CN106019930A - Aerodynamic/control integrated coupling simulating technology in aircraft maneuvering process - Google Patents
Aerodynamic/control integrated coupling simulating technology in aircraft maneuvering process Download PDFInfo
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- CN106019930A CN106019930A CN201610627798.1A CN201610627798A CN106019930A CN 106019930 A CN106019930 A CN 106019930A CN 201610627798 A CN201610627798 A CN 201610627798A CN 106019930 A CN106019930 A CN 106019930A
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- 238000005516 engineering process Methods 0.000 title claims abstract description 18
- 238000000034 method Methods 0.000 title claims abstract description 16
- 230000008878 coupling Effects 0.000 title abstract 2
- 238000010168 coupling process Methods 0.000 title abstract 2
- 238000005859 coupling reaction Methods 0.000 title abstract 2
- 238000004088 simulation Methods 0.000 claims abstract description 19
- 230000010354 integration Effects 0.000 claims description 6
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 abstract description 7
- 230000000694 effects Effects 0.000 abstract description 6
- 239000012530 fluid Substances 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 4
- 238000011160 research Methods 0.000 description 2
- 238000012938 design process Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000009022 nonlinear effect Effects 0.000 description 1
- 238000004904 shortening Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
Classifications
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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
- G05B11/00—Automatic controllers
- G05B11/01—Automatic controllers electric
- G05B11/36—Automatic controllers electric with provision for obtaining particular characteristics, e.g. proportional, integral, differential
- G05B11/42—Automatic controllers electric with provision for obtaining particular characteristics, e.g. proportional, integral, differential for obtaining a characteristic which is both proportional and time-dependent, e.g. P. I., P. I. D.
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Abstract
The invention discloses an aerodynamic /control integrated coupling simulating technology in the aircraft maneuvering process, and relates to the field of computational fluid mechanics and the field of control systems. The main work implementing process includes the steps of generating a control signal through the compared deviation of the attitude angle of an aircraft and a control target, outputting the control signal to a PID controller module, generating a rudder deviation angle signal after computation, outputting the rudder deviation angle signal to a dynamic mesh module, deflecting a rudder face to a corresponding angle through a dynamic mesh technology, obtaining a dynamic flow field existing after deflection of the rudder face through a Navier-Stockes equation module, generating aerodynamic force and torque signals, outputting aerodynamic force and torque to a rigid body dynamics equation and a kinematical equation, obtaining the flight attitude of the next moment, transmitting the new flight attitude to the PID controller module, and forming a closed-loop numerical simulating circuit. The high-precision simulation of a flight control system is achieved, and the technology can be used for evaluating performance of the flight control system and studying the influences of the aerodynamic force unsteady effect on the control system.
Description
Technical field
The present invention relates to Fluid Mechanics Computation field and control system field, be specifically related to the High Precision Simulation of flight control system, assessment flight control system performance, the technology of research aerodynamic force unsteady aerodynamic effect.
Background technology
Currently commonly use Engineering Simulation Method simulation and assessment flight control, but the method does not accounts for, and aerodynamic force completely is non-linear, unsteady flo w feature, when the big angles-of-attack of aircraft or fast reserve, application is limited to, the simulation result be given is likely to significantly underestimate the hesitation of control system, adds flight risk.
The numerical simulation technology of development flight vehicle aerodynamic/controls integration maneuvering flight, by setting up Unsteady Flow and solving, aircraft moves and flight controls integrated coupled simulation method, can the mobile process of real-time Simulation aircraft.Owing to having taken into full account the aerodynamic force unsteady aerodynamic effect (including the motion of UNSTEADY FLOW, aircraft, the control flaps deflection etc.) impact on control system, it is particularly well-suited to unsteady aerodynamic force phenomenon when the big angles-of-attack of exploratory flight device or fast reserve, the control system performance under assessment unsteady aerodynamic force effect.To shortening the aircraft lead time, reduce significant to the dependence of flight test.
Summary of the invention
The present invention provides the pneumatic/control integration coupled simulation technology of aircraft mobile process, it is an object of the invention to provide a kind of technological means using Numerical Method Study control system.This technology is by close-coupled that is pneumatic and that control, it is achieved that the High Precision Simulation to flight control system, can be used for assessing flight control system performance, studies the impact on control system of the aerodynamic force unsteady aerodynamic effect.
