CN114167887A - Aircraft landing speed control method, device, equipment and readable storage medium - Google Patents
Aircraft landing speed control method, device, equipment and readable storage medium Download PDFInfo
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Abstract
The invention provides a method, a device, equipment and a readable storage medium for controlling the landing speed of an aircraft, wherein the method comprises the following steps: detecting whether the drop speed difference value of the predicted drop speed and the standard drop speed is greater than a threshold value; and if the drop speed difference value is greater than a threshold value, calculating drop point position control overload and drop angle control overload, calculating the drop speed control overload according to the drop point position control overload and the drop angle control overload, synthesizing a first control overload instruction by using the drop point position control overload, the drop angle control overload and the drop speed control overload, and controlling the aircraft to fly by using the first control overload instruction. The invention can effectively control the speed of the aircraft when the aircraft reaches the target point, and prevent the condition that the landing speed of the aircraft when the aircraft reaches the target point is too high.
Description
Technical Field
The invention relates to the field of aircraft guidance control, in particular to an aircraft falling speed control method, device and equipment and a readable storage medium.
Background
The speed control of the terminal guidance of the aircraft is important, and if the falling speed is too high, the aircraft terminal may exceed the restriction of heat flow and dynamic pressure lamps, so that the use effect of the seeker is influenced. Meanwhile, the aircraft warhead can only play the best damage effect within a certain falling speed range. Therefore, a drop speed control guidance law needs to be designed so that the aircraft strikes the target at a desired drop speed, and the best striking effect is achieved. The prior art mainly solves the problem by providing an ideal speed curve control method, an optimal control theory control method and a guidance parameter interpolation method by scholars at home and abroad. However, these falling speed control methods have respective problems, for example, the ideal speed curve control method has more assumptions, and more factors affecting speed control can be ignored, so that the falling speed control accuracy is insufficient; the optimization theory is complex in calculation and is difficult to realize in practice; the guidance parameter interpolation is a falling speed open-loop control, and the control precision is insufficient.
Disclosure of Invention
The invention mainly aims to provide an aircraft landing speed control method, an aircraft landing speed control device, aircraft landing speed control equipment and a readable storage medium, and aims to solve the problems that the guidance precision of an aircraft is not high and the speed of the aircraft is too high when the aircraft reaches a target point.
In a first aspect, the present invention provides an aircraft landing speed control method, where the aircraft landing speed control method includes:
detecting whether the drop speed difference value of the predicted drop speed and the standard drop speed is greater than a threshold value;
and if the drop speed difference value is greater than a threshold value, calculating drop point position control overload and drop angle control overload, calculating the drop speed control overload according to the drop point position control overload and the drop angle control overload, synthesizing a first control overload instruction by using the drop point position control overload, the drop angle control overload and the drop speed control overload, and controlling the aircraft to fly by using the first control overload instruction.
Optionally, after the step of detecting whether the drop speed difference between the predicted drop speed and the standard drop speed is greater than the threshold, the method further includes:
and if the drop speed difference value is not greater than the threshold value, calculating the drop point position control overload and the drop angle control overload, synthesizing the drop point position control overload and the drop angle control overload into a second overload instruction, and controlling the aircraft to fly by using the second overload control instruction.
Optionally, before the step of detecting whether the drop velocity difference between the predicted drop velocity and the preset standard drop velocity is greater than the threshold, the method further includes:
and calculating the predicted falling speed by using an integral extrapolation algorithm according to the flight data of the aircraft.
Optionally, the step of calculating the landing point position control overload and the landing angle control overload includes:
calculating according to the constraint falling angle, the residual flight time, the normal plane bullet eye sight angle and the derivative of the normal plane bullet eye sight angle to time to obtain the longitudinal control overload of the falling point position and the longitudinal control overload of the falling angle;
calculating according to the derivative of the horizontal plane bullet eye sight angle to time to obtain the horizontal control overload of the falling point position and the horizontal control overload of the falling angle;
synthesizing the longitudinal control overload of the drop point position and the transverse control overload of the drop point position to obtain the control overload of the drop point position;
and synthesizing the longitudinal control overload of the falling angle and the transverse control overload of the falling angle to obtain the control overload of the falling angle.
