Detection orbit design method and system based on entering influence ball maneuvering leveraging flight

Abstract

The invention provides a detection orbit design method and system based on entering influence ball maneuver leveraging flight. The method comprises the steps that the initial position speed, the initial flight time, a leveraging target and a rendezvous target of a detector are determined; designing a flight orbit of the detector from an initial state to a leveraging target, and calculating a speed increment required by the first deep space maneuver; the detector adopts an entry influence ball maneuver leveraging method for leveraging, and the speed increment required in the leveraging process is calculated; designing a flight orbit of the detector flying from the leveraging target to the intersection target, and calculating a speed increment required by braking; and S4, optimizing the processes from the step S2 to the step S4 by adopting a genetic algorithm to obtain the detection orbit with the minimum speed increment under the determined leveraging target. The method aims at solving the problems that in the current deep space exploration orbit design, the transient constraint of a satellite exploration time window is not considered, an existing leveraging flight orbit optimization method is insufficient in universality, and engineering practice is not adapted.

Description

Technical Field

[0001] This invention relates to the field of deep space exploration, specifically to a method and system for designing exploration trajectories based on maneuvering and leveraging the influence of an impact sphere. Background Technology

[0002] Deep space exploration missions have long flight cycles and consume a lot of energy. After reaching the target celestial body, designing an energy-efficient flight trajectory that can detect multiple targets is of great significance for improving the scientific output of the mission. Gravitational flight technology can effectively reduce the velocity increment required by the probe. During the gravity assist process... Figure 2 As shown. The magnitude of the probe's velocity relative to the celestial body remains constant before and after the glide. Assuming the probe's position remains unchanged and only its velocity changes, we can obtain:

[0003]

[0004]

[0005]

[0006] In the formula: This represents the position of the detector in the reference coordinate system at the moment of leverage. The position of the celestial body at the moment of leveraging the force, in the reference coordinate system; and These represent the positions of the detector in the reference coordinate system before and after using the force; and These represent the probe's velocity in the reference coordinate system before and after using the force; The velocity of the celestial body in the reference coordinate system at the moment of leveraging; Hyperbolic overspeed as the probe approaches the lever-equipped celestial body; The hyperbolic speed increase when leaving the celestial body that is being propelled by gravity.

[0007] In situations where flight time is free and there are no other constraints, it is easy to find the optimal trajectory for leveraging gravitational pull, thereby minimizing the total velocity increment. However, in practical engineering problems, constraints such as mission time limit prevent the probe from achieving ideal results during the leveraging process. To maximize the utilization of the celestial body and obtain the ideal post-leverage velocity, thrust-assisted leveraging and aerodynamic-gravity assisted transfer technologies have been developed based on leveraging gravitational pull technology. Thrust-assisted leveraging involves applying a pulse during the leveraging process, thereby altering the post-leverage velocity. However, it involves 10 independent parameters, making the design of the leveraging trajectory complex. The principle is as follows: Figure 3 As shown. Aerodynamic-gravitational flight technology refers to the process of allowing a probe to pass through the atmosphere of a celestial body during glide, further altering the angle of velocity during the glide. This requires specific atmospheric density from the celestial body being used. The principle is as follows: Figure 4 As shown.

[0008] The above methods are mostly applicable to orbits where planets are the target for leveraging. However, satellite leveraging has different characteristics from planetary leveraging: because the time window for satellite detection is short after reaching the planetary system, satellite leveraging can theoretically be carried out at any position on the satellite's orbit, greatly increasing the degree of design freedom. It is difficult to optimize using the current maneuvering thrust leveraging flight technology at the pericenter. At the same time, many satellites have thin atmospheres, making it impossible to apply aerodynamic-leverage flight technology. This undoubtedly makes the optimization of deep-space leveraging flight orbits involving satellites more difficult.

[0009] The patent with publication number CN116541968A discloses a method for determining the optimal transfer orbit of the Earth-Moon DRO, but the optimal orbit design of this method is only applicable to dual-master celestial system and does not involve multi-target gravitational exploration.

