Design method and system for effectively capturing caliber of a net-capture load
By acquiring the multi-directional dimensional parameters and position aiming parameters of abandoned satellites, the effective capture aperture of the net-capture payload is calculated, solving the problem of unreliable capture of satellites with different shape characteristics and achieving reliable capture results.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- SHANGHAI AEROSPACE SYST ENG INST
- Filing Date
- 2023-09-22
- Publication Date
- 2026-05-29
AI Technical Summary
Existing technologies make it difficult to design effective capture apertures for net-capture payloads that can adapt to the different shapes and features of abandoned satellites, resulting in unreliable capture.
By acquiring the multi-directional dimensional parameters of the abandoned satellite, the aiming parameters and installation position parameters of the spacecraft relative to the satellite are generated. Combined with the capture flight time and deployment efficiency, the effective capture aperture of the net-capture payload is calculated.
It has achieved reliable capture of abandoned satellites with different shapes and features, and provides input basis for the design of net-capture payloads.
Smart Images
Figure CN117290949B_ABST
Abstract
Description
Technical Field
[0001] This invention belongs to the field of net-catching load design technology, and particularly relates to the design method and system for the effective capture aperture of net-catching loads. Background Technology
[0002] Using a capture payload to capture defunct satellites and remove them from their operational orbit is a safe and effective method for orbital cleanup. Satellites have varying missions and shapes when they enter orbit. The effective capture aperture is a key parameter in the design of capture payloads to reliably capture different types of defunct satellites. Determining the effective capture aperture of a capture payload is a crucial task in capture payload design and requires further in-depth research. Summary of the Invention
[0003] To address the aforementioned problems, the present invention aims to provide a design method and system for the effective capture aperture of a net-capture payload. This system can design the effective capture aperture of the net-capture payload based on the external dimensions of the abandoned satellite, launch position aiming parameters, payload installation position, capture flight time, and deployment efficiency, thereby achieving reliable capture of abandoned satellites with different external shapes.
[0004] To achieve the above objectives, the technical solution of the present invention is as follows: a design method for an effective capture aperture of a net-capturing payload, comprising the following steps: obtaining multi-directional dimensional parameters of a defunct satellite; wherein the multi-directional dimensional parameters include at least the length L. l Width L w and height L h Based on the aforementioned multi-directional dimensional parameters, position aiming parameters of the spacecraft relative to the defunct satellite are generated when launching the payload; wherein the position aiming parameters include at least the distance D of the spacecraft relative to the defunct satellite. f The lateral velocity V of the spacecraft relative to the defunct satellite yz θ (aiming accuracy of the aircraft) and ω (aiming stability of the aircraft) θ ; Obtain the installation position parameters of the net-capturing payload relative to the center of mass of the spacecraft; wherein the installation position parameters include at least the launch direction installation parameter d x Vertical launch direction installation parameter d yz Estimate the capture flight time t of the net-captured payload. net And the deployment efficiency η; based on the multi-directional dimensional parameters of the abandoned satellite, the aiming parameters of the spacecraft relative to the abandoned satellite when launching the net-capturing payload, the installation position parameters, the capture flight time, and the deployment efficiency, the effective capture aperture R of the net-capturing payload is calculated. net .
[0005] Preferably, the method for obtaining the multi-directional dimensional parameters of the abandoned satellite includes: acquiring image information of the abandoned satellite from multiple directions using a preset optical camera; and calculating the multi-directional dimensional parameters of the abandoned satellite based on the image information using a preset algorithm.
[0006] Preferably, the aiming parameters of the spacecraft relative to the defunct satellite when generating the launch net-capturing payload based on the multi-directional dimensional parameters further include: the distance D of the spacecraft relative to the defunct satellite. f The value is determined based on the maximum external dimensions of the abandoned satellite, and is generally taken as D. f ≥1.2×max{L l L w L h}, max{} represents taking the maximum value; the lateral velocity V of the spacecraft relative to the defunct satellite yz θ (aiming accuracy of the aircraft) and ω (aiming stability of the aircraft) θ The values are determined based on the relative measurement capabilities of the tracking aircraft configured on the aircraft.
