Method and system for carrying out landing attack angle constant approach power compensation on aircraft on deck

Abstract

The invention belongs to the technical field of control over landing of an aircraft on a deck, and particularly relates to an attack angle constant approach power compensation method and system for landing of the aircraft on the deck. The attack angle constant approach power compensation method for landing of the aircraft on the deck comprises the steps that an attack angle # imgabs0 #, a normal overload # imgabs1 #, a pitch angle rate # imgabs2 #, a longitudinal instruction # imgabs3 # and a roll angle # imgabs4 # are used for compensating the attack angle constant approach power of the aircraft on the deck according to the attack angle # imgabs0 #, the normal overload # imgabs1 #, the pitch angle rate # imgabs2 #, the longitudinal instruction # imgabs3 # and the roll angle # imgabs4 #; a throttle lever angle compensation instruction # imgabs5 #: # imgabs6 # is calculated as a feedback signal; wherein the # imgabs7 is a reference angle of attack, and the # imgabs8 is an angle of attack integral gain coefficient; # imgabs9 # is an incidence angle proportional gain coefficient; # imgabs10 # is a normal overload gain coefficient; the # imgabs11 # is a pitch angle rate gain coefficient; # imgabs12 # is a longitudinal instruction feed-forward gain coefficient; the # imgabs13 # is a roll angle gain coefficient, and the throttle lever is controlled according to the calculated throttle lever angle compensation instruction # imgabs14 #.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft landing control on a deck, and specifically relates to a power compensation method and system for an aircraft performing a constant angle of attack approach on a deck. Background Art

[0002] When an aircraft lands on a ship deck, it is restricted by many harsh conditions such as the limited length of the deck. When approaching and landing, it is necessary to reduce the landing speed as much as possible. To reduce the speed of the aircraft approaching and landing, it is necessary to increase the aircraft's angle of attack to maintain a suitable sinking rate.

[0003] When an aircraft lands on a ship deck, the increase in the angle of attack usually exceeds the critical angle of attack corresponding to the maximum lift-to-drag ratio point, causing the aircraft to enter a speed instability region, i.e., a speed reversal region. Within the speed reversal region, it is difficult to maintain the reference track using the elevator alone, and the track responds to the elevator command with a slow full-pass characteristic, i.e., when the push stick is operated, after the elevator is positively deflected, the aircraft's altitude first decreases, which is consistent with normal operation. However, since the aircraft speed will be less than the minimum drag speed, the final steady-state track angle increases, causing the aircraft's track and attitude to be unstable, posing a major safety hazard.

[0004] This application is proposed in view of the above-mentioned technical defects. Summary of the invention

[0005] The purpose of the present application is to provide a power compensation method and system for an aircraft making a constant angle of attack approach on a deck. By utilizing power compensation, the aircraft can maintain a constant speed and angle of attack during landing on the deck, avoid the increase of the angle of attack exceeding the critical angle of attack, and prevent the aircraft from entering a speed unstable area. The stability of the aircraft's track and attitude is maintained, and the safety hazards of the aircraft landing on the deck are eliminated.

[0006] The technical solution of this application is: On the one hand, a method for compensating power of an aircraft landing on a deck with a constant angle of attack is provided, comprising: Angle of attack , Normal Overload , pitch rate , vertical instructions , Roll Angle , as feedback signal, calculate the throttle stick angle compensation command : ; in, is the reference angle of attack; is the angle of attack integral gain coefficient; is the angle of attack proportional gain coefficient; is the normal overload gain coefficient; is the pitch angle rate gain coefficient; is the longitudinal command feedforward gain coefficient; is the roll angle gain coefficient; The calculated throttle stick angle compensation command , control the throttle lever.

[0007] Optionally, in the above-mentioned method for compensating the power of the aircraft landing on the deck at a constant angle of attack, the reference angle of attack Take 10°~12°.

[0008] Optionally, in the above-mentioned method for compensating the power of the aircraft landing on the deck with a constant angle of attack, the angle of attack integral gain coefficient Take 0.1~1.5; Angle of attack proportional gain factor Take 1~5.

[0009] Optionally, in the above-mentioned power compensation method for a constant angle of attack approach of an aircraft landing on a deck, / The value of is between 0.2 and 0.5.

[0010] Optionally, in the above-mentioned method for compensating the aircraft for a constant angle of attack approach on the deck, the normal overload gain coefficient Take 0.5~1.5; Pitch rate gain factor Take 0.3~0.8; Longitudinal command feedforward gain coefficient Take 0.8~1.2; Roll angle gain factor Take 0.3~0.8.

