CN117034456A - Rocket flight trajectory evaluation method and device, storage medium and electronic equipment - Google Patents
Rocket flight trajectory evaluation method and device, storage medium and electronic equipment Download PDFInfo
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Abstract
The application provides a flight trajectory evaluation method and device of a rocket, a storage medium and electronic equipment, and relates to the field of trajectory planning. The electronic equipment acquires a simulated flight track of a flight object; determining at least one ground sensitive object with collision risk with the flying object according to the projection track of the simulated flying track; and determining the safety of the simulated flight trajectory according to the at least one ground sensitive object. In this way, compared with the prior art that the direction without the sensitive object or the personnel is qualitatively selected as the transmitting direction, the method and the device utilize at least one ground sensitive object determined by the projection track of the simulated flight track to more accurately and effectively evaluate the safety of the simulated flight track.
Description
Technical Field
The application relates to the field of trajectory planning, in particular to a flight trajectory evaluation method and device of a rocket, a storage medium and electronic equipment.
Background
Safety is always an absolute first condition of space launching, and in order to ensure smooth launching process, the most ideal launching field for site selection should be located in a vast and rare area. Furthermore, rocket launches involve certain risks and instability factors. The dropping of debris may present a significant risk to surrounding structures and personnel upon failure of the firing or the occurrence of an accident. Thus, the direction without sensitive objects or persons is usually chosen as the emission direction.
Therefore, through comprehensive safety analysis of the flight trajectory, potential risks can be predicted and identified better, and corresponding measures can be taken to ensure the safety of the launching process. However, it has been found after investigation that there is still a lack of effective methods for safety assessment of the post-launch flight trajectory.
Disclosure of Invention
In order to overcome at least one defect in the prior art, the application provides a flight trajectory evaluation method and device of a rocket, a storage medium and electronic equipment, which specifically comprise the following steps:
in a first aspect, the present application provides a method for estimating a flight trajectory of a rocket, the method comprising:
obtaining a simulated flight track of a flight object;
determining at least one ground sensitive object with collision risk with the flying object according to the projection track of the simulated flying track;
and determining the safety of the simulated flight trajectory according to the at least one ground sensitive object. With reference to the optional implementation manner of the first aspect, the determining, according to the at least one ground sensitive object, safety of the simulated flight trajectory includes:
determining the distance between each ground sensitive object and the projection track;
according to the distance between each ground sensitive object and the projection track, determining the nearest distance as a target sensitive object;
and determining the safety of the simulated flight trajectory according to the distance between the target sensitive object and the projection trajectory.
With reference to the optional implementation manner of the first aspect, the determining a distance between each ground sensitive object and the projection trajectory includes:
for each ground-sensitive object, determining a shortest physical distance between the ground-sensitive object and the projected trajectory;
converting the shortest physical distance to an equivalent distance;
and taking the equivalent distance as the distance between the ground sensitive object and the projection track.
With reference to the optional implementation manner of the first aspect, the expression for converting the shortest physical distance into an equivalent distance is:
d′＝d/p；
where d' represents the equivalent distance, d represents the shortest physical distance, and p represents the scaling.
With reference to the optional implementation manner of the first aspect, the determining the safety of the simulated flight trajectory according to the distance between the target sensitive object and the projected trajectory includes:
according to the distance between the target sensitive object and the flight track, calculating the flight track environment safety coefficient, wherein the expression is as follows:
S＝(D min /D threshold )*(1-p)*(f)；
wherein S represents the environmental safety factor, D min Representing the distance between the target sensitive object and the flight trajectory, D threshold Representing the minimum safety distance, p represents the probability that the simulated flight trajectory passes through the target sensitive object, and f represents the probability that the target sensitive object is impacted;
and if the environmental safety coefficient is smaller than a preset threshold value, determining that the safety of the flight track meets the requirement.
With reference to the optional implementation manner of the first aspect, the determining, according to the projected trajectory of the simulated flight trajectory, at least one ground-sensitive object that has an impact risk with the flight object includes:
according to the projection track, determining risk areas which are distributed along the projection track and are positioned at two sides of the projection track, wherein the width of the risk areas is in positive correlation with the projection height corresponding to the projection track;
at least one ground-sensitive object located within the risk area is determined to be a ground-sensitive object that is at risk of impact with the flying object.