[0007] Preferably, the lateral velocity V of the spacecraft relative to the defunct satellite yz θ (aiming accuracy of the aircraft) and ω (aiming stability of the aircraft) θ The value is taken as 1.5 to 2.5 times the single-machine measurement capability of the tracking and aiming device.
[0008] Preferably, obtaining the installation position parameters of the net-catching payload relative to the center of mass of the aircraft further includes: directly measuring the installation position parameters of the net-catching payload relative to the center of mass of the aircraft from the digital model of the aircraft configuration layout, wherein the launch direction of the net-catching payload is installed through the center of mass of the aircraft.
[0009] Preferably, the estimated capture flight time t of the net-captured payload is... net The deployment efficiency η further includes: based on the mass m of the net-captured load traction body. q Net mass m net Transmission rate V net Launch angle α net and the distance D of the spacecraft relative to the defunct satellite at launch. f Calculate the capture flight time t net : The unfolding efficiency η is between 80% and 90%.
[0010] Preferably, based on the multi-directional dimensional parameters of the abandoned satellite, the aiming parameters of the spacecraft relative to the abandoned satellite when launching the net-capturing payload, the installation position parameters, the capture flight time, and the deployment efficiency, the effective capture aperture R of the net-capturing payload is calculated. netFurther includes: multi-directional dimensional parameters based on abandoned satellites, position aiming parameters when the spacecraft launches the net-capturing payload, installation position parameters, and acquisition flight time t. net And the deployment efficiency η, calculate the effective capture aperture R of the net-capturing load. net :
[0011] Based on the same concept, the present invention also provides a design system for the effective capture aperture of a net-capturing payload, comprising: a measurement module for acquiring multi-directional dimensional parameters of a defunct satellite; wherein the multi-directional dimensional parameters include at least a length L. l Width L w and height L h The launch position determination module is used to generate position aiming parameters of the spacecraft relative to the defunct satellite when launching the payload based on the multi-directional dimensional parameters; wherein the position aiming parameters include at least the distance D of the spacecraft relative to the defunct satellite. f The lateral velocity V of the spacecraft relative to the defunct satellite yz θ (aiming accuracy of the aircraft) and ω (aiming stability of the aircraft) θ The installation position determination module is used to obtain the installation position parameters of the net-capturing payload relative to the center of mass of the aircraft; wherein the installation position parameters include at least the launch direction installation parameter d. x Vertical launch direction installation parameter d yz The estimation module is used to estimate the capture flight time t of the net-captured payload. net And the deployment efficiency η; a calculation module, used to calculate the effective capture aperture R of the net-capture payload based on the multi-directional dimensional parameters of the defunct satellite, the aiming parameters of the spacecraft relative to the defunct satellite when launching the net-capture payload, the installation position parameters, the capture flight time, and the deployment efficiency. net .
[0012] Based on the same concept, the present invention also provides an electronic device, characterized in that it includes: a memory for storing a processing program; and a processor, wherein the processor, when executing the processing program, implements the design method for the effective capture caliber of the net-catching payload described in any one of the above-mentioned methods.
[0013] Based on the same concept, the present invention also provides a readable storage medium, characterized in that the readable storage medium stores a processing program, which, when executed by a processor, implements the design method for the effective capture caliber of the net-capturing payload described in any of the above-mentioned claims.