Optionally, the step of calculating to obtain the falling speed control overload according to the falling point position control overload and the falling angle control overload includes:
calculating an additional resistance coefficient;
obtaining a first attack angle according to the additional resistance coefficient and the Mach number;
obtaining an additional lift coefficient according to the first attack angle and the Mach number;
calculating to obtain the change rate of the additional speed direction according to the additional lift coefficient;
and calculating to obtain the falling speed control overload according to the additional speed direction change rate, the falling point position control overload and the falling angle control overload.
In a second aspect, the present invention also provides an aircraft landing speed control device, including:
the detection module is used for detecting whether the drop speed difference value of the predicted drop speed and the standard drop speed is larger than a threshold value;
and the control module is used for calculating the landing point position control overload and the landing angle control overload if the landing speed difference value is greater than a threshold value, calculating the landing speed control overload according to the landing point position control overload and the landing angle control overload, synthesizing a first control overload instruction by the landing point position control overload, the landing angle control overload and the landing speed control overload, and controlling the aircraft to fly by the first control overload instruction.
Optionally, the control module is further configured to:
and if the drop speed difference value is not greater than the threshold value, calculating the drop point position control overload and the drop angle control overload, synthesizing the drop point position control overload and the drop angle control overload into a second overload instruction, and controlling the aircraft to fly by using the second overload control instruction.
Optionally, the control module is further configured to:
calculating an additional resistance coefficient;
obtaining a first attack angle according to the additional resistance coefficient and the Mach number;
obtaining an additional lift coefficient according to the first attack angle and the Mach number;
calculating to obtain the change rate of the additional speed direction according to the additional lift coefficient;
and calculating to obtain the falling speed control overload according to the additional speed direction change rate, the falling point position control overload and the falling angle control overload.
Optionally, the control module is further configured to:
calculating according to the constraint falling angle, the residual flight time, the normal plane bullet eye sight angle and the derivative of the normal plane bullet eye sight angle to time to obtain the longitudinal control overload of the falling point position and the longitudinal control overload of the falling angle;
calculating according to the derivative of the horizontal plane bullet eye sight angle to time to obtain the horizontal control overload of the falling point position and the horizontal control overload of the falling angle;
synthesizing the longitudinal control overload of the drop point position and the transverse control overload of the drop point position to obtain the drop point control overload;
and synthesizing the longitudinal control overload of the falling angle and the transverse control overload of the falling angle to obtain the control overload of the falling angle.
Optionally, the aircraft landing speed control device further includes a calculation module, and the calculation module is configured to calculate, according to flight data of the aircraft, a predicted landing speed by using an integral extrapolation algorithm.
In a third aspect, the present invention further provides an aircraft landing speed control device, which is characterized in that the aircraft landing speed control device includes a processor, a memory, and an aircraft landing speed control program stored on the memory and executable by the processor, wherein when the aircraft landing speed control program is executed by the processor, the steps of the aircraft landing speed control method as described above are implemented.
In a fourth aspect, the present invention also provides a readable storage medium, which is characterized in that the readable storage medium stores an aircraft landing speed control program, wherein the aircraft landing speed control program, when executed by a processor, implements the steps of the aircraft landing speed control method as described above.
The invention provides a method, a device, equipment and a readable storage medium for controlling the landing speed of an aircraft, wherein the method comprises the following steps: detecting whether the drop speed difference value of the predicted drop speed and the standard drop speed is greater than a threshold value; and if the drop speed difference value is greater than a threshold value, calculating drop point position control overload and drop angle control overload, calculating the drop speed control overload according to the drop point position control overload and the drop angle control overload, synthesizing a first control overload instruction by using the drop point position control overload, the drop angle control overload and the drop speed control overload, and controlling the aircraft to fly by using the first control overload instruction. The invention can effectively control the speed of the aircraft when the aircraft reaches the target point, and prevent the condition that the landing speed of the aircraft when the aircraft reaches the target point is too high.
