Satellite structure self-supporting integrated antenna and solar array unfolding method and system

Abstract

The invention provides a satellite structure self-supporting integrated antenna and solar array unfolding method and system. The satellite structure self-supporting integrated antenna and solar array unfolding method comprises the steps that a tool installation interface of a satellite structure and a fixing interface of a whole satellite parking tool are designed; tool fixing suspension point interface planes of the antenna frame and the solar cell array substrate are parallel to a satellite structure mounting interface plane; designing an integrated unfolding tool system based on satellite structure installation; assembling and checking the three-dimensional model of the expansion tool system and the three-dimensional model of the satellite body; micro-deformation simulation analysis of the whole satellite structure is carried out; carrying out impact simulation analysis on a whole-satellite structure and expansion tool system assembly; designing a satellite parking vehicle according to an expansion impact simulation result; and during unfolding, the satellite structure is fixed on the parking vehicle. The unfolding tool system can move along with a satellite body, places can be rapidly switched, and the problems of short-period and high-quality unfolding of antennas and solar cell arrays of rapid batch development of satellites are solved, so that the satellite development period is greatly shortened, and the labor cost is greatly reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of satellites as a whole, and in particular to a method and system for deploying a self-supporting integrated antenna and solar array in a satellite structure. Background Art

[0002] In the field of satellite technology, particularly in the overall assembly design of remote sensing satellites, deploying the large solar arrays and antennas of traditional satellites has long been a technical challenge. Traditional deployment methods typically utilize air-floating deployment on a marble platform. This method relies on a complex and expensive system of marble platforms and air-floating fixtures, which must be securely fixed to the ground. Deploying the solar arrays and antennas requires extremely high precision in the satellite's attitude, as even the slightest deviation could result in deployment failure or damage the satellite structure. Traditional deployment processes deploy only one component at a time, and the entire satellite's attitude must be frequently adjusted and switched when deploying different large components. This not only consumes significant manpower and resources but also significantly prolongs the satellite's development cycle. For example, pre-deployment assembly of the marble platform requires significant time, and during the deployment process, due to the need for high precision, deployment can only be performed on a single component at a time, resulting in low efficiency.

[0003] Patent document CN107255570B discloses a posture adjustment method suitable for large component rollover deployment tests, which includes the following steps: Step 1: Determine the rollover deployment test unloading plan based on the configuration plan and mass characteristics of the satellite's large components, and calculate the unloading force and fixing points required by the unloading tooling; Step 2: After the satellite is rolled over to the deployment state, in the absence of unloading by the large component unloading tooling, adjust the satellite's posture through the precise measurement results of the pitch angle and offset angle of the main reference prism set on the satellite's large component frame to ensure the verticality of the large component's deployment axis to the earth's level.

[0004] Traditional deployment methods also suffer from significant site restrictions and limited flexibility. The marble platform and air-floating assembly system are large, heavy, and difficult to move, limiting the choice of sites for satellite deployment tests. Once a test site is determined, it is difficult to change, a significant obstacle for satellite development projects that require rapid site changes.

[0005] Therefore, it is necessary to propose a new technical solution to improve the above technical problems. Summary of the Invention

[0006] In view of the defects in the prior art, the purpose of the present invention is to provide a method and system for deploying an integrated antenna and solar array with a self-supporting satellite structure.

[0007] According to the present invention, a method for deploying a self-supporting integrated antenna and solar array for a satellite structure is provided, the method comprising the following steps:

[0008] Step S1: Designing the tooling installation interface of the satellite structure; the installation points of the satellite body structure provided to the deployment tooling system are located at the four end areas at the top of the body structure, which can be fitted into a plane;

[0009] Step S2: Designing the fixed interface of the whole satellite parking tooling of the satellite structure;

[0010] Step S3: aligning the interface planes of the tooling fixing points of the antenna frame and the solar cell array substrate to be parallel to the satellite structure installation interface plane;

[0011] Step S4: Designing an integrated deployment tooling system for satellite structure installation based on the configuration position and layout space between the tooling installation point interface at the top of the satellite, the single-unit layout at the top of the satellite, and the tooling fixing and hanging point interfaces of the antenna frame and the solar cell array substrate;

[0012] Step S5: Perform an assembly check on the three-dimensional model of the deployment tooling system and the three-dimensional model of the satellite body to check that there is no interference with external products along the entire deployment movement path of the antenna and solar array;

[0013] Step S6: Conduct micro-deformation simulation analysis of the entire satellite structure and assemble the satellite model and the deployment tooling system into a complete unit;

[0014] Step S7: Conducting an impact simulation analysis of the entire satellite structure and the deployment fixture system assembly. This simulation analysis requires that after the antenna and solar array are connected to the deployment fixture system and the assembly is deployed and locked, the impact caused by the impact does not exceed the strength of the satellite's onboard products and the deployment fixture system, ensuring that the onboard products have a safety margin and are not damaged.

