CN114167887B - 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 and equipment for controlling the falling speed of an aircraft and a readable storage medium, wherein the method comprises the following steps: detecting whether the difference between the predicted falling speed and the standard falling speed is larger than a threshold value; if the drop speed difference is larger than a threshold value, calculating a drop point position control overload and a drop angle control overload, calculating a 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 flight of the aircraft by the first control overload instruction. The invention can effectively control the speed of the aircraft when reaching the target point, and prevent the situation that the landing speed of the aircraft reaching the target point is too fast.
Description
Technical Field
The present invention relates to the field of aircraft guidance control, and in particular, to a method, apparatus, and device for controlling landing speed of an aircraft, and a readable storage medium.
Background
Speed control of terminal guidance of the aircraft is important, and if the falling speed is too high, the aircraft terminal may exceed the heat flow and dynamic pressure lamp constraint, thereby affecting the use effect of the seeker. Meanwhile, the aircraft warhead can only play the best damage effect in a certain falling speed range. It is therefore necessary to design a landing speed control guidance law to enable the aircraft to strike the target at the desired landing speed, so as to achieve the best strike effect. The prior art solves the problem mainly by students at home and abroad, such as an ideal speed curve control method, an optimal control theory control method and a guidance parameter interpolation method. However, these falling speed control methods have problems, such as that the ideal speed curve control method has a relatively large number of assumptions, and many factors affecting the speed control are ignored, so that the falling speed control accuracy is insufficient; the optimization theory is complex in calculation and is difficult to realize on a bullet in practice; the guidance parameter interpolation is a falling speed open loop control, and the control precision is not enough.
Disclosure of Invention
The invention mainly aims to provide a method, a device and equipment for controlling the falling speed of an aircraft and a readable storage medium, and aims to solve the problems that the guidance precision of the aircraft is low and the speed of the aircraft is overlarge when the aircraft reaches a target point.
In a first aspect, the present invention provides a method for controlling a landing speed of an aircraft, where the method for controlling a landing speed of an aircraft includes:
detecting whether the difference between the predicted falling speed and the standard falling speed is larger than a threshold value;
if the drop speed difference is larger than a threshold value, calculating a drop point position control overload and a drop angle control overload, calculating a 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 flight of the aircraft by the first control overload instruction.
Optionally, after the step of detecting whether the difference between the predicted falling speed and the standard falling speed is greater than the threshold value, the method further includes:
if the drop speed difference is not greater than the threshold value, calculating a drop point position control overload and a 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 flight of the aircraft by using the second control overload instruction.
Optionally, before the step of detecting whether the difference between the predicted falling speed and the preset standard falling speed is greater than the threshold value, the method further includes:
and calculating to obtain the predicted falling speed by using an integral extrapolation algorithm according to flight data of the aircraft.
Optionally, the step of calculating the falling point position control overload and the falling angle control overload includes:
calculating to obtain a drop point position longitudinal control overload and a drop angle longitudinal control overload according to the constraint drop angle, the residual flight time and the normal plane bullet eye line angle and the derivative of the normal plane bullet eye line angle to time;
calculating according to the derivative of the horizontal plane bullet vision angle with respect to time to obtain a horizontal control overload of the falling point position and a horizontal control overload of the falling angle;
combining the drop point position longitudinal control overload and the drop point position transverse control overload to obtain a drop point position control overload;
and synthesizing the falling angle longitudinal control overload and the falling angle transverse control overload to obtain the falling angle control overload.
Optionally, the step of calculating 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 Mach number;
obtaining an additional lift coefficient according to the first attack angle and Mach number;
calculating an additional speed direction change rate according to the additional lift coefficient;
and calculating according to the additional speed direction change rate, the falling point position control overload and the falling angle control overload to obtain the falling speed control overload.
