Overall configuration method and application of space-based rotary launching platform

Abstract

The invention provides an overall configuration method and application of a space-based rotary launching platform. The model-based system engineering method comprises the following steps of: establishing a demand model, a function model and an architecture model of the platform; a parameterized modeling step: based on the architecture model, constructing a digital model of each subsystem of the platform by using parameterized design software; a dynamic simulation analysis step: carrying out dynamic simulation on the constructed digital model, and analyzing the influence of the load launching process on the platform and the motion of the load; and a scheme iterative optimization step: optimizing the platform design scheme based on the dynamic simulation analysis result. According to the method, disturbance suppression breakthrough innovation is achieved, the launching efficiency is greatly improved, and the orbit precision is effectively guaranteed.

Description

Technical Field

[0001] This invention relates to the field of spacecraft design technology, specifically to a model-based systems engineering and parametric modeling method for the overall configuration of a space-based rotating launch platform. Background Technology

[0002] As human space exploration deepens, the limitations of traditional space launch methods are becoming increasingly apparent. Current mainstream launch technologies can be categorized into four types based on the launch environment: First, there's land-based launch: while the technology is mature, it suffers from poor mobility and environmental pollution. Reusable technologies (like SpaceX's Falcon 9) reduce costs through rocket recovery, but they haven't fundamentally solved the physical limitations of land-based launches. Sea-based launch: While improving mobility, it is costly and has a long preparation time. The system is highly complex, requiring specialized vessels and maritime stabilization technology; its response speed is slow, with launch preparation cycles lasting several weeks; it lacks stealth, as large platforms are easily tracked by satellites; and it is highly dependent on climate, being severely constrained by marine weather conditions.

[0003] Air-based launch: Limited by the capacity and safety of the launch vehicle. Weak payload capacity: Limited by the launch vehicle's carrying capacity (typically ≤5 tons), high safety risks: In-flight separation failure rate is 30% higher than ground launch; the in-flight disintegration of Virgin Spaceship 2 is a prime example of the risks and challenges of air-based launch. Low orbital accuracy: Initial attitude control error reaches ±1.5°. Poor cost-effectiveness: Launch vehicle modification costs exceed $200 million per aircraft.

[0004] Space-based launch is theoretically the best option, but current technologies have insufficient mechanical / electromagnetic catapult thrust; compressed air catapults have difficulty replenishing gas; and gas-fired catapults are not environmentally friendly and are subject to limitations.

[0005] SpinLaunch, as an emerging ground-based rotary launch solution, faces several limitations due to its ground-based design. Atmospheric dissipation: 70% of kinetic energy is lost to air friction. Structural strength bottleneck: centrifugal acceleration >10,000g can damage the payload. Cost per launch: still $500,000 (including vacuum chamber maintenance). Inherent limitation: unsuitable for use in the space environment.

[0006] In summary, the existing launch platforms have the following unresolved issues: 1. Low energy efficiency: Chemical rocket propulsion efficiency <35% 2. Insufficient response speed: minimum launch preparation time > 12 hours 3. Poor environmental adaptability: Constrained by atmospheric / gravity / oceanic conditions. 4. Lack of on-orbit capabilities: No mature space launch platform. 5. Unsustainable cost: Low Earth orbit launch cost > $5,000 / kg There is an urgent need to develop a new type of space launch technology to overcome the limitations of the Earth's environment and achieve efficient, flexible, and low-cost space-based deployment capabilities.

[0007] Traditional design methods cannot efficiently handle the complexity of space-based rotating launch platforms, including multi-system integration, dynamic disturbance suppression, and rapid iterative optimization. Summary of the Invention

[0008] According to one aspect of this application, the present invention aims to provide a systematic and digital overall configuration method for a space-based rotating launch platform, addressing these challenges. The present invention provides an overall configuration method for a space-based rotating launch platform, comprising: Model-based systems engineering steps: Establishing a requirements model, functional model, and architecture model for the platform; Parametric modeling steps: Based on the architecture model, construct digital models of each subsystem of the platform using parametric design software; Dynamic simulation analysis steps: Perform dynamic simulation on the constructed digital model to analyze the impact of the payload launch process on the platform and the payload's own motion; Scheme Iterative Optimization Steps: Based on the dynamic simulation analysis results, the platform design scheme is optimized.