[0010] In summary, given the problems of the existing technologies, researching a detection trajectory design method and system based on maneuvering and leveraging the influence of an impact sphere has become a critical task that urgently needs to be addressed. Summary of the Invention

[0011] To address the shortcomings of existing technologies, the purpose of this invention is to provide a method and system for designing a detection trajectory based on maneuvering and leveraging the influence of an incoming sphere.

[0012] The present invention provides a method for designing a probe trajectory based on maneuvering with the influence sphere, comprising the following steps: Step S1, determining the probe's initial position and velocity, initial flight time, the target to be leveraged, and the rendezvous target; Step S2, designing the probe's flight trajectory from the initial state to the target to be leveraged, and calculating the velocity increment required for the first deep-space maneuver; Step S3, the probe uses the maneuvering with the influence sphere to leverage the influence, and calculating the velocity increment required for the leverage process; Step S4, designing the probe's flight trajectory from the target to the rendezvous target, and calculating the velocity increment required for braking; Step S5, using a genetic algorithm to optimize the processes of steps S2 to S4, obtaining the probe trajectory with the minimum velocity increment under the determined target to leverage the influence.

[0013] Preferably, the design of the probe's flight trajectory from its initial state to the target, and the calculation of the velocity increment required for the first deep-space maneuver, includes: using the probe's initial epoch... The position and velocity at a given time are the initial states, after which... The time is for deep space maneuvering to fly towards the lever satellite, the flight time is Starting from the position and velocity of the probe at its initial epoch, a Kepler orbit recursion is performed to obtain... The time probe's heliocentric position and velocity; querying the ephemeris to read... By constantly monitoring the heliocentric position and velocity of the celestial body, the Lambert problem is solved to obtain the initial and final velocities of the probe as it flies towards the celestial body. The difference between these velocities yields the velocity increment required for the first deep-space maneuver. .

[0014] Preferably, the detector uses a leverage method by entering the influence sphere, and calculates the velocity increment required for the leverage process, including: based on the detector's position in... The hyperbolic velocity upon arrival at the boundary of the sphere influenced by the celestial body and the heliocentric velocity of the celestial body at the same instant are used to calculate the hyperbolic hyperbolic velocity; an adjustment velocity increment is then applied to adjust the hyperbolic hyperbolic velocity. The new hyperbolic overspeed was obtained; the B-plane angle was set. and leverage height Solve for the actual hyperbolic speed of the probe after it leaves the gravity-assisted celestial body and flies towards the rendezvous target; the flight time is... Query ephemeris table to read By determining the heliocentric position and velocity of the target at each rendezvous point, the Lambert problem is solved to obtain the initial and final velocities of the probe flying towards the target. The initial velocity is the ideal hyperbolic exit speed. The difference between the ideal hyperbolic exit speed and the actual hyperbolic exit speed is used to obtain the required speed increment after leveraging the hyperbolic speed. The sum of the speed increments for hyperbolic entry speed and hyperbolic exit speed is the speed increment required for the leveraging process.

[0015] Preferably, the design of the probe's flight trajectory from the lever-assisted target to the rendezvous target, and the calculation of the required braking velocity increment, includes: based on the probe's... By calculating the heliocentric velocity of the probe relative to the rendezvous target at the same instant as the heliocentric velocity of the target at the same instant, and the orbital velocity of the probe relative to the target, the required velocity increment for braking can be obtained. .

