Aerospace multidirectional power rotating machine driving method

Abstract

The invention discloses an aerospace multidirectional power rotating machine driving method, and relates to the technical field of aerospace, and the method comprises the following specific steps: power unit pre-configuration: selecting a power unit according to the specific task demand, the overall performance parameter and the expected operation condition of an aerospace aircraft, by integrating an innovative energy conversion and management mechanism, the redundant mechanical energy in the running process of the rotating machine can be fully utilized for efficient storage, so that the aircraft can quickly and reliably convert the stored chemical energy into mechanical energy for auxiliary driving at a key node needing instantaneous high-power output or energy supplement, and the reliability of the aircraft is improved. In addition, through a real-time operation state monitoring and adjusting mechanism, a power unit and a main driving shaft of the aircraft are continuously monitored, a corresponding adjusting mechanism is immediately triggered once abnormity is found, and it is ensured that the whole system operates stably and reliably all the time.

Description

Technical Field

[0001] The invention relates to the field of aerospace technology, and in particular to an aerospace multi-directional power transfer machine driving method. Background Art

[0002] As an important means for human beings to explore the universe and realize space utilization, aerospace technology has achieved rapid development in recent years. In aerospace missions, aircraft need to perform various complex and changeable operations, such as orbit transfer, space docking, attitude adjustment, etc. These operations not only require the aircraft to have high-precision navigation and control capabilities, but also put forward extremely high requirements on the flexibility and efficiency of its power system. Multi-directional power transfer drive technology, as a core component of the aircraft power system, plays a vital role in realizing key functions such as aircraft attitude adjustment and power output direction control.

[0003] However, the application of traditional power transfer drive methods in the aerospace field faces many challenges. On the one hand, traditional drive methods often cannot achieve omnidirectional flexible rotation, and the drive angle range is limited, which makes it difficult to meet the high-precision requirements of aircraft for attitude adjustment in complex flight missions. On the other hand, traditional drive methods have slow response speeds when switching in multiple directions and cannot quickly adapt to the needs of aircraft to quickly adjust their attitude in emergency situations. In addition, the power output efficiency in different directions fluctuates greatly, which not only affects the overall flight performance of the aircraft, but also increases energy waste and reduces the efficiency of flight mission execution. In addition, existing aircraft energy storage and utilization methods have obvious shortcomings in facing instantaneous high-power output requirements and effectively recycling and utilizing excess mechanical energy generated during transfer operation, which further limits the improvement of aircraft control performance and mission execution capabilities.

[0004] In view of the above problems, it is necessary to optimize the existing aerospace multi-directional power steering drive method. Through precise power distribution algorithm, high-precision steering adjustment mechanism and unique energy conversion and management method, the multi-directional drive flexibility and power output stability of the aircraft in complex flight missions are achieved. Therefore, it is of great significance to develop an aerospace multi-directional power steering drive method that can comprehensively realize the above characteristics. Summary of the invention

[0005] The purpose of the present invention is to make up for the shortcomings of the prior art and to provide an aerospace multi-directional power transfer drive method, which can realize 360-degree omnidirectional power output and transfer steering operation through precise control algorithms combined with the reasonable layout of each power unit and a high-precision steering adjustment mechanism, and the steering accuracy can be controlled within a very small range, thereby greatly improving the flexibility of attitude adjustment and power application of aerospace vehicles. At the same time, the present invention also effectively avoids power conflicts and waste between power units through precise power distribution algorithms and real-time operation status monitoring and adjustment mechanisms, and ensures the high efficiency and stability of power output. In addition, the unique energy conversion and management method enables the present invention to make full use of the excess mechanical energy in the transfer operation process for efficient storage, and quickly and reliably convert chemical energy back into mechanical energy to assist in driving when needed, further enhancing the power guarantee flexibility and stability of the aircraft in a complex and changeable flight environment.