[0009] Optionally, in the model-based systems engineering steps: The requirement model is built on three typical application scenarios: maintenance proximity, rapid network replenishment, and regional coverage, and clarifies the core target parameters of the platform. The functional model describes the platform's functional links through task use case diagrams; The architecture model decomposes the platform into nine subsystems: structural support, energy, centrifugal launch, integrated electronics, navigation, detection, thermal control, communication and measurement and control, and rotation drive and control.

[0010] Optionally, in the parametric modeling step: Parametric modeling is performed using modeling software (such as SolidWorks), which controls the geometry of the model through global variables and equations; Parametric design was carried out for the platform body, the swing arm system, the energy system, the release mechanism and other subsystems, and mass and power constraints were established.

[0011] Optionally, the dynamic simulation analysis steps include: Two simulation examples are set up: sequential load launch and layered load launch, to simulate the motion tracking path, linear motion and angular motion of the platform body and loads; The impact of load launch on platform disturbance is analyzed, and the adaptive counterweight and release timing are optimized.

[0012] Optionally, the iterative optimization steps of the scheme include: Based on the results of dynamic simulation, an adaptive counterweight is added inside the first-stage rotating arm to counteract the disturbance. The release time difference between the front and rear attachment points of the dual attachment point release mechanism is optimized to be 0.1~10 milliseconds to eliminate load spin; The overall design scheme was iteratively optimized through interference verification and granularity verification. Preferably, the release time difference between the front and rear attachment points of the optimized dual attachment point release mechanism is 1.0~1.2 milliseconds; Preferably, the release time difference between the front and rear attachment points of the optimized dual attachment point release mechanism is 1.1115 milliseconds.

[0013] Optionally, the method further includes a digital model building step: Integrate the parameterized models of each subsystem to construct the platform's initial digital model.

[0014] Optionally, ensure that the model can be accommodated by a fairing with a diameter not exceeding 5.2 meters, a length not exceeding 20.5 meters, and an envelope diameter not exceeding 4.5 meters. For example, the fairing of the Long March 5B rocket.

[0015] Optionally, it is characterized in that, The iterative optimization steps of the scheme include: An adaptive counterweight mechanism is added inside the first-stage rotary arm to counteract load release disturbances; and / or Optimize the release time difference between the front and rear attachment points of the dual attachment point release mechanism to eliminate load spin.

[0016] According to another aspect of this application, a non-transitory computer-readable medium storing a computer program is provided, which, when executed by a processor, implements the overall configuration method of a space-based rotating launch platform as described in any of the preceding claims. According to another aspect of this application, a method for overall configuration of a space-based rotating launch platform using any of the above-described methods is provided, and a method for launching payloads using the configured space-based rotating launch platform is provided, characterized in that it includes: Deploy the platform on the designated track; Unfold the spiral arm; The rotary drive mechanism drives the rotary arm to rotate to a predetermined angular velocity; The load is released via the load release mechanism; Among them, when releasing the load, the adaptive counterweight mechanism is used to dynamically balance the disturbance, and / or the dual-hanging-point release mechanism is used to release the hanging point with a preset time difference to suppress the spin.

[0017] The beneficial effects that this application can produce include: 1. Efficiency Improvement: Through MBSE and parametric modeling, the design cycle is shortened by 40% and the model update efficiency is improved by 70%.

[0018]

[0019] 2. Performance optimization: Dynamic simulation accurately predicts disturbances, and after optimization, the platform linear displacement disturbance is reduced by 52%, and load spin is eliminated.

[0020] Track accuracy is guaranteed: the launch angle error is ≤0.1° and the attitude recovery time is shortened to 8 seconds.

[0021] 3. Cost reduction: Reduced need for physical prototypes, resulting in a 30% reduction in development costs.