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Fig. 1 is a schematic flow chart of an aircraft landing speed control method according to a first embodiment of the present invention;
FIG. 2 is a functional block diagram of an aircraft landing speed control device according to a first embodiment of the present invention;
fig. 3 is a schematic diagram of a hardware configuration of an aircraft landing speed control device according to a first embodiment of the present invention.
The implementation, functional features and advantages of the objects of the present invention will be further explained with reference to the accompanying drawings.
Detailed Description
It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
In a first aspect, an embodiment of the present invention provides an aircraft landing speed control method.
Referring to fig. 1, fig. 1 is a schematic flow chart of an aircraft landing speed control method according to a first embodiment of the present invention. As shown in fig. 1, the aircraft landing speed control method includes:
step S10, detecting whether the drop speed difference value of the predicted drop speed and the standard drop speed is larger than a threshold value;
and step S20, if the drop speed difference is larger than a threshold value, calculating the drop point position control overload and the drop angle control overload, calculating the drop speed control overload according to the drop point position control overload and the drop angle control overload, synthesizing a first control overload instruction by the drop point position control overload, the drop angle control overload and the drop speed control overload, and controlling the aircraft to fly by the first control overload instruction.
In this embodiment, the threshold is a calibration value set in advance when the aircraft executes a flight mission, and is changed according to different flight scenarios and used as a basis for detection. The predicted falling speed is calculated according to an integral extrapolation algorithm, and the standard falling speed is a value set by the aircraft according to a specific flight scene. If the difference value of the falling speeds is larger than the threshold value, the aircraft needs to be controlled to the falling speed at the moment, because if the aircraft is not controlled, the speed of the aircraft reaching the target point is overlarge. Before the falling speed control overload is calculated, the falling point position control overload and the falling angle control overload need to be calculated, an additional resistance coefficient also needs to be calculated, and the falling speed control overload is obtained based on the additional resistance coefficient, the falling point position control overload and the falling angle control overload.
The calculation formula of the drop speed control overload in the embodiment is as follows:
synthesizing the first overload control instruction specifically means that the first overload control is obtained by calculation, and a calculation formula of the first overload control is as follows:
in the formula for calculating the overload of the falling speed control
Is that the longitudinal speed control is overloaded,
is a side-to-side speed control overload,
is the derivative of the ballistic declination angle with respect to time,
is the derivative of the ballistic inclination angle with respect to time. In the formula for calculating the first control overload
In order to control the overload in the longitudinal direction,
the overload is controlled in the side direction,
is the derivative of the ballistic inclination angle with respect to time,
is the derivative of the ballistic declination angle with respect to time,
is the additional velocity direction change rate.
The control of the landing speed of the aircraft is not performed only once. Since the aircraft is flying until reaching the target point, the speed is changed, and the magnitude and direction of the speed are changed along with the time, the step of controlling overload by the falling speed is required to be continuously executed. Specifically, after the landing speed control is finished once, the aircraft continues flying, and the system continues to use the aircraft landing speed control method related by the invention. The system will continue to detect whether the drop velocity difference between the predicted drop velocity and the standard drop velocity is greater than the threshold value, and execute different control instructions to the aircraft according to different detection results. The detected frequency is preset by the system, and if the drop speed difference value between the predicted drop speed and the standard drop speed is larger than the threshold value, the drop speed control still needs to be carried out.
Further, in an embodiment, after the step of detecting whether the drop speed difference between the predicted drop speed and the standard drop speed is greater than the threshold, the method further includes:
and if the drop speed difference value is not greater than the threshold value, calculating the drop point position control overload and the drop angle control overload, synthesizing the drop point position control overload and the drop angle control overload into a second overload instruction, and controlling the aircraft to fly by using the second overload control instruction.
