Pre-launch selection method, selection device and electronic equipment for spacecraft passive load reduction trajectory

Abstract

The present application provides a method, a selection device and an electronic device for pre-launch selection of a passive load reduction trajectory for a spacecraft. The selection method comprises: calculating first and second high-altitude wind data at a preset altitude according to the standard high-altitude wind data used in the design of the passive load reduction trajectory and the high-altitude wind data involved in the forecast of the spacecraft launch window; calculating the comprehensive characteristic value corresponding to the standard high-altitude wind data used in the design of the passive load reduction trajectory and the comprehensive characteristic value corresponding to the high-altitude wind data of the spacecraft launch window forecast according to the average value of the first and second high-altitude wind data with altitude and the weight of the characteristic wind speed and wind direction of the spacecraft high-altitude wind; calculating the error between the comprehensive characteristic value of the standard high-altitude wind data used in the design of the passive load reduction trajectory and the comprehensive characteristic value of the high-altitude wind data of the spacecraft launch window forecast; selecting the passive load reduction trajectory scheme corresponding to the minimum error, and binding the flight parameters corresponding to the scheme to carry out the corresponding flight test mission.

Description

Technical Field

[0001] The present application belongs to the field of aerospace technology, and specifically relates to a method, a selection device, and electronic equipment for pre-launch selection of a spacecraft passive load reduction trajectory. Background Art

[0002] Spacecraft such as launch vehicles, recoverable satellites, and manned spacecraft are essential tools for modern space activities. During flight, they are subject to a variety of complex forces, including aerodynamic forces, engine thrust, and inertial forces. Under traditional ballistics, these forces can cause significant stress on the spacecraft structure, exposing it to the risk of structural damage or fatigue under high stress, especially in windy areas. To mitigate this risk, passive load-reducing trajectory designs are often employed.

[0003] Passive load reduction trajectory design typically requires the development of multiple passive load reduction trajectory designs based on historical wind field data from the launch base. Before a spacecraft launch, a large number of random target simulation tests are conducted for different passive load reduction trajectories, based on the high-altitude wind data predicted for the launch window. By comparing the aerodynamic loads at each level, a passive load reduction trajectory is selected for subsequent flight test missions. However, this process can extend the pre-launch process for the spacecraft. A lengthy pre-launch process has many drawbacks. On the one hand, it increases the probability of spacecraft component failure; on the other hand, spacecraft are more susceptible to changes in meteorological conditions. For example, sudden severe weather may force a rocket launch to be delayed. Furthermore, a lengthy process can lead to high labor costs, as well as design, maintenance, and operating costs. Summary of the Invention

[0004] In order to overcome the problems existing in the related art to at least a certain extent, the present application provides a method, a selection device and an electronic device for selecting a spacecraft passive load reduction trajectory before launch.

[0005] According to a first aspect of an embodiment of the present application, the present application provides a method for selecting a spacecraft passive load reduction trajectory before launch, comprising the following steps:

[0006] Calculate the first high-altitude wind data at a preset altitude based on the standard high-altitude wind data used in the design of the passive load reduction trajectory; calculate the second high-altitude wind data at a preset altitude based on the high-altitude wind data involved in the spacecraft launch window forecast;

[0007] Based on the average value of the first high-altitude wind data with altitude and the weight of the spacecraft high-altitude wind characteristic wind speed and wind direction, the comprehensive characteristic value corresponding to the standard high-altitude wind data used in the passive load reduction trajectory design is calculated; based on the average value of the second high-altitude wind data with altitude and the weight of the spacecraft high-altitude wind characteristic wind speed and wind direction, the comprehensive characteristic value corresponding to the spacecraft launch window forecast high-altitude wind data used in the passive load reduction trajectory design is calculated;

[0008] Calculate the error between the comprehensive characteristic value of the standard high-altitude wind data used in the design of the passive load reduction trajectory and the comprehensive characteristic value of the high-altitude wind data predicted during the spacecraft launch window;

[0009] The passive load reduction trajectory scheme corresponding to the minimum error is selected, and the flight parameters corresponding to the scheme are bound to carry out the corresponding flight test mission.

[0010] Optionally, the calculating of the first high-altitude wind data at a preset altitude based on the standard high-altitude wind data used in the design of the passive load-reducing trajectory includes:

[0011] Obtain the standard high-altitude wind speed and direction data used in the design of each level of passive load reduction trajectory;

[0012] Set the altitude sequence of the spacecraft during the flight phase in the first-level high wind zone;

[0013] According to the standard high-altitude wind speed and direction data, a parabolic interpolation method is used to calculate the first high-altitude wind data at a preset height in the height sequence, wherein the first high-altitude wind data includes first high-altitude wind speed data and first high-altitude wind direction data.

[0014] Optionally, during the flight segment of the spacecraft in the first-level strong wind zone, the first high-altitude wind speed data and the first high-altitude wind direction data at a preset altitude are respectively:

[0015] ,

[0016] ,

[0017] Where, Indicates height The first high-altitude wind speed data under Indicates height The first high-altitude wind direction data under Indicates the flight segment height in the interpolation table corresponding to the first-level strong wind area The closest spacecraft j The serial number corresponding to the standard high-altitude wind height value used in the design of the passive load reduction trajectory; Indicates the spacecraft j The serial number in the standard high-altitude wind interpolation table used in the design of the passive load reduction trajectory The wind speed value below Indicates the spacecraft j The serial number in the standard high-altitude wind interpolation table used in the design of the passive load reduction trajectory The wind speed value below Indicates the spacecraft j The serial number in the standard high-altitude wind interpolation table used in the design of the passive load reduction trajectory The wind speed value under Indicates the spacecraft j The serial number in the standard high-altitude wind interpolation table used in the design of the passive load reduction trajectory The wind direction value below, Indicates the spacecraft j The serial number in the standard high-altitude wind interpolation table used in the design of the passive load reduction trajectory The wind direction value below, Indicates the spacecraft j The serial number in the standard high-altitude wind interpolation table used in the design of the passive load reduction trajectory The wind direction value below; j Indicates the gear number of the passive load reduction trajectory; Indicates the serial number in the standard high-altitude wind interpolation table used in the design of the spacecraft passive load reduction trajectory The height value below, Indicates the serial number in the standard high-altitude wind interpolation table used in the design of spacecraft passive load reduction trajectory The height value below, Indicates the serial number in the standard high-altitude wind interpolation table used in the design of spacecraft passive load reduction trajectory The height value below.