[0014] Because the present invention adopts the above technical solution, it has the following advantages and positive effects compared with the prior art:
[0015] The technical solution of this invention designs an effective capture aperture for the net-capture payload based on the external dimensions of defunct satellites, launch position aiming parameters, payload installation position, capture flight time, and deployment efficiency, achieving reliable capture of defunct satellites with different shapes. The proposed method solves the problem of designing the effective aperture of the net-capture payload for defunct satellites with different shapes, providing input basis for the design of net-capture payloads. Attached Figure Description
[0016] The specific embodiments of the present invention will be further described in detail below with reference to the accompanying drawings, wherein:
[0017] Figure 1 This is a schematic diagram of the design method for the effective capture aperture of the net-capturing load according to the present invention. Detailed Implementation
[0018] The present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. The advantages and features of the present invention will become clearer from the following description and claims. It should be noted that the drawings are all in a very simplified form and use non-precise ratios, and are only used to facilitate and clarify the illustration of the embodiments of the present invention.
[0019] It should be noted that all directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present invention are only used to explain the relative positional relationship and movement of each component in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indication will also change accordingly.
[0020] First Embodiment
[0021] like Figure 1 As shown in the diagram, this embodiment provides a schematic flowchart of a design method for an effective capture aperture of a net-captured payload, including the following steps:
[0022] Step 1: Obtain the anisotropic dimensional parameters of the abandoned satellite, including length L. l Width L w and height L h ;
[0023] Preferably, the maximum external dimensions of a defunct satellite can be obtained by imaging and observing it from different azimuths using an optical camera. Obtaining the multi-directional dimensions of a defunct satellite using an optical camera is simple, reliable, and can easily achieve the maximum dimensions in more than three directions, allowing for the acquisition of dimensions in multiple directions according to actual accuracy requirements.
[0024] Step 2: Determine the aiming parameters of the spacecraft relative to the defunct satellite when launching the net-capturing payload. The aiming parameters include the distance D of the spacecraft relative to the defunct satellite. fThe lateral velocity V of the spacecraft relative to the defunct satellite yz θ (aiming accuracy of the aircraft) and ω (aiming stability of the aircraft) θ ;
[0025] Preferably, the distance D of the spacecraft relative to the defunct satellite f The value is determined based on the maximum external dimensions of the abandoned satellite, and is generally taken as D. f ≥1.2×max{L l L w L h}, max{} represents taking the maximum value. The lateral velocity V of the spacecraft relative to the defunct satellite. yz θ (aiming accuracy of the aircraft) and ω (aiming stability of the aircraft) θ The value is determined based on the relative measurement capability of the tracking and aiming unit configured on the aircraft, and is generally 1.5 to 2.5 times the measurement capability of the tracking and aiming unit.
[0026] Step 3: Obtain the installation position parameters of the net-capturing payload relative to the spacecraft's center of mass, including the launch direction installation parameter d. x Vertical launch direction installation parameter d yz ;
[0027] Preferably, the installation position parameters of the net-catching payload relative to the aircraft's center of mass can be directly measured from the digital model of the aircraft's configuration layout. The launch direction of the net-catching payload is generally required to be installed past the aircraft's center of mass. Parameter acquisition is convenient. Directly measuring the installation position parameters from the digital model of the aircraft's configuration layout is a simple and quick method.
[0028] Step 4: Estimate the capture flight time t of the net-capture payload net And the unfolding efficiency η;
[0029] Preferably, the capture flight time t of the net-capture payload net Based on the mass m of the net-captured load traction body q Net mass m net Transmission rate V net Launch angle α net and the distance D of the spacecraft relative to the defunct satellite at launch. f To make an estimate, we generally take...
[0030] Optionally, the deployment efficiency η of the net-captured load is selected based on engineering experience, and is generally taken as 80% to 90%.
