CN110987421A - Dynamic fatigue test support method for whole-machine main control system - Google Patents
Dynamic fatigue test support method for whole-machine main control system Download PDFInfo
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
- G01M13/02—Gearings; Transmission mechanisms
- G01M13/025—Test-benches with rotational drive means and loading means; Load or drive simulation
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- B—PERFORMING OPERATIONS; TRANSPORTING
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- B64F5/60—Testing or inspecting aircraft components or systems
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- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/08—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces
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Abstract
The invention belongs to the fatigue test technology of an airplane control system, and relates to a dynamic fatigue test support method for a full-airplane main control system for mechanical hard irreversible control. The invention provides a test support method for a full-aircraft main control system on an aircraft fatigue testing machine, which is used for carrying out independent control and composite control coordinated loading on an aileron/horizontal tail/rudder control system on an aircraft steering column and a pedal, implementing a full-aircraft main control system control load displacement spectrum compiled based on control load and control displacement measured data, and examining and verifying the fatigue performance and the static performance of the aileron/horizontal tail/rudder control system.
Description
Technical Field
The invention belongs to the fatigue test technology of an airplane control system, and particularly relates to a dynamic fatigue test support method of a full-airplane main control system.
Background
For the static fatigue test of the whole-aircraft main control system, generally, the fatigue test is carried out on the fatigue testing machine or an aircraft booster or a composite steering engine on a test bench or other designated system positions by fixing and supporting load conditions such as neutral and limit control of an aileron/horizontal tail/rudder control system and applying a static fatigue test load spectrum to an aircraft steering rod and a pedal or other designated loading points. However, for the dynamic fatigue test of the aircraft main control system, i.e. performing dynamic fatigue coordination loading of the control load and the control displacement on the steering column and the pedals, and examining and verifying the fatigue performance and the static performance index of the aileron/horizontal tail/rudder control system, the system structure and the support state of the aircraft main control system, including the corresponding setting/adjustment of the booster and the composite steering engine dummy piece, etc., are required to ensure that the components and the supports of the aircraft aileron/horizontal tail/rudder control system can reflect the normal use condition of the outfield active full-service main control system and bear the control load/displacement coordination loading spectrum of the aircraft main control system.
Disclosure of Invention
The purpose of the invention is: the method is used for meeting the requirements of performing coordinated loading of independent control and composite control on the load and displacement of an aileron/horizontal tail/rudder control system on an airplane steering column and a pedal, implementing an operating load/displacement spectrum of the main control system of the whole airplane based on measured data of the operating load and the operating displacement, and examining and verifying the fatigue performance and the static performance of the aileron/horizontal tail/rudder control system.
The application provides a method for supporting a dynamic fatigue test of a full-machine main control system, which comprises the following steps:
carrying out nondestructive flaw detection inspection and measurement inspection on the airplane aileron/horizontal tail/rudder control system on a fatigue testing machine, confirming that the structural state and the static performance of the whole airplane main control system meet preset requirements, and adjusting and confirming that the aileron/horizontal tail/rudder control system is in a neutral state;
aiming at the whole main control system, setting a first dummy piece 1 and a tension compensator dummy piece 2, fixing the first dummy piece 1 and the tension compensator dummy piece 2 at a neutral position, and confirming that the tension compensator dummy piece 2 works and moves normally;
respectively setting a aileron/horizontal tail steering engine dummy piece 3 and an adjustment sheet effect mechanism dummy piece 4, fixing the aileron/horizontal tail steering engine dummy pieces at a neutral position, and confirming that a manual steering rod and pedals can normally operate a whole-engine main control system;
the left/right pedal brake rocker arm fixing and connecting rod dummy pieces 5 are respectively arranged;
and confirming that the manual steering column and the left pedal and the right pedal can normally operate the main operating system of the whole machine.