In this embodiment, if the detection result indicates that the landing velocity difference is not greater than the threshold, it indicates that the aircraft does not need to perform landing velocity control at this time, but still performs landing point position control and landing angle control, and finally synthesizes a second overload control instruction, and controls the aircraft to fly according to the second overload control instruction. The landing point position control overload and the landing angle control overload are not only executed once, because the aircraft flies, the predicted landing speed of the subsequent flying process is likely to be increased, the landing speed difference value between the predicted landing speed and the standard landing speed needs to be continuously detected, and when the landing speed difference value between the predicted landing speed and the standard landing speed is larger than the threshold value, the landing speed control still needs to be carried out.
Further, in an embodiment, before the step of detecting whether the drop velocity difference between the predicted drop velocity and the preset standard drop velocity is greater than the threshold, the method further includes:
and calculating the predicted falling speed by using an integral extrapolation algorithm according to the flight data of the aircraft.
In this embodiment, the predicted falling speed of the aircraft is calculated by using the current position and speed of the aircraft as initial values and using an integral extrapolation algorithm set, where the formula of the integral extrapolation algorithm is as follows:
the lift coefficient in the integral extrapolation algorithm formula needs to be calculated, and the calculation formula of the lift coefficient is as follows:
the lateral force coefficient in the extrapolation algorithm formula needs to be calculated; the calculation formula of the lateral force coefficient is as follows:
the calculation mode of the resistance coefficient specifically means that a second attack angle is obtained according to the lift coefficient and the Mach number in a lift coefficient table, and the lift coefficient table is preset. And in a resistance coefficient table, the resistance coefficient is obtained according to the Mach number and the second attack angle, and the resistance coefficient table is preset. The calculation formula of the normal plane bullet eye sight angle is as follows:
the calculation formula of the horizontal plane bullet eye sight angle is as follows:
the remaining flight times are calculated as follows:
in the formula of the integral extrapolation algorithm group, subscript 0 represents the current time, subscript T represents the landing time of the aircraft, V represents the speed of the aircraft, theta represents the ballistic inclination angle, sigma represents the ballistic deflection angle, and x, y and z represent the coordinates of the current position of the aircraft. q is dynamic pressure, S is reference area, m is mass, g is gravitational acceleration, CDIs a coefficient of resistance, CLIs a coefficient of lift, CZIs the coefficient of lateral force, VTIs the predicted falling velocity;
in the lift coefficient calculation formula, thetafIn order to restrict the falling angle, eta is the normal plane bullet eye sight angle,
is the time derivative of the normal plane bullet eye line-of-sight angle;
in the formula for calculating the lateral force coefficient, s is the visual angle of the transverse plane bullet eye, and TgoTo be the remaining time of flight,
is the derivative of the horizontal plane bullet eye line-of-sight angle to time;
normal plane bullet eye sight angle, transverse plane bullet eyeIn the calculation formula of the line angle and the remaining flight time,
coordinates of the aircraft target point. The coordinates of the target point are determined before the flight of the aircraft, and are set according to the specific target point requirement of each flight task.
Further, in an embodiment, the step of calculating the landing point position control overload and the landing angle control overload includes:
calculating according to the constraint falling angle, the residual flight time, the normal plane bullet eye sight angle and the derivative of the normal plane bullet eye sight angle to time to obtain the longitudinal control overload of the falling point position and the longitudinal control overload of the falling angle;
calculating according to the derivative of the horizontal plane bullet eye sight angle to time to obtain the horizontal control overload of the falling point position and the horizontal control overload of the falling angle;
synthesizing the longitudinal control overload of the drop point position and the transverse control overload of the drop point position to obtain the control overload of the drop point position;
and synthesizing the longitudinal control overload of the falling angle and the transverse control overload of the falling angle to obtain the control overload of the falling angle.
In this embodiment, the calculation formulas of the longitudinal control overload at the landing point and the longitudinal control overload at the landing angle are as follows:
the calculation formulas of the transverse control overload of the drop point position and the transverse control overload of the drop angle are as follows:
in the above formula, θfIn order to restrict the falling angle, eta is the normal plane bullet eye sight angle,
as the time derivative of normal plane projectile line-of-sight angle，TgoTo be the remaining time of flight,
is the derivative of the ballistic declination angle with respect to time,
the derivative of the transverse planar projectile line of sight angle with respect to time,
is the derivative of the ballistic inclination angle with respect to time.