[0011] On the other hand, a power compensation system for a constant angle of attack approach of an aircraft landing on a deck is provided, which is implemented based on the above-mentioned power compensation method for a constant angle of attack approach of an aircraft landing on a deck, and includes a throttle lever angle compensation instruction calculation module and a throttle lever angle compensation control module; Throttle lever angle compensation command calculation module based on angle of attack , Normal Overload , pitch rate , vertical instructions , Roll Angle , as feedback signal, calculate the throttle stick angle compensation command : ; in, is the reference angle of attack; is the angle of attack integral gain coefficient; is the angle of attack proportional gain coefficient; is the normal overload gain coefficient; is the pitch angle rate gain coefficient; is the longitudinal command feedforward gain coefficient; is the roll angle gain coefficient; The throttle lever angle compensation control module sends the calculated throttle lever angle compensation command to the aircraft control system , control the throttle lever.

[0012] Optionally, in the above aircraft landing on the deck constant angle of attack approach power compensation system, in the throttle angle compensation command calculation module, the reference angle of attack Take 10°~12°.

[0013] Optionally, in the above-mentioned aircraft landing on the deck constant angle of attack approach power compensation system, in the throttle angle compensation instruction calculation module, the angle of attack integral gain coefficient Take 0.1~1.5, angle of attack proportional gain coefficient Take 1~5.

[0014] Optionally, in the above-mentioned aircraft landing on the deck constant angle of attack approach power compensation system, in the throttle lever angle compensation instruction calculation module, / The value of is between 0.2 and 0.5.

[0015] Optionally, in the above-mentioned aircraft landing on the deck constant angle approach power compensation system, in the throttle angle compensation instruction calculation module, the normal overload gain coefficient Take 0.5~1.5, the pitch rate gain coefficient Take 0.3~0.8 as the longitudinal command feedforward gain coefficient Take 0.8~1.2, roll angle gain coefficient Take 0.3~0.8.

[0016] This application has at least the following beneficial technical effects: Provides a method and system for power compensation of an aircraft landing on a deck with a constant angle of attack, and a dynamic fusion angle of attack , Normal Overload , pitch rate , vertical instructions , Roll Angle , as the feedback signal, the throttle lever angle compensation command is calculated , control the throttle lever and perform approach power compensation on the aircraft, so that the aircraft can effectively maintain a constant speed and angle of attack during landing on the deck, avoid the increase of the angle of attack exceeding the critical angle of attack, and cause the aircraft to enter the speed unstable area, so that the aircraft can maintain the stability of the track and attitude, and improve the safety of the aircraft landing on the deck. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a schematic diagram of a control structure of a power compensation method for a constant angle of attack approach of an aircraft on a deck for landing provided by an embodiment of the present application; Figure 2 It is a schematic diagram of an aircraft landing on a deck with a gust angle interference of 1° provided in an embodiment of the present application.

[0018] Figure 3 It is a schematic diagram of the aircraft landing on the deck with a 1° gust angle of attack interfering with the angle of attack response provided by the embodiment of the present application.

[0019] Figure 4 It is a schematic diagram of the flight path angle response of an aircraft landing on a deck with a gust of 1° at an attack angle interfering with the flight path angle provided by an embodiment of the present application; Figure 5 It is a schematic diagram of a power compensation system for an aircraft performing a constant angle of attack approach on a landing deck provided in an embodiment of the present application.

[0020] In order to better illustrate the present embodiment, some contents of the drawings may be omitted, enlarged or reduced, which is only used for illustrative purposes and should not be construed as limiting the present application. DETAILED DESCRIPTION

[0021] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be described in further detail in detail and in detail with reference to the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design.

[0022] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application should be the common meanings understood by those skilled in the art in the field to which this application belongs. The term "include" used in the description of this application means that the concepts appearing before the term include the concepts listed after the term and their equivalents, without excluding other related concepts.

[0023] Flight mechanics theory shows that within the speed reversal zone, the stability of the aircraft's flight path and attitude cannot be maintained by relying solely on the inner and outer loop control systems. The introduction of approach power compensation, that is, compensation with thrust controlled by the throttle lever angle, can enable the aircraft to maintain a constant speed and angle of attack during landing on the deck, thereby preventing the angle of attack from increasing beyond the critical angle of attack and causing the aircraft to enter a speed unstable area. The stability of the aircraft's flight path and attitude can be maintained, eliminating safety hazards when the aircraft lands on the deck.

[0024] Based on the above, the present application provides a power compensation method for an aircraft landing on a deck at a constant angle of attack, and its control structure is as follows: Figure 1 shown.

[0025] Angle of attack , Normal Overload , pitch rate , vertical instructions , Roll Angle , as feedback signal, calculate the throttle stick angle compensation command .

