Multi-mode switching system for full-life-cycle cluster-type aircraft formation

Abstract

The invention discloses a multi-mode switching system for a full-life-cycle cluster type aircraft formation. The multi-mode switching system comprises a ground test launch control system and an on-rocket cluster system, the ground test launch control system is used for controlling a ground flow by using the multi-mode system flow planning module and the task planning module; and the on-rocket cluster system is used for performing multi-mode control on the point location data cluster of the difference parameters by using an upper-layer instruction received by the central computer of the ground test launch control system. Switching among multiple modes of point location data clusters of difference parameters can be effectively achieved, the multi-mode conversion process of the aircraft is automatically monitored, and multi-mode system measurement and control are achieved.

Description

Technical Field

[0001] This invention belongs to the field of multi-modal switching technology for aircraft, and specifically relates to a multi-modal switching system for clustered aircraft formations throughout their entire life cycle. Background Technology

[0002] Aircraft are special products designed for long-term storage and single-launch use. Their testing and control during operation involves multiple modes. Effectively classifying these modes and seamlessly switching between them has long been a major challenge for research, development, production, and user departments. Due to their complex structure, high cost, and small production runs, and the immaturity of accelerated lifespan research methods, it is difficult to develop scientific and practical mode control strategies to achieve optimal health management during research and production. Lacking supporting data from actual storage environments and real-world aircraft testing, the current internationally accepted approach is to use continuous power-on, single-mode testing and control, which typically reduces the aircraft's lifespan.

[0003] Multimodal (multiple operating modes) aircraft development primarily aims to meet the mission requirements of the aircraft's equipment systems by sacrificing some performance of the aircraft system platform to achieve the development goals of low loss and cost in multimodal management. However, the reduced performance does not affect the normal operation of the entire aircraft system because, as an aircraft system under development, each design mode is not required for long-term use and is generally kept on standby. When the aircraft system needs to enter a certain mode or simulation state, the multimodal autonomous system can quickly start from the low-loss mode and enter the normal operating mode, ensuring the normal operation of the aircraft system. However, during the process of the multimodal autonomous system quickly starting from the low-loss mode and entering the normal operating mode, a degradation trend may occur. Summary of the Invention

[0004] This invention overcomes one of the shortcomings of the prior art and provides a multi-modal switching system for clustered aircraft formations throughout their entire life cycle. It can effectively realize the switching between multi-modal modes of point parameters with different parameters in the cluster, as well as automatically monitor the multi-modal conversion process of the aircraft, and realize multi-mode system measurement and control.

[0005] According to one aspect of this disclosure, a multi-modal switching system for clustered aircraft formations throughout their entire lifecycle is proposed, the system comprising: a ground-based telemetry, tracking, and command system and an onboard clustering system;

[0006] The ground-based telemetry, tracking, and command system is used to control ground processes using the multi-mode system process planning module and the mission planning module.

[0007] The onboard cluster system is used to perform multi-mode control of the point data cluster of the differential parameters using upper-level instructions received by the central computer of the ground-based launch and control system.

[0008] In one possible implementation, the multi-mode system process planning module includes: a measurement and control processing unit, a power supply system, a processor, and a front-end health system;

[0009] The task planning module includes a cluster emergency response device and a central computer.

[0010] In one possible implementation, the multi-mode control of the cluster of point parameters of the differential parameters using upper-level instructions received by the central computer of the ground-based telemetry and control system includes:

[0011] When the central computer of the ground-based telemetry, launch and control system receives an upper-level instruction to control the aircraft to start working in emergency launch mode, the fire support module and the calculation planning and scheduling module of the ground-based telemetry, launch and control system are in working state.

[0012] When the central computer of the ground-based telemetry, tracking, and command system receives an upper-level instruction to control the aircraft to start operating in a non-emergency launch mode, the field planning module and the point parameter control module for the differential parameters of the ground-based telemetry, tracking, and command system are in operation.