Preferably, the tension compensator dummy part 2 is an internal spring type load simulation device and is used for simulating the operation force/displacement characteristics of an auxiliary wing/horizontal tail booster of an operation plane and an oil distributing valve of a rudder composite steering engine.
Preferably, the tension compensator dummy 2 comprises an aileron tension compensator dummy, a horizontal tail tension compensator dummy and a rudder tension compensator dummy.
Preferably, the tension compensator dummy 2 is configured to specifically include:
the left/right aileron booster dummy part, the left/right horizontal tail booster dummy part, the rudder composite steering engine dummy part and the corresponding aileron/horizontal tail/rudder control system are respectively connected;
the positions of the mounting connection points at the two ends of the tension compensator dummy piece 2 are respectively adjusted and fixed to be the same as the neutral positions of the airplane booster and the composite steering engine oil distributing valve operating lever.
Preferably, set up aileron/horizontal tail steering wheel dummy member 3 and adjustment slice effect mechanism dummy member 4, specifically include:
the connection of the aileron/horizontal tail steering engine dummy part 3 is adjusted/fixed according to the neutral position of the airplane aileron/horizontal tail steering engine at the connection position of the aileron/horizontal tail control system composite rocker arm;
the connection of the adjustment sheet effect mechanism dummy piece 4 is adjusted/fixed according to the neutral position of the airplane aileron/horizontal tail loading mechanism and the rudder hydraulic loading mechanism at the rear end rocker arm connection position.
Preferably, set up left/right pedal brake rocking arm fixed and connecting rod dummy 5 respectively, specifically include:
the double-foot brake operation is carried out to carry out neutral fixed support and enable the left/right foot pedal shafts to be aligned;
it was confirmed that the two-foot brakes can bear the braking load of the airplane in the case of normal operation of the rudder steering system with the left-foot forward/right-foot forward, respectively.
Preferably, the trim tab effect mechanism dummy 4 includes a flap trim tab effect mechanism dummy, a horizontal tail trim tab effect mechanism dummy, and a rudder trim tab effect mechanism dummy.
Preferably, the first dummy part 1 comprises an aileron booster dummy part, a horizontal tail booster dummy part and a rudder composite steering engine dummy part.
The invention has the advantages and beneficial effects that: the invention provides a test support method for a main control system on an airplane fatigue testing machine, which is used for carrying out independent control and composite control coordination loading on an aileron/horizontal tail/rudder control system on an airplane steering column and pedals, implementing a full-airplane main control system control load displacement spectrum compiled based on control load and control displacement measured data, and carrying out a full-airplane main control system dynamic fatigue test for checking and verifying the fatigue performance and the static performance of the aileron/horizontal tail/rudder control system.
Drawings
FIG. 1 is a schematic diagram of a dynamic fatigue test support for an aircraft main control system according to the present invention;
FIG. 2 is another schematic diagram of the aircraft main control system dynamic fatigue test support of the present invention;
FIG. 3 is a further schematic diagram of the aircraft main control system dynamic fatigue test support of the present invention;
FIG. 4 is a schematic diagram of a dynamic fatigue test support for the main control system of the aircraft according to the present invention;
the device comprises an aircraft booster dummy part or a composite steering engine dummy part, a tension compensator dummy part, a 3-aileron/horizontal tail steering engine dummy part, a 4-aileron/horizontal tail/rudder adjusting effect mechanism dummy part and a 5-brake rocker fixing and connecting rod dummy part, wherein the aircraft booster dummy part or the composite steering engine dummy part is connected with a tension compensator dummy part through a connecting rod.
