CN102680236A - Structural strength test loading device for aircraft wing-mounted engine - Google Patents
Structural strength test loading device for aircraft wing-mounted engine Download PDFInfo
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- CN102680236A CN102680236A CN2012101461557A CN201210146155A CN102680236A CN 102680236 A CN102680236 A CN 102680236A CN 2012101461557 A CN2012101461557 A CN 2012101461557A CN 201210146155 A CN201210146155 A CN 201210146155A CN 102680236 A CN102680236 A CN 102680236A
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Abstract
The invention belongs to an aircraft strength testing technology and relates to a structural strength test loading device for an aircraft wing-mounted engine. The structural strength test loading device comprises side front loading actuating cylinders, side rear loading actuating cylinders, front actuating cylinders and lower actuating cylinders, and is characterized in that the loading device comprises the two side front loading actuating cylinders, the two side rear loading actuating cylinders, the two front actuating cylinders and the lower actuating cylinders. According to the loading device disclosed by the invention, a course load of the engine is applied through a pair of the actuating cylinders which mutually form the angle, so that the loading device can ensure that the course load can be always positioned along the direction of the axial line of the engine under the condition that the deformation of airfoils occurs during testing; a lateral load of the engine can be applied through the pair of the actuating cylinders which mutually form the angle, so that the loading device can ensure that the lateral load can be always positioned in the horizontal direction under the condition that the deformation of the airfoils occurs; and a hanging lateral load of the engine is applied by the pair of the actuating cylinders which mutually form the angle, so that the loading device can ensure that the lateral load can be always positioned in the horizontal direction under the condition that the deformation of the airfoils occurs. The loading device can ensure the loading precision of the loads of the wing-mounted engine under the condition that the deformation of the airfoils occurs so as to enable a testing check result to be more accurate and reliable.
Description
Technical field
The invention belongs to the strength of aircraft experimental technique, relate to a kind of aircraft wing and hang engine structure strength test charger.
Background technology
It is airplane in transportation category design form commonly used that the wing hangs engine, and engine is hung and connected needs through the strength test checking, and wherein accurately applying of engine load is the essential condition of carrying out the intensity checking.At present; The wing hangs engine strength when test, mainly adopts five to apply power and moment on the engine to pressurized strut, and this load applies mode owing to do not consider the displacement that wing is vertical; To cause bigger error; Particularly when the large aircraft ala lateralis being hung the engine loading, cause the distortion of loading, thus the result of appraisal of influence test.
Summary of the invention
The purpose of this invention is to provide a kind of can be under the condition of wing self-deformation, guarantee that the direction aircraft wing consistent with actual conditions that apply of engine load hangs engine structure strength test charger.Technical solution of the present invention is to comprise that the preceding loading of side pressurized strut, rear flank load pressurized strut, preceding pressurized strut, bottom pressurized strut; It is characterized in that charger loads pressurized strut before comprising two sides, two rear flank load pressurized strut, two preceding pressurized struts, bottom pressurized strut; Load pressurized strut before two sides and be positioned at engine one side; Two preceding load(ing) points that load pressurized strut of side are connected the engine centre of gravity place, are used to apply the engine side load, load pressurized struts before two sides and are positioned at same plane; This plane loads pressurized strut and forms 30--90 degree angle perpendicular to engine axis and vertical with surface level before two sides; Two rear flank loading pressurized struts and two the preceding loading of side pressurized struts are positioned at engine the same side; The load(ing) point of two rear flank loading pressurized struts is connected the centre of gravity place that engine is hung; Be used to apply the side load that engine is hung; Two rear flank load pressurized strut and are positioned at same plane, and this plane is perpendicular to engine axis and vertical with surface level, and two rear flank load pressurized strut and form 30--90 degree angle; Two preceding pressurized struts all are positioned at the symmetrical plane of engine, and the load(ing) point of two preceding pressurized struts acts on engine axis, are used to apply the load in engine course, and two preceding pressurized struts become 30--90 degree angle; Two bottom pressurized struts are positioned at the engine plane of symmetry; Two bottom pressurized struts are vertical with surface level; The load(ing) point of one of them bottom pressurized strut is connected engine center of gravity place; Be used to apply the engine vertical load, the load(ing) point of another bottom pressurized strut is connected the center of gravity place that engine is hung, and is used to apply the vertical load that engine is hung.