[0013] In one possible implementation, the telemetry and control processing unit is used to send the received preset control commands for the operation of the aircraft to the aircraft, and control the aircraft to execute the task requirements corresponding to the control commands;

[0014] The power system is used to provide multi-mode power to the multi-mode ground-based telemetry, tracking, and command system of a cluster of aircraft throughout its entire life cycle.

[0015] The processor is used to execute corresponding control decisions based on the received upper-level switching instructions from the ground-based telemetry, tracking, and command system.

[0016] The front-end health system is used to process the received aircraft system monitoring data before the aircraft takes off;

[0017] The central computer is used to receive upper-level switching instructions sent by the aircraft;

[0018] The cluster emergency processing device is used to process redundant data from aircraft in emergency situations.

[0019] In one possible implementation, the fire support module is used to switch the aircraft configuration parameters according to the upper-level instructions.

[0020] The computational planning and scheduling module is used to control the motion attitude and flight drop point of the payload carried by the aircraft that has been switched to valid configuration parameters;

[0021] The on-site planning module is used to determine whether the current launch response time, hardware configuration status and software health status of the aircraft are within the preset conditions for aircraft launch preparation based on the heterogeneous wave parameters.

[0022] The point parameter control module for the differential parameters is used to switch the configuration strategy of the differential wave parameters based on the upper-level command when the launch preparation of the aircraft is within the preset condition range.

[0023] In one possible implementation, the multi-mode system process planning module and task planning module adopt a two-level deployment mode.

[0024] In one possible implementation, the aircraft configuration parameters include four strategy parameters: penetration, jamming, reconnaissance, and decoy; the differential wave parameters include five strategy parameters: trajectory control, information support, point of contact, target, and destruction.

[0025] In one possible implementation, each aircraft in the swarm aircraft formation system adopts a three-stage cabin structure, which includes a primary boost propulsion cabin, a secondary maneuver control cabin, and a tertiary payload gliding target control cabin.

[0026] In one possible implementation, the first-stage booster cabin is used for active-phase high-thrust flight control and recovery control of the first-stage booster cabin after the aircraft takes off.

[0027] The secondary maneuver control cabin and the tertiary payload gliding target control cabin are both used for flight control of the aircraft's level flight layer and for controlling the payload to enter the preset orbit.

[0028] In one possible implementation, each of the three-level cabins includes an actuator, an integrated machine, and an inertial navigation system;

[0029] The actuator of the first-stage booster cabin is set as the core actuator, the integrated machine of the third-stage payload gliding target control cabin is set as an integrated machine, and the inertial group of the third-stage payload gliding target control cabin is set as the main inertial group.

[0030] This disclosure discloses a multi-modal switching system for clustered aircraft formations throughout their entire lifecycle, comprising: a ground-based telemetry, launch, and control system and an onboard clustering system; the ground-based telemetry, launch, and control system is used to control ground processes using the multi-mode system process planning module and mission planning module; the onboard clustering system is used to perform multi-mode control of the point parameter clusters with different parameters using upper-level instructions received by the central computer of the ground-based telemetry, launch, and control system. This system effectively enables switching between multi-mode modes of the point parameter clusters with different parameters, and automatically monitors the multi-mode conversion process of the aircraft, thus achieving multi-mode system telemetry and control. Attached Figure Description

[0031] The accompanying drawings are used to provide a further understanding of the technical solutions of this application or the prior art, and constitute a part of the specification. The drawings illustrating embodiments of this application, together with the embodiments of this application, are used to explain the technical solutions of this application, but do not constitute a limitation on the technical solutions of this application.

[0032] Figure 1 A schematic block diagram of a multi-mode switching system for a cluster of aircraft throughout its entire life cycle, according to an embodiment of the present disclosure, is shown.

