CN112257222B - Ballistic reentry rotational speed calculation method, device, storage medium, and apparatus - Google Patents
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Abstract
The scheme discloses a ballistic reentry rotational speed calculation method, a device, a storage medium and equipment, wherein the method comprises the following steps: respectively determining an upper speed limit value and a lower speed limit value of the angular speed of rotation; and determining the rotation angle speed according to the measurement and control requirement and the weight coefficient for reducing the falling point scattering requirement based on the upper limit value and the lower limit value. According to the scheme, the spinning angular speed of the aerospace vehicle can be determined according to different conditions such as the type and the task of the aerospace vehicle, and the aerospace vehicle can perform ballistic reentry in a spinning mode, so that the ballistic stability is improved, and the drop point scattering is reduced.
Description
Technical Field
The scheme relates to the technical field of aerospace. And more particularly, to a ballistic reentry spin angle calculation method, apparatus, readable storage medium, and device.
Background
At present, the reentry modes of the spacecraft are divided into 3 types according to the existence of lift force actions: lift reentry, semi-ballistic reentry, and ballistic reentry. Wherein the ballistic reentry has no lifting force effect, and the deceleration of the reentry process is realized only by the pneumatic resistance. In task implementation, in order to improve ballistic stability and reduce drop point scattering, ballistic reentry often employs a spin-up approach. According to different categories and different tasks of reentry space vehicles, the angular speed of rotation is different.
Disclosure of Invention
The scheme aims at providing a ballistic reentry lifting angle calculation method, a ballistic reentry lifting angle calculation device, a readable storage medium and a device.
In order to achieve the above purpose, the scheme is as follows:
in a first aspect, the present invention provides a method for calculating a ballistic reentry rotational speed, the method comprising the steps of:
respectively determining an upper speed limit value and a lower speed limit value of the angular speed of rotation;
and determining the rotation angle speed according to the measurement and control requirement and the weight coefficient for reducing the falling point scattering requirement based on the upper limit value and the lower limit value.
In a preferred embodiment, the step of determining the upper speed limit includes:
and determining the upper limit value of the rotation starting angular speed according to the measurement and control requirements and the type of the measurement and control antenna. When the angular velocity of rotation is too high, the world link will be frequently interrupted or unable to be established. It is therefore necessary to determine an acceptable time to break the link from the ground to the day, and from this to determine the upper limit value of the cranking angular velocity.
In a preferred embodiment, the upper limit value ω of the cranking angular velocity max ：ω max ＝θ/t min Wherein t is min For the shortest acquisition time, θ is the antenna beam angle.
In a preferred embodiment, the step of determining the lower speed limit comprises:
the lower limit value of the angular velocity of rotation is determined according to the need to reduce the spreading of the drop points and the influencing parameters during reentry. When the take-up angular velocity is too small, it will not function to reduce the landing point spread, so the lower limit value of the take-up angular velocity is determined accordingly.
In a preferred embodiment, the lower limit value ω of the cranking angular velocity min ：
Wherein C is dx The method is characterized in that the method is an aerodynamic roll damping coefficient of an aerospace vehicle, q is dynamic pressure, S is a reference area, l is a reference length, ω is roll angle speed, v is speed, M is aerodynamic roll damping moment, I x The rotational inertia of the spacecraft in the roll direction is alpha, the angular acceleration generated by pneumatic roll damping is alpha, and t is reentry flight time.
In a second aspect, the present invention provides a ballistic reentry angular velocity calculation device, the device comprising:
an upper limit value determining module for determining an upper limit value of the rotational angular velocity;
the lower limit value determining module is used for determining a lower limit value of the starting rotation angular speed;
and the rotation starting angular velocity determining module is used for determining the rotation starting angular velocity according to the weight coefficient of the measurement and control requirement and the falling point scattering requirement reduction based on the upper limit value and the lower limit value.
In a preferred embodiment, the upper limit value determining module specifically performs the following steps:
determining an upper limit value of the rotation starting angular speed according to measurement and control requirements and measurement and control antenna types;
the upper limit value omega of the angular velocity of rotation max ：ω max ＝θ/t min Wherein t is min For the shortest acquisition time, θ is the antenna beam angle.