Said engine side load realizes by adjusting any load that loads pressurized strut that loads in the pressurized strut before two sides.
Said engine is hung side load and is realized by any load that loads pressurized strut that two rear flank of adjustment load in the pressurized strut.
Said engine course load is realized by any load that loads pressurized strut in two preceding pressurized struts of adjustment.
Said engine vertical load is realized that by the load of adjustment bottom pressurized strut engine is hung the load realization of vertical load by adjustment bottom pressurized strut.
Advantage that the present invention has and beneficial effect, the present invention applies engine course load through a pair of pressurized strut of angle each other, and wing produces and guarantees under the distortion situation that course load is all the time along the engine axis direction in test; Apply the engine side load through a pair of pressurized strut of angle each other, guarantee that under wing distortion situation side load is positioned at horizontal direction all the time; Apply engine through a pair of pressurized strut of angle each other and hang side load, guarantee that under wing distortion situation side load is positioned at horizontal direction all the time.This charger can guarantee that wing distortion situation bottom wing hangs the loading accuracy of engine load, and the result of appraisal that make test more accurately and reliably.
Description of drawings
Fig. 1 is a vertical view of the present invention;
Fig. 2 is a front view of the present invention;
Fig. 3 is a side view of the present invention.
Embodiment
Explain further details in the face of the present invention down.Referring to Fig. 1, Fig. 2 and Fig. 3, the aircraft wing hangs engine structure strength test charger, comprises preceding pressurized strut 1, the 1' of loading of side; The rear flank loads pressurized strut 2,2', preceding pressurized strut 3,3', and bottom pressurized strut 5,6 is characterized in that; Charger comprises that loading pressurized strut 1,1', two rear flank before two sides loads the preceding pressurized strut of pressurized strut 2,2', two 3,3', loads pressurized strut 1 before 5,6, two sides of bottom pressurized strut, 1' is positioned at engine one side; Two preceding load(ing) points that load pressurized strut 1,1' of side are connected the engine centre of gravity place; Be used to apply the engine side load, loading pressurized strut 1,1' are positioned at same plane before two sides, and this plane is perpendicular to engine axis and vertical with surface level; Load pressurized strut 1,1' formation 30 degree angles before two sides; Along with the increase of pressurized strut angle, under size was made a concerted effort in same requirement, the load that each pressurized strut need apply increased; Therefore the pressurized strut angle should not surpass 90 degree, and the angle in this scope can satisfy the variation of load under the wing distortion; Two rear flank load pressurized strut 2,2' and two the preceding loading of sides pressurized struts 1,1' and are positioned at engine the same side; The load(ing) point that two rear flank load pressurized strut 2,2' is connected the centre of gravity place that engine is hung; Be used to apply the side load that engine is hung, two rear flank load pressurized strut [2,2'] and are positioned at same plane, and this plane is perpendicular to engine axis and vertical with surface level; Two rear flank load pressurized strut 2,2' formation 30 degree angles; Along with the increase of pressurized strut angle, under size was made a concerted effort in same requirement, the load that each pressurized strut need apply increased; Therefore the pressurized strut angle should not surpass 90 degree, and the angle in this scope can satisfy the variation of load under the wing distortion; Two preceding pressurized struts 3,3' all are positioned at the symmetrical plane of engine, and the load(ing) point of two preceding pressurized struts 3,3' acts on engine axis, is used to apply the load in engine course; Two preceding pressurized struts 3,3' become 30 degree angles; Along with the increase of pressurized strut angle, under size was made a concerted effort in same requirement, the load that each pressurized strut need apply increased; Therefore the pressurized strut angle should not surpass 90 degree, and the angle in this scope can satisfy the variation of load under the wing distortion; Two bottom pressurized struts 5,6 are positioned at the engine plane of symmetry; Two bottom pressurized struts 5,6 are vertical with surface level; The load(ing) point of one of them bottom pressurized strut 5 is connected engine center of gravity place; Be used to apply the engine vertical load, the load(ing) point of another bottom pressurized strut 6 is connected the center of gravity place that engine is hung, and is used to apply the vertical load that engine is hung.Said engine side load realizes by adjusting any load that loads pressurized strut that loads in the pressurized strut before two sides.Said engine is hung side load and is realized by any load that loads pressurized strut that two rear flank of adjustment load in the pressurized strut.Said engine course load is realized by any load that loads pressurized strut in two preceding pressurized struts of adjustment.Said engine vertical load is realized that by the load of adjustment bottom pressurized strut engine is hung the load realization of vertical load by adjustment bottom pressurized strut.