With reference to the optional implementation manner of the first aspect, the acquiring a simulated flight trajectory of the flight object includes:
obtaining a simulation model required by the flying object in the flying process;
and simulating the flight process of the simulation model in a three-dimensional scene according to the configured simulation parameters to obtain the simulation flight track, wherein the three-dimensional scene is an equivalent scene of a real physical scene.
In a second aspect, the present application provides a flight trajectory evaluation device for a rocket, the device comprising:
the track simulation module is used for acquiring a simulated flight track of the flight object;
the object screening module is used for determining at least one ground sensitive object with collision risk with the flying object according to the projection track of the simulated flying track;
and the safety evaluation module is used for determining the safety of the simulated flight track according to the at least one ground sensitive object.
With reference to the optional implementation manner of the second aspect, the security evaluation module is further specifically configured to:
determining the distance between each ground sensitive object and the projection track;
according to the distance between each ground sensitive object and the projection track, determining the nearest distance as a target sensitive object;
and determining the safety of the simulated flight trajectory according to the distance between the target sensitive object and the projection trajectory.
With reference to the optional implementation manner of the second aspect, the security evaluation module is further specifically configured to:
for each ground-sensitive object, determining a shortest physical distance between the ground-sensitive object and the projected trajectory;
converting the shortest physical distance to an equivalent distance;
and taking the equivalent distance as the distance between the ground sensitive object and the projection track.
With reference to the optional implementation manner of the second aspect, the expression for converting the shortest physical distance into an equivalent distance is:
d′＝d/p；
where d' represents the equivalent distance, d represents the shortest physical distance, and p represents the scaling.
With reference to the optional implementation manner of the second aspect, the object screening module is further specifically configured to:
according to the projection track, determining risk areas which are distributed along the projection track and are positioned at two sides of the projection track, wherein the width of the risk areas is in positive correlation with the projection height corresponding to the projection track;
at least one ground-sensitive object located within the risk area is determined to be a ground-sensitive object that is at risk of impact with the flying object.
With reference to the optional implementation manner of the second aspect, the security evaluation module is further specifically configured to:
according to the distance between the target sensitive object and the flight track, calculating the flight track environment safety coefficient, wherein the expression is as follows:
S＝(D min /D threshold )*(1-p)*(f)；
wherein S represents the environmental safety factor, D min Representing the distance between the target sensitive object and the flight trajectory, D threshold Representing the minimum safety distance, p represents the probability that the simulated flight trajectory passes through the target sensitive object, and f represents the probability that the target sensitive object is impacted;
and if the environmental safety coefficient is smaller than a preset threshold value, determining that the safety of the flight track meets the requirement.
With reference to the optional implementation manner of the second aspect, the trajectory simulation module is further specifically configured to:
obtaining a simulation model required by the flying object in the flying process;
and simulating the flight process of the simulation model in a three-dimensional scene according to the configured simulation parameters to obtain the simulation flight track, wherein the three-dimensional scene is an equivalent scene of a real physical scene.
In a third aspect, the present application further provides a storage medium storing a computer program, where the computer program when executed by a processor implements a method for estimating a flight trajectory of the rocket.
In a fourth aspect, the present application further provides an electronic device, where the electronic device includes a processor and a memory, where the memory stores a computer program, and when the computer program is executed by the processor, the method for estimating a flight trajectory of the rocket is implemented.
Compared with the prior art, the application has the following beneficial effects:
the application provides a flight trajectory evaluation method and device of a rocket, a storage medium and electronic equipment. The electronic equipment acquires a simulated flight track of a flight object; determining at least one ground sensitive object with collision risk with the flying object according to the projection track of the simulated flying track; and determining the safety of the simulated flight trajectory according to the at least one ground sensitive object. In this way, compared with the prior art that the direction without the sensitive object or the personnel is qualitatively selected as the transmitting direction, the method and the device utilize at least one ground sensitive object determined by the projection track of the simulated flight track to more accurately and effectively evaluate the safety of the simulated flight track.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the embodiments will be briefly described below, it being understood that the following drawings only illustrate some embodiments of the present application and therefore should not be considered as limiting the scope, and other related drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a flow chart of a method for evaluating the flight trajectory of a rocket provided by an embodiment of the application;
FIG. 2 is a schematic diagram of a risk area according to an embodiment of the present application;
FIG. 3 is a schematic diagram of a probability of traversing according to an embodiment of the present application;
FIG. 4 is a schematic diagram of the impact probability according to the embodiment of the present application;
FIG. 5 is a schematic structural diagram of a rocket flight trajectory evaluation device according to an embodiment of the present application;
fig. 6 is a schematic structural diagram of an electronic device according to an embodiment of the present application.