[0015] Step S8: Designing a satellite parking vehicle based on the deployment impact simulation results;

[0016] Step S9: During deployment, the satellite structure is fixed on the parking vehicle, and the deployment tooling system is directly fixed on the top of the satellite structure. The deployment tooling system is interconnected with the tooling lifting points of the antenna and solar array; after the satellite attitude adjustment meets the requirements, the pressing points of the antenna and solar array are unlocked to complete the deployment and locking of the antenna and solar array.

[0017] Preferably, the satellite body structure described in step S1 is provided to the installation point of the unfolding tooling system using the joint position of the star body structure, with an integrated embedded part embedded inside, a wire screw sleeve installed in the threaded hole of the installation point, and an aluminum alloy scraper attached to the installation hole area for combined processing.

[0018] Preferably, the fixed interface of the whole satellite parking tooling of the satellite structure in step S2 adopts the load-bearing joint position of the satellite structure, which is the satellite-rocket separation interface of the satellite.

[0019] Preferably, the unfolding tooling system in step S4 is made of high-rigidity, lightweight materials, and the rotation axes of each unfolding rocker mechanism are collinear and parallel to the rotation axes of the antenna hinge mechanism and the solar cell array hinge mechanism, and each rotation axis remains perpendicular to the ground.

[0020] Preferably, the onboard product in step S7 has a safety margin when subjected to impact, the safety margin being no less than 2, and the deployment tooling system is designed with a buffer device that is deployed and locked in place;

[0021] Before being installed on the satellite structure, the deployment tooling system performs a self-check on the ground to complete the horizontal calibration of the unloading pendulum and the unloading force calibration of the constant force spring;

[0022] The unfolding tooling system is designed as an integrated product; the unfolding tooling system unloads the single antenna frame and the single solar cell array substrate according to their weight, and the unloading force exceeds the center of mass of the single panel.

[0023] The present invention also provides a satellite structure self-supporting integrated antenna and solar array deployment system, the system comprising the following modules:

[0024] Module M1: Design the tooling installation interface of the satellite structure; the installation points of the satellite structure for the deployment tooling system are located at the four end areas at the top of the satellite structure, which can be fitted into a plane;

[0025] Module M2: Design the fixed interface of the satellite structure and the whole satellite parking tooling;

[0026] Module M3: Align the interface plane of the tooling fixing points of the antenna frame and the solar cell array substrate with the satellite structure installation interface plane;

[0027] Module M4: Design an integrated deployment tooling system for satellite structure installation based on the configuration position and layout space between the tooling installation point interface at the top of the satellite, the single-unit layout at the top of the satellite, and the tooling fixing and hanging point interfaces of the antenna frame and solar cell array substrate;

[0028] Module M5: Perform assembly inspection on the 3D model of the deployment tooling system and the 3D model of the satellite body to check that there is no interference with external products along the entire deployment path of the antenna and solar array.

[0029] Module M6: Conduct micro-deformation simulation analysis of the entire satellite structure and assemble the satellite model and deployment tooling system into a complete unit;

[0030] Module M7: Conduct impact simulation analysis of the entire satellite structure and deployment fixture system assembly. This simulation analysis requires that after the antenna and solar array are connected to the deployment fixture system and the assembly is deployed and locked, the impact caused by the impact does not exceed the strength of the satellite onboard products and the deployment fixture, and the onboard products have a safety margin and are not damaged.

[0031] Module M8: Design a satellite parking vehicle based on the deployment impact simulation results;

[0032] Module M9: When deployed, the satellite structure is fixed on the parking vehicle, and the deployment tooling system is directly fixed to the top of the satellite structure. The deployment tooling system is interconnected with the tooling lifting points of the antenna and solar array; after the satellite attitude adjustment meets the requirements, the pressing points of the antenna and solar array are unlocked to complete the deployment and locking of the antenna and solar array.

[0033] Preferably, the satellite body structure described in the module M1 provides the installation point of the unfolding tooling system with the joint position of the star body structure, embedded integrated embedded parts, wire screw sleeves are installed in the threaded holes of the installation points, and aluminum alloy scrapers are pasted in the installation hole area for combined processing.

[0034] Preferably, the fixed interface of the whole satellite parking tooling of the satellite structure in the module M2 adopts the load-bearing joint position of the satellite structure, which is the satellite-rocket separation interface.

[0035] Preferably, the unfolding tooling system in the module M4 is made of high-rigidity, lightweight materials, and the rotation axes of each unfolding rocker mechanism are collinear and parallel to the rotation axes of the antenna hinge mechanism and the solar cell array hinge mechanism, and each rotation axis remains perpendicular to the ground.