[0016] Preferably, the optimization of steps S2 to S4 using a genetic algorithm to obtain the probe trajectory with the minimum velocity increment under the target assistance includes: optimization using a MATLAB genetic algorithm function, with the objective function and variables to be optimized as follows: the optimization index is:

[0017] in, The speed increment required for the first deep-space maneuver. To adjust the speed increment required for hyperbolic overspeed, The velocity increment required to brake to the target celestial body For the barrier function, As a penalty factor;

[0018] in, To actually fly out of hyperbolic speed range, To achieve the ideal, it flew out of the hyperbola at supersonic speed; The parameters to be optimized are: in, It is the time during which the probe performs deep space maneuvers. It is the time it takes for the probe to fly toward the celestial body that will provide leverage. It is the time it takes for the probe to fly from the celestial body it is using to reach the rendezvous target. It is the probe's maneuver velocity vector that adjusts the velocity of the probe flying into the hyperbola. It is the plane angle of plane B. It is the angle of the B plane and the height of the leverage.

[0019] This invention also provides a detection trajectory design system based on maneuvering and leveraging flight upon entering an influence sphere. This system can be implemented by executing the steps of the method for designing a detection trajectory based on maneuvering and leveraging flight upon entering an influence sphere. That is, those skilled in the art can understand the method for designing a detection trajectory based on maneuvering and leveraging flight upon entering an influence sphere as a preferred embodiment of the system. The system includes: Module M1 determines the probe's initial position and velocity, initial flight time, target for leverage, and rendezvous target; Module M2 designs the probe's flight trajectory from its initial state to the target it is leveraging, and calculates the velocity increment required for the first deep-space maneuver. Module M3, the detector uses the method of leveraging the influence of the sphere to gain leverage, and calculates the velocity increment required for the leveraging process; Module M4 is used to design the probe's flight trajectory from the lever-assisted target to the rendezvous target and to calculate the required speed increment for braking. Module M5 uses a genetic algorithm to optimize the processes of modules M2, M3, and M4, obtaining the detection trajectory with the minimum velocity increment under the determined target.

[0020] Compared with existing technologies, this invention has the following advantages: This invention overcomes the shortcomings of current research that ignores practical limitations such as the characteristics of satellite gravitational pull. Under the constraints faced in practical engineering missions such as limited flight time and using celestial bodies as satellites, this invention proposes a gravitational pull flight probe trajectory design method that maneuvers upon entering the influence sphere in order to fully utilize the gravitational pull of celestial bodies. By using different satellites as gravitational pull targets and applying a genetic algorithm for probe trajectory design, this invention reduces the total velocity increment of the probe when flying to the rendezvous target, solves the optimization problem of deep space exploration trajectories, adapts to the engineering realities of deep space exploration missions, and provides a better approach for deep space exploration gravitational pull trajectory design. Attached Figure Description

[0021] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings: Figure 1 The flowchart illustrates a detection trajectory design method based on maneuvering and leveraging the influence of an incoming sphere, as provided by this invention.

[0022] Figure 2 This is a schematic diagram of the leveraging process provided in an embodiment of the present invention.

[0023] Figure 3 This is a schematic diagram of thrust-assisted flight provided in an embodiment of the present invention.

[0024] Figure 4 This is a schematic diagram of aerodynamic-assisted flight provided in an embodiment of the present invention.

[0025] Figure 5 A flowchart illustrating the detection trajectory design method based on maneuvering and leveraging flight upon entering an influence sphere, as provided in an embodiment of the present invention. Detailed Implementation

[0026] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0027] The following describes the specific implementation of this invention using the example of a probe that travels from its initial position within the Jupiter system, leveraging Ganymede to reach Europa for rendezvous. Figure 1 As shown: Step 1: Given initial conditions, determine the initial position and velocity, the initial flight time, the target to be used for leverage, and the rendezvous target.

[0028] Specifically, given the initial position and velocity vectors in the core inertial coordinate system, the start time of the flight is 4:00 AM UTC on June 30, 2036, the target for leveraging is Europa, and the rendezvous target is Ganymede.

[0029] Step 2: Design the probe to fly to Ganymede orbit and obtain the speed increment required for the first deep space maneuver.