Principle of work of the present invention is: the size of at first hanging all directions load under each operating condition of test according to engine and engine; Calculate the load of pressurized strut under each operating condition of test; Make in the test that all directions gross load is consistent with the size and Orientation that requires gross load under each operating condition of test; Again according to the deflection under each operating condition of test of wing; Calculate in the same plane each respectively to loading load adjustment amount that loads pressurized strut in the pressurized strut, make that the gross load in each plane is consistent with the gross load size and Orientation of requirement under each operating condition of test, in each operating condition of test practical implementation, adjust pressurized strut load with the load adjustment amount; Thereby realize the accurate simulation of each operating condition of test load under the wing distortion situation, guarantee test examination precision.
In the embodiments of the invention, finished parts is all adopted in each pressurized strut.
Claims (5)
1. the aircraft wing hangs engine structure strength test charger; Load pressurized strut [1], rear flank loading pressurized strut [2], preceding pressurized strut [3] before comprising side, bottom pressurized strut [5,6] is characterized in that; Charger comprises that loading pressurized strut [1,1'], two rear flank before two sides loads pressurized strut [2,2'], two preceding pressurized struts [3,3']; Load pressurized strut [1,1'] before the bottom pressurized strut [5,6], two sides and be positioned at engine one side, the load(ing) point that loads pressurized strut [1,1'] before two sides is connected the engine centre of gravity place; Be used to apply the engine side load; Load pressurized strut [1,1'] before two sides and be positioned at same plane, this plane is perpendicular to engine axis and vertical with surface level, loads pressurized strut [1,1'] before two sides and forms 30--90 degree angle; Two rear flank load and load pressurized strut [1,1'] before pressurized strut [2,2'] and two sides and be positioned at engine the same side; The load(ing) point that two rear flank load pressurized strut [2,2'] is connected the centre of gravity place that engine is hung; Be used to apply the side load that engine is hung; Two rear flank load pressurized strut [2,2'] and are positioned at same plane, and this plane is perpendicular to engine axis and vertical with surface level, and two rear flank load pressurized strut [2,2'] and form 30--90 degree angle; Two preceding pressurized struts [3,3'] all are positioned at the symmetrical plane of engine, and the load(ing) point of two preceding pressurized struts [3,3'] acts on engine axis, is used to apply the load in engine course, and two preceding pressurized struts [3,3'] become 30--90 degree angle; Two bottom pressurized struts [5,6] are positioned at the engine plane of symmetry; Two bottom pressurized struts [5,6] are vertical with surface level; The load(ing) point of one of them bottom pressurized strut [5] is connected engine center of gravity place; Be used to apply the engine vertical load, the load(ing) point of another bottom pressurized strut [6] is connected the center of gravity place that engine is hung, and is used to apply the vertical load that engine is hung.
2. the aircraft wing according to claim 1 hangs engine structure strength test charger, it is characterized in that, any load that loads pressurized strut that said engine side load loads before by two sides of adjustment in the pressurized strut [1,1'] realizes.
3. the aircraft wing according to claim 1 hangs engine structure strength test charger, it is characterized in that, said engine is hung side load and realized by any load that loads pressurized strut that two rear flank of adjustment load in the pressurized struts [2,2'].
4. the aircraft wing according to claim 1 hangs engine structure strength test charger, it is characterized in that, said engine course load is realized by any load that loads pressurized strut in two preceding pressurized struts of adjustment [3,3'].
5. the aircraft wing according to claim 1 hangs engine structure strength test charger; It is characterized in that; Said engine vertical load is realized that by the load of adjustment bottom pressurized strut [5] engine is hung the load realization of vertical load by adjustment bottom pressurized strut [6].
