CN102991726A - Loading system and method for airplane structure test - Google Patents
Loading system and method for airplane structure test Download PDFInfo
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- CN102991726A CN102991726A CN2012105287776A CN201210528777A CN102991726A CN 102991726 A CN102991726 A CN 102991726A CN 2012105287776 A CN2012105287776 A CN 2012105287776A CN 201210528777 A CN201210528777 A CN 201210528777A CN 102991726 A CN102991726 A CN 102991726A
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Abstract
The invention belongs to an airplane testing technology and relates to a loading system and method for an airplane structure test. The loading system for the airplane structure test comprises a loading force-bearing system, a loading cross beam, a guide fixed pulley, a movable pulley set, a loading connecting member, a first force sensor, a second force sensor and a loading actuating cylinder, wherein the loading cross beam is arranged on the loading force-bearing system, the guide fixed pulley is fixed on the loading cross beam, the movable pulley set is arranged on the top end of the loading actuating cylinder, the loading actuating cylinder is fixed on a force-carrying terrace, and the loading connecting member surrounds the movable pulley set and the guide fixed pulley. According to the invention, a large-deformation part of a structure in an airplane structure static and fatigue test is loaded; by using a method for increasing a load by the actuating cylinder by the small-travel actuating cylinder, the retracting travel of a loading device is reduced; and under the condition of large deformation of the structure, the accuracy of deflection angle loading is ensured.
Description
Technical field
The invention belongs to the aircraft testing technology, relate to a kind of loading system for aircraft structure test and method.
Background technology
When aircaft configuration static(al) in the past, fatigue test loading, the structure maximum distortion reaches 1m～1.5m usually, and therefore loading the pressurized strut stroke is 1.5m to the maximum; If structural distortion during greater than 1.5m, then adopts the mode of 2 pressurized struts of series connection to load.
Along with the improvement of aeroplane structure design theory and the raising of material property, structural flexibility increases, and high aspect ratio, long straight wing carry out problem that deflection angle load thereby brought in the test owing to being out of shape the pressurized strut of presetting that causes so that the structure maximum distortion has often surpassed the loading stroke of existing installation in the large aircraft.Not only installation workload is large for the test loading method of continuation employing series connection pressurized strut, has also increased the difficulty of controlling test; And design, use large stroke pressurized strut, and not only make to load the increase of load supporting system height, experimentation cost is improved greatly.
Summary of the invention
The objective of the invention is: provide a kind of in aircraft structure test, adopt the loading at existing little stroke pressurized strut implementation structure large deformation position, and the high loading system of loading accuracy.
In addition, the present invention also provides a kind of loading method for aircraft structure test.
Technical scheme of the present invention is:
A kind of loading system for aircraft structure test, it comprises the loading load supporting system, load crossbeam, the guiding fixed pulley, the movable pulley external member, load attaching parts, the first power sensor, the second power sensor, load pressurized strut, loading the crossbeam built is loading on the load supporting system, the guiding fixed pulley is fixed on and loads on the crossbeam, the movable pulley external member is installed in and loads the pressurized strut top, loading pressurized strut is fixed on the load terrace, and load attaching parts around movable pulley external member and guiding fixed pulley, one end links to each other with the loading crossbeam, the other end connects the first power sensor, and link to each other with lever system is terminal, the second power sensor setting is on the loading attaching parts between pressurized strut and the movable pulley external member.
The heavy frame of described loading load supporting system for being formed by the beam and column overlap joint is fixed on the load terrace.
Described loading attaching parts is the cable wire that non-rotating cable consists of.
Loading pressurized strut is arranged on the load terrace by the pressurized strut permanent seat.
A kind of loading method for aircraft structure test, its outside oil sources provides fluid for loading pressurized strut, produces the folding and unfolding action so that load pressurized strut, causes the transmission that loads attaching parts load; The movable pulley external member is so that load pressurized strut folding and unfolding stroke and load the attaching parts stroke alteration, and implementation structure produces moderate finite deformation and the loading of the less stroke of pressurized strut folding and unfolding; And the direction that guarantees loading attaching parts load by the guiding fixed pulley is consistent with the theoretical loading direction of test structure.
The movable pulley external member is so that the move distance of loading attaching parts one end is 2 times of retractable actuating cylinder move distance.
