CN116306035A - Carrier rocket trajectory optimization method and device, electronic equipment and storage medium - Google Patents
Carrier rocket trajectory optimization method and device, electronic equipment and storage medium Download PDFInfo
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Abstract
The application discloses a carrier rocket trajectory optimization method, a carrier rocket trajectory optimization device, electronic equipment and a storage medium, and relates to the technical field of aerospace, wherein the method comprises the following steps: simulating a current flight event of the carrier rocket in the flight process based on a preset step length, and determining event correlation parameters corresponding to the current simulation moment; under the condition that the event-related parameters corresponding to the current simulation time meet the switching parameter conditions for the first time but do not meet the switching precision conditions, iteratively determining a variable step simulation time between the current simulation time and the last simulation time, and determining the variable step simulation time as the switching time of the current flight event; event-related parameters corresponding to the variable step-length simulation moment meet the switching parameter conditions and meet the switching precision conditions; and optimizing the trajectory of the carrier rocket based on the switching moment of each flight event in the flight process of the carrier rocket. The method and the device provided by the application improve the speed and the precision of the carrier rocket trajectory optimization.
Description
Technical Field
The application relates to the technical field of aerospace, in particular to a carrier rocket trajectory optimization method, a carrier rocket trajectory optimization device, electronic equipment and a storage medium.
Background
The trajectory of a launch vehicle generally consists of multiple flight phases, and the whole rocket flight trajectory can involve a plurality of events. The existing carrier rocket trajectory optimization design program generally adopts fixed step length to carry out simulation calculation, the fixed step length brings certain error to event switching, and particularly when large step length is adopted for accelerating trajectory optimization speed, the event switching error brought by the large step length is often larger, so that the carrier rocket trajectory optimization precision is not high. Although a smaller step size can be selected for improving the event switching precision, the carrier rocket generally needs to have a longer flight time from ignition to orbit entering, and the full ballistic calculation workload is exploded due to the excessively small step size, so that the ballistic optimization speed is drastically reduced.
Therefore, how to simultaneously improve the speed and accuracy of trajectory optimization calculation is a technical problem to be solved in the industry.
Disclosure of Invention
The application provides a carrier rocket trajectory optimization method, a carrier rocket trajectory optimization device, electronic equipment and a storage medium, which are used for solving the technical problem of how to simultaneously improve the speed and the accuracy of trajectory optimization calculation.
The application provides a carrier rocket trajectory optimization method, which comprises the following steps:
simulating a current flight event of the carrier rocket in the flight process based on a preset step length, and determining event correlation parameters corresponding to the current simulation moment;
under the condition that the event-related parameters corresponding to the current simulation time meet the switching parameter conditions for the first time but do not meet the switching precision conditions, iteratively determining a variable step simulation time between the current simulation time and the last simulation time, and determining the variable step simulation time as the switching time of the current flight event; the event-related parameters corresponding to the variable step-length simulation moment meet the switching parameter conditions and meet the switching precision conditions;
and optimizing the trajectory of the carrier rocket based on the switching moment of each flight event in the flight process of the carrier rocket.
In some embodiments, the iteratively determining the variable step simulation time between the current simulation time and a previous simulation time includes:
under the condition that event-related parameters corresponding to variable step-length simulation time in a current iteration round do not meet the switching parameter conditions, taking the variable step-length simulation time in the current iteration round as new iteration starting time and taking the current simulation time as new iteration ending time;
determining a new variable step simulation time based on the new iteration start time and the new iteration end time;
and determining the new variable step simulation time as the variable step simulation time in the next iteration round.
In some embodiments, the iteratively determining the variable step simulation time between the current simulation time and a previous simulation time includes:
when event-related parameters corresponding to variable step simulation time in a current iteration round meet the switching parameter conditions but do not meet the switching precision conditions, taking the last simulation time as a new iteration starting time and taking the variable step simulation time in the current iteration round as a new iteration ending time;
determining a new variable step simulation time based on the new iteration start time and the new iteration end time;
and determining the new variable step simulation time as the variable step simulation time in the next iteration round.
In some embodiments, the determining the variable step simulation time as the switching time of the current flight event includes:
determining the current iteration round;
and under the condition that the current iteration round is larger than a preset iteration round, taking the variable step simulation time in the current iteration round as the switching time of the current flight event.
