CN102680221B - Fatigue test method for full-aircraft main operating system of aircraft - Google Patents
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Abstract
The invention belongs to a fatigue life determining technology for an operating system of an aircraft and relates to a fatigue test method for a full-aircraft main operating system of the aircraft. According to the fatigue test method, the fatigue coordination loading of an operating load and an operating displacement can be carried out, a fatigue test including the operating load and an operating displacement spectrum on the full-aircraft main operating system of the aircraft can be implemented, and meanwhile, the problem of simultaneous test of aircraft body fatigue on the same fatigue testing machine is taken into account, so that the fatigue properties of components and supporting parts of the full-aircraft main operating system and static performance indicators of the full-aircraft main operating system are all actually assessed; the actual loaded conditions of the main operating system of the aircraft under normal operating and emergency operating conditions are more truly reflected, the fatigue properties of the structure and mechanism of the main operating system of the aircraft are embodied; and the test cost is reduced, and the reliability of a test result is improved.
Description
Technical field
The invention belongs to flight control system fatigue and determine longevity technology, relate to a kind of main control system of whole plane fatigue test method.
Background technology
Because test condition and experimental scale limit, existing main control system of whole plane torture test, all do not relate to the measured data using full machine control loads and handle displacement and compile spectrum, primary flight control system spare part and supporter fatigue behaviour and full machine control system static performance index thereof is made all to obtain actual examination, do not consider flight control system state issues, do not consider that tired same may well ask is inscribed with airframe yet.What have fixes flight control system, implements comparatively conservative control loads program block spectrum and tests, only examined the fatigue behaviour of Purely mechanical spare part; Some enforcement fatigue wear test loads spectrum, only examine control system quiet/dynamic performance index and system wear, do not examine the system fatigue behaviour in emergency maneuver situation; What have then replaces primary flight control system torture test with several control system key part and component torture tests and carries out under machine, these tests are routine tests, its test findings is too conservative or examination is not comprehensive, really can not reflect that aircraft primary control circuit is structure and the fatigue behaviour of mechanism, the fiduciary level of its test findings reduces.According to such test findings, be difficult to provide fatigue lifetime primary flight control system assess accurately.
Summary of the invention
Order of the present invention: the main control system of whole plane fatigue test load spectrum, the simultaneously consideration that provide a kind of energy to implement to comprise control loads and handle displacement spectra are inscribed with may well ask with airframe fatigue, make full owner's maneuverability system zero assembly and supporter fatigue lifetime and full machine control system static performance index thereof all obtain the main control system of whole plane fatigue test method of actual examination.
Technical solution of the present invention: fatigue test method is following steps,
(1) according to main control system of whole plane torture test requirement, respectively control loads/manipulation displacement the measured data of aircraft aileron, horizontal tail and rudder control system is chosen to filtering principal parameter and filtering threshold value, carried out filtering process;
(2) data processing is carried out to the control loads after filtering process/manipulation displacement measured data, solve the actual measurement spectrum frequency problem relating to and handle displacement and bring, that is: control loads and the frequency matching problem handling displacement simultaneously; By carrying out peak value/valley counting to each control loads/manipulation displacement filtering data risen and fallen of aircraft, provide rise and fall spectrum and the average spectrum of each mission profile of aircraft, and then formation provides ground actual measurement score with the form of control loads/manipulation displacement spectra and surveys score in the air;
(3) survey score according to ground and survey score data in the air, by the form establishment measured test spectrum of the actual measurement peak value that jociey stick is handled or pedal is handled/valley spectrum, handle measured test spectrum with aircraft aileron, horizontal tail and rudder control system measured test spectrum, ground brake measured test spectrum and compound respectively to provide, wherein, horizontal tail control system divides four kinds of arm of force states, and rudder control system divides greatly/little speed two states; Ground brake measured test spectrum and compound are handled measured test spectrum and are provided all separately;
(4) with the constant amplitude block of 50% and 100% two of limit load rank spectrum establishment main control system of whole plane fatigue checking spectrum, examine and verify the fatigue behaviour of aircraft primary control circuit in emergency maneuver situation, wherein, aircraft aileron, horizontal tail control system, by left avertence/right avertence or frontly to push away/symmetrical cycle of post-tensioning loads; Rudder control system, loads by the pulsating cyclic of left/right pedal blocked operation; For ground brake, the pulsating cyclic simultaneously operated by left/right pedal loads;