In a preferred embodiment, the upper limit value determining module specifically performs the following steps:
determining a lower limit value of the rotation starting angular velocity according to the requirement of reducing the falling point scattering and the influence parameters in the reentry process;
the lower limit value omega of the angular velocity of rotation min ：
Wherein C is dx The method is characterized in that the method is an aerodynamic roll damping coefficient of an aerospace vehicle, q is dynamic pressure, S is a reference area, l is a reference length, ω is roll angle speed, v is speed, M is aerodynamic roll damping moment, I x The rotational inertia of the spacecraft in the roll direction is alpha, the angular acceleration generated by pneumatic roll damping, and t is reentry flight time
In a third aspect, the present invention provides a computer-readable storage medium having stored thereon a computer program which, when executed by a processor, performs the steps of the ballistic reentry 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 the instructions in the memory; the storage medium stores therein instructions for executing the steps of the ballistic reentry angular velocity calculation method described above.
The beneficial effects of this scheme are as follows:
according to the scheme, the spinning angular speed of the aerospace vehicle can be determined according to different conditions such as the type and the task of the aerospace vehicle, and the aerospace vehicle can perform ballistic reentry in a spinning mode, so that the ballistic stability is improved, and the drop point scattering is reduced.
Drawings
In order to more clearly illustrate the practice of the present solution, the drawings that are required for the description of the embodiments will be briefly described below, it being apparent that the drawings in the following description are only some embodiments of the present solution and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram showing an example of a ballistic reentry angular velocity calculation method according to the present embodiment;
FIG. 2 is a schematic diagram showing an example of a ballistic reentry angular velocity calculation device according to the present aspect;
fig. 3 shows a schematic diagram of an electronic device according to the present solution.
Detailed Description
Embodiments of the present invention will be described in further detail below with reference to the accompanying drawings. It is clear that the described embodiments are only some of the embodiments of the present solution, not an exhaustive list of all embodiments. It should be noted that, in the case of no conflict, the embodiments and features in the embodiments in the present solution may be combined with each other.
Through research and analysis, the reentry modes of the spacecraft are divided into 3 types according to the existence of lift force effect: lift reentry, semi-ballistic reentry, and ballistic reentry. Wherein the ballistic reentry has no lifting force effect, and the deceleration of the reentry process is realized only by the pneumatic resistance. According to different categories and different tasks of reentry space vehicles, the angular speed of rotation is different.
Therefore, the scheme aims to provide the ballistic reentry angular velocity calculation method, which can determine the ballistic reentry angular velocity according to the type of the aerospace vehicle, the task type and other conditions, so as to meet the design requirements of reentry vehicles of different types.
The following describes a video advertisement identification method according to the present embodiment in detail with reference to the accompanying drawings. As shown in fig. 1, the method may include the steps of:
s1, respectively determining an upper limit value and a lower limit value of the starting angular velocity;
and S2, determining the rotation starting angular speed according to the measurement and control requirement and the weight coefficient for reducing the falling point scattering requirement based on the upper limit value and the lower limit value.
In step S1, the upper limit value of the cranking angular velocity may be adjusted according to the measurement and control requirements. For example, the need to maintain a communication link with the ground during a spacecraft reentry may result in a communication link time-out. 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 upper limit value of the cranking angular velocity is determined according to measurement and controlThe requirements and the measurement and control antenna type. In one embodiment, the upper limit value ω of the cranking angular velocity max ：ω max ＝θ/t min Wherein t is min For the shortest acquisition time, θ is the antenna beam angle.
In step S1, the lower limit value of the cranking angular velocity may be adjusted according to the need to reduce the falling point spread. For example, if the aircraft is not spun during reentry, the aircraft is influenced by deviation of the actual mass center from the central axis, etc., and a tiny lifting force is generated along one direction, and the deviation of the landing point is greatly influenced after the integral along the whole trajectory. To improve ballistic stability, reduce landing point spread, it is necessary to spin the aircraft to balance the minute lift in all directions. The aircraft is also subjected to aerodynamic damping during reentry, resulting in a gradual decay in spin angular velocity. The lower limit of the spin angle speed must therefore be such that the spin angle speed does not decay to 0 throughout the reentry.