[0018] Optionally, the calculating of second high-altitude wind data at a preset altitude based on high-altitude wind data involved in the spacecraft launch window forecast includes:

[0019] Obtain forecast upper-altitude wind speed and direction data for the spacecraft launch window; where forecast upper-altitude wind speed and direction vary with altitude;

[0020] Set the altitude sequence of the spacecraft during the flight phase in the first-level high wind zone;

[0021] According to the forecast high-altitude wind speed data and wind direction data, a parabolic interpolation method is used to calculate the second high-altitude wind data at a preset height in the height sequence, wherein the second high-altitude wind data includes the second high-altitude wind speed data and the second high-altitude wind direction data.

[0022] Optionally, during the flight segment of the spacecraft in the first-level strong wind zone, the second-altitude wind speed data and the second-altitude wind direction data at the preset altitude are respectively:

[0023] ,

[0024] ,

[0025] Where, Indicates height The second highest wind speed data under Indicates height The second highest wind direction data, Indicates the flight segment height in the interpolation table corresponding to the first-level strong wind area The serial number corresponding to the upper wind height value predicted for the nearest spacecraft launch window; Indicates the sequence number in the interpolation table of the upper-altitude wind forecast for the spacecraft launch window The wind speed value below Indicates the sequence number in the interpolation table of the upper-altitude wind forecast for the spacecraft launch window The wind speed value below Indicates the sequence number in the interpolation table of the upper-altitude wind forecast for the spacecraft launch window The wind speed value under Indicates the sequence number in the interpolation table of the upper-altitude wind forecast for the spacecraft launch window The wind direction value below, Indicates the sequence number in the interpolation table of the upper-altitude wind forecast for the spacecraft launch window The wind direction value below, Indicates the sequence number in the interpolation table of the upper-altitude wind forecast for the spacecraft launch window The wind direction value below; Indicates the sequence number in the interpolation table of the upper-altitude wind forecast for the spacecraft launch window The height value below, Indicates the sequence number in the interpolation table of the upper-altitude wind forecast for the spacecraft launch window The height value below, Indicates the sequence number in the interpolation table of the upper-altitude wind forecast for the spacecraft launch window The height value below.

[0026] Optionally, the calculation of the comprehensive characteristic value corresponding to the standard high-altitude wind data used in the passive load reduction trajectory design based on the average value of the first high-altitude wind data with altitude and the weight of the spacecraft high-altitude wind characteristic wind speed and wind direction includes:

[0027] Calculate the average value of the first high-altitude wind data with altitude, the average value includes the spacecraft first j The average value of the standard high-altitude wind speed used in the design of the passive load reduction trajectory in the flight segment height sequence of the first-level strong wind area and spacecraft j The average value of the standard high-altitude wind direction used in the design of the passive load reduction trajectory in the flight segment height sequence of the first-level strong wind area ;

[0028] in, , ;

[0029] Where, Indicates height The first high-altitude wind speed data under Indicates height The first high-altitude wind direction data under; n It represents the dimension of the altitude sequence of the spacecraft in the first-level high wind zone flight segment;

[0030] The weight of the spacecraft upper-altitude wind characteristic speed is set to , the weight of wind direction is set to ;

[0031] Computing spacecraft j The comprehensive characteristic value of the standard high-altitude wind used in the design of the passive load reduction trajectory in the flight segment height sequence of the first-level strong wind area , for:

[0032] .

[0033] Optionally, the calculation of the comprehensive characteristic value corresponding to the spacecraft launch window forecast high-altitude wind data used in the passive load reduction trajectory design based on the average value of the second high-altitude wind data with altitude and the weight of the spacecraft high-altitude wind characteristic wind speed and wind direction includes:

[0034] Calculate the average value of the second high-altitude wind data with altitude; the average value includes the average value of the high-altitude wind speed forecasted during the launch window of the spacecraft under the altitude sequence of the flight segment in the first-level strong wind zone The average value of the high-altitude wind direction forecast during the launch window of the spacecraft in the flight segment height sequence of the first-level strong wind area ;

[0035] in, , ;

[0036] Where, Indicates height The second highest wind speed data under Indicates height The second highest wind direction data below;

[0037] The weight of the spacecraft upper-altitude wind characteristic speed is set to , the weight of wind direction is set to ;

[0038] Calculate the comprehensive characteristic value corresponding to the predicted high-altitude wind data of the spacecraft launch window used in the design of the passive load reduction trajectory , for:

[0039] .

[0040] Where, Indicates height The second highest wind speed data under Indicates height The second highest wind direction data below;

[0041] The weight of the spacecraft upper-altitude wind characteristic speed is set to , the weight of wind direction is set to ;

[0042] Calculate the comprehensive characteristic value corresponding to the predicted high-altitude wind data of the spacecraft launch window used in the design of the passive load reduction trajectory , for:

[0043] .

[0044] As an option, the error between the comprehensive characteristic value of the standard high-altitude wind data used in the passive load reduction trajectory design and the comprehensive characteristic value of the high-altitude wind data predicted during the spacecraft launch window is for:

[0045] .

[0046] According to a second aspect of the embodiment of the present application, the present application further provides a pre-launch selection device for a spacecraft passive load reduction trajectory, which includes a high-altitude wind data calculation module, a comprehensive characteristic value calculation module, an error calculation module, and a selection module;

[0047] The high-altitude wind data calculation module is configured to calculate first high-altitude wind data at a preset altitude based on standard high-altitude wind data used in the design of a passive load reduction trajectory; and calculate second high-altitude wind data at a preset altitude based on high-altitude wind data involved in the spacecraft launch window forecast;

[0048] The comprehensive characteristic value calculation module is configured to calculate the comprehensive characteristic value corresponding to the standard high-altitude wind data used in the passive load reduction trajectory design based on the average value of the first high-altitude wind data with altitude and the weight of the spacecraft high-altitude wind characteristic wind speed and wind direction; and calculate the comprehensive characteristic value corresponding to the spacecraft launch window forecast high-altitude wind data used in the passive load reduction trajectory design based on the average value of the second high-altitude wind data with altitude and the weight of the spacecraft high-altitude wind characteristic wind speed and wind direction;

[0049] The error calculation module is configured to calculate the error between the comprehensive characteristic value of the standard high-altitude wind data used in the passive load reduction trajectory design and the comprehensive characteristic value of the high-altitude wind data predicted during the spacecraft launch window;

[0050] The selection module is configured to select the passive load reduction trajectory scheme corresponding to the minimum error, and bind the flight parameters corresponding to the scheme to carry out the corresponding flight test mission.

[0051] According to the third aspect of the embodiments of the present application, the present application also provides an electronic device, which includes a memory and a processor coupled to the memory, and the processor is configured to execute the spacecraft passive load reduction trajectory pre-launch selection method as described in any one of the above items based on instructions stored in the memory.