[0022] 4. High flexibility: Supports rapid iteration in multiple scenarios, such as maintenance of proximity, rapid network replenishment, and regional coverage. 5. Full lifecycle optimization: MBSE design cycle shortened by 40%; The efficiency of parameterized model updates is improved by 70%. Attached Figure Description

[0023] Figure 1 Model usage and corresponding analysis tools at each design stage Figure 2 Space-based rotating launch platform mission requirements diagram Figure 3 Space-based rotating launch platform mission use case diagram Figure 4 Space-based rotating launch platform subsystem architecture block diagram Figure 5 Platform main structure diagram Figure 6 Rotary arm connector configuration diagram Figure 7 Flip open the structural configuration diagram Figure 8 Docking structure configuration diagram Figure 9 First-stage spiral arm configuration diagram Figure 10 Second-stage spiral arm configuration diagram Figure 11 Solar panel configuration diagram Figure 12 Platform folding diagram (umbrella shape) Figure 13 Platform expansion (cross-shaped) Figure 14 Motion tracking path Figure 15 Rotary arm and counterweight Figure 16Typical application scenarios Detailed Implementation The present application is described in detail below with reference to the embodiments, but the present application is not limited to these embodiments.

[0024] The basic process of space-based rotating launch is as follows: The rotating launch platform is deployed in a space orbit. The platform has a rotating arm structure. Based on the centrifugal acceleration principle and the principle of electro-kinetic energy conversion, the payload rotates with the rotating arm inside the arm, and the launch speed is accumulated by increasing the angular velocity.

[0025] To design the overall scheme of the space-based rotating launch platform, three typical application scenarios for the platform were first constructed—maintenance proximity, rapid network replenishment, and regional coverage—and the overall technical specifications of the space-based rotating launch platform were determined based on mission requirements. Then, under specific application scenarios, the core technical parameter targets of the platform were determined, and other sub-parameters were determined using these parameter targets as a guide.

[0026] Space-based rotating launch platform A space-based rotating launch platform for performing launch missions, in conjunction with the method of the present invention, includes: Platform entity; At least one deployable rotary arm is mounted on the platform body to accommodate and rotate the acceleration load; A rotary drive mechanism, connected to the rotary arm, is used to drive the rotary arm to rotate; A load release mechanism is provided at the end of the rotating arm to release the load at a predetermined speed, so that the load can obtain tangential velocity and enter the predetermined track. An attitude control system for stabilizing and adjusting the attitude of the platform, the attitude control system including at least an attitude adjustment flywheel; An energy system for providing power to the platform, the energy system including at least solar panels; The platform is configured to operate in space orbit and perform payload launch missions.

[0027] Optionally, the rotating arm includes a primary rotating arm and a secondary rotating arm, the primary rotating arm being connected to the platform body, the secondary rotating arm being connected to the primary rotating arm, and the load being accommodated within the secondary rotating arm.

[0028] Optionally, the primary rotating arm is provided with an adaptive counterweight mechanism; The adaptive counterweight mechanism is configured to move along the primary rotating arm when the load is released, so as to dynamically balance the platform disturbance caused by the load release.

[0029] Optionally, the load release mechanism includes a dual-hook-point mounting device with two hook points at the front and rear. The dual-attachment-point mounting device is configured to release the front and rear attachment points sequentially with a preset time difference to suppress the spin of the load after release.

[0030] Optionally, the preset time difference is determined based on the rotational speed, radius, and distance between the front and rear hanging points of the rotating arm, and is optimized to approximately 0.1 to 10 milliseconds.

[0031] Optionally, the rotating arm has a cross-shaped configuration when fully extended.

[0032] Optionally, the attitude control system further includes: a BeiDou receiver, a star sensor, an attitude-sensing gyroscope, and a Hall effect thruster.

[0033] Rotary launch process Rotary launch is an unconventional space launch technology based on centrifugal acceleration and kinetic energy conversion. It converts electrical energy into kinetic energy and accumulates velocity through centrifugal force. Its aim is to reduce the dependence of traditional rocket launches on chemical fuels and achieve a more economical and environmentally friendly way to enter space.

[0034] S1 Centrifugal acceleration process The core physical principle of rotary launch is to use centrifugal force to provide initial kinetic energy to the payload. On a space-based rotary launch platform, the payload is fixed to a rotating arm and rotated at high speed, causing the payload to accelerate along a circular motion path. According to the kinematic equations for rigid body rotation (2-1) and (2-2): (2-1) (2-2) in, For the tangential velocity of the load, For the centripetal acceleration of the load, Angular velocity of rotation Let be the radius of the spiral arm.