In some embodiments, the determining a new variable-step simulation time based on the new iteration start time and the new iteration end time includes:
and determining the new variable step simulation moment based on the intermediate value of the new iteration starting moment and the new iteration ending moment.
In some embodiments, after the determining the variable step simulation time as the switching time of the current flight event, the method further comprises:
and simulating the next flight event of the carrier rocket along the trajectory flight based on the preset step length.
In some embodiments, after the determining the event correlation parameter corresponding to the current simulation time, the method further includes:
and taking the current simulation time as the switching time of the current flight event under the condition that the event-related parameter corresponding to the current simulation time meets the switching parameter condition for the first time and meets the switching precision condition.
The application provides a launch vehicle trajectory optimizing device, include:
the fixed-step simulation module is used for simulating the current flight event of the carrier rocket in the flight process based on a preset step length, and determining event correlation parameters corresponding to the current simulation moment;
the variable step simulation module is used for iteratively determining a variable step simulation moment between the current simulation moment and the last simulation moment and determining the variable step simulation moment as the switching moment of the current flight event under the condition that the event-related parameter corresponding to the current simulation moment meets the switching parameter condition for the first time but does not meet the switching precision condition; the event-related parameters corresponding to the variable step-length simulation moment meet the switching parameter conditions and meet the switching precision conditions;
and the trajectory optimization module is used for optimizing the trajectory of the carrier rocket based on the switching moment of each flight event in the flight process of the carrier rocket.
The application provides an electronic device, which comprises a memory, a processor and a computer program stored in the memory and capable of running on the processor, wherein the processor realizes the carrier rocket trajectory optimization method when executing the program.
The present application provides a non-transitory computer readable storage medium having stored thereon a computer program which when executed by a processor implements the launch vehicle trajectory optimization method.
According to the carrier rocket trajectory optimization method, the carrier rocket trajectory optimization device, the electronic equipment and the storage medium, a current flight event of the carrier rocket in the flight process is simulated according to a preset step length, and event association parameters corresponding to the current simulation moment are determined; under the condition that the event-related parameters corresponding to the current simulation time meet the switching parameter conditions for the first time but do not meet the switching precision conditions, iteratively determining a variable step-size simulation time which meets the switching parameter conditions and the switching precision conditions simultaneously between the current simulation time and the last simulation time, and determining the variable step-size simulation time as the switching time of the current flight event; according to the switching moment of each flight event in the flight process of the carrier rocket, the trajectory of the carrier rocket is optimized, and because the fixed preset step length is adopted for simulation in the flight event, the variable step length is adopted for simulation in the flight event switching, the carrier rocket trajectory optimization design has the rapidity brought by adopting the fixed simulation step length in the event, and simultaneously has the high precision brought by the time-varying simulation step length of the event switching, and the speed and the precision of the carrier rocket trajectory optimization are improved.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the application and together with the description, serve to explain the principles of the application.
In order to more clearly illustrate the technical solutions of the present application or the prior art, the following description will briefly introduce the drawings used in the embodiments or the description of the prior art, and it is obvious that, in the following description, the drawings are some embodiments of the present application, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic flow chart of a method for optimizing the trajectory of a launch vehicle according to an embodiment of the present application;
FIG. 2 is a schematic structural view of a launch vehicle trajectory optimization device according to one embodiment of the present application;
fig. 3 is a schematic structural diagram of an electronic device according to an embodiment of the present application.
Detailed Description
In order to make the present application solution better understood by those skilled in the art, the following description will be made in detail and with reference to the accompanying drawings in the embodiments of the present application, it is apparent that the described embodiments are only some embodiments of the present application, not all embodiments. All other embodiments, which can be made by one of ordinary skill in the art based on the embodiments herein without making any inventive effort, shall fall within the scope of the present application.
It should be noted that the terms "first," "second," and the like herein are used for distinguishing between similar objects and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used may be interchanged where appropriate such that embodiments of the present application described herein may be implemented in sequences other than those illustrated or otherwise described herein. Furthermore, the terms "comprises," "comprising," and "having," and any variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, system, article, or apparatus that comprises a list of steps or modules is not necessarily limited to those steps or modules that are expressly listed or inherent to such process, method, article, or apparatus.