When the overload of the position control of the landing point and the overload of the angle control are calculated, calculation needs to be carried out from the longitudinal level and the transverse level, so that the calculation result is more accurate, and the accuracy of the second overload control obtained by synthesis is improved.
Further, in an embodiment, the step of calculating the landing speed control overload according to the landing point position control overload and the landing angle control overload includes:
calculating an additional resistance coefficient;
obtaining a first attack angle according to the additional resistance coefficient and the Mach number;
obtaining an additional lift coefficient according to the first attack angle and the Mach number;
calculating to obtain the change rate of the additional speed direction according to the additional lift coefficient;
and calculating to obtain the falling speed control overload according to the additional speed direction change rate, the falling point position control overload and the falling angle control overload.
In this embodiment, the calculation formula of the additional resistance coefficient is as follows:
and in the resistance coefficient table, a first attack angle is obtained according to the Mach number and the additional resistance coefficient, and the resistance coefficient table is preset. And obtaining an additional lift coefficient according to the first attack angle and the Mach number in a lift coefficient table, wherein the lift coefficient table is preset. After the additional lift coefficient is obtained, the additional speed direction change rate needs to be calculated according to the additional lift coefficient. The calculation formula of the additional speed direction change rate is as follows:
in the formula for calculating the additional resistance coefficient, CDIIs the additional drag coefficient;
in the formula for calculating the additional velocity direction change rate,
for the additional velocity direction change rate, CLIFor the additional lift coefficient, K is a correction coefficient, which is selected by simulation, typically from 1 to 4.
The invention relates to a first embodiment and provides an aircraft landing speed control method, device, equipment and a readable storage medium, wherein the method comprises the following steps: detecting whether the drop speed difference value of the predicted drop speed and the standard drop speed is greater than a threshold value; and if the drop speed difference value is greater than a threshold value, calculating drop point position control overload and drop angle control overload, calculating the drop speed control overload according to the drop point position control overload and the drop angle control overload, synthesizing a first control overload instruction by using the drop point position control overload, the drop angle control overload and the drop speed control overload, and controlling the aircraft to fly by using the first control overload instruction. The speed of the aircraft reaching the target point can be effectively controlled, and the situation that the landing speed of the aircraft reaching the target point is too high is prevented.
In a second aspect, the embodiment of the invention further provides an aircraft landing speed control device.
Referring to fig. 2, a functional block diagram of a first embodiment of an aircraft landing speed control device is shown.
In this embodiment, the aircraft landing speed control device includes:
a detection module 10, configured to detect whether a drop velocity difference between the predicted drop velocity and the standard drop velocity is greater than a threshold;
and the control module 20 is configured to calculate a landing point position control overload and a landing angle control overload if the landing speed difference is greater than a threshold value, calculate a landing speed control overload according to the landing point position control overload and the landing angle control overload, synthesize a first control overload instruction according to the landing point position control overload, the landing angle control overload and the landing speed control overload, and control the aircraft to fly according to the first control overload instruction.
Further, in an embodiment, the control module 20 is further configured to:
and if the drop speed difference value is not greater than the threshold value, calculating the drop point position control overload and the drop angle control overload, synthesizing the drop point position control overload and the drop angle control overload into a second overload instruction, and controlling the aircraft to fly by using the second overload control instruction.
Further, in an embodiment, the control module 20 is further configured to:
calculating an additional resistance coefficient;
obtaining a first attack angle according to the additional resistance coefficient and the Mach number;
obtaining an additional lift coefficient according to the first attack angle and the Mach number;
calculating to obtain the change rate of the additional speed direction according to the additional lift coefficient;
and calculating to obtain the falling speed control overload according to the additional speed direction change rate, the falling point position control overload and the falling angle control overload.