[0035] Once the payload reaches the predetermined tangential velocity, the spacecraft is released, and the centrifugal force is converted into the spacecraft's initial tangential velocity, making it easier for it to overcome Earth's gravity or enter the predetermined orbit.

[0036] S2 Electrical Energy to Kinetic Energy Conversion The physical essence of rotary launch is to efficiently convert electrical energy into kinetic energy. The electrical energy input to the rotary launch platform is converted into rotational kinetic energy through a motor, and the relationship is shown in formula (2-3).

[0037] (2-3) in As kinetic energy, Let be the moment of inertia of the rotating arm and the load. ω is the rotational angular velocity.

[0038] At the moment of release, the load detaches from the rotating arm, and its kinetic energy is converted into translational kinetic energy, causing the load to fly out along a tangential trajectory, thereby escaping Earth's gravity or entering a predetermined orbit.

[0039] Example 1: Model-Based Systems Engineering (MBSE) Steps Application scenario: For the "rapid network replenishment" scenario (constellation satellites fail and need to be replaced quickly).

[0040] Suppose that some satellites of a low-Earth orbit satellite internet constellation deployed in my country are damaged due to a strong particle stream impact, resulting in a complete loss of operational capability. There is an urgent need to quickly repair the network and restore global network coverage.

[0041] Prior to the mission, the initial positions and orbital altitudes of the satellite requiring network replenishment and the space-based rotating launch platform were known. It was assumed that there would be no interference from other satellites between the launch of the replenishment satellite and its location. The specific steps are the same as in Example 1. The overall structure and deployment of the platform are as follows: Figure 12 , 13 As shown.

[0042] step: like Figure 1 Steps: Build a three-layer model based on the SysML language: Requirements Model: Core target parameters (such as payload launch velocity v, launch recovery period T, and launch accuracy ε) are derived from typical application scenarios (maintaining proximity, rapid network replenishment, and regional coverage) and decomposed into functional and performance requirements. The requirements model is based on these requirements. Figure 2 express.

[0043] Functional model: for task use Figure 3 Describe the platform's functions, including launch, orbit change, and navigation, and clearly define the functional links and interaction relationships.

[0044] Architecture Model: The platform is decomposed into nine subsystems (structural support, energy, centrifugal launch, etc.), interfaces and constraints are defined, and architecture blocks are used to define these subsystems. Figure 4 express.

[0045] Specific implementation steps: Use MBSE tools (such as IBM Rhapsody) to build a requirements model: derive core parameters from the scenario (launch speed v=1.5km / s, recovery period T≤5 minutes).

[0046] Build a functional model: Define use cases such as "payload launch" and "orbital maneuver" and clarify the functional flow.

[0047] Architecture model: Decompose the subsystems, determine the power requirement of the energy system ≥20kW, and the mass constraint of the structural system ≤10 tons.

[0048] Result: The requirement model directly drives parametric modeling, ensuring that the design meets the scenario requirements.

[0049] Example 2: Parametric Modeling Steps Parametric design can be achieved using SolidWorks software through global variables and equations: Platform main body modeling: Define dimensional variables (such as length, width, and height), and associate parameters through equations to ensure that the model can be automatically updated. Figure 5 As shown.

[0050] Modeling of the swing arm system: The primary and secondary swing arms are designed parametrically, with variables including length, radius, and connection interfaces. Figure 8-9 As shown.

[0051] Other subsystems, including the energy system (solar panels) and release mechanism (dual attachment point device), are modeled using parametric methods.

[0052] Scenario: Design a rotary arm system and perform dynamic verification.

[0053] step: In SolidWorks, a parametric model is created: the length of the rotating arm is defined as a global variable (initial value 40m), and the acceleration curve is associated with the equation (Equation 2-4).

[0054] Exporting the model to simulation software: Setting up a sequential load launch example, simulating platform angular velocity disturbance ( Figure 4-8 ).

[0055] Analysis results: The peak disturbance value reached 50 deg / s, requiring optimization.

[0056] Iterative optimization: Modify the parameterized model, add an adaptive counterweight (mass 50kg), resimulate, and the disturbance is reduced to 20deg / s.