[0006] In order to solve the above technical problems, the present invention provides the following technical solutions: a method for driving an aerospace multi-directional power transfer machine, the method comprising the following specific steps:

[0007] Power unit pre-configuration: Select the power unit according to the specific mission requirements, overall performance parameters and expected operating conditions of the aerospace vehicle, determine the number of each power unit and the spatial layout around the turntable base, and connect it to the turntable main drive shaft with a clutch coupling;

[0008] Target direction determination and power distribution: The high-precision attitude sensor on the aircraft obtains the current attitude data of the aircraft in real time, and transmits the data to the central control unit. The central control unit compares and analyzes the currently acquired attitude data with the target attitude to be achieved based on the preset space vector decomposition algorithm combined with the trigonometric function relationship, and decomposes the target direction vector according to the relative angle relationship of the layout of each power unit, thereby calculating the power ratio that each power unit should provide under the current mission requirements;

[0009] Steering adjustment and power coupling: According to the calculated power distribution results, the central control unit controls the clutch state of the coupling between the output shaft of each power unit and the main drive shaft of the transfer machine. For the power unit that needs to participate in the power output, its coupling is closed to achieve effective transmission of power to the main drive shaft. For the power unit that does not need to provide power temporarily, its coupling is kept disconnected to avoid interference with the system operation. At the same time, the central control unit sends an angle adjustment instruction to the steering adjustment mechanism based on the target direction information. After the steering adjustment mechanism receives the instruction, the electric push rod performs telescopic movement according to the preset movement law, drives the universal joint to rotate, and then fine-tunes the angle of the main drive shaft;

[0010] Energy conversion and management: During the operation of the transfer machine, the speed sensor and torque sensor continuously monitor the operation status of the transfer machine and transmit the data to the central control unit. The central control unit determines whether to start the energy conversion management process based on the data and the energy demand of the aircraft. For the need to store excess mechanical energy, the mechanical energy is transferred to the energy storage medium with the help of a mechanical structure including gears and hydraulic transmission, and the mechanical energy is converted into chemical energy by relying on its chemical bond energy characteristics. During the process, the pressure and chemical sensors feedback data, and the central control unit precisely controls to ensure efficient and stable conversion and storage. For the need to supplement power and release energy, the central control unit triggers the reverse chemical reaction of the energy storage medium based on sensor feedback and energy demand, selects the triggering method according to its characteristics to convert chemical energy into mechanical energy, and then couples it back to the drive shaft through a specific mechanical structure to assist the transfer machine in outputting power;

[0011] Power output and dynamic monitoring and adjustment: Each power unit distributes power according to the central control unit, and drives the actuators through the main drive shaft to achieve multi-directional power output and attitude adjustment of the aircraft. It also uses a variety of sensors to collect operating parameters in real time and feed them back to the central control unit. The received data is analyzed in real time. Through preset threshold judgment and fault diagnosis algorithms, once it is detected that the actual operating parameters exceed the preset normal range, the corresponding adjustment mechanism is immediately triggered according to the built-in adjustment strategy.

[0012] Furthermore, in the power unit preconfiguration step, the power unit includes an electric motor and a small turbine engine, the number of the power units is at least three, and the spatial layout thereof determines the angular interval between the output shafts of each power unit according to the number of the power units.

[0013] Furthermore, in the target direction determination and power distribution step, the central control unit compares and analyzes the currently acquired attitude data with the target attitude to be achieved according to the preset space vector decomposition algorithm combined with the trigonometric function relationship. Specifically, the target attitude transformation vector of the aircraft is The power output direction vector of power unit i is The power output capacity coefficient of power unit i is K i , the power distribution ratio factor R of the i-th power unit i The calculation formula is: Where m is the total number of power units, K j Represents the power output capacity coefficient of power unit j.

[0014] Furthermore, in the steering adjustment and power coupling step, the central control unit sends an angle adjustment instruction to the steering adjustment mechanism according to the target direction information. After the steering adjustment mechanism receives the instruction, the electric push rod performs telescopic movement according to a preset motion law. Specifically, the target angle deviation vector of the main drive shaft is The arm length of the electric push rod i in the steering adjustment mechanism is L i , the driving efficiency coefficient of the electric push rod i is η i , driving torque M of electric push rod i i The calculation formula is: in, is the unit vector of the action direction of electric push rod i, p is the total number of electric push rods, M total The total torque required to drive the main drive shaft to reach the target angle is calculated to ensure that each electric push rod drives the components to rotate with precise torque to adjust the angle of the main drive shaft.