Technique effect of the present invention is: the present invention is applied in the cautiously point loading of aircraft funicular machine.When structure large deformation position in the past loaded, the series connection pressurized strut can cause that when stroke is changed the test load error changes suddenly, and the test protection is stopped, and can not occur the conversion of pressurized strut stroke in this method, thereby had guaranteed carrying out smoothly of test.Not only solved the loading of adopting existing little stroke pressurized strut implementation structure large deformation position, also so that in deflection angle loads since loading direction accurately and so that loading accuracy has had large increase.In deflection angle loaded, because (loading pressurized strut and the attaching parts) meeting of loading facilities weight has deviation so that loading direction calculates with theory, loaded load was less, and deviation is larger.The weight that affects loading direction in this method only has the loading attaching parts, select lightweight cable wire so that loading facilities weight the impact of deflection angle is reduced greatly.
Description of drawings
Fig. 1 is the structural representation that the present invention is used for the loading system of aircraft structure test,
Wherein, 1, guiding fixed pulley 2, load crossbeam 3, load attaching parts 4, the first power sensor 5, the second power sensor 6, ground fixed equipment 7, load pressurized strut 8, movable pulley external member 9, load load supporting system.
The specific embodiment
Many the present invention are described further below in conjunction with accompanying drawing:
See also Fig. 1, it is the structural representation that the present invention is used for the loading system of aircraft structure test.Described loading system for aircraft structure test comprises the loading load supporting system, load crossbeam, the guiding fixed pulley, the movable pulley external member, load attaching parts, the first power sensor, the second power sensor, load pressurized strut and ground fixed equipment, loading the crossbeam built is loading on the load supporting system, the guiding fixed pulley is fixed on and loads on the crossbeam, the movable pulley external member is installed in and loads the pressurized strut top, loading pressurized strut is fixed on the load terrace, and load attaching parts around movable pulley external member and guiding fixed pulley, one end links to each other with the loading crossbeam, the other end connects the first power sensor, and link to each other with lever system is terminal, the second power sensor setting is on the loading attaching parts between pressurized strut and the movable pulley external member.
Wherein, each parts concrete structure and function are as follows:
Load load supporting system: be fixed on the test carrying terrace by beam, post, bear the antagonistic force of loading when test loads.
Load crossbeam: built is used for the restraint test loading facilities loading on the load supporting system, can dismantle and move.
Guiding fixed pulley: be assembled on the loading crossbeam, be used for changing the test loading direction.
Movable pulley external member: be connected with loading pressurized strut, loading attaching parts, realize increasing pressurized strut load, reducing its folding and unfolding stroke.
Sensor: comprise control sensor and monitoring sensor, the control sensor has guaranteed the accuracy of test loaded load size; Monitoring sensor is used for the supervision of pressurized strut load-carrying capacity, and according to the feedback comparing calculation of its feedback with the control sensor, the accuracy that certification testing loads.
Load attaching parts: be used for connecting the connection that loads pressurized strut and test structure loading lever system, make pressurized strut load be delivered to test and load the position.
Load pressurized strut: provide load applying by oil hydraulic system.
Pressurized strut base: pressurized strut is fixed on the load terrace.
Principle and the process of loading method are described
As shown in the figure, the core of this method is the accuracy that loads and guarantee the deflection angle loading by the enforcement at pulley block system implementation structure large deformation position.
By the folding and unfolding campaign of a cover pulley block system and a controlled hydraulic pressurized strut, realize increasing the pressurized strut loaded load, reduce loading facilities folding and unfolding stroke; Warranty test loads accuracy under structure large deformation condition.In theory, this loading technique that loads by the assembly pulley guiding can realize that the test of Arbitrary Loads size, any deflection angle and loading stroke loads.
When test loaded, outside oil sources provided fluid for loading pressurized strut, produced the folding and unfolding action so that load pressurized strut, thereby caused the transmission that loads attaching parts load.The movable pulley external member is so that loading pressurized strut folding and unfolding stroke and the stroke alteration of loading attaching parts have been realized the structure generation moderate finite deformation and the loading of the less stroke of pressurized strut folding and unfolding.Fixed pulley has guaranteed that the direction of loading attaching parts load is consistent with the theoretical loading direction of test structure, thereby reach the purpose that deflection angle accurately loads, and not only so that the test loading is easy for installation simple, also effectively utilized existing loading facilities, saved cost.
Claims (6)
1. loading system that is used for aircraft structure test, it is characterized in that, comprise the loading load supporting system, load crossbeam, the guiding fixed pulley, the movable pulley external member, load attaching parts, the first power sensor, the second power sensor, load pressurized strut, loading the crossbeam built is loading on the load supporting system, the guiding fixed pulley is fixed on and loads on the crossbeam, the movable pulley external member is installed in and loads the pressurized strut top, loading pressurized strut is fixed on the load terrace, and load attaching parts around movable pulley external member and guiding fixed pulley, one end links to each other with the loading crossbeam, the other end connects the first power sensor, and link to each other with lever system is terminal, the second power sensor setting is on the loading attaching parts between pressurized strut and the movable pulley external member.