[0036] Preferably, the onboard products in the module M7 have a safety margin when affected by impact, the safety margin is not less than 2, and the deployment tooling system is designed with a buffer device after being deployed into place and locked;

[0037] Before being installed on the satellite structure, the deployment tooling system performs a self-check on the ground to complete the horizontal calibration of the unloading pendulum and the unloading force calibration of the constant force spring;

[0038] The unfolding tooling system is designed as an integrated product; the unfolding tooling system unloads the single antenna frame and the single solar cell array substrate according to their weight, and the unloading force exceeds the center of mass of the single panel.

[0039] Compared with the prior art, the present invention has the following beneficial effects:

[0040] 1. This invention simplifies the traditionally complex deployment process by directly mounting and fixing the deployment fixture system on top of the satellite structure, eliminating the need for a marble platform and air-floating assembly fixture system required for ground-based deployment testing. The deployment of both the antenna and solar array can be completed using the same deployment fixture system, eliminating the need for repeated attitude adjustments and conversions of the satellite structure. This reduces the traditional seven-day deployment test time for remote sensing satellite antennas and solar arrays to less than one day, significantly shortening the satellite development cycle.

[0041] 2. The deployment tooling system of the present invention can be moved with the satellite, allowing for the conversion of test sites. This eliminates the need for large marble platforms, significantly reducing the labor and material requirements during satellite development. This reduces satellite development costs, brings considerable economic benefits, and provides an effective solution for rapid mass production of satellites.

[0042] 3. The deployment tooling system of the present invention is simple and convenient to operate and can be easily promoted and applied in multiple satellite projects. It has been successfully applied to a remote sensing satellite that is rapidly and rapidly developed, and has been used as a reference and promoted by other satellite projects, proving its reliability and efficiency in practical applications. It further improves the efficiency and quality of satellite development and has great promotion value. BRIEF DESCRIPTION OF THE DRAWINGS

[0043] Other features, objects and advantages of the present invention will become more apparent upon reading the detailed description of non-limiting embodiments with reference to the following drawings:

[0044] Figure 1 is a flow chart of the design method of the present invention;

[0045] Figure 2 It is a schematic diagram of the integrated development design of the present invention. DETAILED DESCRIPTION

[0046] The present invention will be described in detail below with reference to specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those skilled in the art, several changes and improvements can be made without departing from the scope of the present invention. These all fall within the scope of protection of the present invention.

[0047] Example 1:

[0048] Reference Figure 1 and Figure 2 According to the present invention, a method for deploying a self-supporting integrated antenna and solar array for a satellite structure is provided, the method comprising the following steps:

[0049] Step S1: Design the tooling installation interface of the satellite structure; the installation points provided by the satellite star structure to the deployment tooling system are located at the four end areas at the top of the star structure and can be fitted into a plane; the installation points provided by the satellite star structure to the deployment tooling system adopt the joint position of the star structure, with integrated embedded parts embedded, and wire screw sleeves installed in the threaded holes of the installation points, and aluminum alloy scrapers are pasted in the installation hole area for combined processing.

[0050] Step S2: Designing a fixed interface of the satellite structure for the whole-satellite parking tooling; the fixed interface of the whole-satellite parking tooling adopts the load-bearing joint position of the satellite structure, which is the satellite-rocket separation interface of the satellite.

[0051] Step S3: aligning the interface planes of the tooling fixing points of the antenna frame and the solar cell array substrate to be parallel to the satellite structure installation interface plane;

[0052] Step S4: Based on the configuration position and layout space between the tooling installation point interface at the top of the satellite, the single-machine layout at the top of the satellite, and the tooling fixed suspension point interface of the antenna frame and the solar cell array substrate, an integrated deployment tooling system based on satellite structure installation is designed; the deployment tooling system uses high-rigidity, lightweight materials, and the rotation axes of its various deployment rocker mechanisms are collinear and parallel to the rotation axes of the antenna hinge mechanism and the solar cell array hinge mechanism, and each rotation axis remains perpendicular to the earth.

[0053] Step S5: Perform an assembly check on the three-dimensional model of the deployment tooling system and the three-dimensional model of the satellite body to check that there is no interference with external products along the entire deployment movement path of the antenna and solar array;

[0054] Step S6: Conduct micro-deformation simulation analysis of the entire satellite structure and assemble the satellite model and the deployment tooling system into a complete unit;

[0055] Step S7: Conducting an impact simulation analysis of the entire satellite structure and the deployment fixture system assembly. This simulation analysis requires that after the antenna and solar array are connected to the deployment fixture system and the assembly is deployed and locked, the impact caused by the impact does not exceed the strength of the satellite's onboard products and the deployment fixture system, ensuring that the onboard products have a safety margin and are not damaged.

[0056] Step S8: Designing a satellite parking vehicle based on the deployment impact simulation results;

[0057] Step S9: During deployment, the satellite structure is fixed on the parking vehicle, and the deployment tooling system is directly fixed on the top of the satellite structure. The deployment tooling system is interconnected with the tooling lifting points of the antenna and solar array; after the satellite attitude adjustment meets the requirements, the pressing points of the antenna and solar array are unlocked to complete the deployment and locking of the antenna and solar array.