[0033] Figure 2 A schematic diagram of the point parameter cluster multi-mode control principle according to another embodiment of the present disclosure is shown;

[0034] Figure 3 A schematic diagram of a three-stage cabin structure of an aircraft according to an embodiment of the present disclosure is shown. Detailed Implementation

[0035] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings and examples, so that the process of how the present invention uses technical means to solve technical problems and achieve corresponding technical effects can be fully understood and implemented accordingly. The various features in the examples and embodiments of this application can be combined with each other without conflict, and the resulting technical solutions are all within the protection scope of the present invention.

[0036] Furthermore, the steps illustrated in the flowcharts of the accompanying drawings can be executed in a computer, such as a set of computer-executable instructions. Also, although a logical order is shown in the flowcharts, in some cases the steps shown or described may be performed in a different order than that presented here.

[0037] Figure 1 A block diagram illustrating the principle of a multi-mode switching system for a cluster of aircraft throughout its entire lifecycle, according to an embodiment of this disclosure, is shown. Figure 1 As shown, the method may include: a ground-based launch and control system and an onboard cluster system.

[0038] The ground-based telemetry, tracking, and command (TT&C) system utilizes the multi-mode system process planning module and mission planning module to control ground processes. These modules employ a two-tier deployment model, enabling multiple aircraft to perform different missions, facilitating hierarchical and segmented flight separation, and multi-mode control during startup. The multi-mode system process planning module includes a TT&C processing unit, a power system, a processor, and a front-end health system. The mission planning module includes a cluster emergency response device and a central computer. The mission planning module categorizes and manages multiple aircraft, delegating mission requirements from each aircraft to the processor of the ground-based TT&C system for execution.

[0039] The telemetry, tracking, and command (TT&C) processing unit is used to send the received preset control commands for the aircraft to the aircraft, control the aircraft to execute the task requirements corresponding to the control commands, and perform multi-threaded online scheduling of the ground-based TT&C system. For example, compared to the fire control box, the TT&C processing unit adds complex ground-based TT&C system operation functions and supports multi-threaded online scheduling capabilities. The power system, compared to the small power supply in emergency launch mode, can achieve high-power, variable-frequency, and high-voltage power output, supporting the testing and control requirements of the aircraft's core structural hot-backup components.

[0040] The power system provides multi-mode power to the multi-aircraft, multi-mode cluster ground-based telemetry, tracking, and command (TT&C) system throughout its entire lifecycle. For example, the power system supplies power voltage to the TT&C processing unit, command and control system, and processor. The command and control system assists the ground-based TT&C system in making control decisions, ensuring the robustness and stability of non-aircraft test and control operations.

[0041] The processor is used to execute corresponding control decisions based on the received upper-level switching instructions from the ground-based telemetry, tracking, and command system, and to improve the processing of system data acquired before the aircraft takes off.

[0042] The front-end health system is used to process the aircraft system monitoring data received before the aircraft takes off. By using the system monitoring data before the aircraft takes off, the lifespan and faults of the aircraft components can be monitored in a timely manner to ensure the safety of the aircraft.

[0043] Emergency processing units are used to handle redundant data from the aircraft in emergency situations. These units, including the command and control system, processors, emergency processing units, and mains power, ensure the redundancy, fault tolerance, and robustness of the ground-based telemetry, launch, and control system, allowing it to operate in full hot-standby mode.

[0044] The central computer receives upper-level switching commands and preset control commands for aircraft operation from the aircraft, such as the human-in-the-loop interactive information platform. It receives preset commands from higher levels and intervenes in the test and control process as needed. Through the central computer, the preset control commands for aircraft operation can be transmitted to the near-end telemetry and control processing unit and the aircraft, thereby controlling the near-end of the ground telemetry, launch, and control system and the aircraft to switch to the corresponding operating mode.

[0045] In addition to the hardware circuitry for energy management, the ground-based telemetry, tracking, and command system also includes analog circuit designs for various hardware aircraft systems, such as a core processor, peripheral circuitry, memory, communication interface, signal conditioning circuitry, and analog-to-digital conversion circuitry. These will not be discussed in detail here.

