CN105716838A - Single-point double force control actuator cylinder servo loading method - Google Patents
Single-point double force control actuator cylinder servo loading method Download PDFInfo
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- CN105716838A CN105716838A CN201410728078.5A CN201410728078A CN105716838A CN 105716838 A CN105716838 A CN 105716838A CN 201410728078 A CN201410728078 A CN 201410728078A CN 105716838 A CN105716838 A CN 105716838A
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Abstract
The invention provides a single-point double force control actuator cylinder servo loading method, which is characterized by comprising the steps of according to theoretical trajectory of a movable wing surface, dispersing the theoretical trajectory into a plurality of positioning points, which are respectively represented by i=0,1, ...,n, determining a loading plane by a starting angle loading force line and an ending angle loading force line of the movable wing surface, and selecting two positions randomly in the loading plane for fixing two force control actuator cylinders which are connected to tail ends of a lever system of the movable wing surface simultaneously through connecting members; and according to the dispersed points, the loading lever length and the connecting member length, determining a double force composition point coordinate and a force line direction of a vertical chord plane, and further obtaining included angles <alpha>i and <beta>i between the two force control actuator cylinders and the force line direction through a trigonometric function.
Description
Technical field
The present invention relates to a kind of test loading technique, be especially applicable to complete aircraft movable wing and handle inspection static(al), fatigue test.
Background technology
In the past movable wing was in and carried out under no load state when complete aircraft movable wing handles checkout facility, this kind of loading method have ignored the deformation of movable wing body, continuous scapegoat along with the development of experimental technique and flying quality, the requirement of test is also improved day by day, for more real simulation game aerofoil loading conditions in manipulation process, propose in test movable wing and handle the requirement in checkout facility, movable wing loaded, now handle the loading direction of movable wing in checking process at movable wing and be perpendicular to movable wing string plane all the time, magnitude of load and loading direction need to coordinate to load.
Following loading problem is handled in checkout facility in slow test and movable wing also once to be occurred, all undertaken individually fixing on ground for movable wing in the past, its solution is all that the mode synthesized by multiple load vectors is realized, this method due to testpieces support height, testpieces constraints requirement higher, being only used for movable wing and situation that body construction is individually supported, the movable wing not being suitable for complete aircraft slow test handles checkout facility.
Summary of the invention
It is an object of the invention to utilize this loading method, it is possible to complete the static(al) of movable wing following loading of complete aircraft, fatigue test；Single or multiple movable wing can be completed and handle checkout facility.
The invention provides a kind of single-point dual force control pressurized strut following loading method, it is characterised in that comprise the following steps:
Theory movement track according to movable wing is discrete for several location points by it, it is expressed as i=0,1, ..., n, being loaded the line of force by movable wing start angle and termination point loads the line of force and determines the loaded planar of test, arbitrarily select two positions to fix two power control pressurized struts in this loaded planar, two power control pressurized struts are simultaneously connected to the lever system end of movable wing by connector；
According to discrete point position, load lever length and connector length and determine two power synthetic point coordinates and the line of force direction of vertical string plane step by step, can be obtained by trigonometric function relation two power control pressurized struts with line of force direction angle α furtheriAnd βi,
P1i、P2iIt is the load value of two power control pressurized struts, PiFor the load value of string plane vertical on each location point, ignore the weight loading lever, load must be fulfilled for following relation for meeting vertical string plane:
P1icos(αi)+P2icos(βi)=Pi(1)
P1isin(αi)-P2isin(βi)=0 (2)
Above-mentioned equation is solved and can obtain:
P1i=Pisin(βi)/sin(αi+βi)(3)
P2i=Pisin(αi)/sin(αi+βi)(4)
The load value of two power control pressurized struts can calculate according to above-mentioned formula (3) and (4) and obtain；
The control system load value P according to two power control pressurized struts corresponding to each location point1i、P2iTest.