Further, in an embodiment, the control module 20 is further configured to:
calculating according to the constraint falling angle, the residual flight time, the normal plane bullet eye sight angle and the derivative of the normal plane bullet eye sight angle to time to obtain the longitudinal control overload of the falling point position and the longitudinal control overload of the falling angle;
calculating according to the derivative of the horizontal plane bullet eye sight angle to time to obtain the horizontal control overload of the falling point position and the horizontal control overload of the falling angle;
synthesizing the longitudinal control overload of the drop point position and the transverse control overload of the drop point position to obtain the control overload of the drop point position;
and synthesizing the longitudinal control overload of the falling angle and the transverse control overload of the falling angle to obtain the control overload of the falling angle.
Further, in an embodiment, the aircraft landing speed control device further includes a calculation module, and the calculation module is configured to calculate, according to flight data of the aircraft, a predicted landing speed by using an integral extrapolation algorithm.
The function implementation of each module in the aircraft landing speed control device corresponds to each step in the aircraft landing speed control method embodiment, and the function and implementation process are not described in detail here.
In a third aspect, embodiments of the present invention provide an aircraft landing speed control device, which may be a Personal Computer (PC), a laptop, a server, or other device having a data processing function.
Referring to fig. 3, fig. 3 is a schematic diagram of a hardware structure of an aircraft landing speed control device according to an embodiment of the present invention. In an embodiment of the present invention, the aircraft landing speed control device may include a processor 1001 (e.g., a Central Processing Unit, CPU), a communication bus 1002, a user interface 1003, a network interface 1004, and a memory 1005. The communication bus 1002 is used for realizing connection communication among the components; the user interface 1003 may include a Display screen (Display), an input unit such as a Keyboard (Keyboard); the network interface 1004 may optionally include a standard wired interface, a WIreless interface (e.g., a WI-FI interface, WI-FI interface); the memory 1005 may be a Random Access Memory (RAM) or a non-volatile memory (non-volatile memory), such as a magnetic disk memory, and the memory 1005 may optionally be a storage device independent of the processor 1001. Those skilled in the art will appreciate that the hardware configuration shown in fig. 3 is not intended to be limiting of the present invention and may include more or fewer components than those shown, or some components may be combined, or a different arrangement of components.
With continued reference to FIG. 3, the memory 1005 of FIG. 3, which is one type of computer storage medium, may include an operating system, a network communication module, a user interface module, and an aircraft landing speed control program. The processor 1001 may call an aircraft landing speed control program stored in the memory 1005, and execute the aircraft landing speed control method provided by the embodiment of the present invention.
In a fourth aspect, the embodiment of the present invention further provides a readable storage medium.
The readable storage medium of the present invention stores an aircraft landing speed control program, wherein the aircraft landing speed control program, when executed by a processor, implements the steps of the aircraft landing speed control method as described above.
The method for implementing the aircraft landing speed control program when executed may refer to various embodiments of the aircraft landing speed control method of the present invention, and will not be described herein again.
It should be noted that, in this document, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or system that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or system. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other like elements in a process, method, article, or system that comprises the element.
The above-mentioned serial numbers of the embodiments of the present invention are merely for description and do not represent the merits of the embodiments.
Through the above description of the embodiments, those skilled in the art will clearly understand that the method of the above embodiments can be implemented by software plus a necessary general hardware platform, and certainly can also be implemented by hardware, but in many cases, the former is a better implementation manner. Based on such understanding, the technical solution of the present invention may be embodied in the form of a software product, which is stored in a storage medium (e.g., ROM/RAM, magnetic disk, optical disk) as described above and includes instructions for causing a terminal device to execute the method according to the embodiments of the present invention.
The above description is only a preferred embodiment of the present invention, and not intended to limit the scope of the present invention, and all modifications of equivalent structures and equivalent processes, which are made by using the contents of the present specification and the accompanying drawings, or directly or indirectly applied to other related technical fields, are included in the scope of the present invention.
Claims (10)
1. An aircraft landing speed control method, characterized in that the aircraft landing speed control method comprises:
detecting whether the drop speed difference value of the predicted drop speed and the standard drop speed is greater than a threshold value;
and if the drop speed difference value is greater than a threshold value, calculating drop point position control overload and drop angle control overload, calculating the drop speed control overload according to the drop point position control overload and the drop angle control overload, synthesizing a first control overload instruction by using the drop point position control overload, the drop angle control overload and the drop speed control overload, and controlling the aircraft to fly by using the first control overload instruction.
