Power compensation method and system for aircraft landing on deck with constant angle of attack

Abstract

The present application belongs to the technical field of aircraft landing control on a deck, and specifically relates to a method and system for power compensation of an aircraft landing on a deck at a constant angle of attack. The method comprises: using the angle of attack #imgabs0#, normal overload #imgabs1#, pitch angle rate #imgabs2#, longitudinal instruction #imgabs3#, and roll angle #imgabs4# as feedback signals to calculate the throttle stick angle compensation instruction #imgabs5#: #i mgabs6#; among them, #imgabs7# is the reference angle of attack, #imgabs8# is the angle of attack integral gain coefficient, #imgabs9# is the angle of attack proportional gain coefficient, #imgabs10# is the normal overload gain coefficient, #imgabs11# is the pitch angle rate gain coefficient, #imgabs12# is the longitudinal command feedforward gain coefficient, and #imgabs13# is the roll angle gain coefficient. The throttle stick is controlled by calculating the throttle stick angle compensation command #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] Aircraft landing on a ship's deck is subject to numerous stringent conditions, including the limited deck length. During approach and landing, the aircraft must minimize its landing speed. This requires increasing the aircraft's angle of attack to maintain a suitable sink rate.

[0003] When an aircraft lands on a ship's deck, the increase in angle of attack often exceeds the critical angle of attack corresponding to the maximum lift-to-drag ratio, causing the aircraft to enter a region of speed instability, known as the speed reversal zone. Within this reversal zone, maintaining the reference track using the elevator alone is difficult, and the track's response to elevator commands exhibits a slow full-pass characteristic. That is, when the push-stick is manipulated, positive elevator deflection initially reduces the aircraft's altitude, consistent with normal control. However, because the aircraft's speed is less than the minimum drag speed, the final steady-state track angle increases, causing the aircraft's track and attitude to become unstable, posing a significant safety hazard.

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

[0005] The purpose of this application is to provide a power compensation method and system for an aircraft performing a constant angle of attack approach on a landing 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 cause the aircraft to enter a speed unstable area, maintain the stability of the aircraft's track and attitude, and eliminate safety hazards when the aircraft lands on the deck.

[0006] The technical solution of this application is:

[0007] On the one hand, a method for compensating power when an aircraft performs a constant angle of attack approach on a landing deck is provided, comprising:

[0008] Angle of attack , Normal Overload , pitch angular rate , vertical instructions , roll angle , as feedback signal, calculate the throttle stick angle compensation command :

[0009] ;

[0010] in,

[0011] is the reference angle of attack;

[0012] is the angle of attack integral gain coefficient;

[0013] is the angle of attack proportional gain coefficient;

[0014] is the normal overload gain coefficient;

[0015] is the pitch rate gain coefficient;

[0016] is the longitudinal command feedforward gain coefficient;

[0017] is the roll angle gain coefficient;

[0018] The calculated throttle stick angle compensation command , control the throttle stick.

[0019] Optionally, in the above-mentioned method for power compensation of an aircraft landing on a deck at a constant angle of attack, the reference angle of attack Take 10°~12°.

[0020] Optionally, in the above-mentioned method for compensating the power of a constant angle approach when the aircraft is landing on the deck, the angle of attack integral gain coefficient Take 0.1~1.5;

[0021] Angle of attack proportional gain coefficient Take 1~5.

[0022] 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 0.2~0.5.

[0023] Optionally, in the above-mentioned method for compensating the aircraft for landing on the deck with a constant angle of attack, the normal overload gain coefficient Take 0.5~1.5;

[0024] Pitch rate gain coefficient Take 0.3~0.8;

[0025] Longitudinal command feedforward gain coefficient Take 0.8~1.2;

[0026] Roll angle gain coefficient Take 0.3~0.8.