In a second aspect, the present invention also provides an aircraft landing speed control device, the aircraft landing speed control device comprising:
the detection module is used for detecting whether the falling speed difference between the predicted falling speed and the standard falling speed is larger than a threshold value;
and the control module is used for calculating the falling point position control overload and the falling angle control overload if the falling speed difference value is larger than the threshold value, calculating the falling speed control overload according to the falling point position control overload and the falling angle control overload, synthesizing a first control overload instruction by the falling point position control overload, the falling angle control overload and the falling speed control overload, and controlling the flight of the aircraft by the first control overload instruction.
Optionally, the control module is further configured to:
if the drop speed difference is not greater than the threshold value, calculating a drop point position control overload and a 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 flight of the aircraft by using the second control overload 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 Mach number;
obtaining an additional lift coefficient according to the first attack angle and Mach number;
calculating an additional speed direction change rate according to the additional lift coefficient;
and calculating according to the additional speed direction change rate, the falling point position control overload and the falling angle control overload to obtain the falling speed control overload.
Optionally, the control module is further configured to:
calculating to obtain a drop point position longitudinal control overload and a drop angle longitudinal control overload according to the constraint drop angle, the residual flight time and the normal plane bullet eye line angle and the derivative of the normal plane bullet eye line angle to time;
calculating according to the derivative of the horizontal plane bullet vision angle with respect to time to obtain a horizontal control overload of the falling point position and a horizontal control overload of the falling angle;
combining the drop point position longitudinal control overload and the drop point position transverse control overload to obtain a drop point control overload;
and synthesizing the falling angle longitudinal control overload and the falling angle transverse control overload to obtain the falling angle control overload.
Optionally, the aircraft landing speed control device further comprises a calculation module, wherein the calculation module is used for calculating the predicted landing speed by using an integral extrapolation algorithm according to flight data of the aircraft.
In a third aspect, the present invention also provides an aircraft landing speed control device, characterized in that the aircraft landing speed control device comprises 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 as described above.
In a fourth aspect, the present invention further provides a readable storage medium, wherein the readable storage medium stores an aircraft landing speed control program, and when the aircraft landing speed control program is executed by a processor, the steps of the aircraft landing speed control method described above are implemented.
The invention provides a method, a device and equipment for controlling the falling speed of an aircraft and a readable storage medium, wherein the method comprises the following steps: detecting whether the difference between the predicted falling speed and the standard falling speed is larger than a threshold value; if the drop speed difference is larger than a threshold value, calculating a drop point position control overload and a drop angle control overload, calculating a 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 flight of the aircraft by the first control overload instruction. The invention can effectively control the speed of the aircraft when reaching the target point, and prevent the situation that the landing speed of the aircraft reaching the target point is too fast.
Drawings
FIG. 1 is a flow chart of a method for controlling aircraft landing speed 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 hardware configuration of an aircraft landing speed control device according to a first embodiment of the present invention.
The achievement of the objects, functional features and advantages of the present invention will be further described with reference to the accompanying drawings, in conjunction with the embodiments.
Detailed Description
It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the invention.
In a first aspect, an embodiment of the invention provides a method for controlling landing speed of an aircraft.
Referring to fig. 1, fig. 1 is a schematic flow chart of a method for controlling a landing speed of an aircraft 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 falling speed difference between the predicted falling speed and the standard falling speed is larger than a threshold value;
and step S20, if the drop speed difference value is larger than a threshold value, calculating a drop point position control overload and a 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 flight of the aircraft by the first control overload instruction.
