CN105523168A - Method for inhibiting flutter of control plane of aircraft - Google Patents
Method for inhibiting flutter of control plane of aircraft Download PDFInfo
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- CN105523168A CN105523168A CN201410508979.3A CN201410508979A CN105523168A CN 105523168 A CN105523168 A CN 105523168A CN 201410508979 A CN201410508979 A CN 201410508979A CN 105523168 A CN105523168 A CN 105523168A
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- current limiting
- limiting valve
- bidirectional current
- flutter
- aircraft
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Abstract
The invention relates to the field of a servo control system for an aircraft and particularly relates to a method for inhibiting flutter of a control plane of the aircraft by changing mutual leakage of actuators of a servo actuation system. According to the method, a two-way flow restrictor valve is connected in series between a fuel inlet and a fuel return port of an actuation cylinder in the servo actuation system so as to change the internal leakage of the actuators, thereby changing the inherent frequency of the whole servo control system to inhibit the flutter of the control plane.
Description
Technical field
The present invention relates to Airplane Flight Control System ' and fly to control rudder face field, particularly relate to actuating system and the coupling vibration field flying to control rudder face.
Background technology
In space flight and aviation development history, Aeroelastic Problems is that the important technology of puzzlement aircraft security and development is crucial always.Along with the flying speed of contemporary aircraft and the significantly tune of manoevreability improve, Flutter Problem is than more outstanding in the past.The servo control unit of contemporary aircraft has very high Frequency Response, easily causes frame elastic to vibrate and servo control unit coupled oscillations.Especially the natural frequency of airplane servo control system and the natural frequency of rudder face close to time, then easier generation systems coupled resonance, thus cause rudder face flutter.
The method of rudder face flutter is suppressed to have multiple, normally based on the design parameters of the math modeling determination control system of rigidity body, the math modeling of elasticity body is set up again for body single order mode of flexural vibration, design a suitable die filter, the means combined by experience and test regulate parameter wherein, then the stability of control system is checked, under guarantee does not affect the prerequisite of control system key property, avoid the generation of servo flutter.The method is applicable to design phase, still has rudder face flutter to occur if Aircraft Production manufacture assembling is complete, then the method is just difficult to use.The present invention is then that now, rudder face has been shaped and not easily changed, and therefore considers to address this problem from servo control unit for the complete situation still having rudder face flutter to occur of Aircraft Production manufacture assembling.Its method be the pressurized strut of actuating system oil-feed be connected in series bidirectional current limiting valve between oil return, thus change the mutual leakage of actuator, and then change the natural frequency of actuating system, reach the effect of the servo flutter suppressing rudder face.
Summary of the invention
Object of the present invention: overcome existing aircraft when structure design manufacture complete and not easily change, the natural frequency of servo control unit and rudder face natural frequency are close and the rudder face Flutter Problem that causes.
Technical scheme of the present invention: for achieving the above object, the present invention by the pressurized strut of servo control unit oil-feed be connected in series bidirectional current limiting valve between oil return, change the mutual leakage of actuating system, and then change the natural frequency of servo control unit, thus suppress the servo flutter of rudder face.The present invention is realized by research technique.
Suppress a method for aircraft rudder surface flutter, by the oil-feed of the pressurized strut in servo control unit be connected in series bidirectional current limiting valve between oil return, the defining method of bidirectional current limiting valve comprises the following steps:
The first step: according to the performance requriements of actuating system, by test, obtains the bandwidth sum resonant frequency parameter of actuating system;
Second step: select multiple bidirectional current limiting valve that internal diameter is suitable;
With reference to the bandwidth sum resonant frequency parameter of actuating system, select the bidirectional current limiting valve of more than five different inner diameters, the inside diameter ranges of the bidirectional current limiting valve chosen is 0.1mm ~ 1.5mm, and the difference in internal diameters of different bidirectional current limiting valve is not more than 0.15mm.
3rd step: the bidirectional current limiting valve installing different inner diameters, by test, alternative is on the minimum bidirectional current limiting valve that inhibit again rudder face flutter of system performance impact;
4th step: the bidirectional current limiting valve selected to the 3rd step, then by test, confirms that its impact on system performance inhibits rudder face flutter very well within the scope of designing requirement, is then arranged in the pressurized strut of aircraft.
The good effect that the present invention produces: the present invention by the pressurized strut of servo control unit oil-feed be connected in series bidirectional current limiting valve between oil return, suppress the servo flutter of rudder face.The method is realized by research technique, simple and reliable, easy and simple to handle, is applicable to the complete situation still having rudder face flutter to occur of Aircraft Production manufacture assembling, saves the time of dealing with problems, reduce design productive costs, ensure that Flight Safety.
Accompanying drawing explanation
Fig. 1 is serial connection bidirectional current limiting valve scheme of installation of the present invention.
Specific implementation method
Suppress a method for aircraft rudder surface flutter, by the oil-feed of the pressurized strut in servo control unit be connected in series bidirectional current limiting valve between oil return, the defining method of bidirectional current limiting valve comprises the following steps:
The first step: according to the performance requriements of actuating system, by test, obtains the bandwidth sum resonant frequency parameter of actuating system;
Check actuating system designing requirement, specify the performance perameter of actuator, and by test, obtain the bandwidth sum resonant frequency of actuating system.