Fig. 1 is a schematic flow chart of a method for optimizing the trajectory of a launch vehicle according to an embodiment of the present application, as shown in fig. 1, the method includes steps 110, 120 and 130.
Specifically, an execution main body of the launch vehicle trajectory optimization method provided by the embodiment of the application is a trajectory optimization device. The device may be embodied in software, for example, as a ballistic optimization program for a launch vehicle; may also be embodied in hardware, such as a computer system that performs ballistic optimization.
Flight events refer to events in which a launch vehicle performs a nodal action during flight. The execution time of these nodal actions, i.e. the switching time of the flight event. Taking a four-stage solid carrier rocket as an example, the carrier rocket generally needs to undergo the following events from ignition take-off to successful orbit entering: primary ignition, secondary separation, secondary shutdown, fairing separation, secondary-tertiary separation, tertiary ignition, tertiary shutdown, tertiary-quaternary separation, quaternary ignition, quaternary shutdown. The switching moments of these flight events constitute the flight timing of the launch vehicle.
Based on these flight events, the optimal design simulation of the trajectory of the launch vehicle can be divided into an event internal simulation and an event switching simulation. The event internal simulation is to simulate the process that the carrier rocket flies on the trajectory from the switching time of the last flying event to the switching time of the current flying event. The event switching simulation is to simulate the process that the carrier rocket flies on the trajectory at the switching moment of the current flight event.
And simulating each flight event of the carrier rocket in the flight process according to the preset step length by the trajectory optimization device. The preset step length is a preset fixed step length and represents the time difference between two simulation moments. The longer the preset step length is, the larger the interval between simulation moments is, the lower the simulation precision is, and the smaller the demand on computing resources is; the shorter the preset step length is, the smaller the interval between simulation moments is, the higher the simulation precision is, and the larger the demand for computing resources is.
In ballistic optimization design, event-related parameters are typically used to determine whether to switch flight events. Different flight events may correspond to different event-related parameters. The event-related parameters may be determined from flight state parameters of the launch vehicle. For example, the event-related parameters may be selected to be time of flight, altitude of flight, engine thrust, and the like.
For example, when the current flight event is secondary ignition, the flight time can be selected as an event-related parameter, and when the flight time meets the requirement, the carrier rocket performs secondary engine ignition; when the current flight event is fairing separation, the flight altitude can be selected as an event-related parameter, and when the flight altitude meets the requirement, the carrier rocket executes fairing throwing; when the current flight event is secondary shutdown, the thrust of the secondary engine can be selected as an event-related parameter, and when the thrust of the secondary engine meets the requirement, the carrier rocket executes secondary engine shutdown.
And the trajectory optimization device calculates event-related parameters corresponding to each simulation moment of the carrier rocket flying on the trajectory according to a kinetic equation of the carrier rocket and the like.
Specifically, the switching parameter condition is used for judging whether the event-related parameter meets the parameter requirement of the flight event switching. For example, when the current flight event is a fairing separation, the flight altitude is an event related parameter, and the switching parameter condition is that the flight altitude must be greater than or equal to a preset altitude threshold. After the switching parameter condition is met, the current flight event can be switched, and the throwing fairing is executed.
In order to improve the trajectory optimization precision of the carrier rocket, namely to improve the switching precision of the flight event, a switching precision condition can be set. The switching precision condition is used for judging whether the event-related parameters meet the precision requirement of the flight event switching. For example, the flying height is an event-related parameter, the switching accuracy condition is that the flying height must be less than or equal to a preset accuracy threshold, and the preset accuracy threshold is the sum of a preset height threshold and an accuracy index requirement. After the switching parameter condition is met, the current flight event can be switched, but performing the parabolic fairing needs to be within the flight altitude required to switch the accuracy condition.
When the event related parameters corresponding to the current simulation time meet the switching parameter conditions for the first time, the switching of the current flight event can be indicated, but whether the switching precision conditions are met is further judged.
If so, the switching moment meeting the precision requirement is considered to be successfully found, and the node action corresponding to the current flight event can be executed.
If the accuracy requirement is not met, a variable step simulation mode can be adopted to determine the switching time meeting the accuracy requirement.
The variable step-length simulation time can be determined in an iterative solution manner in the time range between the current simulation time and the last simulation time. The iteration termination condition may be set such that the event-related parameter corresponding to the variable step-size simulation time satisfies the switching parameter condition and the switching accuracy condition at the same time. The iterative solution method may select a dichotomy.