[0026] ; in, is the reference angle of attack, which does not exceed the critical angle of attack corresponding to the maximum lift-to-drag ratio point, and is usually 10°~12°; is the angle of attack integral gain coefficient, ranging from 0.1 to 1.5; is the angle of attack proportional gain coefficient, ranging from 1 to 5; is the normal overload gain coefficient, ranging from 0.5 to 1.5; is the pitch angle rate gain coefficient, ranging from 0.3 to 0.8; is the longitudinal command feedforward gain coefficient, ranging from 0.8 to 1.2; is the roll angle gain coefficient, and its value range is 0.3~0.8.

[0027] The calculated throttle stick angle compensation command , control the throttle lever, perform approach power compensation on the aircraft, so that the aircraft maintains a constant speed and angle of attack during landing on the deck.

[0028] In the power compensation method for a constant angle of attack approach of an aircraft landing on a deck disclosed in the above embodiment, the design is mainly based on the angle of attack With reference angle of attack The deviation is converted into the throttle lever angle compensation command through the integral gain and proportional gain. , which enables the power compensation to have a faster track response capability, and considering that only the angle of attack Feedback can make the power compensation respond faster, but the damping is insufficient during the dynamic response. Therefore, the normal overload is introduced. Feedback is used to increase long-period damping and improve the dynamic characteristics of power compensation. In addition, the pitch angle rate is introduced Feedback allows power compensation to respond quickly to changes in aircraft drag caused by changes in pitch attitude, as well as to introduce longitudinal commands Feedback, as a feedforward signal, can improve the response rate of power compensation to the angle of attack, increase the power compensation bandwidth, and consider the impact of aircraft lateral motion changes and control input on aerodynamic forces, introducing the roll angle Feedback provides corresponding lateral and heading cross-link compensation.

[0029] In the power compensation method for a constant angle of attack approach of an aircraft landing on a deck disclosed in the above embodiment, the angle of attack integral gain coefficient can be further designed. Proportional gain factor with angle of attack The proportional relationship satisfies: / The value of is 0.2~0.5 to form proportional-integral compound compensation control.

[0030] The above embodiment discloses a method for compensating the power of an aircraft landing on a deck at a constant angle of attack. The method is a method for compensating the power of an aircraft landing on a deck at a constant angle of attack based on a hybrid instruction form. , Normal Overload , pitch rate , vertical instructions , Roll Angle , as the feedback signal, the throttle lever angle compensation command is calculated , control the throttle lever, and perform approach power compensation on the aircraft, which can improve the stability of power compensation under complex external disturbances and reduce the lag of phase-frequency characteristics, so that the aircraft can effectively maintain a constant speed and angle of attack during landing on the deck. The angle of attack can be quickly restored after being disturbed by gusts, maintaining the stability of the track and attitude, and improving the safety of the aircraft landing on the deck.

[0031] In a specific simulation example, a gust angle of attack interference of 1° is added, such as Figure 2 As shown, the power compensation method for a constant angle approach of an aircraft landing on a deck disclosed in the above embodiment responds to a step gust as follows: Figure 3-4As shown, it can be seen that it takes about 10 seconds from encountering a gust to completely eliminating the error caused by the gust. When eliminating the angle of attack error caused by the gust, the reverse deviation generated is about 0.7°, which has excellent anti-interference ability.

[0032] Based on the power compensation method for a constant angle of attack approach of an aircraft landing on a deck disclosed in the above embodiment, the present application further provides a power compensation system for a constant angle of attack approach of an aircraft landing on a deck, such as Figure 5 As shown, it includes a throttle lever angle compensation instruction calculation module and a throttle lever angle compensation control module; Throttle lever angle compensation command calculation module based on angle of attack , Normal Overload , pitch rate , vertical instructions , Roll Angle , as feedback signal, calculate the throttle stick angle compensation command : ; in, is the reference angle of attack; is the angle of attack integral gain coefficient; is the angle of attack proportional gain coefficient; is the normal overload gain coefficient; is the pitch angle rate gain coefficient; is the longitudinal command feedforward gain coefficient; is the roll angle gain coefficient; The throttle lever angle compensation control module sends the calculated throttle lever angle compensation command to the aircraft control system , control the throttle lever.

[0033] In the throttle lever angle compensation command calculation module, the reference angle of attack can be designed Take 10°~12°, angle of attack integral gain coefficient Take 0.1~1.5, angle of attack proportional gain coefficient Take 1~5, normal overload gain coefficient Take 0.5~1.5, the pitch rate gain coefficient Take 0.3~0.8 as the longitudinal command feedforward gain coefficient Take 0.8~1.2, roll angle gain coefficient Take 0.3~0.8, and can be further designed / The value of is between 0.2 and 0.5.

