculation software. STK software or Matlab is usually used for orbit analysis. The initial characteristic parameters such as the orbit six elements of the separation point, the atmospheric model, the planetary perturbation model, the light pressure parameters, and the surface area are inputted;

[0098] Step S600, the calculation results in step S400 are inputted into the separation characteristic parameters in the orbit model. Generally, the separation process is simplified, and it is considered that the two stages fly together before separation. The separation is considered as a change of orbit for the two stages;

[0099] Step S700, the relative distance after the two-stage separation is calculated. Generally, the trend of the relative distance with respect to time is considered to determine whether there is a far-field safety risk. If the relative distance becomes closer and closer with respect to time, it is considered to be at risk, and the input conditions are adjusted to return to step S100 for recalculation. If the relative distance decreases first and then increases with respect to time, the minimum relative distance of the two spacecraft is taken as the evaluation point. If the minimum relative distance is greater than 10 m, it is considered to be safe, otherwise it is considered to be at risk, and the input conditions are adjusted to return to step S100 for recalculation. If the relative distance increases continuously with respect to time, it is determined that the spacecraft has no separation safety risk.

[0100] In summary, the application provides a spacecraft inter-stage separation design evaluation method, electronic equipment and computer program, by using a dynamic model to calculate output parameters, determining whether there is a near-field separation safety risk according to the output parameters, if there is no near-field separation safety risk, performing a far-field separation safety analysis, using a spacecraft two-stage orbit model to calculate the relative distance after two-stage separation, and determining whether there is a collision risk, breaking the original near-field and far-field separation safety evaluation methods which are mutually fragmented, logically serializing and organically unifying the two analysis modes, effectively avoiding the problem of incomplete simulation coverage caused by insufficient variable identification in independent analysis, not only can the spacecraft separation safety under specific conditions be evaluated, but also the input parameter feasible solution without separation safety risk can be obtained through iterative calculation, and the separation design characteristic parameters can be optimized in the feasible solution to obtain the correct design data envelope, which can effectively guide the spacecraft optimization design work.

[0101] In addition, it should be noted that the application can be provided as a method, device or computer program product. Therefore, the embodiments of the application can adopt a completely hardware embodiment, a completely software embodiment or an embodiment combining software and hardware aspects. Moreover, the embodiments of the application can adopt the form of a computer program product implemented on one or more computer usable storage media containing computer usable program codes.

[0102] The embodiments of the application are described with reference to flowcharts and / or block diagrams according to the method, terminal device (system) and computer program product of the embodiments of the application. It should be understood that each flow and / or block in the flowcharts and / or block diagrams, and the combination of the flows and / or blocks in the flowcharts and / or block diagrams can be implemented by computer program instructions. These computer program instructions can be provided to a general-purpose computer, embedded processor or other programmable data processing terminal device to produce a machine, so that the instructions executed by the computer or other programmable data processing terminal device produce a device for implementing the functions specified in the flowcharts and / or block diagrams. Figure 1 The functions specified in one or more flows and / or blocks Figure 1 The device that implements the functions specified in one or more flows and / or blocks.

[0103] These computer program instructions can also be stored in a computer readable memory capable of guiding the computer or other programmable data processing terminal device to work in a specific way, so that the instructions stored in the computer readable memory produce a product including instruction devices, which implement the functions specified in the flowcharts and / or block diagrams. Figure 1 The functions specified in one or more flows and / or blocks Figure 1The computer program instructions can also be loaded onto a computer or other programmable data processing terminal device to cause a series of operational steps to be performed on the computer or other programmable terminal device to produce a computer implemented process such that the instructions which execute on the computer or other programmable terminal device provide steps for implementing the flow Figure 1 The flow or flows and / or blocks Figure 1 Figure 1 The flow or flows and / or blocks

[0104] It is also noted that the terms "comprising", "including", or any other variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but can also include other elements not expressly listed or inherent to such process, method, article, or apparatus. An element proceeded by "comprises a... " does not, without more constraints, exclude the existence of additional identical elements in the process, method, article, or apparatus that comprises the recited element.

[0105] Finally, it is to be noted that the above-mentioned description is of preferred embodiments of the application and that no limitation is intended to the scope of the application as described in the accompanying claims, which should be interpreted as including all modifications and alterations in the preferred embodiments falling within the true spirit and scope of the application. Therefore, the appended claims are intended to cover all the preferred embodiments of the present application and all modifications and alterations as fall within the true spirit and scope of the present application.