The step length between the variable step length simulation time generated by each iteration and the current simulation time or the last simulation time is smaller than the preset step length. With the increase of iteration rounds, the step length is shorter and shorter, and the smaller the interval between simulation moments is, the higher the simulation precision is.
And 130, optimizing the trajectory of the carrier rocket based on the switching moment of each flight event in the flight process of the carrier rocket.
Specifically, after determining the switching time of each flight event of the carrier rocket in the flight process, the trajectory of the carrier rocket can be optimized according to the flight state parameter of each switching time.
According to the carrier rocket trajectory optimization method, a current flight event of the carrier rocket in the flight process is simulated according to a preset step length, and event association parameters corresponding to the current simulation moment are determined; under the condition that the event-related parameters corresponding to the current simulation time meet the switching parameter conditions for the first time but do not meet the switching precision conditions, iteratively determining a variable step-size simulation time which meets the switching parameter conditions and the switching precision conditions simultaneously between the current simulation time and the last simulation time, and determining the variable step-size simulation time as the switching time of the current flight event; according to the switching moment of each flight event in the flight process of the carrier rocket, the trajectory of the carrier rocket is optimized, and because the fixed preset step length is adopted for simulation in the flight event, the variable step length is adopted for simulation in the flight event switching, the carrier rocket trajectory optimization design has the rapidity brought by adopting the fixed simulation step length in the event, and simultaneously has the high precision brought by the time-varying simulation step length of the event switching, and the speed and the precision of the carrier rocket trajectory optimization are improved.
It should be noted that each embodiment of the present application may be freely combined, permuted, or executed separately, and does not need to rely on or rely on a fixed execution sequence.
In some embodiments, step 120 comprises:
under the condition that event-related parameters corresponding to variable step-length simulation moments in the current iteration rounds do not meet the switching parameter conditions, taking the variable step-length simulation moments in the current iteration rounds as new iteration starting moments and taking the current simulation moments as new iteration ending moments;
determining a new variable step simulation time based on the new iteration start time and the new iteration end time;
and determining the new variable step simulation time as the variable step simulation time in the next iteration round.
Specifically, in the initial iteration round, the previous simulation time is taken as the iteration start time, the current simulation time is taken as the iteration end time, and the variable step simulation time in the initial iteration round is determined between the iteration start time and the iteration end time.
According to the rocket dynamics equation, the variable step simulation time of the carrier rocket in the initial iteration round can be solved, and whether the switching parameter condition and the switching precision condition are met or not is judged.
If so, the variable step simulation time in the initial iteration round can be determined as the switching time of the current flight event. If not, the next iteration round is continued.
In the iteration process, if the event-related parameters corresponding to the variable step-length simulation time in the current iteration round do not meet the switching parameter conditions, and the current simulation time is considered to be the time when the switching parameter conditions are met for the first time, the switching time of the current flight event should be closer to the current simulation time.
Therefore, the variable step-length simulation time in the current iteration round is taken as a new iteration starting time, and the current simulation time is taken as a new iteration ending time, so that the determination range of the switching time of the current flight event is further narrowed.
The new variable step length simulation time can be determined according to the new iteration start time and the new iteration end time, and the new variable step length simulation time is determined as the variable step length simulation time in the next iteration round, so that the next iteration round is performed.
According to the carrier rocket trajectory optimization method, under the condition that the event-related parameters corresponding to the variable step simulation time in the current iteration round do not meet the switching parameter conditions, the variable step simulation time in the next iteration round is determined through iteration, the determination range of the switching time of the current flight event is shortened, the determination precision of the switching time of the current flight event is improved, and the precision of carrier rocket trajectory optimization is improved.
In some embodiments, step 120 comprises:
under the condition that event-related parameters corresponding to variable step-length simulation moments in the current iteration round meet the switching parameter conditions but do not meet the switching precision conditions, the previous simulation moment is a new iteration starting moment, and the variable step-length simulation moment in the current iteration round is taken as a new iteration ending moment;
determining a new variable step simulation time based on the new iteration start time and the new iteration end time;
and determining the new variable step simulation time as the variable step simulation time in the next iteration round.