2. the loading system for aircraft structure test according to claim 1 is characterized in that, the heavy frame of described loading load supporting system for being formed by the beam and column overlap joint is fixed on the load terrace.
3. the loading system for aircraft structure test according to claim 2 is characterized in that, described loading attaching parts is the cable wire that non-rotating cable consists of.
4. the loading system for aircraft structure test according to claim 2 is characterized in that, loads pressurized strut and is arranged on the load terrace by the pressurized strut permanent seat.
5. a loading method that is used for aircraft structure test is characterized in that, outside oil sources provides fluid for loading pressurized strut, produces the folding and unfolding action so that load pressurized strut, causes the transmission that loads attaching parts load; The movable pulley external member is so that load pressurized strut folding and unfolding stroke and load the attaching parts stroke alteration, and implementation structure produces moderate finite deformation and the loading of the less stroke of pressurized strut folding and unfolding; And the direction that guarantees loading attaching parts load by the guiding fixed pulley is consistent with the theoretical loading direction of test structure.
6. the loading method for aircraft structure test according to claim 5 is characterized in that, the movable pulley external member is so that the move distance of loading attaching parts one end is 2 times of retractable actuating cylinder move distance.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012105287776A CN102991726A (en) | 2012-12-10 | 2012-12-10 | Loading system and method for airplane structure test |
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| Application Number | Priority Date | Filing Date | Title |
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| CN2012105287776A CN102991726A (en) | 2012-12-10 | 2012-12-10 | Loading system and method for airplane structure test |
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| CN102991726A true CN102991726A (en) | 2013-03-27 |
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| CN2012105287776A Pending CN102991726A (en) | 2012-12-10 | 2012-12-10 | Loading system and method for airplane structure test |
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Cited By (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103776706A (en) * | 2013-09-30 | 2014-05-07 | 中国人民解放军国防科学技术大学 | Rudder plane loading device for composite material |
| CN103926068A (en) * | 2014-04-23 | 2014-07-16 | 青岛海测检测技术有限公司 | Torsion device used for large horizontal tail shaft torsion fatigue test |
| CN103994878A (en) * | 2014-04-17 | 2014-08-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Integration test verification method of airplane movable wing surface |
| CN104002988A (en) * | 2014-04-17 | 2014-08-27 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for implementing aircraft arresting static test |
| CN104048874A (en) * | 2014-06-24 | 2014-09-17 | 西北工业大学 | Load follow-up loading system for plane flap reliability test |
| CN104386265A (en) * | 2014-12-15 | 2015-03-04 | 中国飞机强度研究所 | Actuator cylinder twisting prevention device |
| CN104865123A (en) * | 2015-06-18 | 2015-08-26 | 沈阳飞机工业（集团）有限公司 | Strength and rigidity testing fixture for aircraft draw bar and use method of strength and rigidity testing fixture |
| CN105416609A (en) * | 2015-12-08 | 2016-03-23 | 中国飞机强度研究所 | Multi-field coupling testing system and method |
| CN105571841A (en) * | 2015-12-13 | 2016-05-11 | 中国飞机强度研究所 | Wallboard structure overload test equipment |
| CN106501083A (en) * | 2016-12-12 | 2017-03-15 | 兰州理工大学 | Large scale structure multiple spot ground anchor type drag-line charger and test method |
| CN107499534A (en) * | 2017-07-28 | 2017-12-22 | 中国航空工业集团公司西安飞机设计研究所 | A kind of processing method of aircraft floor lateral load |
| CN107655650A (en) * | 2017-09-27 | 2018-02-02 | 上海交通大学 | Lever load system collision checking method for structural test |
| CN110514428A (en) * | 2019-09-24 | 2019-11-29 | 中国人民解放军空军工程大学 | A kind of bilateral loading platform for aviation connection structure testpieces |
| CN111232243A (en) * | 2020-03-17 | 2020-06-05 | 中国飞机强度研究所 | Load loading device |