[0058] When the onboard product is affected by impact, it has a safety margin of no less than 2, and the deployment tooling system is designed with a buffer device after deployment and locking;

[0059] Before being installed on the satellite structure, the deployment tooling system performs a self-check on the ground to complete the horizontal calibration of the unloading pendulum and the unloading force calibration of the constant force spring;

[0060] The unfolding tooling system is designed as an integrated product; the unfolding tooling system unloads the single antenna frame and the single solar cell array substrate according to their weight, and the unloading force exceeds the center of mass of the single panel.

[0061] The present invention also provides a satellite structure self-supporting integrated antenna and solar array deployment system. The satellite structure self-supporting integrated antenna and solar array deployment system can be realized by executing the process steps of the satellite structure self-supporting integrated antenna and solar array deployment method. That is, those skilled in the art can understand the satellite structure self-supporting integrated antenna and solar array deployment method as a preferred implementation method of the satellite structure self-supporting integrated antenna and solar array deployment system.

[0062] Example 2:

[0063] The present invention also provides a satellite structure self-supporting integrated antenna and solar array deployment system, the system comprising the following modules:

[0064] Module M1: Design the tooling installation interface of the satellite structure; the installation points provided by the satellite body structure to the deployment tooling system are located at the four end areas at the top of the satellite body structure and can be fitted into a plane; the installation points provided by the satellite body structure to the deployment tooling system adopt the joint positions of the satellite body structure, with integrated embedded parts embedded, wire screw sleeves installed in the threaded holes of the installation points, and aluminum alloy scrapers pasted in the installation hole areas for combined processing.

[0065] Module M2: Design the fixed interface of the satellite structure's entire satellite parking tooling; the fixed interface of the satellite structure's entire satellite parking tooling adopts the load-bearing joint position of the satellite structure, which is the satellite-rocket separation interface.

[0066] Module M3: Align the interface plane of the tooling fixing points of the antenna frame and the solar cell array substrate with the satellite structure installation interface plane;

[0067] Module M4: Design an integrated deployment tooling system for satellite structure installation based on the configuration position and layout space between the tooling installation point interface at the top of the satellite, the single-unit layout at the top of the satellite, and the tooling fixed suspension point interface between the antenna frame and the solar array substrate. The deployment tooling system uses high-rigidity, lightweight materials, and the rotation axes of its deployment rocker mechanisms are collinear and parallel to the rotation axes of the antenna hinge mechanism and the solar array hinge mechanism, and each rotation axis remains perpendicular to the earth.

[0068] Module M5: Perform assembly inspection on the 3D model of the deployment tooling system and the 3D model of the satellite body to check that there is no interference with external products along the entire deployment path of the antenna and solar array.

[0069] Module M6: Conduct micro-deformation simulation analysis of the entire satellite structure and assemble the satellite model and deployment tooling system into a complete unit;

[0070] Module M7: Conduct impact simulation analysis of the entire satellite structure and deployment fixture system assembly. This simulation analysis requires that after the antenna and solar array are connected to the deployment fixture system and the assembly is deployed and locked, the impact caused by the impact does not exceed the strength of the satellite onboard products and the deployment fixture, and the onboard products have a safety margin and are not damaged.

[0071] Module M8: Design a satellite parking vehicle based on the deployment impact simulation results;

[0072] Module M9: When deployed, the satellite structure is fixed on the parking vehicle, and the deployment tooling system is directly fixed to the top of the satellite structure. The deployment tooling system is interconnected with the tooling lifting points of the antenna and solar array; after the satellite attitude adjustment meets the requirements, the pressing points of the antenna and solar array are unlocked to complete the deployment and locking of the antenna and solar array.

[0073] When the onboard product is affected by impact, it has a safety margin of no less than 2, and the deployment tooling system is designed with a buffer device after deployment and locking;

[0074] Before being installed on the satellite structure, the deployment tooling system performs a self-check on the ground to complete the horizontal calibration of the unloading pendulum and the unloading force calibration of the constant force spring;

[0075] The unfolding tooling system is designed as an integrated product; the unfolding tooling system unloads the single antenna frame and the single solar cell array substrate according to their weight, and the unloading force exceeds the center of mass of the single panel.

[0076] Example 3:

[0077] The present invention discloses a method for deploying an integrated antenna and solar array based on a self-supporting satellite structure, pertaining to the field of satellite assembly design. Conventional satellites typically deploy large solar arrays and antennas using a marble platform and air-floating deployment fixtures, each securely fixed to the ground. This requires extremely high satellite attitude accuracy during solar array and antenna deployment, and deployment of different components requires the entire satellite to undergo attitude adjustments and switching, which is time-consuming. This invention, based on a self-supporting integrated antenna and solar array deployment method based on a satellite structure, is the first to directly mount and secure the deployment fixtures on top of the satellite structure, eliminating the need for a marble platform and air-floating fixtures during ground-based deployment tests. Furthermore, both solar array and antenna deployment can be performed using the same fixture, eliminating the need for frequent satellite attitude adjustments and switching. Furthermore, the deployment fixtures can be moved with the satellite, enabling rapid site changes. This solves the challenge of rapidly mass-producing satellite antennas and solar arrays with short turnaround times and high quality, significantly reducing satellite development cycles and labor costs.