Specifically, in the iteration process, if the event-related parameter corresponding to the variable step-length simulation time in the current iteration round meets the switching parameter condition but does not meet the switching precision condition, the switching time of the current flight event should be closer to the last simulation time.
Therefore, the last simulation time is the new iteration starting time, the variable step simulation time in the current iteration round is used as the new iteration ending time, and the determination range of the switching time of the current flight event is further narrowed.
The new variable step length simulation time can be determined according to the new iteration start time and the new iteration end time, and the new variable step length simulation time is determined as the variable step length simulation time in the next iteration round, so that the next iteration round is performed.
According to the carrier rocket trajectory optimization method, under the condition that the event-related parameters corresponding to the variable step-length simulation time in the current iteration round meet the switching parameter conditions but do not meet the switching precision conditions, the variable step-length simulation time in the next iteration round is determined through iteration, the determination range of the switching time of the current flight event is shortened, the determination precision of the switching time of the current flight event is improved, and the precision of carrier rocket trajectory optimization is improved.
In some embodiments, step 120 comprises:
determining the current iteration round;
and under the condition that the current iteration round is larger than the preset iteration round, taking the variable step simulation time in the current iteration round as the switching time of the current flight event.
Specifically, as iteration rounds increase, the demand for computing resources increases. Thus, a preset iteration round may be set. Under the condition that the current iteration round is larger than the preset iteration round, the variable step simulation time in the current iteration round can be considered to be the optimal solution, and the variable step simulation time can be used as the switching time of the current flight event. The preset iteration turns can be set according to the needs.
According to the carrier rocket trajectory optimization method, the iteration rounds of the variable step simulation moment are limited by setting the preset iteration rounds, so that the iterative calculation is prevented from entering the loop solution, and the calculation resources are saved.
In some embodiments, determining a new variable step simulation time based on the new iteration start time and the new iteration end time includes:
a new variable step simulation time is determined based on the intermediate value of the new iteration start time and the new iteration end time.
Specifically, a new variable step simulation time may be determined using a dichotomy. For example, an intermediate value of the new iteration start time and the new iteration end time may be determined as the new variable step simulation time.
According to the carrier rocket trajectory optimization method, the variable step simulation moment is determined through the dichotomy, the algorithm is easy to execute, the solving speed is high, and the demand on computing resources is small.
In some embodiments, after step 120, further comprising:
and simulating the next flight event of the carrier rocket along the trajectory flight based on the preset step length.
Specifically, after determining the switching instant of the current flight event, the variable step simulation may be ended. And continuously adopting a preset step length to simulate the next flight event of the carrier rocket along the ballistic flight.
According to the carrier rocket trajectory optimization method, simulation is carried out by adopting fixed preset step sizes in each flight event, so that the trajectory optimization speed of the carrier rocket is improved.
In some embodiments, after step 110, further comprising:
and under the condition that the event-related parameters corresponding to the current simulation time meet the switching parameter conditions for the first time and meet the switching precision conditions, taking the current simulation time as the switching time of the current flight event.
Specifically, if the event-related parameter corresponding to the current simulation time can simultaneously satisfy the switching parameter condition and the switching precision condition, the current simulation time can be considered to be the switching time of the current flight event.
In some embodiments, event-related parameters may be divided into two categories, one category being monotonically increasing rocket flying altitude, such as rocket flight time and rise phase; the other is monotonically decreasing, e.g., engine end thrust, which gradually decreases to zero as the propellant approaches depletion.
The following describes a method for optimizing the trajectory of a carrier rocket provided by the application by taking a current flight event as a fairing separation as an example. The event-related parameter is altitude of flight.
The corresponding trajectory optimization method of the fairing separation stage may include:
first, determining the rocket flying height
Whether the first time is greater than or equal to the preset parabolic fairing height +.>
If yes, performing a second step of action; if not, continuing to perform the simulation calculation of the rocket dynamics with the fixed step length until the rocket flying height is satisfied>
The first time is greater than or equal to the preset parabolic fairing height +.>
。
Step two, judging the current moment obtained by calculating the fixed step length
Rocket altitude at this point +.>
Whether the parameter requirements and the accuracy requirements of the parabolic fairing height are met, i.e. +.>
And
if so, the rocket flight time meeting the requirements of the height precision of the parabolic fairing is considered to be successfully found, and the parabolic fairing flag bit is +.>
Setting 1, namely, throwing a fairing at the moment +.>
Put into->
Then, continuing to perform dynamics simulation calculation of the next event in a fixed step length; if not, the third step is performed.
