CN117555234A - Control surface speed critical value and flight control system hydraulic flow demand analysis method - Google Patents
Control surface speed critical value and flight control system hydraulic flow demand analysis method Download PDFInfo
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- CN117555234A CN117555234A CN202311524232.2A CN202311524232A CN117555234A CN 117555234 A CN117555234 A CN 117555234A CN 202311524232 A CN202311524232 A CN 202311524232A CN 117555234 A CN117555234 A CN 117555234A
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- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 title claims abstract description 33
- 238000004458 analytical method Methods 0.000 title claims abstract description 18
- 238000000034 method Methods 0.000 claims abstract description 23
- 238000013461 design Methods 0.000 claims abstract description 17
- 238000005312 nonlinear dynamic Methods 0.000 claims description 2
- 238000011161 development Methods 0.000 abstract description 6
- 238000004364 calculation method Methods 0.000 description 2
- 238000013016 damping Methods 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 230000009194 climbing Effects 0.000 description 1
- 238000004836 empirical method Methods 0.000 description 1
- 238000011156 evaluation Methods 0.000 description 1
- 238000012804 iterative process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000010355 oscillation Effects 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B13/00—Adaptive control systems, i.e. systems automatically adjusting themselves to have a performance which is optimum according to some preassigned criterion
- G05B13/02—Adaptive control systems, i.e. systems automatically adjusting themselves to have a performance which is optimum according to some preassigned criterion electric
- G05B13/04—Adaptive control systems, i.e. systems automatically adjusting themselves to have a performance which is optimum according to some preassigned criterion electric involving the use of models or simulators
- G05B13/042—Adaptive control systems, i.e. systems automatically adjusting themselves to have a performance which is optimum according to some preassigned criterion electric involving the use of models or simulators in which a parameter or coefficient is automatically adjusted to optimise the performance
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
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Abstract
The invention discloses a control surface speed critical value and a flight control system hydraulic flow demand analysis method. Step 1, inputting a rudder deflection instruction into a steering engine model with a speed limiter to obtain a rudder deflection response with speed limitation; step 2, inputting rudder deflection response into a natural aircraft model or an ideal aircraft model, and calculating flight quality according to aircraft output response; if the flight quality does not meet the requirement, increasing the speed limit, repeating the step 1 until the flight quality meets the requirement, and obtaining a control surface speed critical value; and 3, taking the steering engine model with the speed limiter into a natural aircraft model, and calculating hydraulic flow requirements of the full scene flight control system in each flight stage and each flight working condition according to the process of the task section. The invention can accurately and rapidly provide design input for the flight control system, ensure the rationality of design, shorten the iterative development time and reduce the development risk.
Description
Technical Field
The invention belongs to the technical field of aircraft flight control system design, and particularly relates to a control surface speed critical value and flight control system hydraulic flow demand analysis method.
Background
Flight control systems are important users of hydraulic systems, which are used throughout the flight process and function to control the safe flight of an aircraft. The control surface speed and the hydraulic flow requirement are key inputs for the design of the flight control system. The traditional solving method of the hydraulic flow of the aircraft flight control system is that the control surface hinge moment is provided by the operation stability professional, then the control surface velocity is provided empirically by referring to the same type of aircraft, and finally the peak flow of each control surface is overlapped by using a peak flow overlapping method to obtain the maximum required flow, so that the solving method is more conservative, and the hydraulic flow is over-designed.
In aircraft design, in order to meet the flight quality requirement, the control surface speed needs to reach a certain value, and the control surface speed above the certain value can meet the flight quality requirement, but the larger the control surface speed is, the larger the required flow is, the higher the power of the hydraulic system is, and the larger the volume and the weight of the hydraulic system are, so that the aircraft design is not facilitated.
The aircraft design is a long period, and the main flight control system needs iterative analysis due to the fact that the flight quality and the flight safety of the aircraft are related to the repeated iterative process, so that the rationality of the design is guaranteed. Based on this, it is needed to design an analysis method capable of accurately reflecting the control surface speed critical value and the hydraulic flow demand of the flight control system.
Disclosure of Invention
The purpose of the invention is that: a control surface speed critical value and a flight control system hydraulic flow demand analysis method are provided. The invention can accurately and rapidly provide design input for the flight control system, ensure the rationality of design, shorten the iterative development time and reduce the development risk.