[0052] According to the above-mentioned specific implementation methods of the present application, it can be seen that there are at least the following beneficial effects: the present application calculates the wind speed and wind direction data under a preset altitude sequence before launch based on the standard high-altitude wind data used in the design of each level of passive load reduction trajectory and the high-altitude wind data predicted in the spacecraft launch window, and calculates the error between the comprehensive characteristic value of the high-altitude wind data used in the design of each level of passive load reduction trajectory and the comprehensive characteristic value of the high-altitude wind data predicted in the launch window, and then selects the passive load reduction trajectory with the smallest error to complete the flight test mission; the present application can quickly select the passive load reduction trajectory before launch, thereby greatly shortening the pre-launch launch process time of the carrier rocket.

[0053] It should be understood that the above general description and the following detailed description are only exemplary and illustrative and do not limit the scope of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0054] The accompanying drawings below are part of the specification of the present application, which illustrate embodiments of the present application. The accompanying drawings, together with the description in the specification, are used to explain the principles of the present application.

[0055] Figure 1 A flow chart of a method for selecting a spacecraft passive load reduction trajectory before launch provided in one embodiment of the present application;

[0056] Figure 2 A high-altitude wind speed diagram for the carrier rocket under the four-speed wind-corrected trajectory and launch window forecast state provided in one embodiment of the present application;

[0057] Figure 3 This is a high-altitude wind direction diagram for the carrier rocket in the four-speed wind-corrected trajectory and launch window forecast state provided in one embodiment of the present application;

[0058] Figure 4 A wind speed diagram of the carrier rocket provided in an embodiment of the present application under the four-speed wind-corrected trajectory and launch window forecast state in the altitude sequence of the flight segment in the first-level strong wind zone;

[0059] Figure 5 This is a wind direction diagram of the carrier rocket under the 4-speed wind-corrected trajectory and launch window forecast state in the altitude sequence of the flight segment in the first-level strong wind zone provided in one embodiment of the present application. DETAILED DESCRIPTION

[0060] In order to make the objectives, technical solutions and advantages of the embodiments of the present application more clearly understood, the spirit of the contents disclosed in the present application will be clearly illustrated with the accompanying drawings and detailed descriptions below. After understanding the embodiments of the contents of the present application, any technician in the relevant technical field can change and modify the contents of the present application based on the techniques taught by the contents of the present application without departing from the spirit and scope of the contents of the present application.

[0061] The exemplary embodiments and descriptions of the present application are used to explain the present application, but are not intended to limit the present application. In addition, elements / components with the same or similar reference numerals used in the drawings and embodiments are used to represent the same or similar parts.

[0062] The terms “first,” “second,” etc. used herein do not specifically refer to an order or sequence, nor are they intended to limit this application. They are merely used to distinguish elements or operations described with the same technical terms.

[0063] The directional terms used herein, such as up, down, left, right, front, or back, are only used to refer to the directions in the accompanying drawings. Therefore, the directional terms used are used to illustrate and not to limit the present invention.

[0064] The words “include,” “including,” “have,” “contain,” etc. used in this document are open-ended terms, meaning including but not limited to.

[0065] As used herein, "and / or" includes any or all combinations of the items mentioned.

[0066] Regarding "plurality" herein, "plurality" includes "two" and "more than two"; regarding "plurality groups" herein, "plurality groups" includes "two groups" and "more than two groups".

[0067] As used herein, the terms "substantially" and "approximately" are used to modify any quantity or error that may vary slightly, but such slight variations or errors do not alter the essence of the quantity. Generally speaking, the range of slight variations or errors modified by such terms may be 20% in some embodiments, 10% in some embodiments, 5% in some embodiments, or other values. Those skilled in the art will appreciate that the aforementioned values ​​may be adjusted based on actual needs and are not intended to be limiting.

[0068] Certain terms used to describe the present application are discussed below, or elsewhere in this specification, to provide additional guidance to those skilled in the art regarding the description of the present application.

[0069] In the relevant existing technologies, the launch vehicle adopts a multi-stage passive load reduction ballistic design, which increases the pre-launch process time, thereby increasing the probability of component failure, delaying the rocket launch due to sudden weather changes, and high labor costs and design, maintenance and operation costs.

[0070] This application calculates the wind speed and direction data under a preset altitude sequence based on the standard high-altitude wind data used in the design of each passive load reduction trajectory and the high-altitude wind data predicted in the launch window of the spacecraft before launch. By calculating the error between the comprehensive characteristic value of the high-altitude wind data used in the design of each passive load reduction trajectory and the comprehensive characteristic value of the high-altitude wind data predicted in the launch window, the passive load reduction trajectory with the smallest error is selected to complete the flight test mission. This application can quickly select a passive load reduction trajectory before launch, thereby significantly shortening the pre-launch launch process time of the carrier rocket. At the same time, since the launch process time is shortened, the length of time that the components are in a launch-ready state is reduced, thereby reducing the probability of component failure; and can reduce the waiting time of the spacecraft at the launch pad, reducing the possibility of launch delays due to sudden weather changes; in addition, it can also reduce labor costs and design, maintenance and operating costs to a certain extent.

[0071] The following combination Figure 1 The present invention describes a method for selecting a spacecraft passive load reduction trajectory before launch.

[0072] like Figure 1 As shown, the method for selecting a spacecraft passive load reduction trajectory before launch provided by this application includes the following steps:

[0073] S1. Calculate the first high-altitude wind data at a preset altitude based on the standard high-altitude wind data used in the design of the passive load reduction trajectory; calculate the second high-altitude wind data at a preset altitude based on the high-altitude wind data involved in the spacecraft launch window forecast.

[0074] The standard upper-altitude wind data includes standard upper-altitude wind speed data and wind direction data. The upper-altitude wind data involved in the spacecraft launch window forecast includes the wind speed data and wind direction data involved in the launch window forecast.

[0075] Specifically, passive load reduction trajectories are a technical approach used in the flight of spacecraft or missiles. Through specific trajectory design and utilizing wind field data, they aim to reduce the aerodynamic loads borne by the rocket or missile during flight. In trajectory design for spacecraft (such as spacecraft), the complexity and variability of actual high-altitude wind fields are considered. To address varying wind conditions, wind conditions are divided into multiple levels. Each level represents a set of wind conditions with similar characteristics. Corresponding passive load reduction trajectories are designed for each of these different wind conditions. The corresponding passive load reduction trajectories based on different designs can be considered a specific implementation of passive load reduction. A passive load reduction trajectory is a modified flight trajectory of the original trajectory. Its purpose is to minimize the adverse effects of high-altitude winds on the spacecraft's flight by adjusting flight parameters such as the spacecraft's attitude and speed. This, for example, reduces aerodynamic loads and ensures flight stability and accuracy.