Third step, willThe last time calculated by the fixed step length
Assigning a value to the iteration start time
The current moment calculated by the fixed step length +.>
Assigning values to state variables
Setting the next simulation time:
setting the number of iterations
And (3) when the value is zero, performing a fourth step action.
Fourth, judging the flying height of the rocket
Whether or not to fall outside the range of the high precision requirement of the parabolic fairing, i.e
Or->
If yes, the fifth step is carried out, and if no, the dynamics simulation calculation of the next event is carried out continuously in a fixed step length.
Fifthly, the rocket state quantity at the last moment is calculated
Assigning rocket state quantity to current moment
Solving the kinetic equation to obtain->
Flying height of the rocket at moment and iterating times
And adding 1 to perform the action of the sixth step.
Sixth, judging the flying height of the rocket
Whether or not it is smaller than a predetermined parabolic fairing height +.>
If so, then ∈>
Assigning a value to iteration start time +.>
The current state quantity of rocket
Assigning a state quantity to the last moment +.>
Performing a fourth step of action; if not, the seventh step is performed.
Seventh, judging the flying height of the rocket
Whether or not is greater than->
If so, then
Assign to->
Performing a fourth step of action; if not, the eighth step is performed.
Eighth step, judging the flying height of the rocket
Whether or not the parameter requirements and the accuracy requirements are met, or the number of iterations
Whether or not the upper limit is exceeded->
If yes, the rocket flight time meeting the requirements of the height precision of the parabolic fairing is considered to be successfully found, and the parabolic fairing flag bit is +.>
1, the moment of throwing the fairing
Put into->
Time calculated by fixed step length +.>
Assignment to
Solving a kinetic equation, and recalculating to obtain +.>
State information of the rocket at the moment so as to perform fixed step simulation calculation in the next event; if not, the fourth step is performed.
Through the steps, the execution time of fairing separation can be accurately determined, and the speed and the precision of carrier rocket trajectory optimization are improved.
Fig. 2 is a schematic structural diagram of a launch vehicle trajectory optimization device according to an embodiment of the present application, as shown in fig. 2, the device includes:
the fixed-step simulation module 210 is configured to simulate a current flight event of the carrier rocket in a flight process based on a preset step, and determine an event correlation parameter corresponding to a current simulation time;
the variable step simulation module 220 is configured to iteratively determine a variable step simulation time between a current simulation time and a previous simulation time when an event-related parameter corresponding to the current simulation time satisfies a switching parameter condition for the first time but does not satisfy a switching precision condition, and determine the variable step simulation time as a switching time of the current flight event; event-related parameters corresponding to the variable step-length simulation moment meet the switching parameter conditions and meet the switching precision conditions;
the trajectory optimization module 230 is configured to optimize the trajectory of the carrier rocket based on the switching time of each flight event during the flight of the carrier rocket.
According to the carrier rocket trajectory optimization device provided by the embodiment of the application, the current flight event of the carrier rocket in the flight process is simulated according to the preset step length, and event association parameters corresponding to the current simulation moment are determined; under the condition that the event-related parameters corresponding to the current simulation time meet the switching parameter conditions for the first time but do not meet the switching precision conditions, iteratively determining a variable step-size simulation time which meets the switching parameter conditions and the switching precision conditions simultaneously between the current simulation time and the last simulation time, and determining the variable step-size simulation time as the switching time of the current flight event; according to the switching moment of each flight event in the flight process of the carrier rocket, the trajectory of the carrier rocket is optimized, and because the fixed preset step length is adopted for simulation in the flight event, the variable step length is adopted for simulation in the flight event switching, the carrier rocket trajectory optimization design has the rapidity brought by adopting the fixed simulation step length in the event, and simultaneously has the high precision brought by the time-varying simulation step length of the event switching, and the speed and the precision of the carrier rocket trajectory optimization are improved.
In some embodiments, the variable step simulation module is specifically configured to:
under the condition that event-related parameters corresponding to variable step-length simulation moments in the current iteration rounds do not meet the switching parameter conditions, taking the variable step-length simulation moments in the current iteration rounds as new iteration starting moments and taking the current simulation moments as new iteration ending moments;
determining a new variable step simulation time based on the new iteration start time and the new iteration end time;
and determining the new variable step simulation time as the variable step simulation time in the next iteration round.