[0046] The onboard cluster system is used to perform multi-mode control of the point data cluster of the differential parameters using upper-level instructions received by the central computer of the ground-based launch and control system.

[0047] The differential parameters include aircraft configuration parameters and differential wave parameters. The aircraft configuration parameters include four strategy parameters: penetration, jamming, reconnaissance, and decoy; the differential wave parameters include five strategy parameters: trajectory control, information support, position, target, and destruction.

[0048] This disclosure discloses a multi-modal switching system for clustered aircraft formations throughout their entire lifecycle, comprising: a ground-based telemetry, launch, and control system and an onboard clustering system; the ground-based telemetry, launch, and control system is used to control ground processes using the multi-mode system process planning module and mission planning module; the onboard clustering system is used to perform multi-mode control of the point parameter clusters with different parameters using upper-level instructions received by the central computer of the ground-based telemetry, launch, and control system. This system effectively enables switching between multi-mode modes of the point parameter clusters with different parameters, and automatically monitors the multi-mode conversion process of the aircraft, thus achieving multi-mode system telemetry and control.

[0049] In one example, the multi-mode control of the cluster of point parameters with differential parameters using upper-level instructions received by the central computer of the ground-based telemetry and control system may include:

[0050] When the central computer of the ground-based telemetry, tracking, and command system receives an upper-level instruction to control the aircraft to start working in emergency launch mode, the fire support module and the calculation planning and scheduling module of the ground-based telemetry, tracking, and command system are put into operation, while the field planning module and the point parameter control module for differential parameters are put into sleep mode.

[0051] When the central computer of the ground-based telemetry, tracking, and command system receives an upper-level instruction to control the aircraft to start operating in a non-emergency launch mode, the on-site planning module and the point parameter control module of the ground-based telemetry, tracking, and command system are in working state, while the fire support module and the calculation planning and scheduling module are in dormant state.

[0052] The system includes: a fire support module for switching the aircraft configuration parameters according to upper-level instructions; a calculation, planning, and scheduling module for controlling the payload motion attitude and flight drop point of the aircraft whose configuration parameters have been switched to valid; a field planning module for determining whether the current launch response time, hardware configuration status, and software health status of the aircraft are within the preset conditions for aircraft launch preparation based on the heterogeneous wave parameters; and a point parameter control module for differentiating parameters for switching the configuration strategy of the differentiating wave parameters based on the upper-level instructions when the aircraft launch preparation is within the preset conditions.

[0053] For example, if the central computer of the ground control system receives instructions from the upper level and confirms that an emergency situation requiring real-time response is identified (instruction for the aircraft to start operating in emergency launch mode), then the fire support module and the calculation planning and scheduling module are activated. If it is determined that the requirement for real-time response capability is not particularly stringent (i.e., instruction for the aircraft to start operating in non-emergency launch mode), then the pre-deployed field planning module and the point parameter control module for differential parameters are activated, enabling multi-mode system measurement and control.

[0054] Figure 2 A schematic diagram of the point parameter cluster multi-mode control principle according to another embodiment of the present disclosure is shown.

[0055] In one example, such as Figure 2As shown, the fire support module can be used to switch the aircraft configuration parameters according to the upper-level instructions. These parameters include four strategies: penetration, jamming, reconnaissance, and decoy. For example, when the fire support module is activated, it switches the control of the aircraft model configuration to different emergency launch missions with different penetration, jamming, reconnaissance, and decoy strategies according to the upper-level switching instructions, thus achieving the mode configuration command for this part. Specifically, the fire support module can deactivate aircraft with inactive penetration, jamming, reconnaissance, and decoy strategy parameters according to the upper-level switching instructions, and activate aircraft with the penetration, jamming, reconnaissance, and decoy strategy parameters required by the aircraft system to perform emergency missions. The calculation, planning, and scheduling module is used to control the motion attitude and flight drop point of the payload carried by the aircraft that has been switched to valid configuration parameters. For example, when the calculation, planning, and scheduling module is activated, it controls the timing of penetration, jamming, reconnaissance, and decoy launches, as well as the motion attitude and flight drop point of the payload carried by the aircraft, which are configured by the fire support module to be valid.