The core content of the invention is to adopt " dual force " equivalence decomposition, composition principle, loads pressurized struts by two power controls, it is achieved decompose the applying of vertical string plane load, to reach the requirement of movable wing manipulation checkout facility.Concrete principle is for each and every one location points some by discrete for motion of rudder track, according to movable wing theory movement track, determine pressurized strut installation site and mode, calculate the loading direction of each location point and the angle of power control pressurized strut axis, according to trigonometric function relation by the load-transfer mechanism of each location point to two power control pressurized strut, by ensureing the vertical string plane of loading direction while coordinating to load guarantee magnitude of load in process of the test.
The test loading method of the present invention is in that movable wing is loaded by classification, achieve movable wing and be perpendicular to movable wing string plane at the loading direction of each location point, the coordination of magnitude of load and loading direction loads, simulate the loading conditions of movable wing and suspension thereof in flight course more realistically, more precisely demonstrate movable wing and handling systematic function.
The present invention simulates the loading conditions of movable wing in flight course more really, in ground validation is tested, inspection movable wing handles whether system can produce clamping stagnation or interference in motor process effectively, solving conventional complete aircraft movable wing and handle the problem that movable wing in checkout facility process is not loaded with carrying out handling inspection, its good effect is in that to handle the static(al) of inspection for same type movable wing, fatigue test opens the approach that simulation more really, a checking are tested.
Accompanying drawing explanation
Fig. 1 is the loading principle schematic diagram of the present invention；
The single-point dual force control pressurized strut X-Y scheme of Fig. 2 present invention.
Detailed description of the invention
The detailed description of the invention of a kind of single-point dual force control pressurized strut following loading method is:
Theory movement track according to movable wing is discrete for 3-6 location point by it, it is expressed as i=0,1, ... 6, the loaded planar of test is determined by the initial load angle line of force and the termination point line of force, selecting two positions to fix two power control pressurized struts in this loaded planar, two power control pressurized struts are simultaneously connected to the sensor of the lever system end of movable wing by connector, and this point is designated as A；
According to discrete point position, load lever length and connector length and determine two power synthetic point A coordinates and the line of force direction of vertical string plane step by step, can be obtained by trigonometric function relation two power control pressurized struts with line of force direction angle α furtheriAnd βi,
The load value P of two power control pressurized struts1i、P2i, PiFor the load value of string plane vertical on each location point, ignore the weight loading lever, load must be fulfilled for following relation for meeting vertical string plane:
P1icos(αi)+P2icos(βi)=Pi(5)
P1isin(αi)-P2isin(βi)=0 (6)
Above-mentioned equation is solved and can obtain:
P1i=Pisin(βi)/sin(αi+βi)(7)
P2i=Pisin(αi)/sin(αi+βi)(8)
The load value of two power control pressurized struts can calculate according to above-mentioned formula (3) and (4) and obtain.
Concrete process of the test exists two kinds of loading modes:
Accompanying drawings 1 and Fig. 2, pattern 1 is power control pressurized strut 1 and force transducer 1 forms closed-loop control system, power control pressurized strut 2 and force transducer 2 form closed-loop control system, apply the load value P at different levels of power control pressurized strut 1 and power control pressurized strut 2 step by step when movable wing moves to various discrete point1iAnd P2i, the value of feedback of force transducer 3 real time record Resultant force, and with the theory load value P of force transducer 3iContrasting, whether checking test loading prepares；
Pattern 2 is power control pressurized strut 1 and force transducer 3 forms closed-loop control system, power control pressurized strut 2 and force transducer 2 form closed-loop control system, the load value of loading force control pressurized strut 1 and power control pressurized strut 2 when movable wing moves to various discrete point, the load bid value of now power control pressurized strut 1 be each location point make a concerted effort be worth Pi, the load of power control pressurized strut 2 is P2i, its actual feedback of force transducer 1 real time record, and with the theory load value P of force transducer 11iContrasting, whether check test loading prepares.
By verifying it have been experienced that, these two kinds of loading modes all can well apply the load being perpendicular to string plane at different levels, but the value of making a concerted effort of pattern 2 apply more accurate.