[0015] Furthermore, in the energy conversion and management step, for situations where excess mechanical energy needs to be stored, energy transfer is achieved with the help of a specific integrated gear transmission and hydraulic transmission combination structure. The excess mechanical energy on the main drive shaft and the output shaft of each power unit is initially transmitted and adapted to the speed and torque through gear transmission, and a hydraulic pump is used to convert mechanical energy into hydraulic energy, which is transmitted to a container containing a special energy storage medium through a hydraulic pipeline. The hydraulic motor converts the hydraulic energy back into mechanical energy and inputs it into the energy storage medium. When the energy storage medium receives the action of mechanical energy, a positive reversible chemical reaction occurs based on its internal chemical bond energy change mechanism, thereby realizing the conversion of mechanical energy into chemical energy, and the progress of the chemical reaction in the energy storage medium and the chemical energy storage capacity parameters are detected in real time, and the data is transmitted to the central control unit, and the mechanical energy transmission link and the chemical reaction process are regulated by a control algorithm.

[0016] Furthermore, in the energy conversion and management step, the mechanical energy transfer link and the chemical reaction process are regulated by the control algorithm. Specifically, the excess mechanical energy flow density that can be collected at a certain moment in the transfer system is ρ E , the microstructure activity coefficient of the energy storage medium is α(S), the contact area between the energy storage medium and the mechanical energy transmission component is A, then the total amount of chemical energy E stored in the energy storage medium in the time interval Δt is chem The calculation formula is: chem =ρ E ·α(S)·A·Δt. Through this formula, it is possible to accurately quantify how much mechanical energy can be successfully converted and stored in the energy storage medium within a certain period of time, so that the energy conversion process can be precisely controlled according to the actual system operating status and the characteristics of the energy storage medium.

[0017] Furthermore, in the energy conversion and management step, when power needs to be supplemented or energy needs to be released, the central control unit triggers the reverse chemical reaction in the energy storage medium based on the real-time system status information and the overall energy demand fed back by each sensor, and applies an electrical stimulation signal according to preset trigger parameters through the power supply and control circuit connected to the energy storage medium, so as to prompt the energy storage medium to release the stored chemical energy and convert it into mechanical energy. The converted mechanical energy is coupled to the main drive shaft or the output shaft of the corresponding power unit again through the combined structure of integrated gear transmission and hydraulic transmission, so as to realize power supplement to the multi-directional power transmission machine and assist the transmission machine to complete the corresponding power output operation.

[0018] Furthermore, in the power output and dynamic monitoring adjustment step, if the actual operating parameters are detected to be beyond the preset normal range, the corresponding adjustment mechanism is triggered according to the built-in adjustment strategy, and the theoretical optimal power output power of the power unit i is set to P oi , the actual monitored power output is P i , the power adjustment coefficient β of power unit i i The calculation formula is: By calculating this coefficient, the degree of deviation between the actual operating state of the power unit and the ideal state can be intuitively reflected. i If the value is greater than 1, it means that the current actual output power is lower than the theoretical optimal value, and there is a problem of insufficient power. i If the value is less than 1, it means that the power unit is in an overload condition. Based on this coefficient, the central control unit can accurately determine whether each power unit is working normally, as well as the specific circumstances of deviation from the normal state, and then take corresponding adjustment measures.

[0019] Compared with the prior art, this aerospace multi-directional power transfer drive method has the following beneficial effects:

[0020] 1. The present invention, by incorporating innovative energy conversion and management mechanisms, can fully utilize the excess mechanical energy during the transfer operation process for efficient storage, so that the aircraft can quickly and reliably convert the stored chemical energy back into mechanical energy for auxiliary drive at key nodes where instantaneous high-power output or energy replenishment is required, thereby enhancing the flexibility and stability of the aircraft's power guarantee. In addition, through real-time operation status monitoring and adjustment mechanisms, the aircraft's power unit and main drive shaft are continuously monitored, and once an abnormality is found, the corresponding adjustment mechanism is immediately triggered to ensure that the entire system always operates stably and reliably.

[0021] 2. The present invention realizes 360-degree omnidirectional power output and steering operation of the aircraft through precise control algorithms combined with the reasonable layout of each power unit and a high-precision steering adjustment mechanism, greatly improving the attitude adjustment capability of the aircraft, enabling it to flexibly respond to various mission requirements in a complex and changeable flight environment. At the same time, this method uses a unique impact-type power enhancement mechanism, inertia, symmetrical force collision and lever principle to achieve regular movement of the impact object along an arc, and repeated fast-paced collisions to generate continuous lift, providing additional assistance for power output and significantly improving the power performance of the aircraft.

