CN103558842B - A kind of virtual open-loop frequency scan method of airplane ground servo elasticity test - Google Patents
A kind of virtual open-loop frequency scan method of airplane ground servo elasticity test Download PDFInfo
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- CN103558842B CN103558842B CN201310542584.0A CN201310542584A CN103558842B CN 103558842 B CN103558842 B CN 103558842B CN 201310542584 A CN201310542584 A CN 201310542584A CN 103558842 B CN103558842 B CN 103558842B
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Abstract
The invention belongs to strength of aircraft test field, relate to airplane aero-elasticity test scope, particularly relate to a kind of virtual open-loop frequency scan method of airplane ground servo elasticity test.The present invention adopts and arranges virtual open loop circuit in the comprehensive port of aircraft actuator forward direction instruction, only need simple phase inverter and totalizer, without the need to carrying out any change to flight control system backfeed loop, just virtual open loop can be realized under flight control system physics closed loop states, thus avoid aircraft in ground surface servo elasticity frequency response test, occur coupling, effectively dissolve empirical risk.
Description
Technical field
The invention belongs to strength of aircraft test field, relate to airplane aero-elasticity test scope, particularly relate to a kind of virtual open-loop frequency scan method of airplane ground servo elasticity test.
Background technology
Ground servo elasticity test (also claim structural modal coupling test) be with flight control system Aircraft Flight Test before customary ground experiment.Survey aircraft-fly controls the open loop Frequency Response of combined loop, and to assess aircraft floor servo elastic stability according to test figure be one of main task of this test.
Cannot the aircraft that disconnects of physics for flight control system backfeed loop, under circuit closed state, usually measure the forward and backward loop response signal of swept-frequency signal decanting point, obtain the open loop dynamic perfromance that aircraft-fly controls combined loop.
But newly grind aircraft for what carry out ground servo elasticity test first, there is greater risk in direct employing closed loop sweep method, because once be coupled (frequency sweep order-driven control surface deflection the airborne control sensor output signal that flies that encouraged resolve rear drive rudder face through Flight Control Law solution and continue deflection with larger amplitude, then the larger airborne control sensor that flies is caused to export, until motion of rudder is dispersed), aircaft configuration may be caused to destroy at short notice.
Summary of the invention
The object of the invention is to solve flight control system backfeed loop cannot physics when disconnecting, and adopts closed loop sweep method survey aircraft-fly to control the technical matters that combined loop dynamic perfromance exists larger empirical risk.
Technical solution of the present invention is, virtual open loop circuit is incorporated between the inclined instruction output end of flight control computer rudder and actuator forward direction command input of aircraft, virtual open loop circuit comprises a phase inverter and a totalizer, the rudder inclined instruction δ signal that flight control computer exports enters one of them input port of totalizer after phase inverter is reverse, adder output signal is incorporated to the comprehensive port of actuator forward direction instruction, the rudder inclined instruction δ signal that flight control computer exports accesses the input end of dynamic signal analyzer simultaneously, the output frequency sweep command signal Source of dynamic signal analyzer accesses another input port of totalizer, the rudder inclined instruction δ signal that flight control computer exports is comprehensive in totalizer with dynamic signal analyzer frequency sweep instruction output signal after reverser is reverse, the rudder inclined instruction δ signal that the output signal of totalizer and flight control computer export is comprehensive at the comprehensive port of actuator forward direction instruction, drives the control surface deflection of aircraft, after the aircaft configuration response that control surface deflection causes is flown control sensor senses, change electric signal into and send into flight control computer, the rudder inclined instruction δ signal that flight control computer internal control rule resolves rear output is gathered by dynamic signal analyzer and after process, obtains the open loop dynamic perfromance of aircraft-fly control combined loop.
The advantage that the present invention has and good effect are: by comprehensively holding the inclined command signal of flight control computer output rudder be incorporated to oppositely in the instruction of actuator forward direction, the flight control computer that frequency sweep process is produced due to aircraft vehicle vibrations exports the Rudder loop that the inclined instruction of rudder cannot enter actuator, thus virtual open loop is achieved under flight control system backfeed loop physics closed loop states, completely eliminate and under backfeed loop physics closed loop states, carry out frequency sweep test and the coupling risk brought.In addition, virtual open loop circuit proposed by the invention only needs a phase inverter and a totalizer, without the need to carrying out any change to airborne flight control system backfeed loop, just virtual open loop can be realized under flight control system physics closed loop states, simple and clear, be easy to realize, there is very strong practicality.
Accompanying drawing explanation
Fig. 1 is principle of the invention schematic diagram.
Embodiment
Below in conjunction with accompanying drawing, the present invention is elaborated.
