CN112257222A - Ballistic reentry spin angular velocity calculation method, device, storage medium, and apparatus - Google Patents
Ballistic reentry spin angular velocity calculation method, device, storage medium, and apparatus Download PDFInfo
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Abstract
The scheme discloses a ballistic reentry and spin angular velocity calculation method, a ballistic reentry and spin angular velocity calculation device, a storage medium and equipment, wherein the method comprises the following steps: respectively determining a speed upper limit value and a speed lower limit value of the starting angular speed; and determining the starting angular speed according to the weight coefficients of the measurement and control demand and the reduced drop point scattering demand based on the upper limit value and the lower limit value. According to the scheme, the starting angular speed of the aerospace craft can be determined according to different conditions such as the type and the task of the aerospace craft, and the aerospace craft can carry out ballistic reentry in a starting mode, so that the ballistic stability is improved, and the falling point distribution is reduced.
Description
Technical Field
The scheme relates to the technical field of spaceflight. And more particularly, to a ballistic reentry spin angle calculation method, apparatus, readable storage medium, and device.
Background
At present, the reentry mode of the spacecraft is divided into 3 types according to the existence of lift force action: lift-type reentry, semi-ballistic reentry, and ballistic reentry. Wherein, the ballistic reentry has no lift force, and the deceleration of the reentry process is realized only by aerodynamic resistance. In task implementation, in order to improve ballistic stability and reduce landing point spread, ballistic reentry is often implemented by means of spin-up. According to different types and different tasks of reentry space vehicles, the rotation starting angular speeds are different.
Disclosure of Invention
The scheme aims to provide a ballistic reentry rotation angle calculation method, a ballistic reentry rotation angle calculation device, a readable storage medium and equipment.
In order to achieve the purpose, the scheme is as follows:
in a first aspect, the present disclosure provides a ballistic reentry start angular velocity calculation method, including:
respectively determining a speed upper limit value and a speed lower limit value of the starting angular speed;
and determining the starting angular speed according to the weight coefficients of the measurement and control demand and the reduced drop point scattering demand based on the upper limit value and the lower limit value.
In a preferred embodiment, the step of determining the upper speed limit value comprises:
and determining the upper limit value of the rotation angular speed according to the measurement and control requirement and the type of the measurement and control antenna. When the angular velocity of the start-up is too great, the heaven and earth link will be frequently interrupted or cannot be established. Therefore, the acceptable time for breaking the heaven-earth link needs to be determined according to the task, and the upper limit value of the starting angular speed is determined according to the acceptable time.
In a preferred embodiment, the upper limit value ω of the rotational angular velocity is set tomax：ωmax＝θ/tminWherein, tminFor the shortest acquisition time, θ is the antenna beam angle.
In a preferred embodiment, the step of determining the lower speed limit value comprises:
and determining a lower limit value of the starting angular velocity according to the requirement for reducing the scatter of the falling points and the influence parameters in the reentry process. When the attack angular velocity is too small, it will not play a role in reducing the landing point spread, so the lower limit value of the attack angular velocity is determined accordingly.
In a preferred embodiment, the lower limit value ω of the rotational angular velocity is set tomin：
Wherein, CdxIs the aerodynamic rolling damping coefficient of the aerospace craft, q is dynamic pressure, S is reference area, l is reference length, omega is rolling angular velocity, v is velocity, M is aerodynamic rolling damping torque, IxThe rolling direction rotational inertia of the aerospace craft, alpha is the angular acceleration generated by the aerodynamic rolling damping, and t is the reentry flight time.
In a second aspect, the present disclosure provides a ballistic reentry start angular velocity calculation apparatus including:
an upper limit value determining module for determining a speed upper limit value of the rotation angular speed;
a lower limit value determination module that determines a speed lower limit value of the yaw angular velocity;
and the rotation starting angular speed determining module is used for determining the rotation starting angular speed according to the weight coefficient of the measurement and control demand and the drop point scattering reduction demand on the basis of the upper limit value and the lower limit value.