In one embodiment, when the angular velocity of rotation is too great, the world link will be frequently interrupted or not established. It is therefore necessary to determine an acceptable time to break the link from the ground to the day, and from this to determine the upper limit value of the cranking angular velocity. In one embodiment, when the take-up angular velocity is too small, it will not function to reduce the landing point spread, so the lower limit value of the take-up angular velocity is determined accordingly.
Further, the lower limit value of the cranking angular velocity is determined by the need to reduce the falling point scattering and the influence parameters in the reentry process. In one embodiment, the lower limit value ω of the cranking angular velocity min ：
Wherein C is dx The method is characterized in that the method is an aerodynamic roll damping coefficient of an aerospace vehicle, q is dynamic pressure, S is a reference area, l is a reference length, ω is roll angle speed, v is speed, M is aerodynamic roll damping moment, I x The rotational inertia of the spacecraft in the roll direction is alpha, the angular acceleration generated by pneumatic roll damping is alpha, and t is reentry flight time.
In step S2, the spinning angular velocity is comprehensively determined according to the determined upper and lower limits of the spinning angular velocity, and by combining the measurement and control requirements and the weight coefficient for reducing the falling point scattering requirements. For example, if the measurement and control demand weight is greater than the demand for reduced drop point spread, the angular speed of rotation may be reduced appropriately; and vice versa, can be raised appropriately.
According to the scheme, the spinning angular speed of the aerospace vehicle can be determined according to different conditions such as the type and the task of the aerospace vehicle, and the aerospace vehicle can perform ballistic reentry in a spinning mode, so that the ballistic stability is improved, and the drop point scattering is reduced.
As shown in fig. 2, the present embodiment further provides a ballistic reentry angular velocity calculation device implemented in combination with the ballistic reentry angular velocity calculation method, the device comprising:
an upper limit value determination module 101 that determines a speed upper limit value of the cranking angular speed;
a lower limit value determination module 102 that determines a lower limit value of the cranking angular velocity;
the rotation angular velocity determining module 103 determines the rotation angular velocity according to the measurement and control requirement and the weight coefficient for reducing the falling point scattering requirement based on the upper limit value and the lower limit value.
When the ballistic reentry starting angular velocity calculation device works, an upper limit value determination module 101 is utilized to determine the upper limit value of the starting angular velocity according to measurement and control requirements and measurement and control antenna types; determining a lower limit value of the rotation starting angular speed by using the lower limit value determining module 102 according to the requirement for reducing the falling point scattering and the influence parameters in the reentry process; finally, the angular speed of rotation is determined by the angular speed of rotation determining module 103 based on the upper and lower limit values according to the measurement and control requirements and the weight coefficient for reducing the falling point scattering requirements.
On the basis of the data acquisition method embodiment, the scheme further provides a computer readable storage medium. The computer readable storage medium is a program product for implementing the data acquisition method described above, which may employ a portable compact disc read-only memory (CD-ROM) and comprise 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 thereto, and in this 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. The readable storage medium can be, for example, but is not limited to, an electronic, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or a combination of any of the foregoing. More specific examples (a non-exhaustive list) of the readable storage medium would include the following: an electrical connection having one or more wires, a portable disk, a hard disk, random Access Memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or flash memory), optical fiber, portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the foregoing.
The computer readable storage medium may include a data signal propagated in baseband or as part of a carrier wave, with readable program code embodied therein. Such a propagated data signal may take any of a variety of forms, including, but not limited to, electro-magnetic, optical, or any suitable combination of the foregoing. 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 of the present scheme 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's computing device, partly on a remote computing device, or entirely on the remote computing device or server. In the case of remote computing devices, 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., connected via the Internet using an Internet service provider).
On the basis of the implementation mode of the data acquisition method, the scheme further provides electronic equipment. The electronic device shown in fig. 3 is only an example, and should not impose any limitation on the functions and the scope of use of the embodiment of the present invention.
As shown in fig. 3, the electronic device 201 is in the form of a general purpose computing device. 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 the different system components.
Wherein the storage unit 202 stores program code that is executable by the processing unit 203 such that the processing unit 203 performs the steps of the various exemplary embodiments described in the data acquisition method above. 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 Random Access Memory (RAM) and/or cache memory units, and may further include Read Only Memory (ROM).