Detailed Description
Example one
The technical scheme of the invention is as follows: the fatigue examination and verification of the system structure fatigue performance and the system static performance are implemented on the main control system of the whole airplane, and the dynamic fatigue test support is set as the following steps:
(1) on a fatigue testing machine provided with a qualified mounting part of the whole main control system, carrying out nondestructive flaw detection inspection and measurement inspection on the airplane aileron/horizontal tail/rudder control system, and confirming that the structural state and the static performance of the whole main control system meet preset requirements; and adjusting and confirming that the aileron/horizontal tail/rudder control system is in a neutral state so as to finish the preparation work of changing the dummy piece before the dynamic fatigue test of the whole main control system. Generally, in a test piece matched delivery catalogue submitted with a fatigue test, a true piece cannot be reapplied for a false piece, namely, the true piece is not installed on a fatigue testing machine on an aileron/horizontal tail/rudder booster, a composite steering engine, an aileron/horizontal tail steering engine and an aileron/horizontal tail/rudder adjusting sheet effect mechanism, at the moment, after the installation of related false pieces is completed according to the following steps and requirements, nondestructive flaw detection and measurement inspection are carried out, the structural state and the static performance of the whole main control system are confirmed to meet the preset requirements, and the aileron/horizontal tail/rudder control system is confirmed to be in a neutral state.
(2) Respectively disassembling the installation true pieces and replacing the corresponding first dummy pieces 1, or directly installing the first dummy pieces 1 (when no corresponding installation true pieces exist), wherein the positions and requirements of connecting points at two ends of the first dummy pieces are the same as those of the installation true pieces of the aircraft booster and the composite steering engine; the first dummy piece 1 is correspondingly provided with a tension compensator dummy piece 2 respectively, and an aileron/horizontal tail/rudder control system is connected with a corresponding booster dummy piece and a composite steering engine dummy piece; the normal operation of the whole main operation system can be ensured when a driver manually operates a lever and pedals in the cab. The replacement requirements of the tension compensator dummy 2 are: a) installing aileron tension compensators on the left/right aileron booster dummy parts respectively, wherein the installation connection point position and the requirement of the aileron booster dummy parts are the same as the connection of the neutral position of an operating rod of an oil distributing valve of an airplane aileron booster; b) respectively installing a horizontal tail tension compensator on the left/right horizontal tail booster dummy pieces, wherein the installation connection point position and the requirement of the horizontal tail tension compensator are the same as the connection of the neutral position of an operating rod of an oil distributing valve of an airplane horizontal tail booster; c) a rudder tension compensator is arranged on a rudder composite steering engine dummy piece, and the position and the requirement of the installation connection point of the rudder tension compensator are the same as the connection of the neutral position of an airplane rudder composite steering engine oil distributing valve operating lever.
It should be noted here that the booster and the composite steering engine dummy part are specially designed for the requirement of disconnection at the aircraft booster and the composite steering engine according to the fatigue test scheme of the whole main control system, and the aim is to make the control system in front of the booster meet the static/dynamic fatigue test requirement and make the control system behind the booster support the aileron/horizontal tail/rudder control surface (bear the load spectrum of the control surface of the engine body) according to the position requirement of the control surface;
the tension compensator dummy is a built-in spring type load simulator actually, and is used for simulating the operation load/displacement characteristics of an oil distributing valve of an aileron/horizontal tail/rudder booster or a composite steering engine so as to meet the basic requirements of a dynamic fatigue test of a main control system of the whole airplane on the structure of the control system, namely the dynamic fatigue test operation load/displacement spectrum of the main control system of the whole airplane can be implemented on a pilot lever and a pedal of the airplane.