[0057] Results: Performance optimization can be achieved quickly through parametric tuning and simulation, reducing the need for physical testing.

[0058] Example 3. Dynamic Simulation Analysis Steps Dynamic analysis can be performed using simulation software such as ADAMS or MATLAB. The simulation examples include two modes: sequential load launch and layered launch, to simulate the motion characteristics of the platform body and the loads.

[0059] Analysis of disturbances: Different loads are tracked through curves such as motion tracking path, linear displacement, and angular velocity, for example... Figure 14 As shown, the impact of payload launch on the platform is evaluated. Other aspects are the same as in Example 2.

[0060] Example 4: Scheme Iterative Optimization Steps Optimization based on simulation results: Adaptive counterweight addition: A counterweight is added inside the first-stage rotating arm to dynamically balance the disturbances generated by the load ejection. Other aspects are the same as in Example 2.

[0061] Example 5: Full Platform Integration and Verification Scenario: Complete the digital model of the platform and verify its overall performance.

[0062] step: Integrate the parametric models of various subsystems: platform main body, boom, energy, etc., to construct a complete digital model. Figure 12 , 13 ).

[0063] Dynamics simulation: Running a layered launch example to verify the stability of the platform when launching simultaneously from the upper and lower rotor arms. Figure 13 (Displays no disturbance).

[0064] Scenario verification: Deploy the "regional coverage" scenario, simulate the launch of multiple satellites, and check interference and granularity. Figure 16 (Verification of no collisions).

[0065] Optimize release timing: Through simulation testing of different time differences, 1.1115ms was determined to be the optimal value.

[0066] Result: The platform design meets the needs of all scenarios and is ready to move into the physical manufacturing stage.

[0067] Example 6 Suppose that a Chinese Earth observation satellite deployed in low Earth orbit is damaged due to a collision with space debris, causing its observation function to fail and preventing it from providing normal Earth situational awareness services, it will need to be maintained in a timely manner.

[0068] Prior to the mission, the initial positions and orbital altitudes of the Earth observation satellite and the space-based rotating launch platform were known. It was assumed that there would be no interference from other satellites between the launch of the space-based rotating launch platform and the position of the Earth observation satellite. Figure 1-4 The overall method and steps are as follows, with the target parameters as follows: 1. Design target parameters based on typical application scenarios Based on the maintenance of near-typical application scenarios, this paper selects three core target parameters for space-based rotating launch platforms—payload launch velocity relative to the platform. Launch recovery cycle , launch accuracy .

[0069] Load relative to platform launch velocity It mainly characterizes the payload's orbital insertion capability. Based on flight time, platform initial position, and target orbital insertion trajectory, the payload's launch velocity relative to the platform can be obtained through algorithm simulation architecture for three typical application scenarios.

[0070] Launch recovery cycle The main characteristic is the platform's ability to continuously perform launch missions. The minimum launch recovery cycle can be determined based on the disturbance caused to the platform by the payload launch, obtained from dynamic simulation, and the current level of attitude adjustment technology.

[0071] Exit accuracy It mainly characterizes the orbital insertion accuracy of the load. The higher the launch accuracy, the less attitude adjustment the load needs during the orbital insertion process, and the higher the orbital insertion accuracy.

[0072] 2. Sub-parameter design based on target parameter guidance Based on the three core target parameters of the space-based rotating launch platform, the payload's launch velocity relative to the platform... Launch recovery cycle , launch accuracy This paper designs four sub-parameters for traction, including acceleration. angular acceleration Motor power flywheel moment of inertia .

[0073] Based on the load's relative launch velocity to the platform , launch accuracy Acceleration can be calculated angular acceleration The acceleration curve equation of the space-based rotating launch platform is shown in Equation (2-4), and the angular acceleration curve equation is shown in Equation (2-5). Both are in cubic polynomial form to ensure the smooth start and stop of the platform's rotating arm.

[0074] (2-4) (2-5) in The launch velocity of the load relative to the platform. The current time has been accelerated. Total acceleration time, for The corresponding acceleration at that time, for The corresponding angular acceleration at that time, Let be the radius of the spiral arm.

[0075] Motor selection can be made based on the acceleration curve equation and the angular acceleration curve equation, and the motor power can be further determined. .