Icon: 101-rocket; 102-simulating a flight trajectory; 103-projection trajectory; 104-boundary; 201-impact area; 202-object region; 301-a track simulation module; 302-an object screening module; 303-a security assessment module; 401-memory; 402-a processor; 403-a communication unit; 404-system bus.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present application more apparent, the technical solutions of the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present application, and it is apparent that the described embodiments are some embodiments of the present application, but not all embodiments of the present application. The components of the embodiments of the present application generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the application, as presented in the figures, is not intended to limit the scope of the application, as claimed, but is merely representative of selected embodiments of the application. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
It should be noted that: like reference numerals and letters denote like items in the following figures, and thus once an item is defined in one figure, no further definition or explanation thereof is necessary in the following figures.
In the description of the present application, it should be noted that the terms "first," "second," "third," and the like are used merely to distinguish between descriptions and are not to be construed as indicating or implying relative importance. Furthermore, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one … …" does not exclude the presence of other like elements in a process, method, article, or apparatus that comprises the element.
Based on the above statement, as described in the background art, by performing comprehensive safety analysis on the flight trajectory, potential risks can be better predicted and identified, and corresponding measures can be taken to ensure the safety of the launching process. However, research has found that there is still a lack of effective methods for safety assessment of the flight trajectory after launch.
In view of this, the present embodiment provides a flight trajectory evaluation method of a rocket. In the method, electronic equipment acquires a simulated flight trajectory of a flight object; determining at least one ground sensitive object with collision risk with the flying object according to the projection track of the simulated flying track; and determining the safety of the simulated flight trajectory according to the at least one ground sensitive object. In this way, compared with the prior art that the direction without the sensitive object or the personnel is qualitatively selected as the transmitting direction, the method and the device utilize at least one ground sensitive object determined by the projection track of the simulated flight track to more accurately and effectively evaluate the safety of the simulated flight track.
In this embodiment, the flying object is not limited to a rocket, and may be various types of aircraft such as an airplane, an unmanned plane, and a helicopter. Among them, rocket is a high-speed vertical takeoff spacecraft commonly used for delivering satellites, astronauts or other loads into space. An aircraft is an aircraft with wings and fixed wings, which usually flies in the atmosphere, not only for commercial and civil air transportation, but also for military reconnaissance, rescue missions, etc. Unmanned aerial vehicle is the aircraft that does not have the driver to control then, is widely used in fields such as aerial photography, unmanned aerial vehicle express delivery, agricultural spraying. A helicopter is an aircraft which can take off and land vertically and fly back and forth, and is commonly used for medical rescue, forestry, police and military tasks.
In this embodiment, the ground-sensitive object includes a ground-sensitive area and ground-sensitive facilities. The ground sensitive area comprises a densely populated area, a low-altitude flight area, mountains of an important area and a military base area. The ground sensitive facilities include residential buildings, office buildings, government units, reservoirs, lakes, schools, high-voltage lines, bridges, scientific research institutions, base stations, railways and the like.
Further, the electronic device in the present embodiment may be, but is not limited to, a mobile terminal, a tablet computer, a laptop computer, a desktop computer, a server, or the like. In the case of a server, the server may be a single server or a group of servers. The server farm may be centralized or distributed (e.g., the servers may be distributed systems). In some embodiments, the server may be local or remote to the user terminal. In some embodiments, the server may be implemented on a cloud platform; by way of example only, the Cloud platform may include a private Cloud, public Cloud, hybrid Cloud, community Cloud (Community Cloud), distributed Cloud, cross-Cloud (Inter-Cloud), multi-Cloud (Multi-Cloud), or the like, or any combination thereof. In some embodiments, the server may be implemented on an electronic device having one or more components.