[0076] The design of each passive load reduction trajectory requires reference and basis in wind field data, namely standard upper-altitude wind speed and direction data. These data are representative wind field parameters determined based on statistics, analysis, or assumptions.

[0077] A spacecraft launch window is a pre-set time period during which a spacecraft is permitted to launch. Selecting a launch window requires comprehensive consideration of various factors, including the relative positions of the Earth, Moon, and other celestial bodies, solar activity, and visibility from ground tracking stations. High-altitude wind conditions are also a significant factor, as they affect the spacecraft's flight attitude, trajectory, and forces during ascent.

[0078] Because the actual conditions of high-altitude winds are complex and changeable and difficult to accurately grasp in real time, it is necessary to rely on meteorological observation equipment, numerical weather forecast models, and relevant meteorological theories and experience to predict the conditions of high-altitude winds during the launch window in advance.

[0079] High-altitude wind speed refers to the speed of air flowing at different altitudes during a spacecraft's ascent. Wind speed significantly impacts spacecraft. Excessive wind speed can increase aerodynamic loads on a spacecraft, causing greater stress on its structure and potentially affecting its flight stability and safety. It can also cause the spacecraft's actual flight trajectory to deviate from its planned trajectory, increasing navigation and control difficulties.

[0080] High-altitude wind direction refers to the direction of airflow at high altitudes. Different wind directions generate aerodynamic forces on different sides of a spacecraft, affecting its attitude. For example, crosswinds can cause a spacecraft to drift laterally and rotate, requiring the spacecraft's attitude control system to make corresponding adjustments to maintain the correct flight attitude. Accurate wind direction information helps optimize the spacecraft's launch trajectory before launch, or help implement necessary measures to mitigate the effects of wind direction.

[0081] S2. Based on the average value of the first high-altitude wind data with altitude and the weight of the spacecraft high-altitude wind characteristic wind speed and wind direction, calculate the comprehensive characteristic value corresponding to the standard high-altitude wind data used in the passive load reduction trajectory design; based on the average value of the second high-altitude wind data with altitude and the weight of the spacecraft high-altitude wind characteristic wind speed and wind direction, calculate the comprehensive characteristic value corresponding to the spacecraft launch window forecast high-altitude wind data used in the passive load reduction trajectory design.

[0082] S3. Calculate the error between the comprehensive characteristic value of the standard high-altitude wind data used in the design of the passive load reduction trajectory and the comprehensive characteristic value of the high-altitude wind data predicted during the spacecraft launch window.

[0083] S4. Select the passive load reduction trajectory plan corresponding to the minimum error and bind the flight parameters corresponding to the plan to carry out the corresponding flight test mission.

[0084] By sorting the errors calculated in step S3, the minimum error can be obtained. Selecting the passive load reduction trajectory scheme with the smallest error value can better achieve the passive load reduction effect while meeting the various performance requirements of the flight mission, and is relatively more reliable and feasible.

[0085] Flight parameters are a set of data describing an aircraft's flight status and parameters. These include, but are not limited to, the aircraft's initial position (latitude, longitude, and altitude), initial velocity (magnitude and direction), flight attitude (pitch, yaw, and roll angles), engine operating parameters (thrust, operating time, etc.), flight time, and position and velocity at different times. These parameters are crucial for precisely controlling the aircraft's flight trajectory and ensuring it flies according to the intended plan.

[0086] In the field of aerospace, "binding" usually refers to accurately inputting selected flight data into the aircraft's control system (such as the flight control computer) so that it becomes the basis for control during the aircraft's actual flight.

[0087] In a specific embodiment, in the above step S1, calculating the first high-altitude wind data at a preset altitude based on the standard high-altitude wind data used in the passive load reduction trajectory design includes:

[0088] S11. Obtain the standard high-altitude wind speed used in the design of each level of passive load reduction trajectory and wind direction data.

[0089] S12. Set the altitude sequence for the spacecraft's flight in the first-level high wind zone .

[0090] S13, according to the standard high-altitude wind speed and wind direction The first high-altitude wind data at a preset height is calculated using a parabolic interpolation method, wherein the first high-altitude wind data includes first high-altitude wind speed data and first high-altitude wind direction data.

[0091] Specifically, during the flight phase of the spacecraft in the first-level strong wind zone, the altitude The first high-altitude wind speed data under and the first high altitude wind direction data They are:

[0092] ,

[0093] ,

[0094] Where, Indicates the flight segment height in the interpolation table corresponding to the first-level strong wind area The closest spacecraft j The serial number corresponding to the standard high-altitude wind height value used in the design of the passive load reduction trajectory; Indicates the spacecraft j The serial number in the standard high-altitude wind interpolation table used in the design of the passive load reduction trajectory The wind speed value below Indicates the spacecraft j The serial number in the standard high-altitude wind interpolation table used in the design of the passive load reduction trajectory The wind speed value below Indicates the spacecraft j The serial number in the standard high-altitude wind interpolation table used in the design of the passive load reduction trajectory The wind speed value under Indicates the spacecraft j The serial number in the standard high-altitude wind interpolation table used in the design of the passive load reduction trajectory The wind direction value below, Indicates the spacecraft j The serial number in the standard high-altitude wind interpolation table used in the design of the passive load reduction trajectory The wind direction value below, Indicates the spacecraft j The serial number in the standard high-altitude wind interpolation table used in the design of the passive load reduction trajectory The wind direction value below. j Indicates the gear number of the passive unloading trajectory, which can be . Indicates the serial number in the standard high-altitude wind interpolation table used in the design of spacecraft passive load reduction trajectory The height value below, Indicates the serial number in the standard high-altitude wind interpolation table used in the design of spacecraft passive load reduction trajectory The height value below, Indicates the serial number in the standard high-altitude wind interpolation table used in the design of spacecraft passive load reduction trajectory The height value below.

[0095] Based on the high-altitude wind data involved in the spacecraft launch window forecast, calculate the second-highest-altitude wind data at the preset altitude, including:

[0096] S14. Obtain forecast high-altitude wind speed data for the spacecraft launch window and wind direction data ; Among them, the predicted high-altitude wind speed and direction will change with altitude.

[0097] S15. Set the altitude sequence for the spacecraft's flight in the first-level high wind zone .

[0098] S16. According to the forecast high-altitude wind speed data and wind direction data , a parabolic interpolation method is used to calculate the second high-altitude wind data at a preset height, wherein the second high-altitude wind data includes second high-altitude wind speed data and second high-altitude wind direction data.