In a preferred embodiment, the upper limit value determining module specifically executes the following steps:
determining an upper limit value of the rotation angular speed according to the measurement and control requirement and the measurement and control antenna type;
the upper limit value ω of the rotational angular velocitymax：ωmax＝θ/tminWherein, tminFor the shortest acquisition time, θ is the antenna beam angle.
In a preferred embodiment, the upper limit value determining module specifically executes the following steps:
determining a lower limit value of the starting angular velocity according to the requirement for reducing the scatter of the falling points and the influence parameters in the reentry process;
the lower limit value ω of the rotational angular velocitymin：
Wherein, CdxIs the aerodynamic rolling damping coefficient of the aerospace craft, q is dynamic pressure, S is reference area, l is reference length, omega is rolling angular velocity, v is velocity, M is aerodynamic rolling damping torque, IxThe rolling direction rotational inertia of the aerospace craft, alpha is the angular acceleration generated by the pneumatic rolling damping, and t is the reentry flight time
In a third aspect, the present disclosure provides a computer-readable storage medium on which a computer program is stored, the program, when executed by a processor, implementing the steps of the ballistic reentry and launch angular velocity calculation method described above.
In a fourth aspect, the present solution provides an apparatus comprising: a memory, one or more processors; the memory is connected with the processor through a communication bus; the processor is configured to execute instructions in the memory; the storage medium stores instructions for executing the respective steps in the ballistic reentry start angular velocity calculation method described above.
The scheme has the following beneficial effects:
according to the scheme, the starting angular speed of the aerospace craft can be determined according to different conditions such as the type and the task of the aerospace craft, and the aerospace craft can carry out ballistic reentry in a starting mode, so that the ballistic stability is improved, and the falling point distribution is reduced.
Drawings
In order to illustrate the implementation of the solution more clearly, the drawings that are needed in the description of the embodiments will be briefly described below, it being obvious that the drawings in the following description are only some embodiments of the solution, and that other drawings may be derived from these drawings by a person skilled in the art without inventive effort.
Fig. 1 is a schematic diagram showing an example of a ballistic reentry rotational angular velocity calculation method according to the present embodiment;
fig. 2 is a schematic diagram showing an example of a ballistic reentry rotational angular velocity calculation apparatus according to the present scheme;
fig. 3 shows a schematic diagram of an electronic device according to the present solution.
Detailed Description
Embodiments of the present solution will be described in further detail below with reference to the accompanying drawings. It is clear that the described embodiments are only a part of the embodiments of the present solution, and not an exhaustive list of all embodiments. It should be noted that, in the present embodiment, features of the embodiment and the embodiment may be combined with each other without conflict.
Through research and analysis, the reentry mode of the spacecraft is divided into 3 types according to the existence of the lifting force action: lift-type reentry, semi-ballistic reentry, and ballistic reentry. Wherein, the ballistic reentry has no lift force, and the deceleration of the reentry process is realized only by aerodynamic resistance. According to different types and different tasks of reentry space vehicles, the rotation starting angular speeds are different.
Therefore, the method for calculating the ballistic reentry/spin angular velocity is provided, and the ballistic reentry/spin angular velocity can be determined according to the type of the aerospace vehicle, the task type and other conditions, so that the design requirements of different types of reentry vehicles are met.
Hereinafter, a video advertisement recognition method proposed by the present scheme will be described in detail with reference to the accompanying drawings. As shown in fig. 1, the method may include the steps of:
step S1, respectively determining a speed upper limit value and a speed lower limit value of the starting angular speed;
and step S2, determining the starting angular speed according to the weight coefficient of the measurement and control demand and the drop point scattering reduction demand based on the upper limit value and the lower limit value.