[0078] A method for deploying an integrated antenna and solar array based on a self-supporting satellite structure mainly includes the following steps:

[0079] Step 1: Rationally design the tooling installation points of the satellite structure. The installation points provided by the satellite structure for the deployment tooling system should generally be located at the four end areas of the top of the satellite structure, which can be fitted into a high-precision plane.

[0080] Step 2: Rationally design the satellite structure's parking and fixing interfaces. The satellite structure's parking and fixing interfaces are typically located at the four end areas at the bottom of the structure. They can also be fitted into a high-precision plane parallel to the tooling installation point fitting surface at the top of the structure.

[0081] Step 3: Make the interface plane of the tooling fixing points of the antenna frame and the solar cell array substrate parallel to the fitting surface of the installation point provided by the satellite structure to the tooling, that is, in the same direction.

[0082] Step 4: Rationally design an integrated deployment tooling system based on satellite structure installation according to the configuration position and layout space between the tooling installation point interface at the top of the satellite, the single-machine layout at the top of the satellite, and the tooling fixed suspension point interface between the antenna frame and the solar cell array substrate.

[0083] Step 5: Perform an assembly inspection on the three-dimensional model of the unfolding tooling system and the three-dimensional model of the satellite body to check that there is no interference with external products along the complete unfolding movement path of the antenna and solar array, and that the disassembly and assembly of the unfolding tooling system on the satellite body structure should be easy to operate, and the operation process of the disassembly and assembly tools will not interfere with the satellite product.

[0084] Step 6: Conduct micro-deformation simulation analysis of the entire satellite structure. Assemble the satellite model and the deployment tooling system into a complete unit. Through simulation analysis, the analysis results are required to meet the requirement that after the deployment tooling system is installed and fixed to the satellite structure, the micro-deformation of the satellite structure caused by its weight is far less than the stiffness of the satellite structural parts, and far less than the safety clearance required for the pull-out rods of the antenna and solar array compression points; at the same time, when the deployment tooling system moves with the satellite structure, it will not cause damage to the satellite structure.

[0085] Step 7: Conduct an impact simulation analysis of the entire satellite structure. Through simulation analysis, it is required that after the antenna and solar array are connected to the deployment tooling system and their assembly is deployed and locked, the impact caused should not exceed the strength of the satellite onboard product itself and the strength of the deployment tooling, ensuring that the onboard product has sufficient safety margin and will not cause damage to the onboard product.

[0086] Step 8. Based on the deployment impact simulation results, the satellite parking vehicle is rationally designed to adapt to the changes in the center of mass and the impact of the deployment impact during the deployment of the antenna and solar array. It is required to be reliably fixed and designed with protective measures that will not cause the entire satellite to overturn.

[0087] Step 9: During deployment, the satellite structure is fixed on the parking vehicle, and the deployment tooling system is directly fixed on the top of the satellite structure. The deployment tooling system is interconnected with the tooling lifting points of the antenna and solar array. After the satellite attitude adjustment meets the requirements, the pressing points of the antenna and solar array are unlocked to avoid hooking during the deployment process, and the deployment and locking of the antenna and solar array are completed smoothly.

[0088] The satellite body structure described in step 1 is provided as the installation point for the unfolding tooling system. The joint position of the satellite body structure should be adopted, and integrated embedded parts should be embedded. Wire screw sleeves should be installed in the threaded holes of the installation points to improve the bearing capacity of the installation holes. Aluminum alloy scrapers can be pasted in the installation hole area for combined processing to ensure high precision of the fitting surface of the installation point.

[0089] The parking and fixing interface of the satellite body structure described in step 2 should adopt the load-bearing joint position of the satellite body structure, which is generally also the satellite-rocket separation interface. Appropriate protective measures should be taken during use.

[0090] The deployment tooling system described in step 4 is generally made of high-rigidity, lightweight materials. The rotation axes of each deployment rocker mechanism should be collinear and parallel to the rotation axes of the antenna hinge mechanism and the solar cell array hinge mechanism, and each rotation axis should remain perpendicular to the ground.

[0091] The onboard product described in step 7 should have sufficient safety margin when affected by impact. Generally, the safety margin should be no less than 2, and the deployment tooling system should be designed with a buffer device after being deployed into place and locked.