[0022] Other advantages, objectives and features of the present invention will be set forth in part in the following description and, in part, will be apparent to those skilled in the art based on an examination of the following or may be taught from the practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the prior art descriptions are briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention, and for ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0024] Figure 1 It is a process operation diagram of a multi-directional power transfer driving method for aerospace;

[0025] Figure 2 The present invention is a flow chart of a method for driving an aerospace multi-directional power transfer machine. DETAILED DESCRIPTION

[0026] In order to further explain the technical means and effects adopted by the present invention to achieve the predetermined invention purpose, the specific implementation mode, structure, characteristics and effects of the present invention are described in detail below in combination with the accompanying drawings and preferred embodiments.

[0027] Embodiment 1

[0028] When small satellites perform missions in space, the space environment they are in is complex and changeable, and their stable operation faces many challenges. Precise attitude adjustment and orbit maintenance are the key to ensuring their normal operation. For example, solar panels must always be accurately aimed at the sun to ensure that all satellite systems have sufficient power to maintain normal operation of the equipment. The communication antenna must also be stably pointed in the direction of the ground base station to build a reliable communication link, allowing the ground control center to successfully receive the data collected by the satellite and send control commands to it. In addition, factors such as micrometeoroid impacts in space and resistance in the upper atmosphere can easily cause slight deviations in the satellite orbit. At this time, it is necessary to carry out orbit maintenance operations in a timely manner. The completion of these key tasks places extremely high demands on the efficiency, accuracy and reliability of the power converter drive and energy storage system.

[0029] After comprehensively considering various factors such as the overall mission characteristics, structural size limitations, and energy supply conditions of the small satellite, it was finally decided to use four small electric motors as power units. The reason for choosing this type of electric motor is that the small electric motors are arranged and installed around the turntable base at an even interval of 90 degrees. During the actual installation, the operation is strictly carried out in accordance with high-precision mechanical installation process specifications. With the help of precise positioning fixtures and calibration tools, the installation accuracy is fully guaranteed. For example, the axial position deviation of each electric motor is strictly controlled within the range of no more than ±0.1 mm, and the angle deviation is also controlled within a very small range of no more than ±0.1 degrees. This ensures that the relative angle between the output shaft of each power unit and the main drive shaft is accurate, laying a solid foundation for the smooth transmission of subsequent power and coordinated work. The output shaft of each electric motor is connected to the main drive shaft through an electromagnetic clutch coupling.

[0030] The inertial measurement unit and star sensor on the small satellite collect the satellite's current attitude data in real time, such as the angular velocity of the three axes and the azimuth angle relative to the stars, and transmit these data to the central control unit. When the satellite needs to adjust its attitude, such as pointing the solar panel towards the sun, the central control unit transforms the vector according to the preset target attitude. Combined with the power output direction vector of each electric motor And the power output capacity coefficient K i , calculated by the power distribution proportional factor formula (Here m = 4), calculate the power distribution ratio factor R that each electric motor should bear i Then determine the power required for each electric motor to output for this posture adjustment.

[0031] The central control unit calculates the R iThe clutch state of the coupling between each electric motor and the main drive shaft is controlled by the value, and the coupling corresponding to the electric motor that needs to participate in the power output is closed, so that the power can be transmitted to the main drive shaft. At the same time, an angle adjustment instruction is sent to the steering adjustment mechanism composed of a high-precision electric push rod and a universal joint. Based on the target angle deviation vector of the main drive shaft Combined with the electric push rod arm length L i , driving efficiency coefficient η i Parameters such as the driving torque are calculated by the formula (p is the number of electric linear actuators) The driving torque of each electric linear actuator is reasonably distributed to drive the electric linear actuator to extend and retract to drive the universal joint to rotate, and the angle of the main driving shaft is accurately adjusted to accurately align the solar panel with the direction of the sun. The angle adjustment accuracy is controlled within ±0.1 degrees.