Claims

1. A method for evaluating interstage separation design in spacecraft, characterized in that, Includes the following steps: Step S1: Determine the input conditions for conducting near-field dynamics analysis; Step S2: Establish a three-dimensional spacecraft separation model and construct a dynamic model to clarify the geometric shape, constitutive relationship and motion parameters; Step S3: Preset the dynamics calculation step size, which is not less than 2000 frames / s; Step S10: Calculate the output parameters using the dynamic model. Determine whether there is a near-field separation safety risk based on the output parameters. If there is no near-field separation safety risk, perform a far-field separation safety analysis, which specifically includes: Step S101: Calculate the output parameters using the dynamic calculation step size and dynamic model; Step S102: Determine whether interference exists based on the distance change of the dynamic envelope motion of the two stages of the spacecraft during the separation process; Step S103: When the minimum distance L is less than the preset distance tolerance L0, modify the input conditions and then execute step S1. Step S104: When the minimum distance L is greater than or equal to the preset distance tolerance L0, then proceed to step S11. Step S11: Establish a two-stage orbital model for the spacecraft, perform orbital analysis, and input the initial characteristic parameters of the separation point; Step S12: Using the output parameters obtained in step S1, input the separation characteristic parameters into the orbital model. Treat the separation process as the two stages flying together at the same position before separation, and treat the separation as the two stages performing a change of orbit. Step S20: Using the two-stage orbital model of the spacecraft, calculate the relative distance between the two stages after separation to determine if there is a risk of collision. This includes: Step S201: Calculate the relative distance after the two-stage separation; Step S202: Determine whether there is a far-field security risk based on the trend of relative distance changing over time; Step S203: When the relative distance decreases over time and a risk is confirmed, modify the input conditions and then execute step S1. Step S204: When the relative distance decreases and then increases over time, the minimum relative distance between the two aircraft is used as the evaluation point. If the minimum relative distance is greater than 10m, it is confirmed that there is no risk; otherwise, it is confirmed that there is a risk. Then, after modifying the input conditions, step S1 is executed. Step S205: When the relative distance increases continuously over time, it is confirmed that there is no risk to the spacecraft's separation safety.

2. The method according to claim 1, characterized in that, The initial characteristic parameters include at least the orbital root number, atmospheric model, planetary perturbation model, radiation pressure parameter, and surface area.

3. The method according to claim 2, characterized in that, In step S2, a three-dimensional spacecraft separation model is established, specifically including: Step S21: Import or create a new spacecraft structure model in the modeling software, and set the relative positional relationship between the two-level modes; Step S22: Based on the spacecraft separation simulation analysis structural model, establish an interstage separation mechanism model, place the separation mechanism model on the spacecraft structural model, define the contact relationship between the separation mechanism and the two-stage spacecraft structural model, fix one end of the separation mechanism and contact the spacecraft structure to be separated at the other end, set the contact characteristics according to the material of the contact object, and at the same time give the motion constraints, elastic coefficient and damping characteristics of the separation mechanism. Step S23: Set initial values ​​for the two-stage spacecraft structure in the docking coordinate system, and give the velocity, acceleration, angular velocity and angular acceleration motion parameters of the combined body formed by the two-stage spacecraft at the initial separation moment; Step S24: Complete the modeling of the spacecraft separation model.

4. The method according to claim 2, characterized in that, The distance tolerance L0 is within the range that satisfies: L0 ≥ 0.5m; The output parameters include at least the velocity, acceleration, attitude angular velocity, time-domain response of angular acceleration, and interstage separation mechanism status of the two stages of the spacecraft during the separation process.

5. An electronic device, characterized in that, include: One or more processors, one or more memories, and one or more computer programs; wherein the processor is connected to the memory, and the one or more computer programs are stored in the memory, and when the electronic device is running, the processor executes the one or more computer programs stored in the memory to cause the electronic device to perform a spacecraft inter-stage separation design evaluation method as described in any one of claims 1 to 4.

6. A computer-readable storage medium, characterized in that, Used to store computer instructions, which, when executed by a processor, implement a spacecraft inter-stage separation design evaluation method as described in any one of claims 1 to 4.

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