(5) comprehensive above-mentioned measured test spectrum is composed with tired checking and is combined debugging of dispatching from the factory and handles data and outfield ground maintenance manipulation data, works out and provides main control system of whole plane fatigue test load spectrum;
(6) on fatigue tester, main control system of whole plane torture test is carried out, test method is one of following: (one) loads the coordination jociey stick in fatigue tester passenger cabin or left/right pedal carried out control loads and handle displacement, implements main control system of whole plane fatigue test load spectrum; Complete primary flight control system torture test, provide the conclusion whether primary flight control system fatigue lifetime and full machine control system static performance index meet fatigue life requirements.(2) tired with when trying with airframe, all be enclosed in fatigue tester passenger cabin to the fatigue loading of aircraft aileron, horizontal tail and rudder control system, coordination jociey stick in passenger cabin or left/right pedal carrying out control loads and manipulation displacement is loaded, implements main control system of whole plane fatigue test load spectrum; Install aircraft hydraulic booster bogusware or duplicated control actuator bogusware, the control system after making booster or after duplicated control actuator supports aircraft aileron, horizontal tail and yaw rudder rudder face and tries with organism fatigue is same; Complete primary flight control system torture test, provide the conclusion whether primary flight control system fatigue lifetime and full machine control system static performance index meet fatigue life requirements.
The advantage that the present invention has and beneficial effect: the present invention can carry out control loads and the tired main control system of whole plane torture test coordinating to load, implement to comprise control loads and manipulation displacement spectra of manipulation displacement, considers to inscribe with may well ask with airframe fatigue on same frame fatigue tester, make primary flight control system spare part and supporter fatigue behaviour and full machine control system performance index thereof all obtain actual examination simultaneously.Reflect the actual loading conditions of aircraft primary control circuit in normal operational situation and emergency maneuver situation comparatively truly, embody aircraft primary control circuit and be structure and the fatigue behaviour of mechanism; Reduce experimentation cost, improve the fiduciary level of test findings.The present invention is applicable to the main control system of whole plane torture test of the rigid nonreversible control of common mechanical; For common mechanical formula control system, Flight By Wire aircraft control stick (dish) to load simulator control system, backup mechanical manoeuvring system and aircraft hydraulic booster after or after duplicated control actuator the torture test of control system all have reference and reference role.
Accompanying drawing explanation
Fig. 1 is main control system of whole plane torture test process flow diagram.
Embodiment
The first step carries out filtering process to the control loads of flight control system and manipulation displacement measured data
According to main control system of whole plane torture test requirement, respectively control loads/manipulation displacement the measured data of aircraft aileron, horizontal tail and rudder control system is chosen to filtering principal parameter and filtering threshold value, carried out filtering process.
Second step establishment ground is surveyed score and surveys score in the air
Data processing is carried out to the control loads after filtering process/manipulation displacement measured data, solve the actual measurement spectrum frequency problem relating to and handle displacement and bring simultaneously, that is: control loads and the frequency matching problem (only related to control loads and the correspondence problem loading number of times or the frequency in the past, and do not relate to correspondence problem while handling displacement and control loads and the frequency) handling displacement; By carrying out peak value/valley counting to each control loads/manipulation displacement filtering data risen and fallen of aircraft, provide rise and fall spectrum and the average spectrum of each mission profile of aircraft, and then formation provides ground actual measurement score with the form of control loads/manipulation displacement spectra and surveys score in the air.
3rd step establishment measured test spectrum
Survey score according to ground and survey score data in the air, by the form establishment measured test spectrum of the actual measurement peak value that jociey stick is handled or pedal is handled/valley spectrum, handle measured test spectrum with aircraft aileron, horizontal tail and rudder control system measured test spectrum, ground brake measured test spectrum and compound respectively to provide, wherein, in order to the fatigue behaviour of real embodiment aircraft primary control circuit, the arm of force value of horizontal tail control system is divided into four kinds of arm of force states, and rudder control system is divided into greatly/little speed two states; Ground brake measured test spectrum and compound are handled measured test spectrum and are provided all separately.