In this embodiment, the threshold is a calibration value set in advance when the aircraft executes the flight mission, and the calibration value is changed according to different flight scenes and is used as a detection basis. 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 landing speed difference is greater than the threshold value, this indicates that the aircraft is to be landing speed controlled at this point, because the speed of the aircraft when it reaches the target point will be excessive if not controlled. Before calculating the falling speed control overload, the falling point position control overload and the falling angle control overload are required to be calculated, and meanwhile, an additional resistance coefficient is required to be calculated, so that 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 falling speed control overload in this embodiment is as follows:
the first control overload instruction is specifically synthesized by calculating to obtain a first control overload, and the calculation formula of the first control overload is as follows:
in the calculation formula of the overload of the falling speed controlIs longitudinal speed control overload, < >>Is a lateral speed control overload, < >>Is the derivative of ballistic deflection angle with respect to time, +.>Is the derivative of the ballistic tilt angle with respect to time. In the calculation formula of the first control overload +.>For longitudinal control of overload->Lateral control of overload->For the derivative of the ballistic tilt angle with respect to time, < >>Is the derivative of ballistic deflection angle with respect to time, +.>For additional speed direction change rate.
The landing control of the aircraft is not performed only once. Since the aircraft is flying before reaching the target point, the speed is also changing, and the magnitude and direction of the speed are changed over time, the step of controlling overload by dropping speed is required to be continuously performed. Specifically, after the first landing speed control is executed, the aircraft continues to fly, and the system continues to use the landing speed control method of the aircraft. The system will continue to detect if the difference between the predicted landing speed and the standard landing speed is greater than the threshold value, and execute different control instructions to the aircraft according to different detection results. The frequency of detection is preset by the system, and if the difference between the predicted falling speed and the standard falling speed is larger than a threshold value, the falling speed control still needs to be performed.
Further, in an embodiment, after the step of detecting whether the difference between the predicted falling speed and the standard falling speed is greater than the threshold value, the method further includes:
if the drop speed difference is not greater than the threshold value, calculating a drop point position control overload and a 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 flight of the aircraft by using the second control overload instruction.
In this embodiment, if the detection result indicates that the landing speed difference is not greater than the threshold, it indicates that the aircraft does not need to perform landing speed control at this time, but still performs landing position control and landing angle control, and finally synthesizes a second control overload instruction, and controls the aircraft to fly by using the second control overload instruction. The overload of the drop point position control and the overload of the drop angle control are not only executed once, because the aircraft is flying, the predicted drop speed of the aircraft in the subsequent flying process is possibly increased, the drop speed difference between the predicted drop speed and the standard drop speed is also required to be continuously detected, and the drop speed control is still required when the situation that the drop speed difference between the predicted drop speed and the standard drop speed is larger than a threshold value occurs.
Further, in an embodiment, before the step of detecting whether the difference between the predicted falling speed and the preset standard falling speed is greater than the threshold value, the method further includes:
and calculating to obtain the predicted falling speed by using an integral extrapolation algorithm according to flight data of the aircraft.
In this embodiment, the predicted falling speed of the aircraft is calculated by using an integral extrapolation algorithm set with the current position and speed of the aircraft as initial values, where the formula of the integral extrapolation algorithm is as follows:
the lift coefficient in the integral extrapolation algorithm formula is needed to be calculated, and the lift coefficient is calculated according to the following formula:
the lateral force coefficient in the extrapolation algorithm formula is to be calculated; the calculation formula of the lateral force coefficient is as follows:
the calculation mode of the drag coefficient specifically means that the second attack angle is obtained in the lift coefficient table according to the lift coefficient and the Mach number, and the lift coefficient table is preset. And obtaining the resistance coefficient according to the Mach number and the second attack angle in a resistance coefficient table, wherein the resistance coefficient table is preset. The calculation formula of the normal plane bullet eye line angle is as follows:
the calculation formula of the horizontal plane bullet vision angle is as follows:
the calculation formula of the remaining flight time is as follows:
in the integral extrapolation algorithm group formula, a subscript 0 represents the current moment, a subscript T represents the landing moment of the aircraft, V is the speed of the aircraft, θ is the ballistic inclination angle, σ is the ballistic deflection angle, and x, y and z are the coordinates of the current position of the aircraft. q is dynamic pressure, S is reference area, m is mass, g is gravitational acceleration, C D As drag coefficient, C L For lift coefficient, C Z For the lateral force coefficient, V T For said predicted falling speed;
in the lift coefficient calculation formula, theta f In order to restrict the falling angle, eta is the normal plane bullet visual angle,the derivative of the normal plane bullet eye line of sight angle with respect to time;
in the calculation formula of the lateral force coefficient, s is the horizontal plane elastic visual line angle T go In order for the time of flight to remain,the derivative of the view angle of the horizontal plane bullet with respect to time;
in the calculation formulas of the normal plane bullet eye sight angle, the transverse plane bullet eye sight angle and the residual flight time,is the coordinates of the aircraft target point. The coordinates of the target points are determined before the aircraft flies, and the coordinates of the target points are set according to the specific target point requirements of each flight task.