1, between the inclined instruction output end of flight control computer rudder and actuator forward direction command input of aircraft, be incorporated to virtual open loop circuit, virtual open loop circuit is made up of a totalizer and a phase inverter;
2, flight control computer export the inclined command signal δ of rudder (analog voltage amount) by the phase inverter in virtual open loop circuit oppositely after, inject the instruction of actuator forward direction through totalizer comprehensively to hold, flight control computer oppositely exports the inclined instruction of rudder-δ and exports the inclined command signal δ of rudder comprehensively with the flight control computer transferring to the comprehensive port of actuator forward direction through actuator forward path, thus makes the inclined instruction of flight control computer output rudder cannot enter the Rudder loop of actuator;
3, operate the joystick and make flight control computer export rudder inclined instruction, but due to the existence of virtual open loop circuit, rudder face there is no appoints response, so achieve virtual open loop under backfeed loop physics closed loop states;
4, dynamic signal analyzer output frequency sweep command signal (Source) injects the comprehensive port of actuator forward direction instruction after the totalizer in virtual open loop circuit, drives control surface deflection;
5, after the aircaft configuration response that control surface deflection causes is flown control sensor senses, change electric signal into and send into flight control computer, the rudder inclined instruction δ signal that flight control computer internal control rule resolves rear output is gathered by dynamic signal analyzer and after process, obtains the open loop dynamic perfromance of aircraft-fly control combined loop.
Claims (1)
1. the virtual open-loop frequency scan method of airplane ground servo elasticity test, it is characterized in that, virtual open loop circuit is incorporated between the inclined instruction output end of flight control computer rudder and actuator forward direction command input of aircraft, virtual open loop circuit comprises a phase inverter and a totalizer, the rudder inclined instruction δ signal that flight control computer exports enters one of them input port of totalizer after phase inverter is reverse, adder output signal is incorporated to the comprehensive port of actuator forward direction instruction, the rudder inclined instruction δ signal that flight control computer exports accesses the input end of dynamic signal analyzer simultaneously, the output frequency sweep command signal Source of dynamic signal analyzer accesses another input port of totalizer, the rudder inclined instruction δ signal that flight control computer exports is comprehensive in totalizer with dynamic signal analyzer frequency sweep instruction output signal after reverser is reverse, the rudder inclined instruction δ signal that the output signal of totalizer and flight control computer export is comprehensive at the comprehensive port of actuator forward direction instruction, drives the control surface deflection of aircraft, after the aircaft configuration response that control surface deflection causes is flown control sensor senses, change electric signal into and send into flight control computer, the rudder inclined instruction δ signal that flight control computer internal control rule resolves rear output is gathered by dynamic signal analyzer and after process, obtains the open loop dynamic perfromance of aircraft-fly control combined loop.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310542584.0A CN103558842B (en) | 2013-11-05 | 2013-11-05 | A kind of virtual open-loop frequency scan method of airplane ground servo elasticity test |
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| CN201310542584.0A CN103558842B (en) | 2013-11-05 | 2013-11-05 | A kind of virtual open-loop frequency scan method of airplane ground servo elasticity test |
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| CN103558842A CN103558842A (en) | 2014-02-05 |
| CN103558842B true CN103558842B (en) | 2016-01-13 |
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Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104216402A (en) * | 2014-09-19 | 2014-12-17 | 中国商用飞机有限责任公司 | Dynamic test method for digital electronic transmission master flight control system of aircraft |
| CN104850056B (en) * | 2014-10-30 | 2017-12-22 | 中国运载火箭技术研究院 | A kind of servo elasticity test and analysis method suitable for multi-channel coupling aircraft |
| CN106773782B (en) * | 2016-12-15 | 2020-01-14 | 中国航空工业集团公司西安飞机设计研究所 | Pneumatic servo elastic hybrid modeling method |
| CN109669438B (en) * | 2018-12-14 | 2020-07-21 | 北京东土科技股份有限公司 | Aircraft servo elasticity test analysis system and medium |
| CN114003017B (en) * | 2021-10-25 | 2024-04-09 | 中国航空工业集团公司成都飞机设计研究所 | Structure control coupling characteristic test analysis method suitable for digital flight control system |
| CN114355792A (en) * | 2021-12-24 | 2022-04-15 | 兰州飞行控制有限责任公司 | Closed-loop verification method for stability margin of control law |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5756891A (en) * | 1994-08-23 | 1998-05-26 | National Aerospace Laboratory Of Science & Technology Agency | Verification method of a flight control system using a transportable wind tunnel |
| CN101988864A (en) * | 2009-07-31 | 2011-03-23 | 中国商用飞机有限责任公司 | Signal generator for airplane ground test and application method thereof |
| CN102566440A (en) * | 2011-12-29 | 2012-07-11 | 成都飞机工业（集团）有限责任公司 | Testing method for unmanned plane flight-control structure modal coupling |
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- 2013-11-05 CN CN201310542584.0A patent/CN103558842B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5756891A (en) * | 1994-08-23 | 1998-05-26 | National Aerospace Laboratory Of Science & Technology Agency | Verification method of a flight control system using a transportable wind tunnel |
| CN101988864A (en) * | 2009-07-31 | 2011-03-23 | 中国商用飞机有限责任公司 | Signal generator for airplane ground test and application method thereof |
| CN102566440A (en) * | 2011-12-29 | 2012-07-11 | 成都飞机工业（集团）有限责任公司 | Testing method for unmanned plane flight-control structure modal coupling |
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