2. The aircraft landing speed control method of claim 1, wherein after the step of detecting whether the landing speed difference between the predicted landing speed and the standard landing speed is greater than a threshold value, further comprising:
and if the drop speed difference value is not greater than the threshold value, calculating the drop point position control overload and the drop angle control overload, synthesizing the drop point position control overload and the drop angle control overload into a second overload instruction, and controlling the aircraft to fly by using the second overload control instruction.
3. The aircraft drop speed control method according to claim 1, characterized in that before said step of detecting whether the drop speed difference of the predicted drop speed from a preset standard drop speed is greater than a threshold value, it further comprises:
and calculating the predicted falling speed by using an integral extrapolation algorithm according to the flight data of the aircraft.
4. The aircraft landing speed control method of claim 1, wherein the step of calculating a landing point position control overload and a landing angle control overload comprises:
calculating according to the constraint falling angle, the residual flight time, the normal plane bullet eye sight angle and the derivative of the normal plane bullet eye sight angle to time to obtain the longitudinal control overload of the falling point position and the longitudinal control overload of the falling angle;
calculating according to the derivative of the horizontal plane bullet eye sight angle to time to obtain the horizontal control overload of the falling point position and the horizontal control overload of the falling angle;
synthesizing the longitudinal control overload of the drop point position and the transverse control overload of the drop point position to obtain the control overload of the drop point position;
and synthesizing the longitudinal control overload of the falling angle and the transverse control overload of the falling angle to obtain the control overload of the falling angle.
5. The aircraft landing speed control method of claim 4, wherein the step of calculating a landing speed control overload from a landing point position control overload and a landing angle control overload comprises:
calculating an additional resistance coefficient;
obtaining a first attack angle according to the additional resistance coefficient and the Mach number;
obtaining an additional lift coefficient according to the first attack angle and the Mach number;
calculating to obtain the change rate of the additional speed direction according to the additional lift coefficient;
and calculating to obtain the falling speed control overload according to the additional speed direction change rate, the falling point position control overload and the falling angle control overload.
6. An aircraft landing speed control device, characterized in that the aircraft landing speed control device comprises:
the detection module is used for detecting whether the drop speed difference value of the predicted drop speed and the standard drop speed is larger than a threshold value;
and the control module is used for calculating the landing point position control overload and the landing angle control overload if the landing speed difference value is greater than a threshold value, calculating the landing speed control overload according to the landing point position control overload and the landing angle control overload, synthesizing a first control overload instruction by the landing point position control overload, the landing angle control overload and the landing speed control overload, and controlling the aircraft to fly by the first control overload instruction.
7. The aircraft stall control device of claim 6, wherein the control module is further configured to:
and if the drop speed difference value is not greater than the threshold value, calculating the drop point position control overload and the drop angle control overload, synthesizing the drop point position control overload and the drop angle control overload into a second overload instruction, and controlling the aircraft to fly by using the second overload control instruction.
8. The aircraft stall control device of claim 6, wherein the control module is further configured to:
calculating an additional resistance coefficient;
obtaining a first attack angle according to the additional resistance coefficient and the Mach number;
obtaining an additional lift coefficient according to the first attack angle and the Mach number;
calculating to obtain the change rate of the additional speed direction according to the additional lift coefficient;
and calculating to obtain the falling speed control overload according to the additional speed direction change rate, the falling point position control overload and the falling angle control overload.
9. An aircraft landing speed control apparatus comprising a processor, a memory, and an aircraft landing speed control program stored on the memory and executable by the processor, wherein the aircraft landing speed control program when executed by the processor implements the steps of the aircraft landing speed control method of any of claims 1 to 5.
10. A readable storage medium, characterized in that the readable storage medium has stored thereon an aircraft landing speed control program, wherein the aircraft landing speed control program, when executed by a processor, implements the steps of the aircraft landing speed control method according to any one of claims 1 to 5.
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