The technical scheme of the invention is as follows: a control surface speed critical value and hydraulic flow demand analysis method of a flight control system comprises the following steps:
step 1, inputting a rudder deflection instruction into a steering engine model with a speed limiter to obtain a rudder deflection response with speed limitation;
step 2, inputting rudder deflection response into a natural aircraft model or an ideal aircraft model, and calculating flight quality according to aircraft output response; if the flight quality does not meet the requirement, increasing the speed limit, repeating the step 1 until the flight quality meets the requirement, and obtaining a control surface speed critical value;
and 3, taking the steering engine model with the speed limiter into a natural aircraft model, and calculating hydraulic flow requirements of the full scene flight control system in each flight stage and each flight working condition according to the process of the task section.
In the control surface speed critical value and hydraulic flow demand analysis method of the flight control system, the flight quality in the step 2 is as follows: the flight quality of the aircraft dynamic response as a function of the control surface deflection rate.
In the control surface speed critical value and the hydraulic flow demand analysis method of the flight control system, the flight quality comprises longitudinal flight quality, transverse flight quality, heading flight quality and PIO flight quality.
In the control surface speed critical value and hydraulic flow demand analysis method of the flight control system, the ideal aircraft model in the step 2 is a low-order equivalent aircraft model meeting the flight quality requirement, and is used in the initial stage of aircraft design.
In the control surface speed critical value and the flight control system hydraulic flow demand analysis method, the control surface speed critical value in the step 2 is a control surface speed value which meets the flight quality requirement and enables the volume and the weight of the hydraulic system to be designed as small as possible.
In the control surface speed critical value and hydraulic flow demand analysis method of the flight control system, the natural aircraft model in the step 2 is a nonlinear dynamics model of the aircraft, and is used in the later stage of aircraft design.
In the control surface speed critical value and hydraulic flow demand analysis method of the flight control system, the flight working conditions in the step 3 include: normal operating conditions, crosswind operating conditions, and engine failure operating conditions.
In the control surface speed critical value and flight control system hydraulic flow demand analysis method, the flight stage in the step 3 comprises taxi, take-off, climbing, cruising and descending.
The invention has the advantages that: the traditional control surface speed is based on an empirical method, an aircraft with the same configuration is selected, the maximum control surface speed value obtained in the flight test process of the aircraft is used as a standard, a control surface speed value of a new aircraft is designed, and the hydraulic flow is solved by a peak superposition method under the control surface speed value.
In summary, the invention can accurately and rapidly provide design input for the flight control system, ensure the rationality of design, shorten the iterative development time and reduce the development risk.
Drawings
FIG. 1 is a flow chart of a solution for the control surface bias ratio threshold and the flow demand of a flight control system of an aircraft;
FIG. 2 is a steering engine model with speed limits;
FIG. 3 is a flow chart for solving control surface velocity thresholds;
FIG. 4 is a detailed flow chart of the flow demand solving of the aircraft flight control system.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention more clear, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. It will be apparent that the described embodiments are some, but not all, embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without making any inventive effort are intended to fall within the scope of the present invention.
Features and exemplary embodiments of various aspects of the invention are described in detail below. In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the invention. It will be apparent, however, to one skilled in the art that the present invention may be practiced without some of these specific details. The following description of the embodiments is merely intended to provide a better understanding of the invention by showing examples of the invention. The present invention is in no way limited to any particular arrangement and method set forth below, but rather covers any adaptations, alternatives, and modifications of structure, method, and device without departing from the spirit of the invention. In the drawings and the following description, well-known structures and techniques have not been shown in detail in order not to unnecessarily obscure the present invention.
It should be noted that, without conflict, the embodiments of the present invention and features of the embodiments may be combined with each other, and the embodiments may be referred to and cited with each other. The invention will be described in detail below with reference to the drawings in connection with embodiments.
Example 1. 1-4, a control surface speed critical value and flight control system hydraulic flow demand analysis method, comprising:
and step 1, inputting a rudder deflection command into a steering engine model with a speed limiter to obtain a rudder deflection response with speed limitation. Rudder deflection instructions are obtained according to corresponding flight quality specification requirements, such as step instructions, square wave instructions and the like. The steering engine model with rate limiter is shown in fig. 2, delta e The steering engine input command, e is the difference between the input command and the feedback command, delta' e The steering engine speed v is the steering engine saturation speed, and delta is the steering engine output.