The tired checking spectrum of 4th step establishment
With the constant amplitude block of 50% and 100% two of limit load rank spectrum establishment main control system of whole plane fatigue checking spectrum, examine and verify the fatigue behaviour of aircraft primary control circuit in emergency maneuver situation, wherein, aircraft aileron, horizontal tail control system, by left avertence/right avertence or frontly to push away/symmetrical cycle of post-tensioning loads; Rudder control system, loads by the pulsating cyclic of left/right pedal blocked operation; For ground brake, the pulsating cyclic simultaneously operated by left/right pedal loads.
5th step establishment primary flight control system fatigue test load spectrum
Comprehensive above-mentioned measured test spectrum is composed with tired checking and is combined debugging of dispatching from the factory and handles data and outfield ground maintenance manipulation data, provides main control system of whole plane fatigue test load spectrum.
6th step carries out primary flight control system torture test
Fatigue tester carries out main control system of whole plane torture test, can carry out separately, also can be tired with trying with airframe, test method is one of following: (one) loads the jociey stick in fatigue tester passenger cabin or left/right pedal carrying out control loads and handling displacement coordination, implements main control system of whole plane fatigue test load spectrum; Complete primary flight control system torture test, provide the conclusion whether primary flight control system fatigue lifetime and full machine control system static performance index meet fatigue life requirements.(2) tired with when trying with airframe, all be enclosed in fatigue tester passenger cabin to the fatigue loading of aircraft aileron, horizontal tail and rudder control system, jociey stick in passenger cabin or left/right pedal carry out control loads and handle displacement coordination loading, implements main control system of whole plane fatigue test load spectrum; Aircraft hydraulic booster bogusware or duplicated control actuator bogusware are installed, by the connection of the triangle rocker arm after regulating the connection of its bogusware and airframe and bogusware and aircraft hydraulic booster or after duplicated control actuator and pull bar or aircraft aileron, horizontal tail or yaw rudder rudder face joint, control system after making booster or after duplicated control actuator supports aircraft aileron, horizontal tail and yaw rudder rudder face (being in the rudder face position of specifying and the fatigue load of bearing on aircraft rudder surface), with organism fatigue with trying; Complete primary flight control system torture test, provide the conclusion whether primary flight control system fatigue lifetime and full machine control system static performance index meet fatigue life requirements.
Embodiment one (carrying out separately as example with primary flight control system torture test)
One, filtering process is carried out to flight control system load and displacement measured data: respectively filtering principal parameter and filtering threshold value are chosen to the measured data of aircraft aileron, horizontal tail and rudder control system, carry out filtering process; Before filtering process, pre-service is carried out to measured data, namely remove significantly abnormal data such as some error code, hops etc. by program.
Two, work out ground actual measurement score and survey score in the air: data processing is carried out to the control loads after filtering process and displacement measured data, solving the actual measurement spectrum frequency problem relating to and handle displacement and bring simultaneously; By to each control loads that rises and falls of aircraft and handle displacement filtering data and carry out peak value/valley counting, provide rise and fall spectrum and the average spectrum of each mission profile of aircraft, and then provide ground actual measurement score with the form of control loads and manipulation displacement spectra and survey score in the air.
Three, measured test spectrum is worked out: survey score according to ground and survey score data in the air, by the form establishment measured test spectrum of the actual measurement peak value that jociey stick is handled or pedal is handled/valley spectrum, handle measured test spectrum with aircraft aileron, horizontal tail and rudder control system measured test spectrum, ground brake measured test spectrum and compound respectively to provide, wherein, the arm of force value of horizontal tail control system is divided into four kinds of arm of force states, and rudder control system is divided into greatly/little speed two states; Ground brake measured test spectrum and compound are handled measured test spectrum and are provided all separately.