[0099] Specifically, during the flight phase of the spacecraft in the first-level strong wind zone, the altitude The second highest wind speed data under and the second high altitude wind direction data They are:

[0100] ,

[0101] ,

[0102] Where, Indicates the flight segment height in the interpolation table corresponding to the first-level strong wind area The serial number corresponding to the upper wind height value predicted for the nearest spacecraft launch window; Indicates the sequence number in the interpolation table of the upper-altitude wind forecast for the spacecraft launch window The wind speed value below Indicates the sequence number in the interpolation table of the upper-altitude wind forecast for the spacecraft launch window The wind speed value below Indicates the sequence number in the interpolation table of the upper-altitude wind forecast for the spacecraft launch window The wind speed value under Indicates the sequence number in the interpolation table of the upper-altitude wind forecast for the spacecraft launch window The wind direction value below, Indicates the sequence number in the interpolation table of the upper-altitude wind forecast for the spacecraft launch window The wind direction value below, Indicates the sequence number in the interpolation table of the upper-altitude wind forecast for the spacecraft launch window The wind direction value below. Indicates the sequence number in the interpolation table of the upper-altitude wind forecast for the spacecraft launch window The height value below, Indicates the sequence number in the interpolation table of the upper-altitude wind forecast for the spacecraft launch window The height value below, Indicates the sequence number in the interpolation table of the upper-altitude wind forecast for the spacecraft launch window The height value below.

[0103] In a specific embodiment, in the above step S2, the comprehensive characteristic value corresponding to the standard high-altitude wind data used in the passive load reduction trajectory design is calculated based on the average value of the first high-altitude wind data with altitude and the weight of the spacecraft high-altitude wind characteristic wind speed and wind direction, including:

[0104] S21, calculating the average value of the first high-altitude wind data along with the height;

[0105] Specifically, the average value includes the spacecraft j The average value of the standard high-altitude wind speed used in the design of the passive load reduction trajectory in the flight segment height sequence of the first-level strong wind area and spacecraft j The average value of the standard high-altitude wind direction used in the design of the passive load reduction trajectory in the flight segment height sequence of the first-level strong wind area ;

[0106] in, , .

[0107] Where, n represents the dimension of the height sequence of the spacecraft's first-level high wind zone flight segment, i Represents an index variable.

[0108] S22. Setting the weight of the characteristic wind speed and wind direction of the spacecraft at high altitude;

[0109] Specifically, the weight of the spacecraft high-altitude wind characteristic speed is set to , the weight of wind direction is set to .

[0110] S23. Calculate the comprehensive characteristic values ​​corresponding to the standard high-altitude wind data used in the design of passive load-reducing trajectories;

[0111] Specifically, the spacecraft j The comprehensive characteristic value of the standard high-altitude wind used in the design of the passive load reduction trajectory in the flight segment height sequence of the first-level strong wind area for:

[0112] .

[0113] In a specific embodiment, in the above step S2, the comprehensive characteristic value corresponding to the predicted high-altitude wind data of the spacecraft launch window used in the passive load reduction trajectory design is calculated based on the average value of the second high-altitude wind data with altitude and the weight of the spacecraft high-altitude wind characteristic wind speed and wind direction, including:

[0114] S24, calculating the average value of the second-highest-altitude wind data over the height;

[0115] Specifically, the average value includes the average value of the high-altitude wind speed forecasted during the launch window of the spacecraft under the flight altitude sequence of the first-level strong wind zone. The average value of the high-altitude wind direction forecast during the launch window of the spacecraft in the flight segment height sequence of the first-level strong wind area ;

[0116] in, , .

[0117] S25. Setting the weight of the characteristic wind speed and wind direction of the spacecraft at high altitude;

[0118] Specifically, the weight of the spacecraft high-altitude wind characteristic speed is set to , the weight of wind direction is set to .

[0119] S26. Calculate the comprehensive characteristic value corresponding to the predicted upper-altitude wind data during the launch window of the spacecraft used in the design of the passive load reduction trajectory;

[0120] Specifically, the comprehensive characteristic value corresponding to the high-altitude wind data predicted during the launch window of the spacecraft used in the design of the passive load reduction trajectory is for:

[0121] .

[0122] In a specific embodiment, in the above step S3, the error between the comprehensive characteristic value of the standard high-altitude wind data used in the passive load reduction trajectory design and the comprehensive characteristic value of the high-altitude wind data predicted during the spacecraft launch window is for:

[0123] .

[0124] Calculation error This can include the error between the comprehensive characteristic value of the standard high-altitude wind data used in the calculation of the 4-speed passive load reduction trajectory design and the comprehensive characteristic value of the high-altitude wind data predicted during the launch window of the carrier rocket. .

[0125] in, It represents the error between the comprehensive characteristic value of the standard high-altitude wind data used in the design of the first-gear passive load reduction trajectory of the spacecraft and the comprehensive characteristic value of the high-altitude wind data predicted during the spacecraft launch window; The error between the comprehensive characteristic value of the standard high-altitude wind data used in the design of the second-gear passive load reduction trajectory of the spacecraft and the comprehensive characteristic value of the high-altitude wind data predicted during the spacecraft launch window; The error between the comprehensive characteristic value of the standard high-altitude wind data used in the design of the spacecraft's third-gear passive load reduction trajectory and the comprehensive characteristic value of the high-altitude wind data predicted during the spacecraft launch window; It is the error between the comprehensive characteristic value of the standard high-altitude wind data used in the design of the fourth-gear passive load reduction trajectory of the spacecraft and the comprehensive characteristic value of the high-altitude wind data predicted during the spacecraft launch window.

[0126] The following is a detailed description of the method for selecting a spacecraft passive load reduction trajectory before launch provided by this application through a specific embodiment.

[0127] Assuming that the spacecraft is a launch vehicle, there are four levels of passive load reduction trajectories for launch vehicles. The standard high-altitude wind speed used in the design of the first level of passive load reduction trajectory is , wind direction is The standard high-altitude wind speed used in the design of the second-stage passive load reduction trajectory is , wind direction is The standard high-altitude wind speed used in the design of the third-stage passive load reduction trajectory is , wind direction is The standard high-altitude wind speed used in the design of the 4th gear passive load reduction trajectory is , wind direction is For example, in this embodiment, the height sequence value in the standard high-altitude wind interpolation table used in the passive load reduction trajectory design is The high-altitude wind speed and direction data used in the design of each passive load reduction trajectory are shown in Tables 1 and 2.

[0128] Table 1 High-altitude wind speed data used in the design of each passive load reduction trajectory

[0129]

[0130] Table 2 High-altitude wind direction data used in the design of each passive load reduction trajectory

[0131]

[0132] The high-altitude wind speed data predicted by the carrier rocket during the launch window is as follows: Figure 2 The data represented by the predicted wind speed curve and wind direction data are as follows: Figure 3 Data represented by the forecast wind direction curve.