For solving the problems referred to above, the present invention adopts the following technical scheme that the pneumatic/control integration coupled simulation technology of aircraft mobile process, including PID controller module, dynamic mesh module, Navier-Stockes equation solution module, dynamics of rigid bodies and solving kinematic equation module and flight attitude output module；Work mainly realizes flow process and is: by the deviation comparing attitude of flight vehicle angle with control target, produce control signal；Control signal exports PID controller module, produces the signal of angle of rudder reflection degree after computing；Angle of rudder reflection degree signal exports dynamic mesh module, by Dynamic mesh by control surface deflection to corresponding angle；Navier-Stockes equation module solves the Dynamic Flow Field after control surface deflection, produces flight force and moment signal；Flight force and moment exports dynamics of rigid bodies and kinematical equation, solves the flight attitude obtaining subsequent time；New flight attitude is delivered to PID controller module again, forms the numerical simulation loop of closed loop.
Advantages of the present invention has: 1, present invention achieves close-coupled that is pneumatic and that control, it is contemplated that aerodynamic force unsteady aerodynamic effect completely.
2, relative to the most commonly used Engineering Simulation Method, this technology is provided that more preferably simulation precision in aerodynamic force unsteady flo w, nonlinear effect time strong.
3, this technology is particularly suitable for research and the assessment aircraft control system performance when big angles-of-attack or fast reserve.
Accompanying drawing explanation
Fig. 1 is PID controller schematic diagram of the present invention；
Fig. 2 be the present invention realize procedural block diagram.
Detailed description of the invention
By optimal embodiment, the present invention is described in detail below。
As shown in Figure 1-2, before applying this technology to carry out flight vehicle aerodynamic/control integration numerical simulation, it is necessary first to designing PID controller, this is the preparation of the technology.As shown in Figure 1: the design process of PID controller includes the steps such as aerodynamic force static derivative and dynamic derivative calculating, Unsteady Aerodynamic Modeling, Modifying model, foundation root locus diagram carry out that PID controller parameter is adjusted.
The operation principle of this technology and realize block diagram as shown in Figure 2: by the deviation comparing attitude of flight vehicle angle with control target, produce error controling signal；Error signal exports PID controller module, produces the signal of angle of rudder reflection degree after computing；Angle of rudder reflection degree signal exports dynamic mesh module, by Dynamic mesh by control surface deflection to corresponding angle；Navier-Stockes equation module solves the Unsteady Flow after control surface deflection, produces flight force and moment signal；Flight force and moment exports dynamics of rigid bodies and kinematical equation, solves the flight attitude obtaining subsequent time；New flight attitude is delivered to PID controller module again, forms the numerical simulation loop of closed loop.Through continuous iterative, may finally obtain using rudder face to control aircraft and carry out the real-time process of maneuver.The present invention is the couple solution technology of Navier-Stockes equation and Dynamical Equations of Rigid Body, PID controller and the couple solution of Navier-Stockes equation, Dynamic mesh etc..
It is last that it is noted that obviously above-described embodiment is only for clearly demonstrating example of the present invention, and not restriction to embodiment.For those of ordinary skill in the field, can also make other changes in different forms on the basis of the above description.Here without also cannot all of embodiment be given exhaustive.And the obvious change thus amplified out or variation still in protection scope of the present invention among.
Claims (1)
1. pneumatic/control integration coupled simulation the technology of aircraft mobile process, it is characterized in that, including PID controller module, dynamic mesh module, Navier-Stockes equation solution module, dynamics of rigid bodies and solving kinematic equation module and flight attitude output module；Work mainly realizes flow process and is: by the deviation comparing attitude of flight vehicle angle with control target, produce control signal；Control signal exports PID controller module, produces the signal of angle of rudder reflection degree after computing；Angle of rudder reflection degree signal exports dynamic mesh module, by Dynamic mesh by control surface deflection to corresponding angle；Navier-Stockes equation module solves the Dynamic Flow Field after control surface deflection, produces flight force and moment signal；Flight force and moment exports dynamics of rigid bodies and kinematical equation, solves the flight attitude obtaining subsequent time；New flight attitude is delivered to PID controller module again, forms the numerical simulation loop of closed loop.