In some embodiments, the variable step simulation module is specifically configured to:
under the condition that event-related parameters corresponding to variable step-length simulation moments in the current iteration round meet the switching parameter conditions but do not meet the switching precision conditions, the previous simulation moment is a new iteration starting moment, and the variable step-length simulation moment in the current iteration round is a new iteration ending moment;
determining a new variable step simulation time based on the new iteration start time and the new iteration end time;
and determining the new variable step simulation time as the variable step simulation time in the next iteration round.
In some embodiments, the variable step simulation module is specifically configured to:
determining the current iteration round;
and under the condition that the current iteration round is larger than the preset iteration round, taking the variable step simulation time in the current iteration round as the switching time of the current flight event.
In some embodiments, the variable step simulation module is specifically configured to:
a new variable step simulation time is determined based on the intermediate value of the new iteration start time and the new iteration end time.
In some embodiments, the fixed-step simulation module is specifically configured to:
and simulating the next flight event of the carrier rocket along the trajectory flight based on the preset step length.
In some embodiments, the fixed-step simulation module is specifically configured to:
and under the condition that the event-related parameters corresponding to the current simulation time meet the switching parameter conditions for the first time and meet the switching precision conditions, taking the current simulation time as the switching time of the current flight event.
Fig. 3 is a schematic structural diagram of an electronic device according to an embodiment of the present application, as shown in fig. 3, the electronic device may include: processor (Processor) 310, communication interface (Communications Interface) 320, memory (Memory) 330 and communication bus (Communications Bus) 340, wherein Processor 310, communication interface 320 and Memory 330 accomplish communication with each other through communication bus 340. The processor 310 may invoke logic commands in the memory 330 to perform the following method:
simulating a current flight event of the carrier rocket in the flight process based on a preset step length, and determining event correlation parameters corresponding to the current simulation moment; under the condition that the event-related parameters corresponding to the current simulation time meet the switching parameter conditions for the first time but do not meet the switching precision conditions, iteratively determining a variable step simulation time between the current simulation time and the last simulation time, and determining the variable step simulation time as the switching time of the current flight event; event-related parameters corresponding to the variable step-length simulation moment meet the switching parameter conditions and meet the switching precision conditions; and optimizing the trajectory of the carrier rocket based on the switching moment of each flight event in the flight process of the carrier rocket.
In addition, the logic commands in the memory described above may be implemented in the form of software functional units and may be stored in a computer readable storage medium when sold or used as a stand alone product. Based on such 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 commands for causing a computer device (which may be a personal computer, a server, or a network device, etc.) to perform all or part of the steps of the methods described in the embodiments of the present application. And the aforementioned storage medium includes: a U-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 processor in the electronic device provided by the embodiment of the present application may call the logic instruction in the memory to implement the above method, and the specific implementation manner of the processor is consistent with the implementation manner of the foregoing method, and may achieve the same beneficial effects, which are not described herein again.
The present application also provides a computer-readable storage medium having stored thereon a computer program which, when executed by a processor, is implemented to perform the methods provided by the above embodiments.
The specific embodiment is consistent with the foregoing method embodiment, and the same beneficial effects can be achieved, and will not be described herein.
Embodiments of the present application provide a computer program product comprising a computer program which, when executed by a processor, implements a method as described above.
The apparatus embodiments described above are merely illustrative, wherein the elements illustrated as separate elements may or may not be physically separate, and the elements shown as elements may or may not be physical elements, may be located in one place, or may be distributed over a plurality of network elements. Some or all of the modules may be selected according to actual needs to achieve the purpose of the solution of this embodiment. Those of ordinary skill in the art will understand and implement the present invention without undue burden.
From the above description of the embodiments, it will be apparent to those skilled in the art that the embodiments may be implemented by means of software plus necessary general hardware platforms, or of course may be implemented by means of hardware. Based on this understanding, the foregoing technical solution may be embodied essentially or in a part contributing to the prior art in the form of a software product, which may be stored in a computer readable storage medium, such as ROM/RAM, a magnetic disk, an optical disk, etc., including several instructions for causing a computer device (which may be a personal computer, a server, or a network device, etc.) to execute the method described in the respective embodiments or some parts of the embodiments.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present application, and are not limiting thereof; although the present application has been described in detail with reference to the foregoing embodiments, it should be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit and scope of the corresponding technical solutions.