[0092] Before installation on the satellite structure, the deployment fixture system should facilitate on-ground self-checking to complete the horizontal calibration of the unloading pendulum and the unloading force calibration of the constant-force spring. The deployment fixture system can be designed as an integrated product to accommodate both antenna and solar array deployment, reducing the number of assembly and disassembly adjustments required. The deployment fixture system should unload the antenna frame and solar array substrate separately based on their weight, with the unloading force exceeding the center of mass of the substrate. If necessary, a ground-based unloading force monitoring system should be used to monitor the unloading process.

[0093] Remote sensing satellites are equipped with large components such as a large-area phased array radar antenna, a relay data transmission antenna, and a solar array. The satellite structure is a rectangular, integrated truss structure made of high-strength carbon fiber, serving as the satellite's primary load-bearing framework. The radar antenna consists of three sub-panels arranged in a "U" shape, pressed against the three outer sides of the satellite's truss structure. The relay data transmission antenna is a one-dimensional, oscillating phased array antenna, fixed to the cross-joint of the satellite's truss members. The solar array consists of three stacked baseplates, tucked away on the other side of the satellite's truss structure.

[0094] Through design analysis, integrated aluminum alloy metal embedded parts were installed in the four end joints at the top of the satellite's integrated truss structure. Each joint embedded part has two M6 threaded holes with embedded wire screws to improve the wear resistance of the mounting fixture. A 2mm aluminum alloy scraper was attached to each of the four end joints at the top. This combined processing ensures that the mounting surface accuracy of the four mounting points can reach better than 0.2mm after the integrated truss structure is assembled.

[0095] The four end joints at the base of the satellite's integrated truss structure are designed as aluminum alloy metal joints, providing the connection surface and interface with the launch and separation mechanism. Through combined processing, the flatness of the four aluminum alloy metal joints at the base of the satellite truss structure is guaranteed to be better than 0.2mm. With appropriate protection, these mounting interfaces can normally be used as connectors for the satellite parking vehicle.

[0096] For the three sub-arrays of the radar antenna, the neutron array is rigidly connected to the satellite's integrated truss structure. Only the sub-arrays on either side need to be unfolded 90 degrees and then assembled with the neutron array to form a complete antenna array. During the design process, two threaded holes for tooling points, spaced 900mm apart, were designed on the top of the antenna frames of the two sub-arrays that need to be unfolded. These holes are used to connect the antenna sub-array frames to the unfolding tooling system.

[0097] For the relay data transmission antenna, its antenna array surface needs to achieve one-dimensional ±45° swing. Therefore, during the design, an installation point hole is provided on each side of the antenna array surface for connecting the antenna array surface with the deployment tooling system.

[0098] The three solar array substrates are fixedly connected to the satellite's integrated truss structure. The other two substrates are stacked on top of the center plate, compressed, and then unlocked. Each substrate unfolds 180 degrees to form a complete solar array with the center plate. During the design process, two threaded holes, 700mm apart, were designed on the top of each of the two unfolded substrates to connect the array substrates to the unfolding fixture system.

[0099] Based on the interface positions of the tooling installation points, radar antenna subarray frame hanging points, relay data transmission antenna array hanging points and solar cell array substrate hanging points provided by the above-mentioned satellite integrated truss structure, as well as the satellite configuration layout space, an integrated deployment tooling system is designed. It has an irregular rectangular shape and is entirely welded with high-strength aluminum alloy hollow rods. A rocker mechanism is designed above a single antenna frame and a single solar cell array substrate respectively. The rotation axis of the rocker mechanism is in a straight line with the rotation axis of the hinge mechanism of the antenna frame and the rotation axis of the hinge mechanism of the solar cell array substrate respectively. A pulley and a constant force spring are designed on each rocker, and a buffer vibration damping pad is designed at each deployed and locked position. The deployment tooling system can be fixed to the top of the satellite structure, and the top of the satellite structure is used as the installation support. The constant force springs on each rocker mechanism are connected to the antenna frame and the solar cell array substrate. By adjusting the position and counterweight of the constant force spring, it is ensured that the spring unloading force passes through its center of mass, thereby achieving the deployment of the radar antenna, relay data transmission antenna and solar cell array in a satellite posture. When the antenna and solar cell array are deployed and locked in place, the impact of the deployment process is mitigated by the buffer vibration reduction pad.

[0100] A simulation analysis was carried out on the combination of the deployment tooling system and the satellite model. The analysis results show that the weight of the deployment tooling system causes a micro-deformation of the satellite truss structure of only 0.003mm; the installation of the deployment tooling system to the satellite structure and the deployment path trajectory of the major components were analyzed, and no interference was found; to address the impact of deployment impact, a buffer device was added to the gap when the rotation axis of the deployment tooling system is in place, reducing the impact caused by the rapid deployment process of large components; at the same time, counterweight protection measures were added at appropriate positions on the satellite parking vehicle, so that the changes in the center of mass of the antenna and solar cell array during the deployment process are always within the bearing range of the fixed point of the parking vehicle, avoiding the risk of the satellite attitude overturning during the deployment process.