[0027] On the other hand, a power compensation system for an aircraft landing on a deck with a constant angle of attack approach is provided, which is based on the above-mentioned power compensation method for an aircraft landing on a deck with a constant angle of attack approach and includes a throttle lever angle compensation instruction calculation module and a throttle lever angle compensation control module;

[0028] Throttle stick angle compensation command calculation module is based on angle of attack , Normal Overload , pitch angular rate , vertical instructions , roll angle , as feedback signal, calculate the throttle stick angle compensation command :

[0029] ;

[0030] in,

[0031] is the reference angle of attack;

[0032] is the angle of attack integral gain coefficient;

[0033] is the angle of attack proportional gain coefficient;

[0034] is the normal overload gain coefficient;

[0035] is the pitch rate gain coefficient;

[0036] is the longitudinal command feedforward gain coefficient;

[0037] is the roll angle gain coefficient;

[0038] The throttle stick angle compensation control module sends the calculated throttle stick angle compensation command to the aircraft control system , control the throttle stick.

[0039] Optionally, in the above aircraft landing on the deck constant angle of attack approach power compensation system, in the throttle lever angle compensation instruction calculation module, the reference angle of attack Take 10°~12°.

[0040] Optionally, in the above-mentioned aircraft landing on the deck constant angle approach power compensation system, in the throttle lever 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.

[0041] Optionally, in the above-mentioned constant angle of attack approach power compensation system for the aircraft landing on the deck, in the throttle lever angle compensation instruction calculation module, / The value of is 0.2~0.5.

[0042] Optionally, in the above aircraft landing on the deck constant angle of attack approach power compensation system, in the throttle lever 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.

[0043] This application has at least the following beneficial technical effects:

[0044] Provides a power compensation method and system for an aircraft landing on a deck with a constant angle of attack, dynamically integrating the angle of attack , Normal Overload , pitch angular rate , vertical instructions , roll angle , as the feedback signal, the throttle stick angle compensation command is calculated By manipulating the throttle lever and performing approach power compensation on the aircraft, 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

[0045] Figure 1 1 is a schematic diagram of a control structure of a power compensation method for a constant angle of attack approach of an aircraft landing on a deck provided by an embodiment of the present application;

[0046] Figure 2 This is a schematic diagram of an aircraft landing on a deck with a 1° gust angle of attack interference provided by an embodiment of the present application.

[0047] Figure 3 This is a schematic diagram of an embodiment of the present application providing an aircraft landing on a deck with a 1° gust angle of attack interfering with the angle of attack response.

[0048] Figure 4 Schematic diagram of the flight path angle response of an aircraft landing on a deck with a 1° gust angle of attack, provided by an embodiment of the present application;

[0049] Figure 5It 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.

[0050] In order to better illustrate this 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

[0051] To make the technical solution and its advantages of this application more clear, the technical solution of this application will be further described in detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described here are only some of the embodiments of this application and are only used to explain this application, not to limit this application. It should be noted that for ease of description, only the parts relevant to this application are shown in the accompanying drawings, and other relevant parts can refer to the general design.

[0052] In addition, unless otherwise defined, the technical or scientific terms used in the description of this application shall have the ordinary meanings understood by those skilled in the art to which this application belongs. The term "include" as used in the description of this application means that the concepts preceding the term include the concepts listed after the term and their equivalents, without excluding other related concepts.

[0053] Flight mechanics theory shows that within the speed reversal zone, relying solely on the inner and outer loop control systems cannot maintain the stability of the aircraft's flight path and attitude. The introduction of approach power compensation, that is, compensation using 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. This can maintain the stability of the aircraft's flight path and attitude, eliminating safety hazards when the aircraft lands on the deck.

[0054] 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. The control structure is as follows: Figure 1 shown.

[0055] Angle of attack , Normal Overload , pitch angular rate , vertical instructions , roll angle , as feedback signal, calculate the throttle stick angle compensation command .