[0031] Step 5: Based on the external dimensions of the abandoned satellite, determine the length L. l Width L w and height L h Position aiming parameters when the spacecraft launches its net-capturing payload: distance D of the spacecraft relative to the defunct satellite.f The lateral velocity V of the spacecraft relative to the defunct satellite yz The aiming accuracy θ and the aiming stability ω of the aircraft θ Installation position parameters, launch direction, installation parameter d x Vertical launch direction installation parameter d yz and capture flight time t net Calculate the effective capture aperture R of the net-capturing load, in conjunction with the deployment efficiency η. net ,Pick
[0032] The technical solution in this embodiment designs an effective capture aperture for the net-capture payload based on the external dimensions of the decommissioned satellite, launch position aiming parameters, payload installation position, capture flight time, and deployment efficiency, achieving reliable capture of decommissioned satellites with different shapes. The proposed method solves the problem of designing the effective aperture of the net-capture payload for decommissioned satellites with different shapes, providing input basis for the design of net-capture payloads.
[0033] Second Embodiment
[0034] Based on the same concept, the present invention also provides a design system for the effective capture aperture of a net-capturing payload, comprising: a measurement module for acquiring multi-directional dimensional parameters of a defunct satellite; wherein the multi-directional dimensional parameters include at least a length L. l Width L w and height L h The launch position determination module is used to generate position aiming parameters of the spacecraft relative to the defunct satellite when launching the payload based on the multi-directional dimensional parameters; wherein the position aiming parameters include at least the distance D of the spacecraft relative to the defunct satellite. f The lateral velocity V of the spacecraft relative to the defunct satellite yz θ (aiming accuracy of the aircraft) and ω (aiming stability of the aircraft) θ The installation position determination module is used to obtain the installation position parameters of the net-capturing payload relative to the center of mass of the aircraft; wherein the installation position parameters include at least the launch direction installation parameter d. x Vertical launch direction installation parameter d yz The estimation module is used to estimate the capture flight time t of the net-captured payload. net And the deployment efficiency η; a calculation module, used to calculate the effective capture aperture R of the net-capture payload based on the multi-directional dimensional parameters of the defunct satellite, the aiming parameters of the spacecraft relative to the defunct satellite when launching the net-capture payload, the installation position parameters, the capture flight time, and the deployment efficiency. net .
[0035] Those skilled in the art will clearly understand that, for the sake of convenience and brevity, the specific identification content executed by the system and device described above can be referred to the corresponding process in the foregoing method embodiments.
[0036] The embodiments of the present invention have been described in detail above with reference to the accompanying drawings, but the present invention is not limited to the above embodiments. Even if various changes are made to the present invention, if these changes fall within the scope of the claims of the present invention and their equivalents, they shall still fall within the protection scope of the present invention.
Claims
1. A design method for an effective capture aperture of a net-captured payload, characterized in that, Includes the following steps: Obtain the multi-directional dimensional parameters of the abandoned satellite; wherein the multi-directional dimensional parameters include at least the length L. l Width L w and height L h ; The launch net-capturing payload is generated based on the multi-directional dimensional parameters to determine the spacecraft's position aiming parameters relative to the defunct satellite; wherein the position aiming parameters include at least the spacecraft's distance D relative to the defunct satellite. f The lateral velocity V of the spacecraft relative to the defunct satellite yz θ (aiming accuracy of the aircraft) and ω (aiming stability of the aircraft) θ ; Obtain the installation position parameters of the net-capturing payload relative to the center of mass of the spacecraft; wherein the installation position parameters include at least the launch direction installation parameter d. x Vertical launch direction installation parameter d yz ; Estimate the capture flight time t of the net-capture payload net And the unfolding efficiency η; It further includes: based on the mass m of the net-captured load traction body q Net mass m s Transmission rate V net Launch angle α net and the distance D of the spacecraft relative to the defunct satellite at launch. f Calculate the capture flight time t net : The unfolding efficiency η is between 80% and 90%. Based on the multi-dimensional parameters of the defunct satellite, the aiming parameters of the spacecraft relative to the defunct satellite during launch of the net-capturing payload, the installation position parameters, the capture flight time, and the deployment efficiency, the effective capture aperture R of the net-capturing payload is calculated. net It further includes: multi-directional dimensional parameters based on abandoned satellites, position aiming parameters when the spacecraft launches the net-capturing payload, installation position parameters, and acquisition flight time t. net And the deployment efficiency η, calculate the effective capture aperture R of the net-capturing load. net : .