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| Application Number | Priority Date | Filing Date | Title |
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| CN201210146155.7A CN102680236B (en) | 2012-05-11 | 2012-05-11 | Structural strength test loading device for aircraft wing-mounted engine |
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| CN201210146155.7A CN102680236B (en) | 2012-05-11 | 2012-05-11 | Structural strength test loading device for aircraft wing-mounted engine |
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| CN102680236A true CN102680236A (en) | 2012-09-19 |
| CN102680236B CN102680236B (en) | 2014-10-22 |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103630347A (en) * | 2013-11-26 | 2014-03-12 | 成都发动机（集团）有限公司 | Motor substitution equipment for static force test of airplane wing |
| CN104139866A (en) * | 2013-05-10 | 2014-11-12 | 中国飞机强度研究所 | Follow-up vertical loading device |
| CN104139870A (en) * | 2013-05-10 | 2014-11-12 | 中国飞机强度研究所 | Mounting unit of loading device |
| CN105716842A (en) * | 2014-12-05 | 2016-06-29 | 中国飞机强度研究所 | Double-beam type long straight wing load processing method |
| CN105716835A (en) * | 2014-12-03 | 2016-06-29 | 中国飞机强度研究所 | Chuck-type wing loading device |
| CN108528758A (en) * | 2018-05-04 | 2018-09-14 | 中电科芜湖钻石飞机制造有限公司 | General-purpose aircraft mechanical property testing system |
| CN109018428A (en) * | 2018-05-07 | 2018-12-18 | 上海交通大学 | A kind of engine installation structure load-carrying properties test device |
| CN110282154A (en) * | 2019-06-11 | 2019-09-27 | 中国飞机强度研究所 | A kind of engine installation system test of static strength bogusware |
| CN112729798A (en) * | 2020-12-28 | 2021-04-30 | 国机集团北京飞机强度研究所有限公司 | Load calibration method for engine suspension joint |
| CN113008561A (en) * | 2021-03-01 | 2021-06-22 | 国机集团北京飞机强度研究所有限公司 | Loading device for load calibration test of engine suspension mounting joint |
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Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104139866A (en) * | 2013-05-10 | 2014-11-12 | 中国飞机强度研究所 | Follow-up vertical loading device |
| CN104139870A (en) * | 2013-05-10 | 2014-11-12 | 中国飞机强度研究所 | Mounting unit of loading device |
| CN103630347A (en) * | 2013-11-26 | 2014-03-12 | 成都发动机（集团）有限公司 | Motor substitution equipment for static force test of airplane wing |
| CN103630347B (en) * | 2013-11-26 | 2016-05-18 | 成都发动机（集团）有限公司 | Aircraft wing slow test engine alternate device |
| CN105716835B (en) * | 2014-12-03 | 2018-04-10 | 中国飞机强度研究所 | A kind of chuck type wing loading device |
| CN105716835A (en) * | 2014-12-03 | 2016-06-29 | 中国飞机强度研究所 | Chuck-type wing loading device |
| CN105716842A (en) * | 2014-12-05 | 2016-06-29 | 中国飞机强度研究所 | Double-beam type long straight wing load processing method |
| CN108528758A (en) * | 2018-05-04 | 2018-09-14 | 中电科芜湖钻石飞机制造有限公司 | General-purpose aircraft mechanical property testing system |
| CN108528758B (en) * | 2018-05-04 | 2023-08-15 | 中电科芜湖钻石飞机制造有限公司 | Universal aircraft mechanical property test system |
| CN109018428A (en) * | 2018-05-07 | 2018-12-18 | 上海交通大学 | A kind of engine installation structure load-carrying properties test device |
| CN110282154A (en) * | 2019-06-11 | 2019-09-27 | 中国飞机强度研究所 | A kind of engine installation system test of static strength bogusware |
| CN112729798A (en) * | 2020-12-28 | 2021-04-30 | 国机集团北京飞机强度研究所有限公司 | Load calibration method for engine suspension joint |
| CN112729798B (en) * | 2020-12-28 | 2022-07-29 | 国机集团北京飞机强度研究所有限公司 | Load calibration method for engine suspension joint |
| CN113008561A (en) * | 2021-03-01 | 2021-06-22 | 国机集团北京飞机强度研究所有限公司 | Loading device for load calibration test of engine suspension mounting joint |
| CN113008561B (en) * | 2021-03-01 | 2022-07-29 | 国机集团北京飞机强度研究所有限公司 | Loading device for load calibration test of engine hanging installation joint |
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| CN102680236B (en) | 2014-10-22 |
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