[0056] ;

[0057] in,

[0058] 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°;

[0059] is the angle of attack integral gain coefficient, ranging from 0.1 to 1.5;

[0060] is the angle of attack proportional gain coefficient, ranging from 1 to 5;

[0061] is the normal overload gain coefficient, ranging from 0.5 to 1.5;

[0062] is the pitch angular rate gain coefficient, ranging from 0.3 to 0.8;

[0063] is the longitudinal command feedforward gain coefficient, ranging from 0.8 to 1.2;

[0064] is the roll angle gain coefficient, ranging from 0.3 to 0.8.

[0065] The calculated throttle stick angle compensation command , control the throttle lever and perform approach power compensation on the aircraft so that the aircraft maintains a constant speed and angle of attack during landing on the deck.

[0066] 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 stick angle compensation instruction 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, pitch angle rate is introduced Feedback enables 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 angle of attack, increase the power compensation bandwidth, and consider the impact of aircraft lateral motion changes and control input on aerodynamic forces, introducing roll angle Feedback provides corresponding lateral and heading cross-link compensation.

[0067] In the power compensation method for landing an aircraft on a deck at a constant angle of attack, the angle of attack integral gain coefficient can be further designed. Proportional gain coefficient with angle of attack The proportional relationship satisfies: / The value of is set to 0.2~0.5 to form proportional-integral compound compensation control.

[0068] The above embodiment discloses a method for compensating for a constant angle of attack approach of an aircraft landing on a deck. It is a method for compensating for a constant angle of attack approach of an aircraft landing on a deck based on a hybrid instruction form. , Normal Overload , pitch angular rate , vertical instructions , roll angle , as the feedback signal, the throttle stick 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, reduce the lag of phase-frequency characteristics, and enable the aircraft to 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.

[0069] In a specific simulation example, a gust of 1° is added, such as Figure 2 As shown, the power compensation method for landing an aircraft on a deck at a constant angle of attack disclosed in the above embodiment responds to a step gust as follows: Figure 3-4 As 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.

[0070] 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 stick angle compensation instruction calculation module and a throttle stick angle compensation control module;

[0071] Throttle stick angle compensation command calculation module is based on angle of attack , Normal Overload , pitch angular rate , vertical instructions , roll angle , as feedback signal, calculate the throttle stick angle compensation command :

[0072] ;

[0073] in,

[0074] is the reference angle of attack;

[0075] is the angle of attack integral gain coefficient;

[0076] is the angle of attack proportional gain coefficient;

[0077] is the normal overload gain coefficient;

[0078] is the pitch rate gain coefficient;

[0079] is the longitudinal command feedforward gain coefficient;

[0080] is the roll angle gain coefficient;

[0081] The throttle stick angle compensation control module sends the calculated throttle stick angle compensation command to the aircraft control system , control the throttle stick.

[0082] In the throttle stick 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 0.2~0.5.

[0083] Regarding 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 can 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, and will not be repeated here.

[0084] In addition, those skilled in the art 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. Those skilled in the art 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.

[0085] 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 replacements to the relevant technical features, and the technical solutions after these changes or replacements 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 angular 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 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 stick.

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 at a constant angle of attack according to claim 2, characterized in that: Angle of attack integral gain coefficient Take 0.1~1.5; Angle of attack proportional gain coefficient 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 0.2~0.

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 coefficient Take 0.3~0.8; Longitudinal command feedforward gain coefficient Take 0.8~1.2; Roll angle gain coefficient Take 0.3~0.

8.

6. A power compensation system for an aircraft landing on a deck at 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 stick angle compensation command calculation module is based on angle of attack , Normal Overload , pitch angular 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 rate gain coefficient; is the longitudinal command feedforward gain coefficient; is the roll angle gain coefficient; The throttle stick angle compensation control module sends the calculated throttle stick angle compensation command to the aircraft control system , control the throttle stick.

7. The power compensation system for an aircraft landing at a constant angle of attack on a deck according to claim 6, characterized in that: In the throttle stick 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 stick 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 0.2~0.

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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