[0030] First, convert 4:00 AM UTC on June 30, 2036 to Julian Day as... At that moment, the detector Starting from the initial position, passing through Time will be used for deep space maneuvers, flying towards Ganymede, with a flight time of [time value missing]. Starting from the position and velocity of the probe at its initial epoch, a Kepler orbit recursion is performed to obtain... The position and velocity of the time probe are determined by consulting the ephemeris table. By determining the position and velocity of Ganymede's core at specific times, the Lambert problem is solved to obtain the initial and final velocities of the probe as it flies towards the glide vehicle, thus yielding the velocity increment required for the first deep-space maneuver. .

[0031] Step 3: The probe uses the influence sphere maneuvering method to borrow force from Ganymede and obtain the velocity increment required for the borrowing process.

[0032] Based on the detector obtained in the previous stage Given the velocity of the aircraft reaching the core of Ganymede at any given moment and the velocity of Ganymede's core at that moment, calculate the hyperbolic entry hyperbolic speed. Provide a velocity increment to adjust the hyperbolic entry hyperbolic speed, thus obtaining the new hyperbolic entry hyperbolic speed, given the B-plane angle. and leverage height Then, the actual hyperbolic speed of the probe is calculated.

[0033] To ensure the probe flies directly towards Europa after leaving Ganymede, let's assume the flight path... Arrive at Europa after the appointed time, consult the ephemeris table to read... Given the position and velocity of Europa's core at any given time, solve the Lambert problem to obtain the initial and final velocities of the probe flying towards Europa. The initial velocity flying towards Europa is the ideal hyperbolic speed.

[0034] The difference between the ideal hyperbola exit speed and the actual hyperbola exit speed is used to obtain the leverage effect. The required speed increment is then adjusted, and the sum of the speed increments for the hyperbola entry speed and the hyperbola exit speed is the speed increment required for the leverage process.

[0035] This step involves maneuvering upon entering the sphere of influence. The difference between the speed after the maneuver and the speed of the celestial body being leveraged is used as the hyperbolic speed of entry. The hyperbolic speed of exiting the hyperbolic speed can be obtained using a traditional B-plane parameter leverage model. The optimization difficulty is less than that of active leverage flight and aerodynamic-leverage flight technology at the pericenter.

[0036] Step 4: Design the probe to fly from Ganymede to Europa orbit and calculate the required speed increment for braking.

[0037] After leaving the celestial body that provided the leverage, the probe flew directly toward the rendezvous target. The probe arrives at the rendezvous target after a certain time. Based on the terminal velocity of the probe flying towards the rendezvous target and the velocity required for the probe to orbit the target obtained in step three, the braking pulse is calculated. .

[0038] Step 5: Use a genetic algorithm to optimize the process from Step 2 to Step 4 to obtain the probe trajectory with the minimum velocity increment under the target of leverage.

[0039] The MATLAB genetic algorithm was used for optimization. The maximum number of iterations to terminate the algorithm was 500, the population size was 100, and other parameters were set to default. The objective function and variables to be optimized are as follows: The optimized metrics are:

[0040] In the formula: The speed increment required for the first deep-space maneuver. To adjust the speed increment required for hyperbolic overspeed, The velocity increment required to brake to the target celestial body As a penalty factor, For the barrier function:

[0041] In the formula: To actually fly out of hyperbolic speed range, To achieve the ideal of flying out of the hyperbola at supersonic speed.

[0042] The parameters to be optimized are: In the formula: It is the time during which the probe performs deep space maneuvers. It is the time it takes for the probe to fly toward the celestial body that will provide leverage. It is the time it takes for the probe to fly from the celestial body it is using to reach the rendezvous target. It is the probe's maneuver velocity vector that adjusts the velocity of the probe flying into the hyperbola. It is the angle of plane B. It is the angle of the B plane and the height of the leverage.

[0043] To compare the performance of different methods, multiple sets of initial values ​​were selected for simulation. The initial orbital parameters of the probe flying within the Jupiter system are shown in Table 1. When using the first and second sets of initial values, the time constraint for orbiting Jupiter is 100 days; due to the large distance between the initial position of the third set and the orbit of Io, the time constraint for orbiting Jupiter is 2 years. This invention was applied to a mission using Ganymede as the lever object and Europa as the rendezvous target, and the orbital design results of non-leveraging and traditional leveraging methods were compared, as shown in Table 2. The orbit obtained by this invention requires the smallest velocity increment.