Four, the tired checking spectrum of establishment: with the constant amplitude block of 50% and 100% two rank of limit load in flight control system strength specification spectrum establishment main control system of whole plane fatigue checking spectrum, wherein, aircraft aileron, horizontal tail control system, by left avertence/right avertence or frontly to push away/symmetrical cycle of post-tensioning loads; Rudder control system, loads by the pulsating cyclic of left/right pedal blocked operation; For ground brake, the pulsating cyclic simultaneously operated by left/right pedal loads.
Five, primary flight control system fatigue test load spectrum is worked out: comprehensive above-mentioned measured test spectrum is composed with tired checking and combined debugging of dispatching from the factory and handles data and outfield ground maintenance manipulation data, provides main control system of whole plane fatigue test load spectrum.
Six, primary flight control system torture test is carried out:
(1) testpieces state: on fatigue tester, carries out primary flight control system torture test with the primary control circuit spare part and supporter thereof meeting installation condition.
(2) loading spectrum is implemented:
A. checked by system convention, determine to control the adjustment Pass Test requirement of machine room to horizontal tail control system arm of force state and rudder control system speed state; Determine that the typical loading curve data of aileron, horizontal tail and rudder control system are normal; Determine that the voltage supply of testing ground and flight control system is normal.
B. on jociey stick or left/right pedal (bogusware), the coordination carrying out control loads and manipulation displacement loads, implement primary flight control system fatigue test load spectrum, wherein, comprise individual operation is applied to aileron, horizontal tail and rudder control system, compound handle and ground brake control loads and handle displacement spectra block, aileron, horizontal tail and rudder control system fatigue behaviour and full machine control system static performance index before aircraft hydraulic booster or before duplicated control actuator are examined.
C. to the control system after booster or after duplicated control actuator, then tired with examination in company with airframe when airframe torture test, carry out torture test no longer separately.
(3) off-test and lifetime of system assessment
According to the system zero assembly occurred in above-mentioned primary flight control system torture test process and supporter problem thereof and system state, debugging and maintenance situation, test findings is analyzed, then assessing the static performance index of aileron, horizontal tail and rudder control system, fatigue damage, wearing and tearing and gap, normal operational situation and emergency maneuver situation lower serviceable life and system zero assembly opening and inspecting scope, finally providing the conclusion whether primary flight control system fatigue lifetime and full machine control system static performance index meet fatigue life requirements.
Embodiment two (trying as example together with primary flight control system and organism fatigue)
One, primary flight control system fatigue test load spectrum establishment: primary flight control system fatigue test load spectrum compilation process is identical with the step one in above-described embodiment one ~ step 5.
Two, primary flight control system torture test is carried out:
(1) testpieces state: on fatigue tester, carries out primary flight control system torture test with the primary control circuit spare part and supporter thereof meeting installation condition.
(2) loading spectrum is implemented:
A. checked by system convention, determine to control the adjustment Pass Test requirement of machine room to horizontal tail control system arm of force state and rudder control system speed state; Determine that the typical loading curve data of aileron, horizontal tail and rudder control system are normal; Determine that the voltage supply of testing ground and flight control system is normal.
B. tested by uniting and adjustment, checking primary flight control system torture test and organism fatigue test can be carried out on same fatigue tester simultaneously, do not occur system fatigue and the interactional test problem of organism fatigue.Uniting and adjustment test is for loading heavier in airframe fatigue test load spectrum spectrum block, chooses flight control system carries out torture test simultaneously verification method in the typical case such as individual operation, compound manipulation or ground brake and its.
C., before trying with airframe fatigue is same, all will be enclosed in fatigue tester passenger cabin (airframe torture test has airtight requirement to passenger cabin) to the jociey stick of aircraft aileron, horizontal tail and rudder control system or the fatigue loading of left/right pedal (bogusware); On jociey stick or left/right pedal, the coordination carrying out control loads and manipulation displacement loads, implement primary flight control system fatigue test load spectrum, wherein, comprise individual operation is applied to aileron, horizontal tail and rudder control system, compound handle and ground brake control loads and handle displacement spectra block; Aileron, horizontal tail and rudder control system fatigue behaviour before aircraft hydraulic booster or before duplicated control actuator and full machine control system static performance index are examined.