(3) Respectively disassembling the installation true part and replacing the corresponding aileron/horizontal tail steering engine false part 3 and adjustment sheet effect mechanism false part 4, or directly installing the aileron/horizontal tail steering engine false part 3 and adjustment sheet effect mechanism false part 4 (when no corresponding installation true part exists), fixing the aileron/horizontal tail steering engine false part 3 and the adjustment sheet effect mechanism false part 4 at a neutral position or a neutral state, and confirming that the aileron/horizontal tail/rudder control system can be manually and normally operated or moved; the reloading requirements of the steering engine dummy piece 3 and the adjusting sheet effect mechanism dummy piece 4 are as follows: a) mounting and fixing corresponding steering engine dummy pieces by using original mounting nail holes of an airplane aileron/horizontal tail steering engine mounting piece on an airplane body, and finally setting an output end point of the airplane aileron/horizontal tail steering engine dummy piece at a neutral position through thread adjustment; b) the aircraft aileron/horizontal tail/rudder trimmer effect mechanism is used for installing and fixing a corresponding trimmer effect mechanism dummy piece in an installation nail hole on a machine body, and finally, the output end point of the aircraft aileron/horizontal tail/rudder trimmer effect mechanism dummy piece is arranged at a neutral position through thread adjustment.
It should be noted here that: the aileron/horizontal tail steering engine dummy piece 3 and the adjusting sheet effect mechanism dummy piece 4 are fixed or arranged at the neutral position or neutral state, so that the pure mechanical operation/transmission function of the whole main operation system is fully embodied, and the influence from the steering engine operation is not considered.
(4) Respectively disassembling the installation true piece and replacing the left/right pedal brake rocker fixing and connecting rod dummy piece 5, or directly installing the left/right pedal brake rocker fixing and connecting rod dummy piece 5 (when no corresponding installation true piece exists), fixing and supporting the double-foot pedal brake operation, confirming that the steering control system can be normally operated when the left/right pedal is stepped forwards, and bearing the large/small brake load of the airplane when the double-foot pedal is stepped to brake; the requirements of fixing the pedal brake rocker arm and replacing the connecting rod dummy part 5 are as follows: the aircraft pedals an original brake rocker arm connecting support mounting nail hole on a front end cabin floor to fix a corresponding brake rocker arm and a connecting rod dummy, and the end point of the connecting rod dummy is connected with a rocker arm at the lower end of a pedal arm of force, so that the connecting rod dummy supports a left pedal/a right pedal and enables a left pedal shaft/a right pedal shaft to be aligned, and the aircraft can bear the brake load of double-foot-treading brake.
Example two
The invention is further illustrated by the following specific examples:
first-step replacement booster and composite steering engine dummy part
Before the dynamic fatigue test of the main control system of the whole airplane, respectively carrying out nondestructive flaw detection inspection and measurement inspection on an airplane booster and an aileron/horizontal tail/rudder control system in front of a composite steering engine, confirming that the system structure and static performance of the main control system of the whole airplane meet the requirements of design and fatigue test, adjusting and confirming that the aileron/horizontal tail/rudder control system is in a neutral state; if the installation true part of the aileron/horizontal tail/rudder booster, the composite steering engine, the aileron/horizontal tail steering engine and the aileron/horizontal tail/rudder adjusting sheet effect mechanism is not installed on the fatigue testing machine, after the installation of related false parts is completed according to the following steps and requirements, nondestructive inspection and measurement inspection are carried out, the structural state and the static performance of the whole main control system are confirmed to meet the preset requirements, and meanwhile, the aileron/horizontal tail/rudder control system is confirmed to be in a neutral state. Thereafter, referring to fig. 1, the first dummy parts 1 are replaced respectively.
Second step installation tension compensator dummy
Referring to fig. 1, a tension compensator dummy 2 is respectively installed at an aircraft booster dummy and a composite steering engine dummy, so as to ensure that a manual steering rod and pedals can be used for normally operating a whole main control system. The installation requirements for the tension compensator dummy are: 1) installing aileron tension compensators on the left/right aileron booster dummy parts respectively, wherein the installation connection point position and the requirement of the aileron booster dummy parts are the same as the connection of the neutral position of an operating rod of an oil distributing valve of an airplane aileron booster; 2) respectively installing a horizontal tail tension compensator on the left/right horizontal tail booster dummy pieces, wherein the installation connection point position and the requirement of the horizontal tail tension compensator are the same as the connection of the neutral position of an operating rod of an oil distributing valve of an airplane horizontal tail booster; 3) a rudder tension compensator is arranged on a rudder composite steering engine dummy part, and the position and the requirement of the installation connection point of the rudder tension compensator are the same as the connection of a neutral position rod for operating an oil distributing valve of an airplane rudder composite steering engine.