[0056] For example, when the upper-level command is to control the aircraft to start operating in emergency launch mode, the fire support module and the computational planning and scheduling module in the ground control system are active, while other equipment (the pre-deployed field planning module and the point-based parameter control module with differential parameters) are in a dormant state, creating a specific mode management scheme. The fire support module can output emergency launch missions with different penetration, jamming, reconnaissance, and decoy configurations for different aircraft models through software algorithms. The fire support module has switching strategies; for example, it can disable inactive penetration, jamming, reconnaissance, and decoy strategies, and activate the penetration, jamming, reconnaissance, and decoy strategies required for emergency operation, thus switching to the corresponding mode configuration command. This software algorithm is not limited to a decision model trained through reinforcement learning; it uses effective empirical data parameters provided by an expert system to complete reinforcement learning, and then uses the decision output to achieve mode management according to different field requirements. The computational planning and scheduling module can use algorithms to control the timing of penetration, jamming, reconnaissance, and decoy launches, as well as the attitude and flight release points of the payloads configured by the fire support module. The algorithm of the computational planning and scheduling module has high requirements for the deterministic nature of control. It adopts deterministic uniqueness decision-making, which can achieve efficient decision-making in emergency launch mode and achieve minimum system resource consumption.

[0057] The on-site planning module can be used to determine whether the current launch response time, hardware configuration status, and software health status of the spacecraft are within the preset conditions for launch preparation based on the anisotropic wave parameters. For example, when entering the pre-deployed on-site planning module, it determines whether the current launch response time, hardware configuration status, and software health status of the spacecraft are within the launch preparation conditions for different wave types, such as different orbital control, different information support, different locations, different targets, and different damage types.

[0058] The differential parameter point-of-flight control module can be used to switch the configuration strategy of the differential wavelet parameters based on the upper-level command when the launch preparation of the spacecraft is within a preset condition range. For example, when the differential parameter point-of-flight control module is accessed, it responds to the upper-level switching command for differential wavelets such as different orbital control, different information support, different points, different targets, and different damage when the launch preparation of the spacecraft is within the preset condition range. It switches the configuration conditions for these differential wavelets according to the upper-level switching command. For example, the differential parameter point-of-flight control module, according to the upper-level command, shuts down spacecraft with inactive orbital control, information support, point, target, and damage differential wavelet strategy parameters, and wakes up spacecraft with the orbital control, information support, point, target, and damage differential wavelet strategy parameters required for the spacecraft system to perform its mission.

[0059] For example, when the upper-level command is to control the aircraft to start working in a non-emergency launch mode, the pre-deployed field planning module and the point parameter control module that can realize differential parameter settings in the ground control system are in working state, while other equipment (fire card support module and calculation planning and scheduling module) are in dormant state.

[0060] The pre-deployed on-site planning module uses software algorithms to determine whether the spacecraft's current launch response time, hardware configuration status, and software health status are within the launch preparation conditions, taking into account differences in trajectory control, information support, location, target, and damage levels. This software algorithm is not limited to decision models trained through reinforcement learning; it utilizes effective empirical data parameters provided by an expert system to complete reinforcement learning, and then uses the decision output to achieve pattern management based on different on-site requirements.

[0061] The point-of-use parameter control module, which handles differential parameter settings, responds to upper-level switching commands when the spacecraft is within the preset launch preparation conditions, considering different orbital control, information support, points, targets, and damage waves. It switches the configuration conditions for these different orbital control, information support, points, targets, and damage waves, and controls the execution mode in the ground control system according to the upper-level switching commands. The algorithm for autonomous switching of spacecraft multi-modal modes has high deterministic requirements for control, employing deterministic uniqueness decision-making to achieve efficient decision-making and minimize system resource consumption in emergency launch mode.