[0133] Set the altitude sequence of the first stage of the launch vehicle in the strong wind area, denoted as .

[0134] Based on the standard high-altitude wind speed and direction data used in the design of the above 4-speed wind-modified trajectory, the altitude is calculated using the parabolic interpolation method. The wind speed and direction data under the high wind zone; among them, the height of the first stage of the carrier rocket is The parabolic interpolation launch vehicle j The wind speed data after the standard high-altitude wind speed used in the wind-blocking trajectory design is as follows Figure 4 Middle j The wind speed curve of the wind-blocking ballistic trajectory is shown; the height of the first stage of the launch vehicle in the strong wind area flight section The parabolic interpolation launch vehicle under j The wind direction data after the standard high-altitude wind direction used in the wind-blocking trajectory design is as follows Figure 5 Middle j The wind direction curve of the ballistic trajectory is shown.

[0135] Based on the high-altitude wind data predicted during the launch window of the above-mentioned carrier rocket, the altitude is calculated using the parabolic interpolation method. The wind speed and direction sequence under the wind; among them, the height of the first stage of the carrier rocket in the strong wind area flight section The wind speed data after the parabolic interpolation rocket launch window forecasts the upper wind speed is as follows Figure 4 The wind speed curve of the medium forecast wind is shown; the height of the first stage of the carrier rocket in the strong wind area flight section The wind direction data after the parabolic interpolation rocket launch window forecasts the high-altitude wind direction is as follows Figure 5 The predicted wind direction curve is shown in the figure.

[0136] The standard high-altitude wind data used in the design of the 4-speed wind-corrected trajectory and the average values ​​of the high-altitude wind data predicted during the launch window of the carrier rocket with altitude are:

[0137] .

[0138] The comprehensive characteristic values ​​of the standard high-altitude wind data and the high-altitude wind data predicted during the launch window of the carrier rocket used in the design of the 4-speed wind-modified trajectory are:

[0139] .

[0140] The errors between the comprehensive characteristic values ​​corresponding to the standard high-altitude wind used in the design of the 4-speed wind-corrected trajectory and the comprehensive characteristic values ​​corresponding to the high-altitude wind predicted during the launch window of the carrier rocket are:

[0141] .

[0142] The error order between the comprehensive characteristic values ​​corresponding to each wind-corrected trajectory and the comprehensive characteristic values ​​corresponding to the high-altitude wind forecast during the launch window of the carrier rocket is: , then bind the flight parameters corresponding to the third-level wind-corrected trajectory to carry out the flight test mission.

[0143] Based on the method for pre-launch selection of spacecraft passive load reduction trajectory provided in this application, this application also provides a pre-launch selection device for spacecraft passive load reduction trajectory, which includes a high-altitude wind data calculation module, a comprehensive eigenvalue calculation module, an error calculation module and a selection module.

[0144] Among them, the high-altitude wind data calculation module is configured to calculate the first high-altitude wind data at a preset altitude based on the standard high-altitude wind data used in the design of the passive load reduction trajectory; and calculate the second high-altitude wind data at a preset altitude based on the high-altitude wind data involved in the spacecraft launch window forecast.

[0145] The comprehensive characteristic value calculation module is configured to calculate the comprehensive characteristic value corresponding to the standard high-altitude wind data used in the passive load reduction trajectory design based on the average value of the first high-altitude wind data with altitude and the weight of the characteristic wind speed and wind direction of the spacecraft high-altitude wind; and calculate the comprehensive characteristic value corresponding to the high-altitude wind data predicted in the spacecraft launch window used in the passive load reduction trajectory design based on the average value of the second high-altitude wind data with altitude and the weight of the characteristic wind speed and wind direction of the spacecraft high-altitude wind.

[0146] The error calculation module is configured to calculate the error between the comprehensive characteristic value of the standard high-altitude wind data used in the passive load reduction trajectory design and the comprehensive characteristic value of the high-altitude wind data predicted in the spacecraft launch window.

[0147] The selection module is configured to select the passive load reduction trajectory scheme corresponding to the minimum error and bind the flight parameters corresponding to the scheme to carry out the corresponding flight test mission.

[0148] It should be noted that the spacecraft passive load reduction trajectory pre-launch selection device provided in the above embodiment and the spacecraft passive load reduction trajectory pre-launch selection method embodiment provided in the above embodiment belong to the same concept. The specific implementation process is detailed in the method embodiment and will not be repeated here.

[0149] The present application also provides an electronic device comprising a memory and a processor coupled to the memory, wherein the processor is configured to execute the spacecraft passive load reduction trajectory pre-launch selection method in any embodiment of the present application based on instructions stored in the memory.

[0150] The memory may be a system memory or a fixed non-volatile storage medium, etc. The system memory may store an operating system, application programs, a boot loader, a database, and other programs, etc.

[0151] On the other hand, the present application also provides a computer program product, which includes a computer program. The computer program can be stored on a non-transitory computer-readable storage medium. When the computer program is executed by a processor, the computer can perform the spacecraft passive load reduction trajectory pre-launch selection method provided by the above methods, which includes:

[0152] Based on the standard high-altitude wind data used in the design of passive load reduction trajectory, the first high-altitude wind data at the preset altitude is calculated; based on the high-altitude wind data involved in the spacecraft launch window forecast, the second high-altitude wind data at the preset altitude is calculated.

[0153] Based on the average value of the first high-altitude wind data with altitude and the weight of the characteristic wind speed and wind direction of the spacecraft high-altitude wind, the comprehensive characteristic value corresponding to the standard high-altitude wind data used in the design of the passive load reduction trajectory is calculated; based on the average value of the second high-altitude wind data with altitude and the weight of the characteristic wind speed and wind direction of the spacecraft high-altitude wind, the comprehensive characteristic value corresponding to the high-altitude wind data predicted for the spacecraft launch window used in the design of the passive load reduction trajectory is calculated.

[0154] Calculate the error between the comprehensive characteristic value of the standard high-altitude wind data used in the passive load reduction trajectory design and the comprehensive characteristic value of the high-altitude wind data predicted during the spacecraft launch window.

[0155] The passive load reduction trajectory scheme corresponding to the minimum error is selected, and the flight parameters corresponding to the scheme are bound to carry out the corresponding flight test mission.

[0156] In another aspect, the present application further provides a non-transitory computer-readable storage medium having a computer program stored thereon. When the computer program is executed by a processor, the method for selecting a spacecraft passive load reduction trajectory before launch provided by the above methods is implemented. The method includes:

[0157] Based on the standard high-altitude wind data used in the design of passive load reduction trajectory, the first high-altitude wind data at the preset altitude is calculated; based on the high-altitude wind data involved in the spacecraft launch window forecast, the second high-altitude wind data at the preset altitude is calculated.