[0044] Table 1. Three sets of initial orbital parameters for the probe

[0045] Table 2 Comparison of minimum speed increments for different methods

[0046] Under the constraint of flight time, a pulse is applied when entering the influence sphere of the satellite to adjust the hyperbolic overspeed and allow the velocity after leveraging to turn through an ideal angle, thereby reducing the velocity increment required for subsequent maneuvers and braking. This aims to reduce the total velocity increment required for the entire flight process of the probe, thus adapting to the engineering realities of deep space exploration missions and providing a better approach for the design of leveraging orbits for deep space exploration.

[0047] Through the above implementation steps, this embodiment proposes a method for designing a gravity-assisted flight exploration trajectory that maneuvers upon entering the influence sphere, under the constraints of limited flight time and using celestial bodies as satellites in practical engineering missions, in order to fully utilize the gravity of the celestial body. This method improves the gravity-assisted effect while meeting flight time and related constraints. Figure 5 As shown, this significantly reduces the overall speed increment requirement and fuel consumption, and can be used to guide the design of deep space exploration orbits.

[0048] This invention also provides a detection trajectory design system based on maneuvering and leveraging flight upon entering an influence sphere. This system can be implemented by executing the steps of the method for designing a detection trajectory based on maneuvering and leveraging flight upon entering an influence sphere. That is, those skilled in the art can understand the method for designing a detection trajectory based on maneuvering and leveraging flight upon entering an influence sphere as a preferred embodiment of the system. The system includes: Module M1 determines the probe's initial position and velocity, initial flight time, target for leverage, and rendezvous target; Module M2 designs the probe's flight trajectory from its initial state to the target it is leveraging, and calculates the velocity increment required for the first deep-space maneuver. Module M3, the detector uses the method of leveraging the influence of the sphere to gain leverage, and calculates the velocity increment required for the leveraging process; Module M4 is used to design the probe's flight trajectory from the lever-assisted target to the rendezvous target and to calculate the required speed increment for braking. Module M5 uses a genetic algorithm to optimize the processes of modules M2, M3, and M4, obtaining the detection trajectory with the minimum velocity increment under the determined target.

[0049] Those skilled in the art will understand that, besides implementing the system and its various devices, modules, and units provided by this invention in the form of purely computer-readable program code, the same functions can be achieved entirely through logical programming of the method steps, making the system and its various devices, modules, and units of this invention function in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers, and embedded microcontrollers. Therefore, the system and its various devices, modules, and units provided by this invention can be considered as a hardware component, and the devices, modules, and units included therein for implementing various functions can also be considered as structures within the hardware component; alternatively, the devices, modules, and units for implementing various functions can be considered as both software modules implementing the method and structures within the hardware component.

[0050] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A method for designing a detection trajectory based on maneuvering and leveraging the influence of an incoming sphere, characterized in that, include: Step S1: Determine the probe's initial position and velocity, initial flight time, lever target, and rendezvous target; Step S2: Design the probe's flight trajectory from its initial state to the target it is leveraging, and calculate the velocity increment required for the first deep-space maneuver; Step S3: The detector uses the method of leveraging the influence of the sphere to gain leverage, and calculates the velocity increment required for the leveraging process. Step S4: Design the flight trajectory of the probe from the lever target to the rendezvous target, and calculate the speed increment required for braking; Step S5: Use a genetic algorithm to optimize the process from steps S2 to S4 to obtain the probe trajectory with the minimum velocity increment under the target of leverage.