Further, in an embodiment, the step of calculating the falling point position control overload and the falling angle control overload includes:
calculating to obtain a drop point position longitudinal control overload and a drop angle longitudinal control overload according to the constraint drop angle, the residual flight time and the normal plane bullet eye line angle and the derivative of the normal plane bullet eye line angle to time;
calculating according to the derivative of the horizontal plane bullet vision angle with respect to time to obtain a horizontal control overload of the falling point position and a horizontal control overload of the falling angle;
combining the drop point position longitudinal control overload and the drop point position transverse control overload to obtain a drop point position control overload;
and synthesizing the falling angle longitudinal control overload and the falling angle transverse control overload to obtain the falling angle control overload.
In this embodiment, the calculation formulas of the falling point position longitudinal control overload and the falling angle longitudinal control overload are as follows:
the calculation formulas of the drop point position transverse control overload and the drop angle transverse control overload are as follows:
in the above formula, θ f In order to restrict the falling angle, eta is the normal plane bullet visual angle,for the derivative of normal plane bullet eye line angle with respect to time, T go For the remaining time of flight>Is the derivative of ballistic deflection angle with respect to time, +.>For the derivative of the horizontal plane bullet line of sight angle with respect to time,/->Is the derivative of the ballistic tilt angle with respect to time.
When the overload of the drop point position control and the overload of the drop angle control are calculated, calculation needs to be carried out from two layers of the longitudinal and the transverse, so that the calculation result is more accurate, and the precision of the finally synthesized second overload control is improved.
Further, in an embodiment, the step of calculating 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 Mach number;
obtaining an additional lift coefficient according to the first attack angle and Mach number;
calculating an additional speed direction change rate according to the additional lift coefficient;
and calculating according to the additional speed direction change rate, the falling point position control overload and the falling angle control overload to obtain the falling speed control overload.
In this embodiment, the calculation formula of the additional resistance coefficient is as follows:
and obtaining a first attack angle according to the Mach number and the additional resistance coefficient in a resistance coefficient table, wherein 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, an additional speed direction change rate needs to be calculated from the additional lift coefficient. The calculation formula of the additional speed direction change rate is as follows:
c in the calculation formula of the additional resistance coefficient DI For the additional drag coefficient;
in the calculation formula of the additional speed direction change rate,for the additional speed direction change rate, C LI For the additional lift coefficient, K is a correction coefficient, which is selected by simulation, typically taking 1 to 4.
The first embodiment of 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 difference between the predicted falling speed and the standard falling speed is larger than a threshold value; if the drop speed difference is larger than a threshold value, calculating a drop point position control overload and a drop angle control overload, calculating a 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 flight of the aircraft by the first control overload instruction. The embodiment can effectively control the speed of the aircraft when reaching the target point, and prevent the situation that the landing speed of the aircraft reaching the target point is too fast.
In a second aspect, the embodiment of the invention also 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:
the detection module 10 is used for detecting whether the falling speed difference between the predicted falling speed and the standard falling speed is larger than a threshold value;
the control module 20 is configured to calculate a drop point position control overload and a drop angle control overload if the drop velocity difference is greater than a threshold value, calculate a drop velocity control overload according to the drop point position control overload and the drop angle control overload, and synthesize a first control overload instruction with the drop point position control overload, the drop angle control overload and the drop velocity control overload, and control the flight of the aircraft with the first control overload instruction.