[0158] Based on the average value of the first high-altitude wind data with altitude and the weight of the characteristic wind speed and wind direction of the spacecraft high-altitude wind, the comprehensive characteristic value corresponding to the standard high-altitude wind data used in the design of the passive load reduction trajectory is calculated; based on the average value of the second high-altitude wind data with altitude and the weight of the characteristic wind speed and wind direction of the spacecraft high-altitude wind, the comprehensive characteristic value corresponding to the high-altitude wind data predicted for the spacecraft launch window used in the design of the passive load reduction trajectory is calculated.

[0159] Calculate the error between the comprehensive characteristic value of the standard high-altitude wind data used in the passive load reduction trajectory design and the comprehensive characteristic value of the high-altitude wind data predicted during the spacecraft launch window.

[0160] The passive load reduction trajectory scheme corresponding to the minimum error is selected, and the flight parameters corresponding to the scheme are bound to carry out the corresponding flight test mission.

[0161] The device embodiments described above are merely illustrative. The units described as separate components may or may not be physically separate, and the components shown as units may or may not be physical units, i.e., they may be located in one location or distributed across multiple network units. Some or all of the modules may be selected based on actual needs to achieve the objectives of the present embodiment. Persons of ordinary skill in the art will be able to understand and implement the present invention without inventive effort.

[0162] Through the above description of the embodiments, those skilled in the art will clearly understand that each embodiment can be implemented using software plus a necessary general-purpose hardware platform, or of course, hardware. Based on this understanding, the essence of the above technical solution, or the portion that contributes to the prior art, can be embodied in the form of a software product. This computer software product can be stored in a computer-readable storage medium, such as ROM / RAM, a magnetic disk, or an optical disk, and includes a number of instructions for causing a computer device (such as a personal computer, server, or network device) to execute the methods described in each embodiment or certain portions of the embodiments.

[0163] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit them. Although the present application has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present application.

Claims

1. A method for selecting a spacecraft passive load reduction trajectory before launch, characterized in that: The following steps are involved: Calculating first high-altitude wind data at a preset altitude based on standard high-altitude wind data used in the design of a passive load reduction trajectory; calculating second high-altitude wind data at a preset altitude based on high-altitude wind data involved in a spacecraft launch window forecast; the first high-altitude wind data includes first high-altitude wind speed data and first high-altitude wind direction data, and the second high-altitude wind data includes second high-altitude wind speed data and second high-altitude wind direction data; Based on the average value of the first high-altitude wind data with altitude and the weight of the spacecraft high-altitude wind characteristic wind speed and wind direction, the comprehensive characteristic value corresponding to the standard high-altitude wind data used in the passive load reduction trajectory design is calculated; based on the average value of the second high-altitude wind data with altitude and the weight of the spacecraft high-altitude wind characteristic wind speed and wind direction, the comprehensive characteristic value corresponding to the spacecraft launch window forecast high-altitude wind data used in the passive load reduction trajectory design is calculated; The first high-altitude wind speed data and the first high-altitude wind direction data at a preset altitude during the flight segment of the spacecraft in the first-level strong wind zone are respectively: ， ， Where, 、 Respectively indicate height The first high altitude wind speed data and the first high altitude wind direction data, Indicates the sequence number in the interpolation table; 、 、 Represents the spacecraft j The serial number used in the design of the passive load reduction trajectory 、 、 The wind speed value below 、 、 Represents the spacecraft j The serial number used in the design of the passive load reduction trajectory 、 、 The wind direction value below, j Indicates the gear number of the passive load reduction trajectory; 、 、 Respectively represent the serial numbers used in the design of the spacecraft's passive load reduction trajectory 、 、 The height value below; The second high altitude wind speed data and the second high altitude wind direction data at the preset altitude during the flight segment of the spacecraft in the first level strong wind zone are respectively: ， ， Where, 、 Respectively indicate height The second-highest-altitude wind speed data and the second-highest-altitude wind direction data, Indicates the sequence number in the interpolation table; 、 、 They represent the serial numbers in the interpolation table of the upper-altitude wind forecast for the spacecraft launch window. 、 、 The wind speed value below 、 、 They represent the serial numbers in the interpolation table of the upper-altitude wind forecast for the spacecraft launch window. 、 、 The wind direction value below, 、 、 They represent the serial numbers in the interpolation table of the upper-altitude wind forecast for the spacecraft launch window. 、 、 The height value below; Spacecraft j The comprehensive characteristic value of the standard high-altitude wind used in the design of the passive load reduction trajectory in the flight segment height sequence of the first-level strong wind area for: ， Where, 、 Represents the spacecraft j The average value of the standard high-altitude wind speed and wind direction used in the design of the passive load reduction trajectory in the flight segment height sequence of the first-level strong wind area is 、 They represent the weights of the characteristic wind speed and direction of the spacecraft’s upper air wind respectively; The comprehensive characteristic value corresponding to the high-altitude wind data predicted during the launch window of the spacecraft used in the design of the passive load reduction trajectory for: ， Where, 、 They represent the average values ​​of the predicted upper-altitude wind speed and wind direction during the launch window of the spacecraft under the flight altitude sequence of the first-level strong wind area; Calculate the error between the comprehensive characteristic value of the standard high-altitude wind data used in the design of the passive load reduction trajectory and the comprehensive characteristic value of the high-altitude wind data predicted during the spacecraft launch window; The passive load reduction trajectory scheme corresponding to the minimum error is selected, and the flight parameters corresponding to the scheme are bound to carry out the corresponding flight test mission.

2. The method for selecting a spacecraft passive load reduction trajectory before launch according to claim 1, characterized in that: The calculating of the first high-altitude wind data at a preset altitude based on the standard high-altitude wind data used in the design of the passive load-reducing trajectory includes: Obtain the standard high-altitude wind speed and direction data used in the design of each level of passive load reduction trajectory; Set the altitude sequence of the spacecraft during the flight phase in the first-level high wind zone; The first high-altitude wind data at a preset height in the height sequence is calculated using a parabolic interpolation method based on standard high-altitude wind speed and direction data.

3. The method for selecting a spacecraft passive load reduction trajectory before launch according to claim 1, characterized in that: The step of calculating the second high-altitude wind data at a preset altitude based on the high-altitude wind data involved in the spacecraft launch window forecast includes: Obtain forecast upper-altitude wind speed and direction data for the spacecraft launch window; where forecast upper-altitude wind speed and direction vary with altitude; Set the altitude sequence of the spacecraft during the flight phase in the first-level high wind zone; The second high-altitude wind data at a preset height in the height sequence is calculated using a parabolic interpolation method based on the forecast high-altitude wind speed data and wind direction data.