In order to make the solution provided by this embodiment clearer, the following details of the steps of the method are described with reference to fig. 1. It should be understood that the operations of the flow diagrams may be performed out of order and that steps that have no logical context may be performed in reverse order or concurrently. Moreover, one or more other operations may be added to or removed from the flow diagrams by those skilled in the art under the direction of the present disclosure. As shown in fig. 1, the method includes:
s101, acquiring a simulated flight trajectory of a flight object.
Taking a rocket as an example, the rocket launching process refers to the process from the ignition of a launch pad to the beginning of entering an orbit. In the rocket launching process, the problems of simulating the dynamics, thermodynamics and structural characteristics of the rocket in the atmosphere, controlling the attitude and navigating after entering the orbit and the like are required. It has been found that in conventional simulation methods, numerical simulation methods such as numerical calculation and computational fluid dynamics methods, and simulation methods based on physical models such as multi-body dynamics and particle tracking methods are generally employed. However, the methods have the problems of large calculation amount, long calculation time, low precision, difficult verification of simulation results and the like, and limit the wide application of the methods in practical application.
Therefore, the existing rocket launching process simulation method has certain limitation in calculation amount and precision. For example, numerical computation and computational fluid dynamics methods typically require a significant amount of computational resources and time, failing to meet the requirements of real-time simulation; the accuracy of the multi-body dynamics and particle tracking method is limited to a certain extent when the rocket is affected by aerodynamic force and thermodynamics, and the motion trail and gesture of the rocket cannot be accurately predicted. In view of the above, S101 of the present embodiment may include the following implementations:
s101-1, obtaining a simulation model required in the flight process of the flying object.
S101-2, simulating the flight process of the simulation model in a three-dimensional scene according to the configured simulation parameters to obtain a simulation flight track, wherein the three-dimensional scene is an equivalent scene of a real physical scene.
Illustratively, continuing with rocket launch as an example, the STK (Satellite Tool Kit, satellite kit) provides an interface for modeling and setting various parameters during rocket launch, while also providing a computational interface for algorithm simulation. Cesium is used as an open source JavaScript library of the 3D, 2D and 2.5D visualization engines, and can be used for rendering the STK model and updating the simulation result in real time; and a data interface of the simulation result is also provided, so that the simulation result can be visualized and exported. Therefore, cesium can call the function and the method of STK through JavaScript interface, realize the depth fusion of the two.
In the specific operation, STK software can be adopted to build a three-dimensional model of the rocket launching process, including various elements such as rocket, ground, atmosphere and the like; and configuring various parameters of the rocket, such as speed, angle, quality and the like. Rendering the STK model by using a Cesium visualization engine to generate a vivid three-dimensional scene and realize dynamic update. The STK and Cesium are used for simulating the problems of motion track, attitude control, navigation and the like of the rocket in the lift-off process through a simulation algorithm, so that the simulation precision and instantaneity are improved. The method can also realize simulation of various different scenes, including scenes of different planets such as the earth, the moon, the Mars and the like. The data interfaces provided by the STK and the Cesium can realize the functions of visualization of simulation results, data export and the like, and facilitate subsequent analysis and processing by users. In conclusion, by combining the STK and the Cesium, the simulation flight track of the rocket in the real physical environment can be realized.
It is worth noting that the mass center of the rocket changes along with the consumption of fuel and the separation of the booster during the lift-off process of the rocket. In the embodiment, the motion trail of the mass center of the rocket is taken as a simulated flight trail. The centroid calculation formula is as follows:
where X, Y, Z denote the position of the rocket's centroid in the X, Y, and Z axes, respectively, m1, m2, m3, & gt, mn denote the mass of each portion of the object, X1, X2, X3, & gt, xn, Y1, Y2, Y3, & gt, yn, Z1, Z2, Z3, & gt, zn denote the position of each portion of the object in the X, Y, and Z axes, respectively.
With reference to the description of the simulated flight path in the foregoing embodiment, with continued reference to fig. 1, the flight path evaluation method of the rocket provided in this embodiment further includes:
s102, determining at least one ground sensitive object with collision risk with the flying object according to the projection track of the simulated flying track.
In this regard, studies have found that when an accident occurs at a higher location on a flying object, the greater the range of damage it generates, and therefore, the altitude of the flying object needs to be considered when determining at least one ground-sensitive object that is at risk of striking the flying object. In view of this finding, alternative embodiments of S102 include:
s102-1, determining risk areas distributed along the projection track and located on two sides of the projection track according to the projection track.