Claims (10)
1. A method of optimizing the trajectory of a launch vehicle, comprising:
simulating a current flight event of the carrier rocket in the flight process based on a preset step length, and determining event correlation parameters corresponding to the current simulation moment;
under the condition that the event-related parameters corresponding to the current simulation time meet the switching parameter conditions for the first time but do not meet the switching precision conditions, iteratively determining a variable step simulation time between the current simulation time and the last simulation time, and determining the variable step simulation time as the switching time of the current flight event; the event-related parameters corresponding to the variable step-length simulation moment meet the switching parameter conditions and meet the switching precision conditions;
and optimizing the trajectory of the carrier rocket based on the switching moment of each flight event in the flight process of the carrier rocket.
2. A method of optimizing launch vehicle trajectory according to claim 1, wherein said iteratively determining a variable step simulation time between said current simulation time and a previous simulation time comprises:
under the condition that event-related parameters corresponding to variable step-length simulation time in a current iteration round do not meet the switching parameter conditions, taking the variable step-length simulation time in the current iteration round as new iteration starting time and taking the current simulation time as new iteration ending time;
determining a new variable step simulation time based on the new iteration start time and the new iteration end time;
and determining the new variable step simulation time as the variable step simulation time in the next iteration round.
3. A method of optimizing launch vehicle trajectory according to claim 1, wherein said iteratively determining a variable step simulation time between said current simulation time and a previous simulation time comprises:
when event-related parameters corresponding to variable step simulation time in a current iteration round meet the switching parameter conditions but do not meet the switching precision conditions, taking the last simulation time as a new iteration starting time and taking the variable step simulation time in the current iteration round as a new iteration ending time;
determining a new variable step simulation time based on the new iteration start time and the new iteration end time;
and determining the new variable step simulation time as the variable step simulation time in the next iteration round.
4. The method of claim 1, wherein the determining the variable step simulation time as the switching time of the current flight event comprises:
determining the current iteration round;
and under the condition that the current iteration round is larger than a preset iteration round, taking the variable step simulation time in the current iteration round as the switching time of the current flight event.
5. A launch vehicle trajectory optimization method according to claim 2 or 3, wherein said determining a new variable step simulation moment based on said new iteration start moment and said new iteration end moment comprises:
and determining the new variable step simulation moment based on the intermediate value of the new iteration starting moment and the new iteration ending moment.
6. A method of optimizing launch vehicle trajectory according to claim 1, wherein said determining said variable step simulation time instant as a switching time instant of said current flight event is followed by said method further comprising:
and simulating the next flight event of the carrier rocket along the trajectory flight based on the preset step length.
7. The method of claim 1, wherein after determining the event-related parameters corresponding to the current simulation time, the method further comprises:
and taking the current simulation time as the switching time of the current flight event under the condition that the event-related parameter corresponding to the current simulation time meets the switching parameter condition for the first time and meets the switching precision condition.
8. A launch vehicle trajectory optimization device, comprising:
the fixed-step simulation module is used for simulating the current flight event of the carrier rocket in the flight process based on a preset step length, and determining event correlation parameters corresponding to the current simulation moment;
the variable step simulation module is used for iteratively determining a variable step simulation moment between the current simulation moment and the last simulation moment and determining the variable step simulation moment as the switching moment of the current flight event under the condition that the event-related parameter corresponding to the current simulation moment meets the switching parameter condition for the first time but does not meet the switching precision condition; the event-related parameters corresponding to the variable step-length simulation moment meet the switching parameter conditions and meet the switching precision conditions;
and the trajectory optimization module is used for optimizing the trajectory of the carrier rocket based on the switching moment of each flight event in the flight process of the carrier rocket.
9. An electronic device comprising a memory, a processor and a computer program stored on the memory and executable on the processor, wherein the processor implements the launch vehicle trajectory optimization method of any one of claims 1 to 7 when executing the computer program.
10. A non-transitory computer readable storage medium having stored thereon a computer program, which when executed by a processor implements the launch vehicle trajectory optimization method of any one of claims 1 to 7.
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