[0062] By determining the required real-time response status of the aircraft based on the received upper-level commands, different functional modules of the aircraft's ground control system can be activated to enable multi-mode switching of the aircraft, as well as automatic control and monitoring during the multi-mode transition process; and specific mode management schemes can be implemented to control various devices of the ground control system according to the upper-level switching commands.

[0063] Figure 3 A schematic diagram of a three-stage cabin structure of an aircraft according to an embodiment of the present disclosure is shown.

[0064] In one example, such as Figure 3 As shown, each aircraft in the clustered aircraft formation system adopts a three-stage cabin structure, which includes a first-stage booster cabin, a second-stage maneuver control cabin, and a third-stage payload gliding target control cabin. The first-stage booster cabin is used for high-thrust flight control during the active phase after takeoff and for the recovery control of the first-stage booster cabin (recovery control after the first-stage booster cabin separates from the previous stage after flight).

[0065] Both the secondary maneuvering control cabin and the tertiary payload gliding target control cabin are used for flight control of the aircraft in the level flight stage and for controlling the payload to enter a preset orbit. For example, both the secondary maneuvering control cabin and the tertiary payload gliding target control cabin are designed for energy-saving level flight control and for high-precision control to send the payload into a specific orbit (preset orbit).

[0066] In one example, each of the three stages includes actuators, an integrated machine, and an inertial navigation system (INS). The actuators of the first-stage booster cabin are the core actuators, while the second-stage maneuver control cabin and the third-stage payload gliding target control cabin have less capable actuators. The integrated machine and INS of the third-stage payload gliding target control cabin are the integrated machine and the main INS, respectively, while the integrated machine and INS of the first-stage booster cabin and the second-stage maneuver control cabin have less capable recovery capabilities.

[0067] The core actuator is used to detect whether each component of the aircraft is in its initial state before takeoff. The initial state can be the initial state in which each component is working normally before takeoff, such as the zero state or the preset state, etc., which are not limited here.

[0068] In one example, the core actuators include an energy module, a control drive, and an actuator.

[0069] The energy module is used to detect whether the chemical energy of the aircraft's batteries and boosters meets the requirements for normal operation. For example, it detects whether the energy materials are leaking or damaged, ensuring that the aircraft's energy materials meet the needs during flight. The control actuator is used to detect whether the aircraft's control electronic circuits are functioning properly, for example, detecting whether there are short circuits or open circuits in the control electronic circuits. The actuator is used to detect whether the aircraft's valves and sensors (such as angular displacement sensors and gyroscopes) are damaged.

[0070] The integrated unit is used to receive the upper-level instructions and process the acquired aircraft data. In addition, the integrated unit is also used to switch the aircraft's working mode according to the upper-level instructions and wake up the working components of the aircraft in different working modes.

[0071] The main inertial navigation system (IMU) is used to acquire the position and velocity of the aircraft throughout its entire life cycle. The IMU is mainly used to measure physical information such as attitude angles and accelerations of the aircraft in three mutually orthogonal reference directions during flight.

[0072] By dividing the aircraft into corresponding hierarchical and segmented multi-mode control based on the different missions performed by multiple aircraft, it is possible to detect the flight control mode of the recovery capsule of the cruise aircraft, the self-destruct control mode of the jettison capsule after performing its mission, the variable maneuver self-learning penetration control of the main control module, and the neural network gliding detection of the detection module.

[0073] The above embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit them. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of this application, and should all be included within the protection scope of this application.

Claims

1. A multi-mode switching system for clustered aircraft formations throughout their entire lifecycle, characterized in that, The system includes: a ground-based launch and control system and an onboard cluster system; The ground-based telemetry, tracking, and command system is used to control ground processes using the multi-mode system process planning module and the mission planning module. The onboard cluster system is used to perform multi-mode control of the point data cluster of the differential parameters using upper-level instructions received by the central computer of the ground-based launch and control system.

