CN103723285A - Empennage load applying device used for plane structure strength tests - Google Patents
Empennage load applying device used for plane structure strength tests Download PDFInfo
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- CN103723285A CN103723285A CN201310652040.XA CN201310652040A CN103723285A CN 103723285 A CN103723285 A CN 103723285A CN 201310652040 A CN201310652040 A CN 201310652040A CN 103723285 A CN103723285 A CN 103723285A
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- empennage
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- applying device
- load applying
- bogusware
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Abstract
The invention provides an empennage load applying device which can effectively simulate the empennage stress condition under the state of the maneuvering flight of a plane in plane structure strength tests. The empennage load applying device comprises an empennage fake piece platform, connection lug pieces and loading cross beams, wherein different test loads are applied on a tested piece in the mode of changing the mode of the loading cross beams and the connection lug pieces perpendicular to the surface of the empennage fake piece platform. Reinforced bearing rib plates are arranged at the bottoms of the connection lug pieces at the large load area of the surface of the empennage fake piece platform so as to change the force transmission mode under the large loads, and reliability is increased. The empennage load applying device can truly simulate the transmission of the loads of empennages, meet the requirement of application of the loads of the empennages under different working conditions, and solve the problem that under the action of the large loads of the empennages, the empennage load applying device deforms along with a plane body; the empennage load applying device is convenient to install, saves installation space, shortens installation time, speeds up the test schedule, and can largely save funding of model development.
Description
Technical field
The invention belongs to aircaft configuration strength test empennage loading technique, be specifically related to a kind of tail loads bringing device for aircaft configuration strength test.
Background technology
In complete aircraft stryctyrak test, in order to verify empennage and body connection structure intensity, need empennage stressing conditions under the different maneuvering flight states of simulated aircraft.Conventionally adopt the directly method of applied load on tail structure, need design, processing for this reason and tail structure is installed.But the tail structure design cycle is long, tooling cost is high, the on-the-spot difficulty of installing, the test loading facilities amount of changing the outfit is large.
Summary of the invention
The object of the invention is: provide a kind of in aircaft configuration strength test, the effectively tail loads bringing device of empennage stressing conditions under simulated aircraft maneuvering flight state.
Technical scheme of the present invention is: a kind of tail loads bringing device for aircaft configuration strength test, it comprises empennage bogusware platform, attachment lug, loading crossbeam, wherein, described empennage bogusware platform surface is provided with connecting bore, bottom is hinged by monaural and fuselage empennage joint, attachment lug is arranged on empennage bogusware platform, loads crossbeam and is arranged on empennage bogusware platform by attachment lug.
Load crossbeam by aircraft being applied to vertical load perpendicular to the attachment lug of empennage bogusware platform surface.
Load crossbeam, by the attachment lug that is parallel to empennage bogusware platform surface, aircraft is applied to course and lateral loading.
The attachment lug bottom of the large load zones of empennage bogusware platform surface is provided with strengthens carrying gusset.
Technique effect of the present invention is:
1) can simulate comparatively really the transmission of tail loads;
2) can meet tail loads under different operating modes applies;
3) can solve under the large load of empennage, meet tail loads bringing device with fuselage problem on deformation;
4) easy for installation, save installing space and time, accelerate test progress;
5) model research fund has been saved in the use of tail loads bringing device greatly.
Accompanying drawing explanation
Fig. 1 is the structural representation of the present invention for the empennage bogusware platform of the tail loads bringing device of aircaft configuration strength test;
Fig. 2 is the scheme of installation of attachment lug;
Fig. 3 is the structural representation of the tail loads bringing device for aircaft configuration strength test of the present invention, and wherein, 1-airframe structure, 2-empennage bogusware platform, 3-attachment lug, 4-load crossbeam.
The specific embodiment
Below in conjunction with drawings and Examples, the present invention will be further described:
Please refer to Fig. 1, Fig. 2 and Fig. 3, the present invention comprises empennage bogusware platform, attachment lug, loading crossbeam for the tail loads bringing device of aircaft configuration strength test, wherein, described empennage bogusware platform surface is provided with connecting bore, bottom is hinged by monaural and fuselage empennage joint, attachment lug is arranged on empennage bogusware platform, loads crossbeam and is arranged on empennage bogusware platform by attachment lug.
Empennage bogusware platform is connected with fuselage empennage joint by bolt, Reality simulation fuselage empennage stand under load type of attachment.For the distortion of fuselage in load applying process, leave space simultaneously.
Loading crossbeam is connected with vertical/attachment lug of being parallel to empennage bogusware platform surface by bolt, loading crossbeam two ends installation loading attaching parts, one end connection is directly connected with ground, the other end is connected with loading pressurized strut, by pressurized strut applied load, load truly passes to aircraft by this device by load and applies vertical/course and lateral loading, reaches the examination object of test.
For the load that adapts to different operating modes loads, this device is provided with the loading connecting bore position of diverse location at empennage bogusware platform, loading the loading connecting bore position that different arm of force ratios are set on crossbeam, by adjusting combining of these positions, hole, reach the object that test article is applied to different loads simultaneously.