[0101] When conducting antenna and solar array deployment tests, the deployment fixture system's pendulum horizontality and constant-force spring torque calibration are first completed on the ground. The system is then slowly hoisted and installed atop the satellite structure, which is already parked in a vehicle. The satellite's attitude is adjusted, and the deployment fixture system is connected to the antenna frame and solar array substrate suspension points. Ground-based monitoring equipment monitors the constant-force spring's unloading value, adjusting it to match the product weight, completing pre-deployment test preparations. Next, the antenna frame and solar array's compression points are unlocked and released, and the antenna and solar array are smoothly deployed and locked by the hinge mechanism. Deployment testing of all major components is completed quickly and efficiently within a single day.

[0102] If the satellite test site needs to be moved, loosen the connection between the deployment tooling system and the antenna and solar array hanging points, and fix them separately. Then the deployment tooling system can be fixed on the satellite structure, and the test site can be transferred together with the satellite transfer vehicle. There is no need to frequently disassemble and assemble the deployment tooling system, which greatly reduces the trouble of disassembling and assembling the tooling and saves the main line development time of the entire satellite.

[0103] Through the deployment method of the above invention, the satellite structure is innovatively used as the fixing point of the deployment tooling system, reducing the need for expensive ground equipment such as marble platforms and air-floating components, and achieving the deployment of large components such as antennas and solar arrays within one day, solving the urgent need for rapid batch development of satellites in terms of reducing development cycles and development costs.

[0104] The present invention creates a new design method for the subsequent short-cycle rapid development of satellite antennas and solar cell arrays for the whole-satellite test verification in my country. Especially for satellites developed in a short cycle and rapid mass production, this design method will become the first choice for satellite assembly designers, and the invention will be widely used in this field.

[0105] Those skilled in the art may understand this embodiment as a more specific description of Embodiment 1 and Embodiment 2.

[0106] Those skilled in the art will appreciate that, in addition to implementing the system and its various devices, modules, and units provided by the present invention in purely computer-readable program code, it is entirely possible to implement the same functions of the system and its various devices, modules, and units provided by the present invention in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers, and embedded microcontrollers by logically programming the method steps. Therefore, the system and its various devices, modules, and units provided by the present invention can be considered a hardware component, and the devices, modules, and units included therein for implementing various functions can also be considered as structures within the hardware component; the devices, modules, and units for implementing various functions can also be considered as both software modules implementing the method and structures within the hardware component.

[0107] The above describes specific embodiments of the present invention. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art may make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. The embodiments of this application and the features in the embodiments may be combined with each other in any manner unless there is a conflict.

Claims

1. A method for deploying a self-supporting integrated antenna and solar array for a satellite structure, characterized in that: The method comprises the following steps: Step S1: Designing the tooling installation interface of the satellite structure; the installation points of the satellite body structure provided to the deployment tooling system are located at the four end areas at the top of the body structure, which can be fitted into a plane; Step S2: Designing the fixed interface of the whole satellite parking tooling of the satellite structure; Step S3: aligning the interface planes of the tooling fixing points of the antenna frame and the solar cell array substrate to be parallel to the satellite structure installation interface plane; Step S4: Designing an integrated deployment tooling system for satellite structure installation based on the configuration position and layout space between the tooling installation point interface at the top of the satellite, the single-unit layout at the top of the satellite, and the tooling fixing and hanging point interfaces of the antenna frame and the solar cell array substrate; Step S5: Perform an assembly check on the three-dimensional model of the deployment tooling system and the three-dimensional model of the satellite body to check that there is no interference with external products along the entire deployment movement path of the antenna and solar array; Step S6: Conduct micro-deformation simulation analysis of the entire satellite structure and assemble the satellite model and the deployment tooling system into a complete unit; Step S7: Conducting an impact simulation analysis of the entire satellite structure and the deployment fixture system assembly. This simulation analysis requires that after the antenna and solar array are connected to the deployment fixture system and the assembly is deployed and locked, the impact caused by the impact does not exceed the strength of the satellite's onboard products and the deployment fixture system, ensuring that the onboard products have a safety margin and are not damaged. Step S8: Designing a satellite parking vehicle based on the deployment impact simulation results; Step S9: During deployment, the satellite structure is fixed on the parking vehicle, and the deployment tooling system is directly fixed on the top of the satellite structure. The deployment tooling system is interconnected with the tooling lifting points of the antenna and solar array; after the satellite attitude adjustment meets the requirements, the pressing points of the antenna and solar array are unlocked to complete the deployment and locking of the antenna and solar array.

2. The method for deploying a self-supporting integrated antenna and solar array for a satellite structure according to claim 1, characterized in that: The satellite body structure described in step S1 is provided to the installation point of the unfolding tooling system using the joint position of the star body structure, with an integrated embedded part embedded inside, a wire screw sleeve installed in the threaded hole of the installation point, and an aluminum alloy scraper attached to the installation hole area for combined processing.