Wherein the width of the risk area is positively correlated with the projection height corresponding to the projection trajectory.
S102-2, determining at least one ground sensitive object positioned in the risk area as the ground sensitive object with collision risk with the flying object.
Illustratively, the rocket is continued. Fig. 2 shows a simulated flight trajectory 102 of the rocket 101, a projected trajectory 103 of the simulated flight trajectory 102, and boundaries 104 located on both sides of the projected trajectory 103, wherein a region defined between the boundaries 104 on both sides of the projected trajectory 103 and the projected trajectory 103 is a risk region in the present embodiment. It can be seen that as the flying height of rocket 101 increases, the risk areas on both sides of projected trajectory 103 also increase simultaneously. At least one ground-sensitive object located within the risk area is determined to be a ground-sensitive object that is at risk of collision with the flying object based on the risk area distributed along the projected trajectory 103. The ground sensitive object comprises a ground risk area and ground sensitive facilities, the judgment of the ground sensitive object can be obtained according to manual labeling, and the ground sensitive object can also be obtained through further processing of satellite remote sensing images, such as denoising, contour recognition, optimization and the like.
By way of example, assuming a height of the centroid at rest of the rocket of 10m and a flying height of the rocket of h, the distance l between the boundary of the risk zone and the projected trajectory is calculated as:
x＝lg h
wherein, I max Representing the maximum distance between the boundary of the risk zone and the projected trajectory, h representing the centroid height of the rocket, a representing the fine tuning coefficient, being a positive integer greater than 0, the specific value being determined by the specific rocket model, a=2 for the simulated rocket in the example above.
S103, determining the safety of the simulated flight trajectory according to the at least one ground sensitive object.
In this embodiment, the target sensitive object that is most threatened by the flying object is determined from a plurality of ground sensitive facilities, so as to determine the security of the simulated flight trajectory. Alternative embodiments of S103 include:
s103-1, determining the distance between each ground sensitive object and the projection track.
It is worth to say that the shorter the distance between the ground sensitive object and the projection track in the ideal state, the greater the threat degree of the flying object. However, as described in the above embodiment, the width of the risk area is positively correlated with the projection height corresponding to the projection trajectory, and an increase in the size of the risk area may cause the distance between the ground-sensitive object and the projection trajectory to also gradually increase. In order to compare the distance between the ground-sensitive object and the projection track under the same scale, the distance between the ground-sensitive object and the projection track in the present embodiment is an equivalent distance. Thus, in an alternative embodiment, for each ground-sensitive object, the electronic device determines the shortest physical distance between the ground-sensitive object and the projected trajectory; converting the shortest physical distance into an equivalent distance; the equivalent distance is taken as the distance between the ground sensitive object and the projection track.
Wherein the expression for converting the shortest physical distance into an equivalent distance is:
d′＝d/p；
where d' represents the equivalent distance, d represents the shortest physical distance, and p represents the scaling.
Illustratively, assume that the shortest distance between the boundary of the risk area and the projected trajectory is l min The distance between the boundary of the risk area corresponding to the current position of the nth ground sensitive object and the projection track is l n The scaling corresponding to the nth ground sensitive object p=l n /l min . Thus, the physical distances of different width locations in the risk area are scaled to the same scale by the scaling ratio for comparison.
S103-2, determining the nearest distance as a target sensitive object according to the distance between each ground sensitive object and the projection track.
S103-3, determining the safety of the simulated flight trajectory according to the distance between the target sensitive object and the projection trajectory.
In an alternative embodiment, the electronic device may calculate, according to a distance between the target sensitive object and the flight trajectory, a flight trajectory environmental safety coefficient, where the expression is:
S＝(1-D min /D threshold )*(1-p)*(f)；
wherein S represents an environmental safety factor, D min Representing the distance between the target sensitive object and the flight path, D threshold Represents the minimum safe distance, p represents the probability that the simulated flight path passes through the target sensitive object, and f representsProbability of the target sensitive object being impacted;
if the environmental safety coefficient is smaller than a preset threshold value, the electronic equipment determines that the safety of the simulated flight trajectory meets the requirement.