2. The detection trajectory design method based on maneuvering and leveraging flight upon entering an influence sphere, as described in claim 1, is characterized in that... The design of the probe's flight trajectory from its initial state to the target it is leveraging, and the calculation of the velocity increment required for the first deep-space maneuver, including: With the detector at the initial epoch The position and velocity at a given time are the initial states, after which... The time is for deep space maneuvering to fly towards the lever satellite, the flight time is ; Starting from the position and velocity of the probe at its initial epoch, the Kepler orbit is recursively calculated to obtain... The heliocentric position and velocity of the time probe; Query ephemeris table By constantly monitoring the heliocentric position and velocity of the celestial body, the Lambert problem is solved to obtain the initial and final velocities of the probe as it flies towards the celestial body. The difference between these velocities yields the velocity increment required for the first deep-space maneuver. .

3. The detection trajectory design method based on maneuvering and leveraging flight upon entering an influence sphere, as described in claim 1, is characterized in that... The detector uses a leverage method by entering the influence sphere, and calculates the velocity increment required for the leverage process, including: According to the detector The hyperbolic speed at the moment of arrival at the boundary of the sphere affected by the celestial body and the heliocentric speed of the celestial body at the same moment are used to calculate the hyperbolic speed. Apply a speed increment to adjust the hyperbolic overspeed. After obtaining the new hyperbolic overspeed, it flew into a hyperbolic trajectory. Set plane B angle and leverage height Solve for the actual hyperbolic flight speed of the probe; After leaving the gravity-gathering object, the probe flew towards the rendezvous target, with a flight time of [time missing]. Query ephemeris table to read By determining the heliocentric position and velocity of the target at each rendezvous point, the Lambert problem is solved to obtain the initial and final velocities of the probe flying towards the target. The initial velocity is the ideal hyperbolic speed-overspeed. The difference between the ideal hyperbola exit speed and the actual hyperbola exit speed is used to obtain the leverage effect. The required speed increment is then adjusted, and the sum of the speed increments for the hyperbola entry speed and the hyperbola exit speed is the speed increment required for the leverage process.

4. The detection trajectory design method based on maneuvering and leveraging flight upon entering an influence sphere, as described in claim 1, is characterized in that... The design of the detector, from its flight path from the lever-assisted target to the rendezvous target, calculates the required velocity increment for braking, including: According to the detector Calculate the arrival velocity of the probe relative to the rendezvous target by taking the heliocentric velocity of the probe at the same time as the heliocentric velocity of the rendezvous target. Calculate the orbital velocity of the detector relative to the intersecting target to obtain the required velocity increment for braking. .

5. The detection trajectory design method based on maneuvering and leveraging flight upon entering an influence sphere according to claim 1, characterized in that, The process of optimizing steps S2 to S4 using a genetic algorithm to obtain the detection trajectory with the minimum velocity increment under the leverage target includes: The optimization is performed using MATLAB's genetic algorithm function. The objective function and the variables to be optimized are as follows: The optimized metrics are: in, The speed increment required for the first deep-space maneuver. To adjust the speed increment required for hyperbolic overspeed, The velocity increment required to brake to the target celestial body For the barrier function, As a penalty factor; in, To actually fly out of hyperbolic speed range, To achieve the ideal of flying out of a hyperbola at supersonic speed; The parameters to be optimized are: in, It is the time during which the probe performs deep space maneuvers. It is the time it takes for the probe to fly toward the celestial body that will provide leverage. It is the time it takes for the probe to fly from the celestial body it is using to reach the rendezvous target. It is the probe's maneuver velocity vector that adjusts the velocity of the probe flying into the hyperbola. It is the plane angle of plane B. It is the angle of the B plane and the height of the leverage.

6. A detection trajectory design system based on maneuvering and leveraging the influence of an incoming sphere, characterized in that, include: Module M1 determines the probe's initial position and velocity, initial flight time, target for leverage, and rendezvous target; Module M2 designs the probe's flight trajectory from its initial state to the target it is leveraging, and calculates the velocity increment required for the first deep-space maneuver. Module M3, the detector uses the method of leveraging the influence of the sphere to gain leverage, and calculates the velocity increment required for the leveraging process; Module M4 is used to design the probe's flight trajectory from the lever-assisted target to the rendezvous target and to calculate the required speed increment for braking. Module M5 uses a genetic algorithm to optimize the processes of modules M2, M3, and M4, obtaining the detection trajectory with the minimum velocity increment under the determined target.