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| CN201610627798.1A CN106019930A (en) | 2016-08-03 | 2016-08-03 | Aerodynamic/control integrated coupling simulating technology in aircraft maneuvering process |
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| CN201610627798.1A CN106019930A (en) | 2016-08-03 | 2016-08-03 | Aerodynamic/control integrated coupling simulating technology in aircraft maneuvering process |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110618699A (en) * | 2019-10-24 | 2019-12-27 | 四川航天烽火伺服控制技术有限公司 | Unmanned aerial vehicle control surface control method, system and device computer readable storage medium |
| CN110717221A (en) * | 2019-10-21 | 2020-01-21 | 中国航空工业集团公司沈阳飞机设计研究所 | Method and equipment for finely analyzing energy demand of airplane |
| CN111324931A (en) * | 2020-03-10 | 2020-06-23 | 中国航天空气动力技术研究院 | Interstage separation aerodynamic characteristic obtaining method for afterbody reverse jet flow |
| CN112346359A (en) * | 2020-11-04 | 2021-02-09 | 中国空气动力研究与发展中心高速空气动力研究所 | Direct force-aerodynamic force composite control numerical simulation method based on CFD and RBD coupling |
| CN117077296A (en) * | 2023-10-17 | 2023-11-17 | 中国空气动力研究与发展中心计算空气动力研究所 | Control coupling simulation method for aerodynamic structure of aircraft |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070239414A1 (en) * | 2006-04-05 | 2007-10-11 | Oh-Young Song | Method of simulating detailed movements of fluids using derivative particles |
| CN102073755A (en) * | 2010-11-10 | 2011-05-25 | 南京航空航天大学 | Motion control simulation method for near-space hypersonic aircraft |
| CN103389649A (en) * | 2013-07-29 | 2013-11-13 | 中国空气动力研究与发展中心高速空气动力研究所 | Aircraft maneuvering simulation method based on spherical abutting grids |
| CN103488814A (en) * | 2013-08-16 | 2014-01-01 | 北京航空航天大学 | Closed loop simulation system suitable for controlling attitude of reentry vehicle |
| CN103699757A (en) * | 2014-01-06 | 2014-04-02 | 西北工业大学 | Micro flapping-wing analysis system and method involved with pneumatic and structural coupling properties |
-
2016
- 2016-08-03 CN CN201610627798.1A patent/CN106019930A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070239414A1 (en) * | 2006-04-05 | 2007-10-11 | Oh-Young Song | Method of simulating detailed movements of fluids using derivative particles |
| CN102073755A (en) * | 2010-11-10 | 2011-05-25 | 南京航空航天大学 | Motion control simulation method for near-space hypersonic aircraft |
| CN103389649A (en) * | 2013-07-29 | 2013-11-13 | 中国空气动力研究与发展中心高速空气动力研究所 | Aircraft maneuvering simulation method based on spherical abutting grids |
| CN103488814A (en) * | 2013-08-16 | 2014-01-01 | 北京航空航天大学 | Closed loop simulation system suitable for controlling attitude of reentry vehicle |
| CN103699757A (en) * | 2014-01-06 | 2014-04-02 | 西北工业大学 | Micro flapping-wing analysis system and method involved with pneumatic and structural coupling properties |
Non-Patent Citations (2)
| Title |
|---|
| 张勇等: "高超声速飞行器控制一体化设计", 《航空动力学报》 * |
| 郑勇: "进气道的优化设计及无人机内外流场耦合计算", 《全国优秀硕士学位论文数据库》 * |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110717221A (en) * | 2019-10-21 | 2020-01-21 | 中国航空工业集团公司沈阳飞机设计研究所 | Method and equipment for finely analyzing energy demand of airplane |
| CN110717221B (en) * | 2019-10-21 | 2023-09-22 | 中国航空工业集团公司沈阳飞机设计研究所 | Method and equipment for finely analyzing aircraft energy demand |
| CN110618699A (en) * | 2019-10-24 | 2019-12-27 | 四川航天烽火伺服控制技术有限公司 | Unmanned aerial vehicle control surface control method, system and device computer readable storage medium |
| CN110618699B (en) * | 2019-10-24 | 2022-06-07 | 四川航天烽火伺服控制技术有限公司 | Unmanned aerial vehicle control plane jitter control method, system and device and computer readable storage medium |
| CN111324931A (en) * | 2020-03-10 | 2020-06-23 | 中国航天空气动力技术研究院 | Interstage separation aerodynamic characteristic obtaining method for afterbody reverse jet flow |
| CN111324931B (en) * | 2020-03-10 | 2022-10-28 | 中国航天空气动力技术研究院 | Interstage separation aerodynamic characteristic obtaining method for afterbody reverse jet flow |
| CN112346359A (en) * | 2020-11-04 | 2021-02-09 | 中国空气动力研究与发展中心高速空气动力研究所 | Direct force-aerodynamic force composite control numerical simulation method based on CFD and RBD coupling |
| CN112346359B (en) * | 2020-11-04 | 2022-05-31 | 中国空气动力研究与发展中心高速空气动力研究所 | Direct force-aerodynamic force composite control numerical simulation method based on CFD and RBD coupling |
| CN117077296A (en) * | 2023-10-17 | 2023-11-17 | 中国空气动力研究与发展中心计算空气动力研究所 | Control coupling simulation method for aerodynamic structure of aircraft |
| CN117077296B (en) * | 2023-10-17 | 2024-01-09 | 中国空气动力研究与发展中心计算空气动力研究所 | Control coupling simulation method for aerodynamic structure of aircraft |
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Application publication date: 20161012 |