[0032] During the power transfer operation of the satellite, the speed sensors and torque sensors installed on the main drive shaft and the output shafts of each electric motor monitor the transfer operation status in real time. When the satellite completes an attitude adjustment and the electric motor generates excess mechanical energy during the deceleration stage, the energy conversion and storage process is started, and energy transmission is achieved with the help of a specific integrated gear transmission and hydraulic transmission combination structure. The excess mechanical energy on the main drive shaft and the output shafts of each power unit is initially transmitted through the gear transmission for power transmission and speed and torque adaptation, and a hydraulic pump is used to convert the mechanical energy into hydraulic energy, which is transmitted through hydraulic pipelines to a container containing a special energy storage medium. The hydraulic motor converts the hydraulic energy back into mechanical energy and inputs it into the energy storage medium. The energy storage medium is a new type of metal organic compound with special chemical bond energy characteristics. According to the excess mechanical energy flow density ρ that can be collected E , the energy storage medium microstructure activity coefficient α(S) and the contact area A and other parameters are calculated by formula E chenn =ρ E ·α(S)·A·Δt calculates the total amount of chemical energy stored in the energy storage medium within a certain time interval Δt. At the same time, the central control unit uses the data fed back by the pressure sensor and the chemical sensor to accurately control the energy conversion and storage process. When the satellite needs to perform orbit maintenance operations and requires instantaneous high-power output, the central control unit triggers the chemical reaction in the energy storage medium to proceed in reverse. For example, through electric pulse stimulation, the energy storage medium releases chemical energy and converts it into mechanical energy, which is then coupled back to the main drive shaft through the mechanical structure to assist the converter in outputting sufficient power to achieve orbit maintenance operations.

[0033] Each electric motor outputs power according to the allocated power size, and drives the attitude adjustment nozzle and other actuators through the main drive shaft to achieve the power output function required for satellite attitude adjustment and orbit maintenance, and activates the collision-type power enhancement mechanism. By setting multiple groups of symmetrically distributed impact components inside the turntable, the synergistic effect of multiple groups of symmetrical forces is achieved. The impactor in the impact component reciprocates along the planned arc trajectory. During operation, the impactor accumulates energy in the acceleration section of the arc motion and releases it at the moment of collision by utilizing the principle of inertia. At the same time, by utilizing the principle of lever force, the impact component is equipped with a lever structure. When the impactor moves to the collision point, the lever structure can amplify the impact force and generate an upward component force in each collision. As the collision continues, the component forces are superimposed to form continuous lift, which is then transmitted to the impactor. The structure transmits the information to the main drive shaft, which in turn drives the attitude adjustment nozzle and thruster components of the aircraft, thereby realizing the attitude adjustment and power output of the aircraft during deep space exploration. During this process, various sensors continuously collect speed, torque and temperature operating parameters and feed them back to the central control unit, and analyze the received data in real time. Through the preset threshold judgment and fault diagnosis algorithm, once it is detected that the actual operating parameters exceed the preset normal range, the corresponding adjustment mechanism is immediately triggered according to the built-in adjustment strategy. During the whole process, the operating parameters are continuously monitored through speed sensors, torque sensors, temperature sensors, etc., and the data are fed back to the central control unit. Once the central control unit detects that the speed of a certain electric motor suddenly drops, the torque of the main drive shaft increases abnormally, etc., which exceed the preset normal range, the power adjustment coefficient is immediately adjusted according to the power adjustment coefficient. (where P oi is the theoretical optimal power output, P i To monitor the actual power) determine the abnormal status of the power unit, and then take actions such as adjusting the electric motor input power, redistributing the power, fine-tuning the steering adjustment mechanism, or intervening in the energy conversion management process to ensure stable and reliable operation of the satellite system.

[0034] Embodiment 2

[0035] Manned spacecraft need to adjust their attitude precisely and flexibly during different stages of space flight, rendezvous and docking, and returning to Earth to ensure the normal living and working environment of astronauts in the spacecraft and the smooth progress of the flight mission. At the same time, when encountering emergencies such as the threat of impact from space debris, they must be able to quickly perform emergency maneuvers. This requires the power converter drive and energy storage system to be efficient, reliable and able to respond quickly.

[0036] In view of the complex mission requirements, large payload and requirements for power stability of manned spacecraft, three high-power electric motors and two small turbine engines are selected as power units. They are distributed around the turntable base at specific angles (electric motors are spaced 120 degrees apart, and turbine engines are located at specific positions to optimize the overall power layout). The output shaft of each power unit is connected to the main drive shaft through a high-performance clutch coupling.

[0037] The high-precision inertial measurement unit and star sensor equipped on the spacecraft obtain the current attitude data of the spacecraft in real time, including the spacecraft's three-axis attitude angle angular velocity and other information, and transmit these data to the central control unit. When the spacecraft needs to accurately adjust its attitude during the rendezvous and docking process to align the docking mechanism with the target aircraft, the central control unit transforms the vector according to the preset target attitude. Combined with the power output direction vector of each power unit And power output capacity coefficient K i , calculated by the power distribution proportional factor formula (Here m = 5, corresponding to five power units), accurately calculate the power proportional factor R that should be allocated to each power unit i This can determine the amount of power each power unit needs to output for this posture adjustment, ensuring that the docking operation can be carried out accurately.