In step S1, the upper limit value of the rotational angular velocity may be adjusted according to the measurement and control requirement. For example, a communication link with the ground needs to be maintained during reentry of an aerospace vehicle, and spinning up can cause the communication link to be intermittent. If the measurement and control antenna installed on the aerospace craft is an omnidirectional antenna, the factor can be ignored; if omni-directional coverage is not possible, consideration must be given.
Further, the determination of the upper limit value of the starting angular velocity needs to be performed according to the measurement and control requirement and the type of the measurement and control antenna. In one embodiment, the upper limit value ω of the angular velocity of the start-up is set tomax：ωmax＝θ/tminWherein, tminFor the shortest acquisition time, θ is the antenna beam angle.
In step S1, the lower limit value of the angular velocity of the start may be adjusted according to the need to reduce the scatter of the landing points. For example, in the reentry process of the aircraft, if the aircraft does not spin, the aircraft can generate a small lift force along one direction under the influence of the deviation of the actual center of mass from the central axis and the like, and the deviation of the landing point after the integration along the whole trajectory can be greatly influenced. To improve ballistic stability and reduce landing point spread, it is necessary to spin the aircraft so that the slight lift is balanced in all directions. The aircraft is also subjected to the action of aerodynamic damping in the reentry process, so that the spin angular velocity is gradually attenuated. The lower limit of the spin-up angular velocity must therefore ensure that the spin angular velocity does not decay to 0 over the full re-entry.
In one embodiment, when the angular velocity of the start-up is too great, the world link will be frequently broken or unable to be established. Therefore, the acceptable time for breaking the heaven-earth link needs to be determined according to the task, and the upper limit value of the starting angular speed is determined according to the acceptable time. In one embodiment, when the spin-up angular velocity is too small, it will not function to reduce the drop point spread, so the lower limit value of the spin-up angular velocity is determined accordingly.
Further, the determination of the lower limit value of the angular velocity of the start is determined by the need to reduce the need for scattering of the landing points and the influence parameters during the reentry. In one embodiment, the lower limit value ω of the angular velocity of the start-up is setmin：
Wherein, CdxIs the aerodynamic rolling damping coefficient of the aerospace craft, q is dynamic pressure, S is reference area, l is reference length, omega is rolling angular velocity, v is velocity, M is aerodynamic rolling damping torque, IxIs the rotational inertia in the rolling direction of the aerospace craft, and alpha is gasThe angular acceleration generated by the rolling damping is t, the reentry flight time.
In step S2, after the upper and lower limits of the starting angular velocity are determined, the starting angular velocity is determined comprehensively by combining the weight coefficients of the measurement and control demand and the drop point scattering reduction demand. For example, if the measurement and control demand weight is greater than the demand for reducing the landing point spread, the angular velocity of the start-up may be reduced appropriately; otherwise, it can be raised appropriately.
According to the scheme, the starting angular speed of the aerospace craft can be determined according to different conditions such as the type and the task of the aerospace craft, and the aerospace craft can carry out ballistic reentry in a starting mode, so that the ballistic stability is improved, and the falling point distribution is reduced.
As shown in fig. 2, the present embodiment further provides a ballistic reentry/start angular velocity calculation apparatus implemented in cooperation with the ballistic reentry/start angular velocity calculation method, the apparatus including:
an upper limit value determination module 101 that determines a speed upper limit value of the swing angular speed;
a lower limit value determining module 102 that determines a speed lower limit value of the yaw angular velocity;
and the starting angular velocity determining module 103 determines the starting angular velocity according to the weight coefficient of the measurement and control demand and the drop point scattering reduction demand based on the upper limit value and the lower limit value.
When the ballistic reentry rotation angular velocity calculation device works, the upper limit value determination module 101 is used for determining the upper limit value of the rotation angular velocity according to the measurement and control requirement and the measurement and control antenna type; determining a lower limit value of the starting angular velocity by using a lower limit value determining module 102 according to the requirement for reducing the scatter of the landing points and the influence parameters in the reentry process; and finally, determining the starting angular velocity by using a starting angular velocity determining module 103 according to the weight coefficient of the measurement and control demand and the drop point scattering reduction demand based on the upper limit value and the lower limit value.