[0076] The flywheel adjusts the platform's attitude by changing its own rotational angular momentum, utilizing the law of conservation of angular momentum. The flywheel's moment of inertia can be calculated based on the torque balance equation, attitude control equation, and the platform's angular momentum conservation equation. .

[0077] The attitude control equation describes the relationship between the platform and the flywheel angular acceleration when interference is ignored. The platform's attitude angular velocity can be directly adjusted by controlling the rate of change of the flywheel speed, as shown in formula (2-6).

[0078] (2-6) The torque equation describes the torque generated by the flywheel and the attitude dynamics of the platform, as shown in formulas (2-7, 2-8).

[0079] (2-7) (2-8) The equation for conservation of angular momentum describes the conservation of total angular momentum of the system (platform + flywheel + load) and the relationship between the change in flywheel speed and the change in platform angular velocity, as shown in formulas (2-9, 2-10, 2-11).

[0080] (2-9) (2-10) (2-11) in The moment of inertia of the flywheel. For flywheel torque, For the flywheel angular acceleration, For the flywheel angular acceleration, This represents the change in the flywheel's angular velocity. For the platform's rotational inertia, For the platform's angular velocity, For the platform's angular acceleration, For external disturbance torque, For the momentum of the outgoing load, For the mass of the launched payload, For the launch load velocity, This represents the change in the platform's angular momentum. Let be the radius of the spiral arm.

[0081] The six key units of the space-based rotating launch platform have the following specific configurations: Figure 5-13 As shown.

[0082] (a) Platform Entity The main platform, as the core component of the space-based rotating launch platform, forms the foundation of the entire platform. All other components must be designed and installed on this foundation. Key units directly connected to the main platform include the solar panels and the rotating arm connectors. The main platform has a rectangular shape with a hollow interior for housing components such as the onboard computer, gyroscopes, flywheels, and heat pipes. Space is reserved on the sides for the solar panels when folded. The top and bottom surfaces feature rotating shafts with built-in motors to control the rotation of the rotating arms.

[0083] (ii) Rotary arm connector The swivel arm connector in the platform functions as a connector between the main body and the swivel arm. The preliminary design of the swivel arm connector is a cuboid with a hollow interior to accommodate heat dissipation devices, control components, and other parts. The sides are equipped with a flip-up mechanism and a docking mechanism to control the unfolding of the swivel arm and its subsequent fixation to the swivel arm connector.

[0084] (III) Flip-opening mechanism and docking mechanism The flip-opening mechanism adopts a gear and rack configuration, which is simple in structure and stable and reliable in operation, ensuring the smooth deployment of the rotating arm in space.

[0085] The docking mechanism adopts a cone-shaped claw structure, which is widely used in missions such as space station docking and can tightly connect the rotor arm to the rotating shaft rotor arm connector.

[0086] (iv) First and second stage rotating arms Both the first and second stage rotating arms are rectangular. The first stage rotating arm has a smaller base area, primarily serving to increase the overall length of the rotating arm. Its hollow interior accommodates communication links, heat-conducting components, etc., and its sides house a flip-up and docking mechanism. After unfolding, one side connects to the rotating arm connector on the shaft, and the other side connects to the second stage rotating arm. The second stage rotating arm has a larger base area and a hollow interior for storing loads. It houses load racks and has a docking mechanism on its side. After unfolding, it connects to the first stage rotating arm. The specific configuration of the first stage rotating arm is as follows: Figure 9 As shown, the specific configuration of the second-stage spiral arm is as follows: Figure 10 As shown.

[0087] (v) Solar panels Referring to the basic configuration of the solar panels used on the Chinese space station, the solar panels adopt a flat-plate design. The modular design facilitates subsequent assembly and size updates. Hinges are designed at the front and rear of the panels for interconnection. Each panel consists of two mirror-symmetrical power generation units, as shown in the specific configuration below. Figure 11 As shown.

[0088] Example 7: Area Coverage Suppose a disaster or emergency occurs in a certain region of my country, and there is an urgent need to enhance satellite communication and Earth observation capabilities in that region within a certain timeframe to better assist in handling the disaster or emergency. This would involve launching multiple satellites to that region.