For the probability that the simulated flight trajectory passes through the target sensitive object, in the implementation, the included angle between the current flight direction of the flight object and the target sensitive object is used as the probability that the simulated flight trajectory passes through the target sensitive object. As shown in FIG. 3, Q in the figure 1 The point represents the projection point of the current flight position of the target sensitive object in the projection track, Q 2 Representing the current position of the target sensitive object,and representing the current flight direction of the target sensitive object, wherein the included angle between the current flight direction of the flight object and the target sensitive object is theta, and p=theta/180 degrees. Thus, the smaller the value of p, the greater the probability that the flying object is now involved in an accident, and the target sensitive object is traversed.
As for the probability of the target sensitive object being impacted, in the present embodiment, the ratio between the impact area 201 of the target sensitive object and the flying object is taken as the probability of the target sensitive object being impacted. As shown in fig. 4, assume that the distance between the boundary of the risk area corresponding to the current altitude h of the flying object and the projected trajectory is l t Then use l t A circular area of radius is taken as an impact area 201, and the area is M 1 . If the target sensitive object corresponding region is the object region 202, the area is M 2 F=m 2 /M 1 . Thus, the smaller the value of p, the less the probability that the target sensitive object will be impacted, meaning that the flying target is now involved in an accident.
In the three aspects, the smaller S means that the probability of the target sensitive object being impacted is lower, and when S is smaller than a preset threshold value, the safety of the simulated flight trajectory is satisfied. Otherwise, the simulated flight trajectory has higher safety risk, and the flight trajectory of the flying object needs to be re-simulated. Thus, the simulation flight track meeting the safety requirement is obtained through multiple rounds of simulation.
Based on the same inventive concept as the rocket flight trajectory evaluation method provided by the embodiment, the embodiment also provides a rocket flight trajectory evaluation device. The flight path evaluation device of the rocket comprises at least one software functional module which can be stored in a memory or solidified in an electronic device in the form of software. A processor 402 in the electronic device is used to execute executable modules stored in the memory 401. For example, a software function module and a computer program included in the rocket flight path evaluation device. Referring to fig. 5, functionally divided, the flight trajectory evaluation device of the rocket may include:
the track simulation module 301 is configured to obtain a simulated flight track of a flight object;
the object screening module 302 is configured to determine at least one ground sensitive object that has an impact risk with the flying object according to the projection trajectory of the simulated flying trajectory;
the safety evaluation module 303 is configured to determine the safety of the simulated flight path according to the at least one ground sensitive object.
In this embodiment, the trajectory simulation module 301 is used to implement step S101 in fig. 1, the object screening module 302 is used to implement step S102 in fig. 1, and the security evaluation module 303 is used to implement step S103 in fig. 1. Thus, reference is made to the detailed description of the corresponding steps for a detailed description of the modules. Furthermore, it should be noted that, since the method for evaluating the flight trajectory of the rocket has the same inventive concept, the modules described above can also be used for implementing other steps or sub-steps of the method, and the implementation is not limited in detail.
In addition, functional modules in the embodiments of the present application may be integrated together to form a single part, or each module may exist alone, or two or more modules may be integrated to form a single part.
It should also be appreciated that the above embodiments, if implemented in the form of software functional modules and sold or used as a stand-alone product, may be stored on a computer readable storage medium. Based on this understanding, the technical solution of the present application may be embodied essentially or in a part contributing to the prior art or in a part of the technical solution, in the form of a software product stored in a storage medium, comprising several instructions for causing a computer device (which may be a personal computer, a server, a network device, etc.) to perform all or part of the steps of the method according to the embodiments of the present application.
Therefore, the present embodiment also provides a storage medium storing a computer program which, when executed by a processor, implements the flight trajectory evaluation method of the rocket provided by the present embodiment. The storage medium may be a usb disk, a removable hard disk, a Read-Only Memory (ROM), a random access Memory (RAM, random Access Memory), a magnetic disk, or an optical disk, or other various media capable of storing program codes.
The embodiment provides an electronic device. As shown in fig. 6, the electronic device may include a processor 402 and a memory 401. The memory 401 stores a computer program, and the processor reads and executes the computer program corresponding to the above embodiment in the memory 401, thereby realizing the flight trajectory evaluation method of the rocket provided in the present embodiment.