2. The design method for the effective capture aperture of the net-capturing load according to claim 1, characterized in that, The method for obtaining the multi-directional dimensional parameters of a decommissioned satellite includes: Image information of the abandoned satellite from multiple directions is acquired using a pre-set optical camera; Based on the image information, the multi-directional shape and size parameters of the abandoned satellite are calculated using a preset algorithm.
3. The design method for the effective capture aperture of the net-capturing load according to claim 1, characterized in that, The aiming parameters for the spacecraft's position relative to the defunct satellite when generating the launch net-capturing payload based on the aforementioned multi-directional dimensional parameters further include: The distance D of the spacecraft relative to the defunct satellite f The value is determined based on the maximum external dimensions of the abandoned satellite, and is set to D. f ≥1.2×max{L l ;L w ;L h }, max{} represents taking the maximum value; The lateral velocity V of the spacecraft relative to the defunct satellite yz θ (aiming accuracy of the aircraft) and ω (aiming stability of the aircraft) θ The values are determined based on the relative measurement capabilities of the tracking aircraft configured on the aircraft.
4. The design method for the effective capture aperture of the net-capturing load according to claim 3, characterized in that, The lateral velocity V of the spacecraft relative to the defunct satellite yz θ (aiming accuracy of the aircraft) and ω (aiming stability of the aircraft) θ The value is taken as 1.5 to 2.5 times the single-machine measurement capability of the tracking and aiming device.
5. The design method for the effective capture aperture of the net-capturing load according to claim 1, characterized in that, The acquisition of the installation position parameters of the net-capturing payload relative to the center of mass of the aircraft further includes: The installation position parameters of the net-catching payload relative to the center of mass of the aircraft are directly measured from the digital model of the aircraft configuration layout. The launch direction of the net-catching payload is installed through the center of mass of the aircraft.
6. A design system for effectively capturing the caliber of a net-trapping payload, characterized in that, include: The measurement module is used to obtain the multi-directional dimensional parameters of abandoned satellites; The multi-directional dimensional parameters mentioned above include at least the length L. l Width L w and height L h ; The launch position determination module is used to generate position aiming parameters of the spacecraft relative to the defunct satellite when launching the payload based on the multi-directional dimensional parameters; wherein the position aiming parameters include at least the distance D of the spacecraft relative to the defunct satellite. f The lateral velocity V of the spacecraft relative to the defunct satellite yz θ (aiming accuracy of the aircraft) and ω (aiming stability of the aircraft) θ ; The installation position determination module is used to obtain the installation position parameters of the net-capturing payload relative to the center of mass of the aircraft; wherein the installation position parameters include at least the launch direction installation parameter d. x Vertical launch direction installation parameter d yz ; The estimation module is used to estimate the capture flight time t of the net-captured payload. net And the unfolding efficiency η; It further includes: based on the mass m of the net-captured load traction body q Net mass m s Transmission rate V net Launch angle α net and the distance D of the spacecraft relative to the defunct satellite at launch. f Calculate the capture flight time t net : The unfolding efficiency η is between 80% and 90%. The calculation module is used to calculate the effective capture aperture R of the net-capture payload based on the multi-directional dimensional parameters of the defunct satellite, the aiming parameters of the spacecraft relative to the defunct satellite when launching the net-capture payload, the installation position parameters, the capture flight time, and the deployment efficiency. net It further includes: multi-directional dimensional parameters based on abandoned satellites, position aiming parameters when the spacecraft launches the net-capturing payload, installation position parameters, and acquisition flight time t. net And the deployment efficiency η, calculate the effective capture aperture R of the net-capturing load. net : .