3. The method for deploying a self-supporting integrated antenna and solar array for a satellite structure according to claim 1, characterized in that: The fixed interface of the whole satellite parking tooling of the satellite structure in step S2 adopts the load-bearing joint position of the satellite structure, which is the satellite-rocket separation interface of the satellite.

4. The method for deploying a self-supporting integrated antenna and solar array for a satellite structure according to claim 1, wherein: The deployment tooling system in step S4 is made of high-rigidity, lightweight materials. The rotation axes of the deployment rocker mechanisms are collinear and parallel to the rotation axes of the antenna hinge mechanism and the solar cell array hinge mechanism, and each rotation axis remains perpendicular to the ground.

5. The method for deploying a self-supporting integrated antenna and solar array for a satellite structure according to claim 1, characterized in that: The onboard product in step S7 has a safety margin when affected by impact, the safety margin is not less than 2, and the deployment tooling system is designed with a buffer device after being deployed into position and locked; Before being installed on the satellite structure, the deployment tooling system performs a self-check on the ground to complete the horizontal calibration of the unloading pendulum and the unloading force calibration of the constant force spring; The unfolding tooling system is designed as an integrated product; the unfolding tooling system unloads the single antenna frame and the single solar cell array substrate according to their weight, and the unloading force exceeds the center of mass of the single panel.

6. A satellite structure self-supporting integrated antenna and solar array deployment system, characterized in that: The system includes the following modules: Module M1: Design the tooling installation interface of the satellite structure; the installation points of the satellite structure for the deployment tooling system are located at the four end areas at the top of the satellite structure, which can be fitted into a plane; Module M2: Design the fixed interface of the satellite structure and the whole satellite parking tooling; Module M3: Align the interface plane of the tooling fixing points of the antenna frame and the solar cell array substrate with the satellite structure installation interface plane; Module M4: Design an integrated deployment tooling system for satellite structure installation based on the configuration position and layout space between the tooling installation point interface at the top of the satellite, the single-unit layout at the top of the satellite, and the tooling fixing and hanging point interfaces of the antenna frame and solar cell array substrate; Module M5: Perform assembly inspection on the 3D model of the deployment tooling system and the 3D model of the satellite body to check that there is no interference with external products along the entire deployment path of the antenna and solar array. Module M6: Conduct micro-deformation simulation analysis of the entire satellite structure and assemble the satellite model and deployment tooling system into a complete unit; Module M7: Conduct impact simulation analysis of the entire satellite structure and deployment fixture system assembly. This simulation analysis requires that after the antenna and solar array are connected to the deployment fixture system and the assembly is deployed and locked, the impact caused by the impact does not exceed the strength of the satellite onboard products and the deployment fixture, and the onboard products have a safety margin and are not damaged. Module M8: Design a satellite parking vehicle based on the deployment impact simulation results; Module M9: When deployed, the satellite structure is fixed on the parking vehicle, and the deployment tooling system is directly fixed to the top of the satellite structure. The deployment tooling system is interconnected with the tooling lifting points of the antenna and solar array; after the satellite attitude adjustment meets the requirements, the pressing points of the antenna and solar array are unlocked to complete the deployment and locking of the antenna and solar array.

7. The satellite structure self-supporting integrated antenna and solar array deployment system according to claim 6, characterized in that: The satellite body structure described in the module M1 provides the installation point of the unfolding tooling system with the joint position of the star body structure, embedded integrated embedded parts, wire screw sleeves are installed in the threaded holes of the installation points, and aluminum alloy scrapers are pasted in the installation hole area for combined processing.

8. The satellite structure self-supporting integrated antenna and solar array deployment system according to claim 6, characterized in that: The fixed interface of the whole satellite parking tooling of the satellite structure in the module M2 adopts the load-bearing joint position of the satellite structure, which is the satellite-rocket separation interface.

9. The satellite structure self-supporting integrated antenna and solar array deployment system according to claim 6, characterized in that: The deployment fixture system in the module M4 is made of high-rigidity, lightweight materials. The rotation axes of each deployment rocker mechanism are collinear and parallel to the rotation axes of the antenna hinge mechanism and the solar cell array hinge mechanism, and each rotation axis remains perpendicular to the ground.

10. The satellite structure self-supporting integrated antenna and solar array deployment system according to claim 6, characterized in that: The onboard products in the module M7 have a safety margin when affected by impact, the safety margin is not less than 2, and the deployment tooling system is designed with a buffer device after deployment and locking; Before being installed on the satellite structure, the deployment tooling system performs a self-check on the ground to complete the horizontal calibration of the unloading pendulum and the unloading force calibration of the constant force spring; The unfolding tooling system is designed as an integrated product; the unfolding tooling system unloads the single antenna frame and the single solar cell array substrate according to their weight, and the unloading force exceeds the center of mass of the single panel.

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