Second step: select multiple bidirectional current limiting valve that internal diameter is suitable;
With reference to the bandwidth sum resonant frequency parameter of actuating system, select the bidirectional current limiting valve of more than five different inner diameters respectively.The inside diameter ranges of the bidirectional current limiting valve chosen is 0.1mm ~ 1.5mm, and the difference in internal diameters of different bidirectional current limiting valve is not more than 0.15mm.
3rd step: the bidirectional current limiting valve installing different inner diameters, by test, alternative is on the minimum bidirectional current limiting valve that inhibit again rudder face flutter of system performance impact;
First the bidirectional current limiting valve that internal diameter is 0.1mm is chosen, be installed between the oil-feed of pressurized strut and oil return, by test, obtain the performance perameter of the system after having installed this object additional, contrast with designing requirement, if meet design but poor to suppressing the effect of flutter, then again choosing internal diameter is that the bidirectional current limiting valve of 0.2mm is installed between the oil-feed of pressurized strut and oil return, again contrast through overtesting and designing requirement, if meet design but poor to suppressing the effect of flutter, then continue to change, until choose the bidirectional current limiting valve not only meeting design requirement but also inhibit rudder face flutter.Now, also should choose the bidirectional current limiting valve of larger one-level internal diameter and test, if test results does not meet design requirement, then thinking previous for best.
4th step: the bidirectional current limiting valve selected to the 3rd step, then by test, confirms that its impact on system performance inhibits rudder face flutter very well within the scope of designing requirement, is then arranged in the pressurized strut of aircraft.
Best bidirectional current limiting valve is obtained to selected, be installed between the oil-feed of pressurized strut and oil return, reaffirmed by test and the system various performance parameters after installing additional mainly contain the power output of actuator, output speed, retraction speed and run duration, these parameters can be met the requirements.Then can select goods shelf products or make this object by oneself, finally attaching it on aircraft to solve the problem of rudder face servo flutter.
Claims (1)
1. suppress a method for aircraft rudder surface flutter, by the oil-feed of the pressurized strut in servo control unit be connected in series bidirectional current limiting valve between oil return, the defining method of bidirectional current limiting valve comprises the following steps:
The first step: according to the performance requriements of actuating system, by test, obtains the bandwidth sum resonant frequency parameter of actuating system;
Second step: select multiple bidirectional current limiting valve that internal diameter is suitable;
With reference to the bandwidth sum resonant frequency parameter of actuating system, select the bidirectional current limiting valve of more than five different inner diameters, the inside diameter ranges of the bidirectional current limiting valve chosen is 0.1mm ~ 1.5mm, and the difference in internal diameters of different bidirectional current limiting valve is not more than 0.15mm.
3rd step: the bidirectional current limiting valve installing different inner diameters, by test, alternative is on the minimum bidirectional current limiting valve that inhibit again rudder face flutter of system performance impact;
4th step: the bidirectional current limiting valve selected to the 3rd step, then by test, confirms that its impact on system performance inhibits rudder face flutter very well within the scope of designing requirement, is then arranged in the pressurized strut of aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410508979.3A CN105523168B (en) | 2014-09-28 | 2014-09-28 | A kind of method for suppressing aircraft rudder surface flutter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410508979.3A CN105523168B (en) | 2014-09-28 | 2014-09-28 | A kind of method for suppressing aircraft rudder surface flutter |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105523168A true CN105523168A (en) | 2016-04-27 |
| CN105523168B CN105523168B (en) | 2017-10-31 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201410508979.3A Active CN105523168B (en) | 2014-09-28 | 2014-09-28 | A kind of method for suppressing aircraft rudder surface flutter |
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5135186A (en) * | 1990-06-04 | 1992-08-04 | Teijin Seiki Co., Ltd. | Flutter control system for aircraft wings |
| CN202593868U (en) * | 2012-05-11 | 2012-12-12 | 中国航空工业集团公司西安飞机设计研究所 | Flutter model structure of movable surface |
| CN103592091A (en) * | 2013-11-14 | 2014-02-19 | 北京航空航天大学 | System and method for flutter ground test of aircraft control surface |
-
2014
- 2014-09-28 CN CN201410508979.3A patent/CN105523168B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5135186A (en) * | 1990-06-04 | 1992-08-04 | Teijin Seiki Co., Ltd. | Flutter control system for aircraft wings |
| CN202593868U (en) * | 2012-05-11 | 2012-12-12 | 中国航空工业集团公司西安飞机设计研究所 | Flutter model structure of movable surface |
| CN103592091A (en) * | 2013-11-14 | 2014-02-19 | 北京航空航天大学 | System and method for flutter ground test of aircraft control surface |
Non-Patent Citations (1)
| Title |
|---|
| 李凌: "飞机抑制操纵舵面颤振的方法研究", 《工业科技》 * |
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| CN105523168B (en) | 2017-10-31 |
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