On the basis of the above data acquisition method embodiment, the present solution further provides a computer-readable storage medium. The computer-readable storage medium is a program product for implementing the above-described data acquisition method, which may employ a portable compact disc read only memory (CD-ROM) and include program code, and may be run on a device, such as a personal computer. However, the program product of the present invention is not limited in this regard and, in the present document, a readable storage medium may be any tangible medium that can contain, or store a program for use by or in connection with an instruction execution system, apparatus, or device.
The program product may employ any combination of one or more readable media. The readable medium may be a readable signal medium or a readable storage medium. A readable storage medium may be, for example, but not limited to, an electronic, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any combination of the foregoing. More specific examples (a non-exhaustive list) of the readable storage medium include: an electrical connection having one or more wires, a portable disk, a hard disk, a Random Access Memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber, a portable compact disc read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the foregoing.
A computer readable storage medium may include a propagated data signal with readable program code embodied therein, for example, in baseband or as part of a carrier wave. Such a propagated data signal may take many forms, including, but not limited to, electro-magnetic, optical, or any suitable combination thereof. A readable signal medium may also be any readable medium that is not a readable storage medium and that can communicate, propagate, or transport a program for use by or in connection with an instruction execution system, apparatus, or device.
Program code embodied on a computer readable storage medium may be transmitted using any appropriate medium, including but not limited to wireless, wireline, optical fiber cable, RF, etc., or any suitable combination of the foregoing.
Program code for carrying out operations for aspects of the present invention may be written in any combination of one or more programming languages, including an object oriented programming language such as Java, C + + or the like and conventional procedural programming languages, such as the "C" programming language or similar programming languages. The program code may execute entirely on the user computing device, partly on a remote computing device, or entirely on the remote computing device or server. In the case of a remote computing device, the remote computing device may be connected to the user computing device through any kind of network, including a Local Area Network (LAN) or a Wide Area Network (WAN), or may be connected to an external computing device (e.g., through the internet using an internet service provider).
On the basis of the embodiment of the data acquisition method, the scheme further provides the electronic equipment. The electronic device shown in fig. 3 is only an example, and should not bring any limitation to the functions and the scope of use of the embodiments of the present invention.
As shown in fig. 3, the electronic device 201 is in the form of a general purpose computing device. The components of the electronic device 201 may include, but are not limited to: at least one memory unit 202, at least one processing unit 203, a display unit 204 and a bus 205 for connecting different system components.
Wherein the storage unit 202 stores a program code, which can be executed by the processing unit 203, such that the processing unit 203 performs the steps of the various exemplary embodiments described in the above data acquisition method. For example, the processing unit 203 may perform the steps as shown in fig. 1.
The memory unit 202 may include volatile memory units such as a random access memory unit (RAM) and/or a cache memory unit, and may further include a read only memory unit (ROM).
The storage unit 202 may also include programs/utilities with program modules including, but not limited to: an operating system, one or more application programs, other program modules, and program data, each of which, or some combination thereof, may comprise an implementation of a network environment.
The bus 205 may include a data bus, an address bus, and a control bus.
The electronic device 201 may also communicate with one or more external devices 207 (e.g., keyboard, pointing device, bluetooth device, etc.), which may be through an input/output (I/O) interface 206. It should be appreciated that although not shown in the figures, other hardware and/or software modules may be used in conjunction with the electronic device 201, including but not limited to: microcode, device drivers, redundant processing units, external disk drive arrays, RAID systems, tape drives, and data backup storage systems, among others.