4. The method for selecting a spacecraft passive load reduction trajectory before launch according to claim 2, characterized in that: The calculation of the comprehensive characteristic value corresponding to the standard high-altitude wind data used in the passive load reduction trajectory design based on the average value of the first high-altitude wind data with altitude and the weight of the spacecraft high-altitude wind characteristic wind speed and wind direction includes: Calculate the average value of the first high-altitude wind data with altitude, the average value includes the spacecraft first The average value of the standard high-altitude wind speed used in the design of the passive load reduction trajectory in the flight segment height sequence of the first-level strong wind area and spacecraft The average value of the standard high-altitude wind direction used in the design of the passive load reduction trajectory in the flight segment height sequence of the first-level strong wind area ; in, , ; Where, Indicates height The first high-altitude wind speed data under Indicates height The first high-altitude wind direction data under; n It represents the dimension of the altitude sequence of the spacecraft in the first-level high wind zone flight segment; i Represents an index variable; The weight of the spacecraft upper-altitude wind characteristic speed is set to , the weight of wind direction is set to ; Computing spacecraft j The comprehensive characteristic value of the standard high-altitude wind used in the design of the passive load reduction trajectory in the flight segment height sequence of the first-level strong wind area .

5. The method for selecting a spacecraft passive load reduction trajectory before launch according to claim 4, characterized in that: The calculation of the comprehensive characteristic value corresponding to the spacecraft launch window forecast high-altitude wind data used in the passive load reduction trajectory design based on the average value of the second high-altitude wind data with altitude and the weight of the spacecraft high-altitude wind characteristic wind speed and wind direction includes: Calculate the average value of the second high-altitude wind data with altitude; the average value includes the average value of the high-altitude wind speed forecasted during the launch window of the spacecraft under the altitude sequence of the flight segment in the first-level strong wind zone The average value of the high-altitude wind direction forecast during the launch window of the spacecraft in the flight segment height sequence of the first-level strong wind area ; in, , ; Where, Indicates height The second highest wind speed data under Indicates height The second highest wind direction data below; The weight of the spacecraft upper-altitude wind characteristic speed is set to , the weight of wind direction is set to ; Calculate the comprehensive characteristic value corresponding to the predicted high-altitude wind data of the spacecraft launch window used in the design of the passive load reduction trajectory .

6. The method for selecting a spacecraft passive load reduction trajectory before launch according to claim 5, characterized in that: The error between the comprehensive characteristic value of the standard high-altitude wind data used in the passive load reduction trajectory design and the comprehensive characteristic value of the high-altitude wind data predicted during the spacecraft launch window for: 。 7. A device for selecting a spacecraft passive load reduction trajectory before launch, characterized in that: It includes high-altitude wind data calculation module, comprehensive characteristic value calculation module, error calculation module and selection module; The high-altitude wind data calculation module is configured to calculate first high-altitude wind data at a preset altitude based on standard high-altitude wind data used in the design of a passive load reduction trajectory; and calculate second high-altitude wind data at a preset altitude based on high-altitude wind data involved in a spacecraft launch window forecast; the first high-altitude wind data includes first high-altitude wind speed data and first high-altitude wind direction data, and the second high-altitude wind data includes second high-altitude wind speed data and second high-altitude wind direction data; The comprehensive characteristic value calculation module is configured to calculate the comprehensive characteristic value corresponding to the standard high-altitude wind data used in the passive load reduction trajectory design based on the average value of the first high-altitude wind data with altitude and the weight of the spacecraft high-altitude wind characteristic wind speed and wind direction; and calculate the comprehensive characteristic value corresponding to the spacecraft launch window forecast high-altitude wind data used in the passive load reduction trajectory design based on the average value of the second high-altitude wind data with altitude and the weight of the spacecraft high-altitude wind characteristic wind speed and wind direction; The first high-altitude wind speed data and the first high-altitude wind direction data at a preset altitude during the flight segment of the spacecraft in the first-level strong wind zone are respectively: ， ， Where, 、 Respectively indicate height The first high altitude wind speed data and the first high altitude wind direction data, Indicates the sequence number in the interpolation table; 、 、 Represents the spacecraft j The serial number used in the design of the passive load reduction trajectory 、 、 The wind speed value below 、 、 Represents the spacecraft j The serial number used in the design of the passive load reduction trajectory 、 、 The wind direction value below, j Indicates the gear number of the passive load reduction trajectory; 、 、 Respectively represent the serial numbers used in the design of the spacecraft's passive load reduction trajectory 、 、 The height value below; The second high altitude wind speed data and the second high altitude wind direction data at the preset altitude during the flight segment of the spacecraft in the first level strong wind zone are respectively: ， ， Where, 、 Respectively indicate height The second-highest-altitude wind speed data and the second-highest-altitude wind direction data, Indicates the sequence number in the interpolation table; 、 、 They represent the serial numbers in the interpolation table of the upper-altitude wind forecast for the spacecraft launch window. 、 、 The wind speed value below 、 、 They represent the serial numbers in the interpolation table of the upper-altitude wind forecast for the spacecraft launch window. 、 、 The wind direction value below, 、 、 They represent the serial numbers in the interpolation table of the upper-altitude wind forecast for the spacecraft launch window. 、 、 The height value below; Spacecraft j The comprehensive characteristic value of the standard high-altitude wind used in the design of the passive load reduction trajectory in the flight segment height sequence of the first-level strong wind area for: ， Where, 、 They represent the average values ​​of the standard high-altitude wind speed and wind direction used in the design of the j-th passive load reduction trajectory of the spacecraft in the flight segment altitude sequence of the first-level strong wind area; 、 They represent the weights of the characteristic wind speed and direction of the spacecraft’s upper air wind respectively; The comprehensive characteristic value corresponding to the high-altitude wind data predicted during the launch window of the spacecraft used in the design of the passive load reduction trajectory for: ， Where, 、 They represent the average values ​​of the predicted upper-altitude wind speed and wind direction during the launch window of the spacecraft under the flight altitude sequence of the first-level strong wind area; The error calculation module is configured to calculate the error between the comprehensive characteristic value of the standard high-altitude wind data used in the passive load reduction trajectory design and the comprehensive characteristic value of the high-altitude wind data predicted during the spacecraft launch window; The selection module is configured to select the passive load reduction trajectory scheme corresponding to the minimum error, and bind the flight parameters corresponding to the scheme to carry out the corresponding flight test mission.

8. An electronic device comprising a memory and a processor coupled to the memory, wherein the processor is configured to execute the method for pre-launch selection of a spacecraft passive load reduction trajectory as described in any one of claims 1 to 6 based on instructions stored in the memory.

Images