[0038] The central control unit controls the clutch state of the coupling between each power unit and the main drive shaft according to the calculated power distribution result, so that the corresponding power unit participates in power transmission. At the same time, it sends an angle adjustment instruction to the steering adjustment mechanism. The electric push rod in the mechanism adjusts the angle according to the target angle deviation vector of the main drive shaft. Its own arm length L i , driving efficiency coefficient η i Parameters such as the driving torque are calculated by the formula (p is the number of electric push rods) to obtain the required driving torque, and then extend and retract to drive the universal joint to rotate, and fine-tune the angle of the main drive shaft to ensure that the spacecraft attitude is accurately adjusted. The angle adjustment accuracy is within ±0.1 degrees, meeting the high-precision attitude adjustment requirements such as rendezvous and docking.

[0039] During the spacecraft power conversion operation, the speed sensor, torque sensor and temperature sensor installed in the key parts are used to monitor the system operation status in real time. For example, after the spacecraft completes a certain attitude adjustment, when some power units are in a low-load operation state and generate excess mechanical energy, the energy conversion process is started to store the excess mechanical energy. Through the mechanical structure of the gear transmission and hydraulic transmission combination, the excess mechanical energy is transferred to a special energy storage medium. The energy storage medium uses a special energy-containing compound, which can undergo a positive reversible chemical reaction based on the change of internal chemical bond energy under the action of mechanical energy to realize the conversion of mechanical energy into chemical energy. In this process, according to the excess mechanical energy flow density ρ E , the microstructure activity coefficient α(S) of the energy storage medium, the contact area A and the time interval Δt, through the formula E chem =ρ E ·α(S)·A·Δt calculates the amount of chemical energy stored. Relying on the data fed back by the pressure sensor and the chemical sensor, the central control unit precisely regulates the energy conversion and storage process. When the spacecraft encounters an emergency situation such as the urgent approach of space debris and requires instantaneous high-power output for emergency maneuvers, the central control unit triggers the reverse chemical reaction in the energy storage medium based on the real-time status information fed back by the sensor.

[0040] Each power unit outputs power according to the power allocated by the central control unit, and drives the spacecraft's attitude adjustment nozzle, propulsion blades and other executive components through the main drive shaft to achieve the spacecraft's attitude adjustment and power output functions in different flight stages, and activates the collision-type power enhancement mechanism. By setting up multiple groups of symmetrically distributed impact components inside the turntable, the synergistic effect of multiple groups of symmetrical forces is achieved. The impactor in the impact component reciprocates along the planned arc trajectory. During operation, using the principle of inertia, the impactor accumulates energy in the acceleration section of the arc motion and releases it at the moment of collision. At the same time, by using the principle of lever force, the impact component is equipped with a lever structure When the impact object moves to the collision point, the lever structure can amplify the impact force and generate an upward force component in each collision. As the collision continues, the force components are superimposed to form a continuous lift, which is transmitted to the main drive shaft through the transmission structure, thereby driving the attitude adjustment nozzle and propeller components of the turning machine. During the whole process, various sensors continuously collect operating parameters such as speed, torque, temperature, etc., and feed them back to the central control unit. The built-in fault diagnosis and control strategy module of the central control unit analyzes these data in real time. Once it is detected that the actual operating parameters exceed the preset normal range (for example, the temperature of a power unit is too high, the torque fluctuates abnormally, etc.), the power adjustment coefficient is adjusted according to the power adjustment coefficient. Determine the abnormal situation of the power unit and then take corresponding adjustment measures, such as adjusting the power output of the power unit, redistributing power, fine-tuning the steering adjustment mechanism or intervening in the energy conversion management process, to ensure that the spacecraft system always maintains a stable, reliable and efficient operation state, to ensure the safety of astronauts and the smooth completion of the flight mission.

[0041] The above description is only a preferred embodiment of the present invention and does not limit the present invention in any form. Although the present invention has been disclosed as a preferred embodiment as above, it is not used to limit the present invention. Any technical personnel in this field can make some changes or modify the technical contents disclosed above into equivalent embodiments without departing from the scope of the technical solution of the present invention. However, any brief modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention are still within the scope of the technical solution of the present invention.