And 2, inputting rudder deflection response into a natural aircraft model, calculating flight quality according to aircraft output response, if the flight quality does not meet the requirement, increasing the speed limit, repeating the step 1 until the flight quality meets the requirement, and obtaining a control surface speed critical value. The control surface speed influences the dynamic response of the aircraft, and the flight quality related to the dynamic response of the aircraft comprises short period frequency, damping ratio and CAP manipulation expected parameters in longitudinal quality, pitch angle rate criteria and normal overload time response criteria; a roll modal time constant in transverse flight quality, a roll delay criterion, a roll oscillation criterion; minimum damping and frequency of netherlands roll in heading flight quality, sideslip angle response criteria; the bandwidth criterion in the PIO evaluation criterion, the time domain Neal-smith criterion. According to different stages of the aircraft, requirements for first-class flight quality are given. The specific solving process of the control surface speed critical value is shown in fig. 3.
And step 3, taking the steering engine model with the speed limit into a natural airplane model, and calculating hydraulic flow requirements of the full scene flight control system in different flight phases and different flight conditions according to the process of the task section. The specific calculation process is shown in fig. 4, and the specific steps are as follows:
(1) Giving out state parameters of an initial flight stage, and inputting an instruction for controlling a control surface according to the state parameters required to be reached;
(2) According to the current state parameters of the aircraft and the input control surface instruction, calculating a control instruction according to a control law, and inputting a steering engine;
(3) The steering engine acts according to the control instruction, deflects the control surface, calculates the flow of the input steering engine changing along with the deflection process of the control surface, and the flow (mainly the leakage of a servo valve) leaked by the hydraulic system in the deflection process of the control surface, wherein the sum of the two obtained flows is the flow required by the system;
(4) Inputting rudder deflection into a six-degree-of-freedom dynamics model of the aircraft, calculating the aircraft state, continuously inputting a control surface instruction if the aircraft state does not reach a target value, and entering the next step if the aircraft state reaches the target value;
(5) Judging whether the task is finished, if the task is not finished, entering the next flight stage, and if the task is finished, finishing the whole calculation flow, and outputting a curve of the flow required by the system along with the time.
Claims (8)
1. A control surface speed critical value and hydraulic flow demand analysis method of a flight control system is characterized by comprising the following steps:
step 1, inputting a rudder deflection instruction into a steering engine model with a speed limiter to obtain a rudder deflection response with speed limitation;
step 2, inputting rudder deflection response into a natural aircraft model or an ideal aircraft model, and calculating flight quality according to aircraft output response; if the flight quality does not meet the requirement, increasing the speed limit, repeating the step 1 until the flight quality meets the requirement, and obtaining a control surface speed critical value;
and 3, taking the steering engine model with the speed limiter into a natural aircraft model, and calculating hydraulic flow requirements of the full scene flight control system in each flight stage and each flight working condition according to the process of the task section.
2. The method for analyzing hydraulic flow demand of a flight control system and control surface speed threshold according to claim 1, wherein the flight quality in step 2 is: the flight quality of the aircraft dynamic response as a function of the control surface deflection rate.
3. The method of claim 2, wherein the flight qualities include longitudinal flight quality, transverse flight quality, heading flight quality, and PIO flight quality.
4. The method of claim 1, wherein the ideal aircraft model in step 2 is a low-order equivalent aircraft model meeting the requirements of flight quality, and is used in the initial stage of aircraft design.
5. The control surface speed critical value and hydraulic flow demand analysis method of a flight control system according to claim 1, wherein the control surface speed critical value in step 2 is a control surface speed value which meets the flight quality requirement and enables the volume and weight of the hydraulic system to be designed as small as possible.
6. The method of claim 1, wherein the natural aircraft model in step 2 is a nonlinear dynamics model of an aircraft, and is used in a later stage of aircraft design.
7. The method for analyzing a control surface speed threshold and a hydraulic flow demand of a flight control system according to claim 1, wherein the flight condition in step 3 comprises: normal operating conditions, crosswind operating conditions, and engine failure operating conditions.
8. The method of claim 1, wherein the flight phase in step 3 includes taxiing, takeoff, climb, cruise and descent.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311524232.2A CN117555234A (en) | 2023-11-15 | 2023-11-15 | Control surface speed critical value and flight control system hydraulic flow demand analysis method |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202311524232.2A CN117555234A (en) | 2023-11-15 | 2023-11-15 | Control surface speed critical value and flight control system hydraulic flow demand analysis method |
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| CN117555234A true CN117555234A (en) | 2024-02-13 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202311524232.2A Pending CN117555234A (en) | 2023-11-15 | 2023-11-15 | Control surface speed critical value and flight control system hydraulic flow demand analysis method |
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| CN (1) | CN117555234A (en) |
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- 2023-11-15 CN CN202311524232.2A patent/CN117555234A/en active Pending
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