7. A detection trajectory design system based on maneuvering and leveraging flight upon entering an influence sphere, as described in claim 6, is characterized in that... The design of the probe's flight trajectory from its initial state to the target it is leveraging, and the calculation of the velocity increment required for the first deep-space maneuver, including: With the detector at the initial epoch The position and velocity at a given time are the initial states, after which... The time is for deep space maneuvering to fly towards the lever satellite, the flight time is ; Starting from the position and velocity of the probe at its initial epoch, the Kepler orbit is recursively calculated to obtain... The heliocentric position and velocity of the time probe; Query ephemeris table By constantly monitoring the heliocentric position and velocity of the celestial body, the Lambert problem is solved to obtain the initial and final velocities of the probe as it flies towards the celestial body. The difference between these velocities yields the velocity increment required for the first deep-space maneuver. .

8. The detection trajectory design method based on maneuvering and leveraging flight upon entering an influence sphere, as described in claim 6, is characterized in that... The detector uses a leverage method by entering the influence sphere, and calculates the velocity increment required for the leverage process, including: According to the detector The hyperbolic speed at the moment of arrival at the boundary of the sphere affected by the celestial body and the heliocentric speed of the celestial body at the same moment are used to calculate the hyperbolic speed. Apply a speed increment to adjust the hyperbolic overspeed. After obtaining the new hyperbolic overspeed, it flew into a hyperbolic trajectory. Set plane B angle and leverage height Solve for the actual hyperbolic flight speed of the probe; After leaving the gravity-gathering object, the probe flew towards the rendezvous target, with a flight time of [time missing]. Query ephemeris table to read By determining the heliocentric position and velocity of the target at each rendezvous point, the Lambert problem is solved to obtain the initial and final velocities of the probe flying towards the target. The initial velocity is the ideal hyperbolic speed-overspeed. The difference between the ideal hyperbola exit speed and the actual hyperbola exit speed is used to obtain the leverage effect. The required speed increment is then adjusted, and the sum of the speed increments for the hyperbola entry speed and the hyperbola exit speed is the speed increment required for the leverage process.

9. A detection trajectory design system based on maneuvering and leveraging flight upon entering an influence sphere, as described in claim 6, is characterized in that... The design of the detector, from its flight path from the lever-assisted target to the rendezvous target, calculates the required velocity increment for braking, including: According to the detector Calculate the arrival velocity of the probe relative to the rendezvous target by taking the heliocentric velocity of the probe at the same time as the heliocentric velocity of the rendezvous target. Calculate the orbital velocity of the detector relative to the intersecting target to obtain the required velocity increment for braking. .

10. A detection trajectory design system based on maneuvering and leveraging flight upon entering an influence sphere, as described in claim 6, is characterized in that... The process of optimizing modules M2, M3, and M4 using a genetic algorithm to determine the probe trajectory with the minimum velocity increment under the leverage target includes: The optimization is performed using MATLAB's genetic algorithm function. The objective function and the variables to be optimized are as follows: The optimized metrics are: in, The speed increment required for the first deep-space maneuver. To adjust the speed increment required for hyperbolic overspeed, The velocity increment required to brake to the target celestial body For the barrier function, As a penalty factor; in, To actually fly out of hyperbolic speed range, To achieve the ideal of flying out of a hyperbola at supersonic speed; The parameters to be optimized are: in, It is the time during which the probe performs deep space maneuvers. It is the time it takes for the probe to fly toward the celestial body that will provide leverage. It is the time it takes for the probe to fly from the celestial body it is using to reach the rendezvous target. It is the probe's maneuver velocity vector that adjusts the velocity of the probe flying into the hyperbola. It is the plane angle of plane B. It is the leverage height of plane B.

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