Claims

1. An aerospace multi-directional power transfer machine driving method, characterized in that: The method comprises the following specific steps: Power unit pre-configuration: Select the power unit according to the specific mission requirements, overall performance parameters and expected operating conditions of the aerospace vehicle, determine the number of each power unit and the spatial layout around the turntable base, and connect it to the turntable main drive shaft with a clutch coupling; Target direction determination and power distribution: The high-precision attitude sensor on the aircraft obtains the current attitude data of the aircraft in real time, and transmits the data to the central control unit. The central control unit compares and analyzes the currently acquired attitude data with the target attitude to be achieved based on the preset space vector decomposition algorithm combined with the trigonometric function relationship, and decomposes the target direction vector according to the relative angle relationship of the layout of each power unit, thereby calculating the power ratio that each power unit should provide under the current mission requirements; Steering adjustment and power coupling: According to the calculated power distribution results, the central control unit controls the clutch state of the coupling between the output shaft of each power unit and the main drive shaft of the transfer machine. For the power unit that needs to participate in the power output, its coupling is closed to achieve effective transmission of power to the main drive shaft. For the power unit that does not need to provide power temporarily, its coupling is kept disconnected to avoid interference with the system operation. At the same time, the central control unit sends an angle adjustment instruction to the steering adjustment mechanism based on the target direction information. After the steering adjustment mechanism receives the instruction, the electric push rod performs telescopic movement according to the preset movement law, drives the universal joint to rotate, and then fine-tunes the angle of the main drive shaft; Energy conversion and management: During the operation of the transfer machine, the speed sensor and torque sensor continuously monitor the operation status of the transfer machine and transmit the data to the central control unit. The central control unit determines whether to start the energy conversion management process based on the data and the energy demand of the aircraft. For the need to store excess mechanical energy, the mechanical energy is transferred to the energy storage medium with the help of a mechanical structure including gears and hydraulic transmission, and the mechanical energy is converted into chemical energy by relying on its chemical bond energy characteristics. During the process, the pressure and chemical sensors feedback data, and the central control unit precisely controls to ensure efficient and stable conversion and storage. For the need to supplement power and release energy, the central control unit triggers the reverse chemical reaction of the energy storage medium based on sensor feedback and energy demand, selects the triggering method according to its characteristics to convert chemical energy into mechanical energy, and then couples it back to the drive shaft through a specific mechanical structure to assist the transfer machine in outputting power; Power output and dynamic monitoring and adjustment: Each power unit distributes power according to the central control unit, and drives the execution components through the main drive shaft to realize the multi-directional power output and attitude adjustment of the aircraft, and starts the collision-type power enhancement mechanism. By setting multiple groups of symmetrically distributed impact components inside the turntable, the synergistic effect of multiple groups of symmetrical forces is realized. The impactor in the impact component reciprocates along the planned arc trajectory. During operation, using the principle of inertia, the impactor accumulates energy in the acceleration section of the arc motion and releases it at the moment of collision. At the same time, by using the principle of lever force, the impact component is equipped with a lever structure. When the impactor moves to the collision point, the lever structure can amplify the impact force and generate an upward component force in each collision. As the collision continues, the component forces are superimposed to form a continuous lift, which is transmitted to the main drive shaft through the transmission structure, thereby driving the attitude adjustment nozzle and propeller components of the turntable. In this process, various sensors continuously collect speed, torque and temperature operating parameters and feed them back to the central control unit, and analyze the received data in real time. Through the preset threshold judgment and fault diagnosis algorithm, once it is detected that the actual operating parameters exceed the preset normal range, the corresponding adjustment mechanism is immediately triggered according to the built-in adjustment strategy.

2. The aerospace multi-directional power transfer machine driving method according to claim 1, characterized in that: In the power unit preconfiguration step, the power unit includes an electric motor and a small turbine engine, the number of the power units is at least three, and the spatial layout thereof determines the angular interval between the output shafts of each power unit according to the number of the power units.

3. The aerospace multi-directional power transfer machine driving method according to claim 1, characterized in that: In the target direction determination and power distribution step, the central control unit compares and analyzes the currently acquired attitude data with the target attitude to be achieved based on the preset space vector decomposition algorithm combined with the trigonometric function relationship. Specifically, the target attitude transformation vector of the aircraft is The power output direction vector of power unit i is The power output capacity coefficient of power unit i is K i , the power distribution ratio factor R of the i-th power unit i The calculation formula is: Where m is the total number of power units, K j Represents the power output capacity coefficient of power unit j.