| CN111301712A (en) * | 2020-04-06 | 2020-06-19 | 中国飞机强度研究所 | Multipoint coordination follow-up loading device and method for large-deformation wing |
| CN111572813A (en) * | 2020-05-26 | 2020-08-25 | 中国飞机强度研究所 | Airplane upward loading device |
| CN114441316A (en) * | 2020-10-30 | 2022-05-06 | 大连理工大学 | Air spring tension loading device and application thereof |
| CN114778050A (en) * | 2022-06-27 | 2022-07-22 | 中国飞机强度研究所 | Fatigue load flexible applying system for testing aircraft vibration superposition fatigue strength |
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| CN101788397A (en) * | 2010-02-26 | 2010-07-28 | 中国航空工业集团公司西安飞机设计研究所 | Method for supporting static test for light-aircraft fore fuselages |
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Cited By (26)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103776706B (en) * | 2013-09-30 | 2016-04-27 | 中国人民解放军国防科学技术大学 | A kind of compound substance rudder face load charger |
| CN103776706A (en) * | 2013-09-30 | 2014-05-07 | 中国人民解放军国防科学技术大学 | Rudder plane loading device for composite material |
| CN103994878A (en) * | 2014-04-17 | 2014-08-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Integration test verification method of airplane movable wing surface |
| CN104002988A (en) * | 2014-04-17 | 2014-08-27 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for implementing aircraft arresting static test |
| CN103926068A (en) * | 2014-04-23 | 2014-07-16 | 青岛海测检测技术有限公司 | Torsion device used for large horizontal tail shaft torsion fatigue test |
| CN103926068B (en) * | 2014-04-23 | 2016-10-12 | 青岛苏试海测检测技术有限公司 | A kind of torsion device for stabilizer torque tube testing torsional fatigue |
| CN104048874A (en) * | 2014-06-24 | 2014-09-17 | 西北工业大学 | Load follow-up loading system for plane flap reliability test |
| CN104386265A (en) * | 2014-12-15 | 2015-03-04 | 中国飞机强度研究所 | Actuator cylinder twisting prevention device |
| CN104865123A (en) * | 2015-06-18 | 2015-08-26 | 沈阳飞机工业（集团）有限公司 | Strength and rigidity testing fixture for aircraft draw bar and use method of strength and rigidity testing fixture |
| CN104865123B (en) * | 2015-06-18 | 2018-03-20 | 沈阳飞机工业（集团）有限公司 | Plane draw bar intensity, stiffness test fixture and its application method |
| CN105416609A (en) * | 2015-12-08 | 2016-03-23 | 中国飞机强度研究所 | Multi-field coupling testing system and method |
| CN105571841A (en) * | 2015-12-13 | 2016-05-11 | 中国飞机强度研究所 | Wallboard structure overload test equipment |
| CN105571841B (en) * | 2015-12-13 | 2018-04-13 | 中国飞机强度研究所 | A kind of wall panel structure overload test equipment |
| CN106501083A (en) * | 2016-12-12 | 2017-03-15 | 兰州理工大学 | Large scale structure multiple spot ground anchor type drag-line charger and test method |
| CN107499534A (en) * | 2017-07-28 | 2017-12-22 | 中国航空工业集团公司西安飞机设计研究所 | A kind of processing method of aircraft floor lateral load |
| CN107499534B (en) * | 2017-07-28 | 2020-05-15 | 中国航空工业集团公司西安飞机设计研究所 | Method for processing airplane ground side load |
| CN107655650A (en) * | 2017-09-27 | 2018-02-02 | 上海交通大学 | Lever load system collision checking method for structural test |
| CN110514428A (en) * | 2019-09-24 | 2019-11-29 | 中国人民解放军空军工程大学 | A kind of bilateral loading platform for aviation connection structure testpieces |
| CN110514428B (en) * | 2019-09-24 | 2021-03-26 | 中国人民解放军空军工程大学 | Bidirectional loading test platform for aviation connection structure test piece |
| 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 |
| CN111301712A (en) * | 2020-04-06 | 2020-06-19 | 中国飞机强度研究所 | Multipoint coordination follow-up loading device and method for large-deformation wing |
| CN111572813A (en) * | 2020-05-26 | 2020-08-25 | 中国飞机强度研究所 | Airplane upward loading device |
| CN114441316A (en) * | 2020-10-30 | 2022-05-06 | 大连理工大学 | Air spring tension loading device and application thereof |
| CN114778050A (en) * | 2022-06-27 | 2022-07-22 | 中国飞机强度研究所 | Fatigue load flexible applying system for testing aircraft vibration superposition fatigue strength |
| CN114778050B (en) * | 2022-06-27 | 2022-09-02 | 中国飞机强度研究所 | Fatigue load flexible applying system for testing aircraft vibration superposition fatigue strength |
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Application publication date: 20130327 |