Further, in an embodiment, the control module 20 is further configured to:
if the drop speed difference is not greater than the threshold value, calculating a drop point position control overload and a 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 flight of the aircraft by using the second control overload 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 Mach number;
obtaining an additional lift coefficient according to the first attack angle and Mach number;
calculating an additional speed direction change rate according to the additional lift coefficient;
and calculating according to the additional speed direction change rate, the falling point position control overload and the falling angle control overload to obtain the falling speed control overload.
Further, in an embodiment, the control module 20 is further configured to:
calculating to obtain a drop point position longitudinal control overload and a drop angle longitudinal control overload according to the constraint drop angle, the residual flight time and the normal plane bullet eye line angle and the derivative of the normal plane bullet eye line angle to time;
calculating according to the derivative of the horizontal plane bullet vision angle with respect to time to obtain a horizontal control overload of the falling point position and a horizontal control overload of the falling angle;
combining the drop point position longitudinal control overload and the drop point position transverse control overload to obtain a drop point position control overload;
and synthesizing the falling angle longitudinal control overload and the falling angle transverse control overload to obtain the falling angle control overload.
Further, in an embodiment, the aircraft landing speed control device further includes a calculation module, where the calculation module is configured to calculate, according to flight data of the aircraft, a predicted landing speed 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 of each module are not described in detail herein.
In a third aspect, an embodiment of the present invention provides an aircraft landing speed control device, which may be a device with a data processing function, such as a personal computer (personal computer, PC), a notebook computer, a server, or the like.
Referring to fig. 3, fig. 3 is a schematic hardware structure of an aircraft landing speed control device according to an embodiment of the present invention. In an embodiment of the invention, the aircraft landing speed control device may include a processor 1001 (e.g., central processing unit Central Processing Unit, CPU), a communication bus 1002, a user interface 1003, a network interface 1004, and a memory 1005. Wherein the communication bus 1002 is used to enable connected communications between these 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., WIreless-FIdelity, WI-FI interface); the memory 1005 may be a high-speed random access memory (random access memory, RAM) or a stable memory (non-volatile memory), such as a disk memory, and the memory 1005 may alternatively 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 limiting of the invention and may include more or fewer components than shown, or may combine certain components, or a different arrangement of components.
With continued reference to fig. 3, an operating system, a network communication module, a user interface module, and an aircraft landing speed control program may be included in memory 1005, fig. 3, which is a type of computer storage medium. 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, embodiments of the present invention also provide a readable storage medium.
The invention stores the aircraft landing speed control program on the readable storage medium, wherein the aircraft landing speed control program realizes the steps of the aircraft landing speed control method when being executed by the processor.
The method implemented when the aircraft landing speed control program is executed may refer to various embodiments of the aircraft landing speed control method of the present invention, which are not described herein.
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 one … …" does not exclude the presence of other like elements in a process, method, article, or system that comprises the element.
The foregoing embodiment numbers of the present invention are merely for the purpose of description, and do not represent the advantages or disadvantages of the embodiments.
From the above description of the embodiments, it will be clear to those skilled in the art that the above-described embodiment method may be implemented by means of software plus a necessary general hardware platform, but of course may also be implemented by means of hardware, but in many cases the former is a preferred embodiment. Based on such understanding, the technical solution of the present invention may be embodied essentially or in a part contributing to the prior art in the form of a software product stored in a storage medium (e.g. ROM/RAM, magnetic disk, optical disk) as described above, comprising several instructions for causing a terminal device to perform the method according to the embodiments of the present invention.
The foregoing description is only of the preferred embodiments of the present invention, and is not intended to limit the scope of the invention, but rather is intended to cover any equivalents of the structures or equivalent processes disclosed herein or in the alternative, which may be employed directly or indirectly in other related arts.