2. The multi-mode switching system for clustered aircraft formations according to claim 1, characterized in that, The multi-mode system process planning module includes: a measurement and control processing unit, a power supply system, a processor, and a front-end health system; The task planning module includes a cluster emergency response device and a central computer.

3. The multi-mode switching system for clustered aircraft formations according to claim 1, characterized in that, The multi-mode control of the cluster of point parameters with differential parameters, achieved by receiving upper-level instructions from the central computer of the ground-based telemetry, tracking, and command system, includes: When the central computer of the ground-based telemetry, launch and control system receives an upper-level instruction to control the aircraft to start working in emergency launch mode, the fire support module and the calculation planning and scheduling module of the ground-based telemetry, launch and control system are in working state. When the central computer of the ground-based telemetry, tracking, and command system receives an upper-level instruction to control the aircraft to start operating in a non-emergency launch mode, the field planning module and the point parameter control module for the differential parameters of the ground-based telemetry, tracking, and command system are in operation.

4. The multi-modal switching system for clustered aircraft formations according to claim 2, characterized in that, The telemetry and control processing unit is used to send the received preset control commands for the operation of the aircraft to the aircraft, and control the aircraft to execute the task requirements corresponding to the control commands; The power system is used to provide multi-mode power to the multi-mode ground-based telemetry, tracking, and command system of a cluster of aircraft throughout its entire life cycle. The processor is used to execute corresponding control decisions based on the received upper-level switching instructions from the ground-based telemetry, tracking, and command system. The front-end health system is used to process the received aircraft system monitoring data before the aircraft takes off; The central computer is used to receive upper-level switching instructions sent by the aircraft; The cluster emergency processing device is used to process redundant data from aircraft in emergency situations.

5. The multi-mode switching system for clustered aircraft formations according to claim 3, characterized in that, The fire support module is used to switch the aircraft configuration parameters according to the upper-level instructions. The computational planning and scheduling module is used to control the motion attitude and flight drop point of the payload carried by the aircraft that has been switched to valid configuration parameters; The on-site planning module is used to determine whether the current launch response time, hardware configuration status and software health status of the aircraft are within the preset conditions for aircraft launch preparation based on the heterogeneous wave parameters. The point parameter control module for the differential parameters is used to switch the configuration strategy of the differential wave parameters based on the upper-level command when the launch preparation of the aircraft is within the preset condition range.

6. The multi-mode switching system for clustered aircraft formations according to claim 3, characterized in that: The multi-mode system process planning module and task planning module adopt a two-level deployment mode.

7. The multi-mode switching system for clustered aircraft formations according to claim 5, characterized in that: The aircraft configuration parameters include four strategy parameters: penetration, jamming, reconnaissance, and decoy; the differential wave parameters include five strategy parameters: trajectory control, information support, point of contact, target, and destruction.

8. The multi-mode switching system for clustered aircraft formations according to claim 1, characterized in that: Each aircraft in the clustered aircraft formation system adopts a three-stage cabin structure, which includes a primary boost propulsion cabin, a secondary maneuver control cabin, and a tertiary payload gliding target control cabin.

9. The multi-mode switching system for clustered aircraft formations according to claim 8, characterized in that: The first-stage booster cabin is used for flight control of the active phase with high thrust after the aircraft takes off and for the recovery control of the first-stage booster cabin. The secondary maneuver control cabin and the tertiary payload gliding target control cabin are both used for flight control of the aircraft's level flight layer and for controlling the payload to enter the preset orbit.

10. The multi-mode switching system for clustered aircraft formations according to claim 8, characterized in that: Each of the three-level cabins includes an actuator, an integrated machine, and an inertial navigation system; The actuator of the first-stage booster cabin is set as the core actuator, the integrated machine of the third-stage payload gliding target control cabin is set as an integrated machine, and the inertial group of the third-stage payload gliding target control cabin is set as the main inertial group.

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