D. install and adjust aircraft hydraulic booster bogusware or duplicated control actuator bogusware and connection thereof, control system after making booster or after duplicated control actuator supports aircraft aileron, horizontal tail and yaw rudder rudder face (being in the rudder face position of specifying and the fatigue load of bearing on aircraft rudder surface), tired with trying with airframe.
(3) off-test and lifetime of system assessment
According to the system zero assembly occurred in above-mentioned primary flight control system torture test process and supporter problem thereof and system state, debugging and maintenance situation, test findings is analyzed, then assessing the static performance index of aileron, horizontal tail and rudder control system, fatigue damage, wearing and tearing and gap, normal operational situation and emergency maneuver situation lower serviceable life and system zero assembly opening and inspecting scope, finally providing the conclusion whether primary flight control system fatigue lifetime and full machine control system static performance index meet fatigue life requirements.
Claims (1)
1. a main control system of whole plane fatigue test method, is characterized in that, fatigue test method is following steps:
(1) according to main control system of whole plane torture test requirement, respectively to the control loads of aircraft aileron, horizontal tail and rudder control system or handle displacement measured data and choose filtering principal parameter and filtering threshold value, filtering process is carried out;
(2) data processing is carried out to the control loads after filtering process or manipulation displacement measured data, solve the actual measurement spectrum frequency problem relating to and handle displacement and bring, that is: the frequency matching problem of control loads and manipulation displacement simultaneously; By to each control loads that rises and falls of aircraft or handle displacement filtering data and carry out peak value or valley counting, provide rise and fall spectrum and the average spectrum of each mission profile of aircraft, and then formation provides ground actual measurement score and surveys score in the air with the form of control loads and manipulation displacement spectra;
(3) survey score according to ground and survey score data in the air, compose by the form establishment measured test of the actual measurement peak value that jociey stick is handled or pedal is handled or valley spectrum, handle measured test spectrum with aircraft aileron, horizontal tail and rudder control system measured test spectrum, ground brake measured test spectrum and compound respectively to provide, wherein, horizontal tail control system divides four kinds of arm of force states, and rudder control system divides large or little speed two states; Ground brake measured test spectrum and compound are handled measured test spectrum and are provided all separately;
(4) with the constant amplitude block of 50% and 100% two of limit load rank spectrum establishment main control system of whole plane fatigue checking spectrum, examine and verify the fatigue behaviour of aircraft primary control circuit in emergency maneuver situation, wherein, aircraft aileron, horizontal tail control system, by left avertence or right avertence or frontly to push away or the symmetrical cycle of post-tensioning loads; Rudder control system, loads by the pulsating cyclic of left or right pedal blocked operation; For ground brake, the pulsating cyclic simultaneously operated by left or right pedal loads;
(5) comprehensive above-mentioned measured test spectrum is composed with tired checking and is combined debugging of dispatching from the factory and handles data and outfield ground maintenance manipulation data, works out and provides main control system of whole plane fatigue test load spectrum;
(6) on fatigue tester, main control system of whole plane torture test is carried out, test method is one of following: (one) loads the coordination jociey stick in fatigue tester passenger cabin or left or right pedal carried out control loads and handle displacement, implements main control system of whole plane fatigue test load spectrum; Complete primary flight control system torture test, provide the conclusion whether primary flight control system fatigue lifetime and full machine control system static performance index meet fatigue life requirements; (2) tired with when trying with airframe, all be enclosed in fatigue tester passenger cabin to the fatigue loading of aircraft aileron, horizontal tail and rudder control system, coordination jociey stick in passenger cabin or left or right pedal carrying out control loads and manipulation displacement is loaded, implements main control system of whole plane fatigue test load spectrum; Install aircraft hydraulic booster bogusware or duplicated control actuator bogusware, the control system after making booster or after duplicated control actuator supports aircraft aileron, horizontal tail and yaw rudder rudder face and tries with organism fatigue is same; Complete primary flight control system torture test, provide the conclusion whether primary flight control system fatigue lifetime and full machine control system static performance index meet fatigue life requirements.
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