Claims (6)
1. An aircraft landing speed control method, characterized in that the aircraft landing speed control method comprises the following steps:
calculating to obtain a predicted falling speed by using an integral extrapolation algorithm according to flight data of the aircraft;
detecting whether the difference between the predicted falling speed and the standard falling speed is larger than a threshold value;
if the drop speed difference value is larger than a threshold value, calculating a drop point position control overload and a drop angle control overload, calculating a 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 flight of the aircraft by the first control overload instruction;
if the drop speed difference value is not greater than a threshold value, calculating a drop point position control overload and a 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 flight of the aircraft by using the second control overload instruction;
the step of calculating the falling point position control overload and the falling angle control overload comprises the following steps:
calculating to obtain a drop point position longitudinal control overload and a drop angle longitudinal control overload according to the constraint drop angle, the residual flight time and the normal plane bullet eye line angle and the derivative of the normal plane bullet eye line angle to time;
calculating according to the derivative of the horizontal plane bullet vision angle with respect to time to obtain a horizontal control overload of the falling point position and a horizontal control overload of the falling angle;
combining the drop point position longitudinal control overload and the drop point position transverse control overload to obtain a drop point position control overload;
and synthesizing the falling angle longitudinal control overload and the falling angle transverse control overload to obtain the falling angle control overload.
2. The aircraft landing speed control method of claim 1, wherein the step of calculating a landing speed control overload from the landing position control overload and the landing angle control overload comprises:
calculating an additional resistance coefficient;
obtaining a first attack angle according to the additional resistance coefficient and Mach number;
obtaining an additional lift coefficient according to the first attack angle and Mach number;
calculating an additional speed direction change rate according to the additional lift coefficient;
and calculating according to the additional speed direction change rate, the falling point position control overload and the falling angle control overload to obtain the falling speed control overload.
3. An aircraft landing speed control device, characterized in that the aircraft landing speed control device comprises:
the calculation module is used for calculating to obtain a predicted falling speed by using an integral extrapolation algorithm according to flight data of the aircraft;
the detection module is used for detecting whether the falling speed difference between the predicted falling speed and the standard falling speed is larger than a threshold value;
the control module is used for calculating a drop point position control overload and a drop angle control overload if the drop speed difference value is larger than a threshold value, 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 flight of the aircraft by the first control overload instruction;
the control module is further configured to calculate a drop point position control overload and a drop angle control overload if the drop speed difference value is not greater than a threshold value, and synthesize the drop point position control overload and the drop angle control overload into a second overload instruction, and control the flight of the aircraft with the second overload instruction;
the control module is also used for calculating the falling point position longitudinal control overload and the falling angle longitudinal control overload according to the constraint falling angle, the residual flight time and the normal plane bullet sight line angle and the derivative of the normal plane bullet sight line angle to time; calculating according to the derivative of the horizontal plane bullet vision angle with respect to time to obtain a horizontal control overload of the falling point position and a horizontal control overload of the falling angle; combining the drop point position longitudinal control overload and the drop point position transverse control overload to obtain a drop point position control overload; and synthesizing the falling angle longitudinal control overload and the falling angle transverse control overload to obtain the falling angle control overload.
4. The aircraft landing speed control device of claim 3, 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 Mach number;
obtaining an additional lift coefficient according to the first attack angle and Mach number;
calculating an additional speed direction change rate according to the additional lift coefficient;
and calculating according to the additional speed direction change rate, the falling point position control overload and the falling angle control overload to obtain the falling speed control overload.
5. An aircraft landing speed control device, characterized in that it comprises 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 according to claim 1 or 2.
6. A readable storage medium, wherein an aircraft landing speed control program is stored on the readable storage medium, wherein the aircraft landing speed control program, when executed by a processor, implements the steps of the aircraft landing speed control method according to claim 1 or 2.
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