With continued reference to fig. 5, the electronic device further comprises a communication unit 403. The memory 401, the processor 402, and the communication unit 403 are electrically connected to each other directly or indirectly through a system bus 404 to realize data transmission or interaction.
The memory 401 may be an information recording device based on any electronic, magnetic, optical or other physical principle, for recording execution instructions, data, etc. In some embodiments, the memory 401 may be, but is not limited to, volatile memory, non-volatile memory, storage drives, and the like.
In some embodiments, the volatile memory may be random access memory (Random Access Memory, RAM); in some embodiments, the non-volatile Memory may be Read Only Memory (ROM), programmable ROM (Programmable Read-Only Memory, PROM), erasable ROM (Erasable Programmable Read-Only Memory, EPROM), electrically erasable ROM (Electric Erasable Programmable Read-Only Memory, EEPROM), flash Memory, or the like; in some embodiments, the storage drive may be a magnetic disk drive, a solid state disk, any type of storage disk (e.g., optical disk, DVD, etc.), or a similar storage medium, or a combination thereof, etc.
The communication unit 403 is used for transmitting and receiving data through a network. In some embodiments, the network may include a wired network, a wireless network, a fiber optic network, a telecommunications network, an intranet, the internet, a local area network (Local Area Network, LAN), a wide area network (Wide Area Network, WAN), a wireless local area network (Wireless Local Area Networks, WLAN), a metropolitan area network (Metropolitan Area Network, MAN), a wide area network (Wide Area Network, WAN), a public switched telephone network (Public Switched Telephone Network, PSTN), a bluetooth network, a ZigBee network, a near field communication (Near Field Communication, NFC) network, or the like, or any combination thereof. In some embodiments, the network may include one or more network access points. For example, the network may include wired or wireless network access points, such as base stations and/or network switching nodes, through which one or more components of the service request processing system may connect to the network to exchange data and/or information.
The processor 402 may be an integrated circuit chip with signal processing capabilities and may include one or more processing cores (e.g., a single-core processor or a multi-core processor). By way of example only, the processors may include a central processing unit (Central Processing Unit, CPU), an application specific integrated circuit (Application Specific Integrated Circuit, ASIC), a special instruction set Processor (Application Specific Instruction-set Processor, ASIP), a graphics processing unit (Graphics Processing Unit, GPU), a physical processing unit (Physics Processing Unit, PPU), a digital signal Processor (Digital Signal Processor, DSP), a field programmable gate array (Field Programmable Gate Array, FPGA), a programmable logic device (Programmable Logic Device, PLD), a controller, a microcontroller unit, a reduced instruction set computer (Reduced Instruction Set Computing, RISC), a microprocessor, or the like, or any combination thereof.
It will be appreciated that the configuration shown in fig. 5 is merely illustrative, and that the electronic device may have more or fewer components than shown in fig. 5, or may have a different configuration than shown in fig. 5. Further, the components shown in FIG. 5 may be implemented in hardware, software, or a combination thereof.
It should be understood that the apparatus and method disclosed in the above embodiments may be implemented in other manners. The apparatus embodiments described above are merely illustrative, for example, of the flowcharts and block diagrams in the figures that illustrate the architecture, functionality, and operation of possible implementations of apparatus, methods and computer program products according to various embodiments of the present application. In this regard, each block in the flowchart or block diagrams may represent a module, segment, or portion of code, which comprises one or more executable instructions for implementing the specified logical function(s). It should also be noted that in some alternative implementations, the functions noted in the block may occur out of the order noted in the figures. For example, two blocks shown in succession may, in fact, be executed substantially concurrently, or the blocks may sometimes be executed in the reverse order, depending upon the functionality involved. It will also be noted that each block of the block diagrams and/or flowchart illustration, and combinations of blocks in the block diagrams and/or flowchart illustration, can be implemented by special purpose hardware-based systems which perform the specified functions or acts, or combinations of special purpose hardware and computer instructions.
The above description is merely illustrative of various embodiments of the present application, but the scope of the present application is not limited thereto, and any person skilled in the art can easily think about variations or substitutions within the scope of the present application, and the application is intended to be covered by the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. A method of evaluating a flight trajectory of a rocket, the method comprising:
obtaining a simulated flight track of a flight object;
determining at least one ground sensitive object with collision risk with the flying object according to the projection track of the simulated flying track;
and determining the safety of the simulated flight trajectory according to the at least one ground sensitive object.