[0034] With regard to the power compensation system for a constant angle of attack approach for an aircraft landing on a deck disclosed in the above-mentioned embodiment, since it is implemented based on the power compensation method for a constant angle of attack approach for an aircraft landing on a deck disclosed in the above-mentioned embodiment, the description is relatively simple. For specific related matters, please refer to the relevant description of the power compensation method for a constant angle of attack approach for an aircraft landing on a deck. Its technical effects may also refer to the technical effects of the relevant parts of the power compensation method for a constant angle of attack approach for an aircraft landing on a deck, which will not be repeated here.

[0035] In addition, technicians in the field should also be able to realize that the various modules of the power compensation system for a constant angle of attack approach for an aircraft landing on the deck disclosed in the embodiments of the present application can be implemented by electronic hardware, computer software, or a combination of the two. In order to clearly illustrate the interchangeability of hardware and software, this application generally describes them according to their functions. Whether these functions are performed in hardware or software depends on the specific application and design constraints of the technical solution. Technicians in the field can choose to adopt different methods to implement the described functions for each specific application and its actual constraints, but such implementation should not be considered to be beyond the scope of this application.

[0036] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the scope of protection of the present application.

Claims

1. A power compensation method for an aircraft landing on a deck with a constant angle of attack, characterized in that: include: Angle of attack , Normal Overload , pitch rate , vertical instructions , Roll Angle , as feedback signal, calculate the throttle stick angle compensation command : ； in, is the reference angle of attack; is the angle of attack integral gain coefficient; is the angle of attack proportional gain coefficient; is the normal overload gain coefficient; is the pitch angle rate gain coefficient; is the longitudinal command feedforward gain coefficient; is the roll angle gain coefficient; The calculated throttle stick angle compensation command , control the throttle lever.

2. The power compensation method for an aircraft landing on a deck at a constant angle of attack according to claim 1, characterized in that: Reference angle of attack Take 10°~12°.

3. The power compensation method for an aircraft landing on a deck with a constant angle of attack according to claim 2, characterized in that: Angle of attack integral gain factor Take 0.1~1.5; Angle of attack proportional gain factor Take 1~5.

4. The power compensation method for an aircraft landing on a deck at a constant angle of attack according to claim 3, characterized in that: / The value of is between 0.2 and 0.

5.

5. The power compensation method for an aircraft landing on a deck at a constant angle of attack according to claim 4, characterized in that: Normal overload gain factor Take 0.5~1.5; Pitch rate gain factor Take 0.3~0.8; Longitudinal command feedforward gain coefficient Take 0.8~1.2; Roll angle gain factor Take 0.3~0.

8.

6. A power compensation system for an aircraft landing on a deck with a constant angle of attack, characterized in that: The method for power compensation of an aircraft landing on a deck at a constant angle of attack is implemented based on claim 1, comprising a throttle lever angle compensation instruction calculation module and a throttle lever angle compensation control module; Throttle lever angle compensation command calculation module based on angle of attack , Normal Overload , pitch rate , vertical instructions , Roll Angle , as feedback signal, calculate the throttle stick angle compensation command : ； in, is the reference angle of attack; is the angle of attack integral gain coefficient; is the angle of attack proportional gain coefficient; is the normal overload gain coefficient; is the pitch angle rate gain coefficient; is the longitudinal command feedforward gain coefficient; is the roll angle gain coefficient; The throttle lever angle compensation control module sends the calculated throttle lever angle compensation command to the aircraft control system , control the throttle lever.

7. The power compensation system for an aircraft landing on a deck at a constant angle of attack according to claim 6, characterized in that: In the throttle lever angle compensation command calculation module, the reference angle of attack Take 10°~12°.

8. The power compensation system for an aircraft landing on a deck at a constant angle of attack according to claim 7, characterized in that: In the throttle lever angle compensation command calculation module, the angle of attack integral gain coefficient Take 0.1~1.5, angle of attack proportional gain coefficient Take 1~5.

9. The power compensation system for an aircraft landing on a deck at a constant angle of attack according to claim 8, characterized in that: In the throttle stick angle compensation command calculation module, / The value of is between 0.2 and 0.

5.

10. The power compensation system for an aircraft landing on a deck at a constant angle of attack according to claim 9, characterized in that: In the throttle stick angle compensation command calculation module, the normal overload gain coefficient Take 0.5~1.5, the pitch rate gain coefficient Take 0.3~0.8 as the longitudinal command feedforward gain coefficient Take 0.8~1.2, roll angle gain coefficient Take 0.3~0.8.

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