Claims (1)
1. a single-point dual force control pressurized strut following loading method, it is characterised in that comprise the following steps:
Theory movement track according to movable wing is discrete for several location points by it, it is expressed as i=0,1, ..., n, being loaded the line of force by movable wing start angle and termination point loads the line of force and determines the loaded planar of test, arbitrarily select two positions to fix two power control pressurized struts in this loaded planar, two power control pressurized struts are simultaneously connected to the lever system end of movable wing by connector；
According to discrete point position, load lever length and connector length and determine two power synthetic point coordinates and the line of force direction of vertical string plane step by step, can be obtained by trigonometric function relation two power control pressurized struts with line of force direction angle α furtheriAnd βi,
P1i、P2iIt is the load value of two power control pressurized struts, PiFor the load value of string plane vertical on each location point, ignore the weight loading lever, load must be fulfilled for following relation for meeting vertical string plane:
P1icos(αi)+P2icos(βi)=Pi(1)
P1isin(αi)-P2isin(βi)=0 (2)
Above-mentioned equation is solved and can obtain:
P1i=Pisin(βi)/sin(αi+βi)(3)
P2i=Pisin(αi)/sin(αi+βi)(4)
The load value of two power control pressurized struts can calculate according to above-mentioned formula (3) and (4) and obtain；
The control system load value P according to two power control pressurized struts corresponding to each location point1i、P2iTest.
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| CN201410728078.5A CN105716838A (en) | 2014-12-03 | 2014-12-03 | Single-point double force control actuator cylinder servo loading method |
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| CN201410728078.5A CN105716838A (en) | 2014-12-03 | 2014-12-03 | Single-point double force control actuator cylinder servo loading method |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107748102A (en) * | 2017-11-29 | 2018-03-02 | 中国航空工业集团公司济南特种结构研究所 | It is a kind of to apply the balanced method for drawing load to radome |
| CN108170152A (en) * | 2017-12-04 | 2018-06-15 | 中国飞机强度研究所 | A kind of vector constrains point tolerance Active Control Method |
| CN111003208A (en) * | 2019-12-06 | 2020-04-14 | 江西洪都航空工业集团有限责任公司 | Nonlinear force loading test device for airplane speed reduction plate |
| CN111232243A (en) * | 2020-03-17 | 2020-06-05 | 中国飞机强度研究所 | Load loading device |
| CN111409855A (en) * | 2020-04-13 | 2020-07-14 | 中国飞机强度研究所 | Fuselage lateral and heading load combined applying device and load applying method |
| CN113624437A (en) * | 2021-07-16 | 2021-11-09 | 中国人民解放军总参谋部第六十研究所 | Loading system and method for reliability test of wing and aileron mechanism of unmanned aerial vehicle |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107748102A (en) * | 2017-11-29 | 2018-03-02 | 中国航空工业集团公司济南特种结构研究所 | It is a kind of to apply the balanced method for drawing load to radome |
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| CN108170152B (en) * | 2017-12-04 | 2020-12-29 | 中国飞机强度研究所 | Active control method for aircraft course restraining point error |
| CN111003208A (en) * | 2019-12-06 | 2020-04-14 | 江西洪都航空工业集团有限责任公司 | Nonlinear force loading test device for airplane speed reduction plate |
| CN111232243A (en) * | 2020-03-17 | 2020-06-05 | 中国飞机强度研究所 | Load loading device |
| CN111232243B (en) * | 2020-03-17 | 2021-09-03 | 中国飞机强度研究所 | Load loading device |
| CN111409855A (en) * | 2020-04-13 | 2020-07-14 | 中国飞机强度研究所 | Fuselage lateral and heading load combined applying device and load applying method |
| CN113624437A (en) * | 2021-07-16 | 2021-11-09 | 中国人民解放军总参谋部第六十研究所 | Loading system and method for reliability test of wing and aileron mechanism of unmanned aerial vehicle |
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