2. A method of assessing a flight trajectory of a rocket as claimed in claim 1, wherein said determining the safety of said simulated flight trajectory from said at least one ground sensitive object comprises:
determining the distance between each ground sensitive object and the projection track;
according to the distance between each ground sensitive object and the projection track, determining the nearest distance as a target sensitive object;
and determining the safety of the simulated flight trajectory according to the distance between the target sensitive object and the projection trajectory.
3. A method of assessing a flight trajectory of a rocket as claimed in claim 2, wherein said determining the distance between each ground-sensitive object and said projected trajectory comprises:
for each ground-sensitive object, determining a shortest physical distance between the ground-sensitive object and the projected trajectory;
converting the shortest physical distance to an equivalent distance;
and taking the equivalent distance as the distance between the ground sensitive object and the projection track.
4. A rocket flight trajectory evaluation method according to claim 3 wherein said expression for converting said shortest physical distance into an equivalent distance is:
d′＝d/p；
where d' represents the equivalent distance, d represents the shortest physical distance, and p represents the scaling.
5. A method of assessing a flight trajectory of a rocket as claimed in claim 2, wherein said determining the safety of said simulated flight trajectory as a function of the distance between said target sensitive object and said projected trajectory comprises:
according to the distance between the target sensitive object and the flight track, calculating the flight track environment safety coefficient, wherein the expression is as follows:
S＝(D min /D threshold )*(1-p)*(f)；
wherein S represents the environmental safety factor, D min Representing the distance between the target sensitive object and the flight trajectory, D threshold Representing the minimum safety distance, p represents the probability that the simulated flight trajectory passes through the target sensitive object, and f represents the probability that the target sensitive object is impacted;
and if the environmental safety coefficient is smaller than a preset threshold value, determining that the safety of the flight track meets the requirement.
6. A method of assessing a flight trajectory of a rocket as claimed in claim 1, wherein said determining at least one ground-sensitive object at risk of impact with said flying object from a projected trajectory of said simulated flight trajectory comprises:
according to the projection track, determining risk areas which are distributed along the projection track and are positioned at two sides of the projection track, wherein the width of the risk areas is in positive correlation with the projection height corresponding to the projection track;
at least one ground-sensitive object located within the risk area is determined to be a ground-sensitive object that is at risk of impact with the flying object.
7. A method of assessing the trajectory of a rocket as recited in claim 1, wherein said obtaining a simulated trajectory of a flying object comprises:
obtaining a simulation model required by the flying object in the flying process;
and simulating the flight process of the simulation model in a three-dimensional scene according to the configured simulation parameters to obtain the simulation flight track, wherein the three-dimensional scene is an equivalent scene of a real physical scene.
8. A flight trajectory evaluation device for a rocket, the device comprising:
the track simulation module is used for acquiring a simulated flight track of the flight object;
the object screening module is used for determining at least one ground sensitive object with collision risk with the flying object according to the projection track of the simulated flying track;
and the safety evaluation module is used for determining the safety of the simulated flight track according to the at least one ground sensitive object.
9. A storage medium storing a computer program which, when executed by a processor, implements the method of assessing the flight trajectory of a rocket according to any one of claims 1-7.
10. An electronic device comprising a processor and a memory, the memory storing a computer program which, when executed by the processor, implements the method of flight trajectory assessment of a rocket according to any one of claims 1-7.
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| CN202311000294.3A CN117034456A (en) | 2023-08-09 | 2023-08-09 | Rocket flight trajectory evaluation method and device, storage medium and electronic equipment |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN117434967A (en) * | 2023-12-18 | 2024-01-23 | 成都正扬博创电子技术有限公司 | Unmanned aerial vehicle anti-collision detection method, system, medium and equipment |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN117434967A (en) * | 2023-12-18 | 2024-01-23 | 成都正扬博创电子技术有限公司 | Unmanned aerial vehicle anti-collision detection method, system, medium and equipment |
| CN117434967B (en) * | 2023-12-18 | 2024-03-15 | 成都正扬博创电子技术有限公司 | Unmanned aerial vehicle anti-collision detection method, system, medium and equipment |
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