[0089] Before the mission, the number of satellites to be launched, the operational time period, the initial position and orbital altitude of the space-based rotating launch platform are known. It is assumed that there will be no interference from other satellites between the launch of the supplementary satellites and their arrival at the target position. The specific steps are the same as in Examples 1-4.

[0090] The above description is merely a few embodiments of this application and is not intended to limit this application in any way. Although this application discloses preferred embodiments as described above, it is not intended to limit this application. Any changes or modifications made by those skilled in the art without departing from the scope of the technical solution of this application using the disclosed technical content are equivalent to equivalent implementation cases and fall within the scope of the technical solution.

Claims

1. A general configuration method for a space-based rotating launch platform, characterized in that, include: Model-based systems engineering steps: Establishing a requirements model, functional model, and architecture model for the platform; Parametric modeling steps: Based on the architecture model, construct digital models of each subsystem of the platform using parametric design software; Dynamic simulation analysis steps: Perform dynamic simulation on the constructed digital model to analyze the impact of the payload launch process on the platform and the payload's own motion; Scheme Iterative Optimization Steps: Based on the dynamic simulation analysis results, the platform design scheme is optimized.

2. The method according to claim 1, characterized in that, In the model-based systems engineering steps: The requirement model is built on three typical application scenarios: maintenance proximity, rapid network replenishment, and regional coverage, and clarifies the core target parameters of the platform. The functional model describes the platform's functional links through task use case diagrams; The architecture model decomposes the platform into nine subsystems: structural support, energy, centrifugal launch, integrated electronics, navigation, detection, thermal control, communication and measurement and control, and rotation drive and control.

3. The method according to claim 1, characterized in that, In the parametric modeling step: Parametric modeling is performed using SolidWorks software, and the geometry of the model is controlled through global variables and equations. Parametric design was carried out for the platform body, the swing arm system, the energy system, the release mechanism and other subsystems, and mass and power constraints were established.

4. The method according to claim 1, characterized in that, The dynamic simulation analysis steps include: Two simulation examples are set up: sequential load launch and layered load launch, to simulate the motion tracking path, linear motion and angular motion of the platform body and loads; The impact of load launch on platform disturbance is analyzed, and the adaptive counterweight and release timing are optimized.

5. The method according to claim 1, characterized in that, The iterative optimization steps of the scheme include: Based on the results of dynamic simulation, an adaptive counterweight is added inside the first-stage rotating arm to counteract the disturbance. The release time difference between the front and rear attachment points of the dual attachment point release mechanism is optimized to be 0.1~10 milliseconds to eliminate load spin; The overall design scheme was iteratively optimized through interference verification and granularity verification. Preferably, the release time difference between the front and rear attachment points of the optimized dual attachment point release mechanism is 1.0~1.2 milliseconds; Preferably, the release time difference between the front and rear attachment points of the optimized dual attachment point release mechanism is 1.1115 milliseconds.

6. The method according to claim 1, characterized in that, The method also includes a digital model building step: Integrate the parameterized models of each subsystem to construct the platform's initial digital model.

7. The method according to claim 1, characterized in that, Ensure that the model can be contained in a fairing with a diameter not exceeding 5.2 meters, a length not exceeding 20.5 meters, and an envelope diameter not exceeding 4.5 meters.

8. The method according to claim 1, characterized in that, The iterative optimization steps of the scheme include: An adaptive counterweight mechanism is added inside the first-stage rotary arm to counteract load release disturbances; and / or Optimize the release time difference between the front and rear attachment points of the dual attachment point release mechanism to eliminate load spin.

9. A non-transitory computer-readable medium storing a computer program, which, when executed by a processor, implements the overall configuration method of a space-based rotating launch platform as described in any one of claims 1-8.

10. A method for launching a payload from a space-based rotating launch platform configured using the overall configuration method of any one of claims 1-8, characterized in that, include: Deploy the platform on the designated track; Unfold the spiral arm; The rotary drive mechanism drives the rotary arm to rotate to a predetermined angular velocity; The load is released via the load release mechanism; Among them, when releasing the load, the adaptive counterweight mechanism is used to dynamically balance the disturbance, and / or the dual-hanging-point release mechanism is used to release the hanging point with a preset time difference to suppress the spin.

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