Thirdly, replacing the steering engine dummy part and the adjustment sheet effect mechanism dummy part
Referring to fig. 2 to 3, an aileron/horizontal tail steering engine dummy piece 3 and an adjustment sheet effect mechanism dummy piece 4 are respectively installed or replaced at the aileron/horizontal tail steering engine and the aileron/horizontal tail/rudder adjustment sheet effect mechanism, two ends of the steering engine dummy piece 3/adjustment sheet effect mechanism dummy piece 4 are connected with two ends of an actual steering engine/adjustment sheet effect mechanism installation component of the airplane, the dummy piece is adjusted and fixed to be in a neutral position or a neutral state, and the aileron/horizontal tail/rudder control system can be confirmed to be normally operated or moved. The reloading requirements for the steering engine dummy part 3 and the adjusting sheet effect mechanism dummy part 4 are as follows: 1) mounting and fixing corresponding steering engine dummy pieces by using mounting nail holes of the airplane aileron/horizontal tail steering engine mounting pieces on the airplane body, and finally setting the output end points of the airplane aileron/horizontal tail steering engine dummy pieces at a neutral position; 2) the mounting and fixing of the dummy piece of the corresponding adjusting sheet effect mechanism are carried out by using the mounting nail holes of the mounting piece of the airplane aileron/horizontal tail/rudder adjusting sheet effect mechanism on the airplane body, and finally the output end point of the dummy piece is arranged at a neutral position.
Fourthly, replacing the fixed and connecting rod dummy member of the brake rocker arm
Referring to fig. 4, on the floor of the aircraft cabin at the front end of the left/right foot pedal, the connecting support of the brake rocker arm is removed, the brake rocker arm fixing and connecting rod dummy piece 5 is replaced, and the end of the connecting rod dummy piece is connected with the rocker arm at the lower end of the pedal arm, so as to fixedly support the double-foot-operated brake operation; it was confirmed that the rudder control system could be normally operated both when the left foot was operated forward and when the right foot was operated forward. The requirements for the fixing of the brake rocker arm and the replacement of the connecting rod dummy part 5 are as follows: the aircraft is utilized to connect the mounting nail hole of the support at the front end of the pedal cabin floor for fixing the brake rocker and mounting and fixing the connecting rod dummy, the left/right pedal is supported, the left/right pedal shafts are aligned, and the brake load of the double-foot pedal brake can be borne.
It should be noted that the full-aircraft main control system refers to an aileron control system, a horizontal tail control system and a rudder control system, which are industrial terms; the whole airplane main control system is a general term for the front and rear ailerons/horizontal tail/rudder control system comprising the booster/composite steering engine, and is not a section or a part of the system.
The static fatigue test of the airplane control system is a fatigue test of applying a load spectrum to the fixed control system, and the dynamic fatigue test of the airplane control system is a fatigue test of applying a control load and control displacement dynamic coordination loading spectrum to the control system. The dynamic fatigue test of the main control system of the whole airplane needs to examine and verify the fatigue performance of the structure of the aileron/horizontal tail/rudder control system in the traditional sense and also examines and verifies the static performance index or other related performance indexes of the control system.
The static performance of the aircraft control system is set for providing accurate control force feeling for pilots and ensuring that the aircraft has basic flight control quality, the indexes of the static performance of the aircraft control system relate to a stick force/stick displacement curve, a pedal force/pedal displacement curve, a stick force movable gap, a pedal force movable gap, system and slide valve friction force, system friction force and the like, and measurement and inspection are one of effective methods for measuring and inspecting whether the static performance indexes of the control system meet preset requirements.