Assuming that the beam angle of a certain type of spacecraft antenna is 140 degrees and the shortest capture time is 3s, the upper limit value of the starting angular speed is 46.7 degrees/s; according to the numerical simulation result, the lower limit value of the starting angular velocity is 5 DEG/s. Assuming that the weight of the measurement and control demand and the weight of the drop point spread reduction demand are 50%, the final starting angular velocity is 46.7 × 0.5+5
0.5＝25.85°/s。
It should be understood that the above-mentioned embodiments of the present invention are only examples for clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention, and it will be obvious to those skilled in the art that other variations or modifications may be made on the basis of the above description, and all embodiments may not be exhaustive, and all obvious variations or modifications may be included within the scope of the present invention.
Claims (10)
1. A ballistic reentry start angular velocity calculation method, characterized by the steps of:
respectively determining a speed upper limit value and a speed lower limit value of the starting angular speed;
and determining the starting angular speed according to the weight coefficients of the measurement and control demand and the reduced drop point scattering demand based on the upper limit value and the lower limit value.
2. The method of calculating ballistic reentry rotational angular velocity of claim 1, wherein the step of determining the velocity upper limit value comprises:
and determining the upper limit value of the rotation angular speed according to the measurement and control requirement and the type of the measurement and control antenna.
3. The method according to claim 2, wherein the spin angular velocity upper limit value ω is set tomax：ωmax＝θ/tminWherein, tminFor the shortest acquisition time, θ is the antenna beam angle.
4. The method of calculating ballistic reentry angular velocity of claim 1, wherein the step of determining the lower velocity limit value comprises:
and determining a lower limit value of the starting angular velocity according to the requirement for reducing the scatter of the falling points and the influence parameters in the reentry process.
5. The method of calculating ballistic reentry rotational angular velocity of claim 4, wherein the lower limit value ω of rotational angular velocity is set tomin：
Wherein, CdxIs the aerodynamic rolling damping coefficient of the aerospace craft, q is dynamic pressure, S is reference area, l is reference length, omega is rolling angular velocity, v is velocity, M is aerodynamic rolling damping torque, IxThe rolling direction rotational inertia of the aerospace craft, alpha is the angular acceleration generated by the aerodynamic rolling damping, and t is the reentry flight time.
6. A ballistic reentry start angular velocity calculation apparatus, comprising:
an upper limit value determining module for determining a speed upper limit value of the rotation angular speed;
a lower limit value determination module that determines a speed lower limit value of the yaw angular velocity;
and the rotation starting angular speed determining module is used for determining the rotation starting angular speed according to the weight coefficient of the measurement and control demand and the drop point scattering reduction demand on the basis of the upper limit value and the lower limit value.
7. The ballistic reentry/rotation angular velocity computation apparatus according to claim 6, wherein the upper limit value determination module specifically performs the following steps:
determining an upper limit value of the rotation angular speed according to the measurement and control requirement and the measurement and control antenna type;
the upper limit value ω of the rotational angular velocitymax：ωmax＝θ/tminWherein, tminFor the shortest acquisition time, θ is the antenna beam angle.
8. The ballistic reentry/rotation angular velocity computation apparatus according to claim 6, wherein the upper limit value determination module specifically performs the following steps:
determining a lower limit value of the starting angular velocity according to the requirement for reducing the scatter of the falling points and the influence parameters in the reentry process;
the lower limit value ω of the rotational angular velocitymin：
Wherein, CdxIs the aerodynamic rolling damping coefficient of the aerospace craft, q is dynamic pressure, S is reference area, l is reference length, omega is rolling angular velocity, v is velocity, M is aerodynamic rolling damping torque, IxThe rolling direction rotational inertia of the aerospace craft, alpha is the angular acceleration generated by the aerodynamic rolling damping, and t is the reentry flight time.
9. A computer-readable storage medium, on which a computer program is stored which, when being executed by a processor, carries out the steps of the method according to any one of claims 1 to 5.
10. An apparatus, comprising: a memory, one or more processors; the memory is connected with the processor through a communication bus; the processor is configured to execute instructions in the memory; the storage medium has stored therein instructions for carrying out the steps of the method according to any one of claims 1 to 5.
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