4. The aerospace multi-directional power transfer machine driving method according to claim 1, characterized in that: In the steering adjustment and power coupling step, the central control unit sends an angle adjustment instruction to the steering adjustment mechanism according to the target direction information. After the steering adjustment mechanism receives the instruction, the electric push rod performs telescopic movement according to the preset movement law. Specifically, the target angle deviation vector of the main drive shaft is The arm length of the electric push rod i in the steering adjustment mechanism is L i , the driving efficiency coefficient of the electric push rod i is η i , driving torque M of electric push rod i i The calculation formula is: in, is the unit vector of the action direction of electric push rod i, p is the total number of electric push rods, M total The total torque required to drive the main drive shaft to reach the target angle is calculated to ensure that each electric push rod drives the components to rotate with precise torque to adjust the angle of the main drive shaft.

5. The aerospace multi-directional power transfer machine driving method according to claim 1, characterized in that: In the energy conversion and management step, in the case where excess mechanical energy needs to be stored, energy transmission is achieved with the help of a specific integrated gear transmission and hydraulic transmission combination structure. The excess mechanical energy on the main drive shaft and the output shaft of each power unit is initially transmitted and adapted to the speed and torque through the gear transmission, and a hydraulic pump is used to convert the mechanical energy into hydraulic energy, which is transmitted to a container containing a special energy storage medium through a hydraulic pipeline. The hydraulic motor converts the hydraulic energy back into mechanical energy and inputs it into the energy storage medium. When the energy storage medium receives the action of mechanical energy, a positive reversible chemical reaction occurs based on its internal chemical bond energy change mechanism, thereby realizing the conversion of mechanical energy into chemical energy, and the progress of the chemical reaction in the energy storage medium and the chemical energy storage capacity parameters are detected in real time, and the data is transmitted to the central control unit, and the mechanical energy transmission link and the chemical reaction process are regulated by the control algorithm.

6. The aerospace multi-directional power transfer machine driving method according to claim 5, characterized in that: In the energy conversion and management step, the mechanical energy transfer link and the chemical reaction process are regulated by the control algorithm. Specifically, the excess mechanical energy flow density that can be collected in the transfer system at a certain moment is ρ E , the microstructure activity coefficient of the energy storage medium is α(S), the contact area between the energy storage medium and the mechanical energy transmission component is A, then the total amount of chemical energy E stored in the energy storage medium in the time interval Δt is chem The calculation formula is: chem =ρ E ·α(S)·A·Δt. Through this formula, it is possible to accurately quantify how much mechanical energy can be successfully converted and stored in the energy storage medium within a certain period of time, so that the energy conversion process can be precisely controlled according to the actual system operating status and the characteristics of the energy storage medium.

7. The aerospace multi-directional power transfer machine driving method according to claim 1, characterized in that: In the energy conversion and management step, when power needs to be supplemented or energy needs to be released, the central control unit triggers the reverse chemical reaction in the energy storage medium based on the real-time system status information and the overall energy demand fed back by each sensor, and applies an electrical stimulation signal according to preset trigger parameters through the power supply and control circuit connected to the energy storage medium, so as to prompt the energy storage medium to release the stored chemical energy and convert it into mechanical energy. The converted mechanical energy is coupled to the main drive shaft or the output shaft of the corresponding power unit again through the combined structure of integrated gear transmission and hydraulic transmission, so as to realize power supplement to the multi-directional power transfer machine and assist the transfer machine to complete the corresponding power output operation.

8. The aerospace multi-directional power transfer machine driving method according to claim 1, characterized in that: In the power output and dynamic monitoring adjustment step, if the actual operating parameters are detected to be beyond the preset normal range, the corresponding adjustment mechanism is triggered according to the built-in adjustment strategy. The theoretical optimal power output power of power unit i is set to P oi , the actual monitored power output is P i , the power adjustment coefficient β of power unit i i The calculation formula is: By calculating this coefficient, the degree of deviation between the actual operating state of the power unit and the ideal state can be intuitively reflected. i If the value is greater than 1, it means that the current actual output power is lower than the theoretical optimal value, and there is a problem of insufficient power. i If the value is less than 1, it means that the power unit is in an overload condition. Based on this coefficient, the central control unit can accurately determine whether each power unit is working normally, as well as the specific circumstances of deviation from the normal state, and then take corresponding adjustment measures.

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