Claims (8)
1. A full-machine main control system dynamic fatigue test support method is characterized by comprising the following steps:
carrying out nondestructive flaw detection inspection and measurement inspection on the airplane aileron/horizontal tail/rudder control system on a fatigue testing machine, confirming that the structural state and the static performance of the whole airplane main control system meet preset requirements, and adjusting and confirming that the aileron/horizontal tail/rudder control system is in a neutral state;
aiming at the whole main control system, setting a first dummy piece (1) and a tension compensator dummy piece (2), fixing the first dummy piece and the tension compensator dummy piece at a neutral position, and confirming that the tension compensator dummy piece (2) works and moves normally;
respectively setting a aileron/horizontal tail steering engine dummy piece (3) and an adjustment sheet effect mechanism dummy piece (4), fixing the aileron/horizontal tail steering engine dummy pieces at a neutral position, and confirming that a manual steering rod and pedals can normally operate a whole-engine main control system;
the left/right pedal brake rocker fixing and connecting rod dummy pieces (5) are respectively arranged;
and confirming that the manual steering column and the left pedal and the right pedal can normally operate the main operating system of the whole machine.
2. The method according to claim 1, characterized in that the tension compensator dummy (2) is an internal spring type load simulator for simulating the operating force/displacement characteristics of the aileron/horizontal tail booster and the oil distributing valve of the rudder composite steering engine.
3. The method according to claim 1, characterized in that the tension compensator dummies (2) comprise aileron tension compensator dummies, horizontal tail tension compensator dummies and rudder tension compensator dummies.
4. A method according to claim 3, characterized in that the tension compensator dummy (2) is arranged, in particular comprising:
the left/right aileron booster dummy part, the left/right horizontal tail booster dummy part, the rudder composite steering engine dummy part and the corresponding aileron/horizontal tail/rudder control system are respectively connected;
the positions of the mounting connection points at the two ends of the tension compensator dummy piece (2) are respectively adjusted and fixed to be the same as the neutral positions of the airplane booster and the composite steering engine oil distributing valve operating lever.
5. The method according to claim 1, wherein the aileron/tailplane steering engine dummy (3) and the trim tab effect mechanism dummy (4) are set, and specifically comprise:
the connection of the aileron/horizontal tail steering engine dummy piece (3) is adjusted/fixed according to the neutral position of the airplane aileron/horizontal tail steering engine at the connection of the aileron/horizontal tail steering engine composite rocker arm;
the connection of the adjusting sheet effect mechanism dummy piece (4) is adjusted/fixed according to the neutral position of the airplane aileron/horizontal tail loading mechanism and the rudder hydraulic loading mechanism at the connection part of the rear end rocker arm.
6. The method according to claim 1, wherein the step of providing the left/right pedal brake rocker arm fixing and connecting rod dummy (5) comprises:
the double-foot brake operation is carried out to carry out neutral fixed support and enable the left/right foot pedal shafts to be aligned;
it was confirmed that the two-foot brakes can bear the braking load of the airplane in the case of normal operation of the rudder steering system with the left-foot forward/right-foot forward, respectively.
7. The method of claim 1, wherein the tab effect mechanism dummy (4) comprises a flap tab effect mechanism dummy, a horizontal tail tab effect mechanism dummy, and a rudder tab effect mechanism dummy.
8. The method according to claim 1, characterized in that the first dummy element (1) comprises an aileron booster dummy element, a tailplane booster dummy element and a rudder compound steering engine dummy element.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113942659A (en) * | 2021-09-16 | 2022-01-18 | 中国航空工业集团公司西安飞机设计研究所 | Airplane left and right pedal double-foot brake fatigue test and monitoring method thereof |
| CN113955145A (en) * | 2021-09-16 | 2022-01-21 | 中国航空工业集团公司西安飞机设计研究所 | Fatigue test state monitoring and troubleshooting method for main control system of airplane |
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