The storage unit 202 may also include programs/utilities having program modules including, but not limited to: an operating system, one or more application programs, other program modules, and program data, each or some combination of which may include an implementation of a network environment.
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, other hardware and/or software modules may be used in connection with the electronic device 201, including but not limited to: microcode, device drivers, redundant processing units, external disk drive arrays, RAID systems, tape drives, data backup storage systems, and the like.
Assuming that the beam angle of a certain spacecraft antenna is 140 degrees and the shortest capturing time is 3s, the upper limit value of the spinning angular velocity is 46.7 degrees/s; according to the numerical simulation result, the lower limit value of the starting angular velocity is 5 degrees/s. Assuming that the measurement and control demand and the reduced drop point spread demand weights each account for 50%, the final angular velocity of rotation is 46.7x0.5+5×
0.5＝25.85°/s。
It should be understood that the foregoing examples of the present invention are provided merely for clearly illustrating the present invention and are not intended to limit the embodiments of the present invention, and that various other changes and modifications may be made therein by one skilled in the art without departing from the spirit and scope of the present invention as defined by the appended claims.
Claims (4)
1. A method for calculating a ballistic reentry angular velocity, the method comprising the steps of:
respectively determining a speed upper limit value and a speed lower limit value of the starting angular speed;
based on the upper limit value and the lower limit value, determining the rotation starting angular speed according to the measurement and control requirements and the weight coefficient for reducing the falling point scattering requirements;
the step of determining the speed upper limit value includes:
determining an upper limit value of the rotation starting angular speed according to measurement and control requirements and measurement and control antenna types;
the upper limit value omega of the angular velocity of rotation max ：ω max ＝θ/t min Wherein t is min For the shortest acquisition time, θ is the antenna beam angle;
the step of determining the lower speed limit value comprises the following steps:
determining a lower limit value of the rotation starting angular velocity according to the requirement of reducing the falling point scattering and the influence parameters in the reentry process;
the lower limit value omega of the angular velocity of rotation min ：
Wherein C is dx The method is characterized in that the method is an aerodynamic roll damping coefficient of an aerospace vehicle, q is dynamic pressure, S is a reference area, l is a reference length, ω is roll angle speed, v is speed, M is aerodynamic roll damping moment, I x The rotational inertia of the spacecraft in the roll direction is alpha, the angular acceleration generated by pneumatic roll damping is alpha, and t is reentry flight time.
2. A ballistic reentry angular velocity computing device, the device comprising:
an upper limit value determining module for determining an upper limit value of the rotational angular velocity;
the lower limit value determining module is used for determining a lower limit value of the starting rotation angular speed;
the rotation starting angular velocity determining module is used for determining the rotation starting angular velocity according to the weight coefficient of the measurement and control requirement and the falling point scattering requirement reduction based on the upper limit value and the lower limit value;
the upper limit value determining module specifically executes the following steps:
determining an upper limit value of the rotation starting angular speed according to measurement and control requirements and measurement and control antenna types;
the upper limit value omega of the angular velocity of rotation max ：ω max ＝θ/t min Wherein t is min For the shortest acquisition time, θ is the antenna beam angle;
the upper limit value determining module specifically executes the following steps:
determining a lower limit value of the rotation starting angular velocity according to the requirement of reducing the falling point scattering and the influence parameters in the reentry process;
the lower limit of the angular velocity of rotationValue omega min ：
Wherein C is dx The method is characterized in that the method is an aerodynamic roll damping coefficient of an aerospace vehicle, q is dynamic pressure, S is a reference area, l is a reference length, ω is roll angle speed, v is speed, M is aerodynamic roll damping moment, I x The rotational inertia of the spacecraft in the roll direction is alpha, the angular acceleration generated by pneumatic roll damping is alpha, and t is reentry flight time.
3. A computer readable storage medium, on which a computer program is stored, characterized in that the program, when being executed by a processor, carries out the steps of the method according to claim 1.
4. An electronic device, comprising: a memory, one or more processors; the memory is connected with the processor through a communication bus; the processor is configured to execute the instructions in the memory; the memory having stored therein instructions for carrying out the steps of the method of claim 1.
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