The attachment lug bottom of the large load zones of empennage bogusware platform surface is provided with reinforcement gusset, thereby can be under large load condition, make to load crossbeam and directly transfer loads to the reinforcement gusset place of attachment lug, thus the some power transmission of bolt is changed into the face power transmission of strengthening gusset place, increased the reliability of power transmission.
All parts of the present invention are simple and easy processing component, and the truer tail structure of cost reduces greatly, and this device is easy to installation, saving room and time, quickening test progress.
Claims (4)
1. the tail loads bringing device for aircaft configuration strength test, it is characterized in that, comprise empennage bogusware platform, attachment lug, loading crossbeam, wherein, described empennage bogusware platform surface is provided with connecting bore, bottom is hinged by monaural and fuselage empennage joint, and attachment lug is arranged on empennage bogusware platform, loads crossbeam and is arranged on empennage bogusware platform by attachment lug.
2. the tail loads bringing device for aircaft configuration strength test according to claim 1, is characterized in that, loads crossbeam by aircraft being applied to vertical load perpendicular to the attachment lug of empennage bogusware platform surface.
3. the tail loads bringing device for aircaft configuration strength test according to claim 1, is characterized in that, loads crossbeam, by the attachment lug that is parallel to empennage bogusware platform surface, aircraft is applied to course and lateral loading.
4. the tail loads bringing device for aircaft configuration strength test according to claim 1, is characterized in that, the attachment lug bottom of the large load zones of empennage bogusware platform surface is provided with strengthens carrying gusset.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310652040.XA CN103723285B (en) | 2013-12-04 | 2013-12-04 | A kind of tail loads bringing device for aircraft structure strength test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310652040.XA CN103723285B (en) | 2013-12-04 | 2013-12-04 | A kind of tail loads bringing device for aircraft structure strength test |
Publications (2)
| Publication Number | Publication Date |
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| CN103723285A true CN103723285A (en) | 2014-04-16 |
| CN103723285B CN103723285B (en) | 2016-01-20 |
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| CN201310652040.XA Active CN103723285B (en) | 2013-12-04 | 2013-12-04 | A kind of tail loads bringing device for aircraft structure strength test |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104691780A (en) * | 2015-03-08 | 2015-06-10 | 西安电子科技大学 | Truss structure of long-span and large-deflection cantilever test bench |
| CN106153319A (en) * | 2016-07-01 | 2016-11-23 | 陕西飞机工业（集团）有限公司 | A kind of simulation 8 frame forebody load loaded member for aircraft slow test |
| CN107521721A (en) * | 2017-07-20 | 2017-12-29 | 中国航空工业集团公司西安飞机设计研究所 | A kind of full scale fatigue test fuselage course load designing load method |
| CN109506908A (en) * | 2018-11-09 | 2019-03-22 | 中国直升机设计研究所 | Endpiece testpieces fatigue test horizontal tail load charger |
| CN109655245A (en) * | 2018-10-31 | 2019-04-19 | 中国飞机强度研究所 | A kind of four vertical fin load loading methods |
| 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 |
| CN111746822A (en) * | 2020-06-05 | 2020-10-09 | 中国飞机强度研究所 | Large-tonnage load bearing device |
| CN113071704A (en) * | 2021-03-30 | 2021-07-06 | 中国商用飞机有限责任公司 | Test method and system for simulating wing deformation |
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| CN103033351A (en) * | 2012-12-10 | 2013-04-10 | 中国飞机强度研究所 | Bunching type horizontal loading follow-up weight deducting device |
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| JP2008094154A (en) * | 2006-10-06 | 2008-04-24 | Honda Motor Co Ltd | Testing device in man-powered steering device of aircraft |
| CN201575950U (en) * | 2009-12-14 | 2010-09-08 | 中国飞机强度研究所 | Tension and compression pad-lever loading device |
| 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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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104691780A (en) * | 2015-03-08 | 2015-06-10 | 西安电子科技大学 | Truss structure of long-span and large-deflection cantilever test bench |
| CN106153319A (en) * | 2016-07-01 | 2016-11-23 | 陕西飞机工业（集团）有限公司 | A kind of simulation 8 frame forebody load loaded member for aircraft slow test |
| CN106153319B (en) * | 2016-07-01 | 2018-07-24 | 陕西飞机工业（集团）有限公司 | A kind of 8 frame forebody load loaded member of simulation for aircraft slow test |
| CN107521721A (en) * | 2017-07-20 | 2017-12-29 | 中国航空工业集团公司西安飞机设计研究所 | A kind of full scale fatigue test fuselage course load designing load method |
| CN107521721B (en) * | 2017-07-20 | 2020-07-07 | 中国航空工业集团公司西安飞机设计研究所 | Full-size fatigue test fuselage course load loading design method |
| CN109655245A (en) * | 2018-10-31 | 2019-04-19 | 中国飞机强度研究所 | A kind of four vertical fin load loading methods |
| CN109506908A (en) * | 2018-11-09 | 2019-03-22 | 中国直升机设计研究所 | Endpiece testpieces fatigue test horizontal tail load charger |
| 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 |
| CN111746822A (en) * | 2020-06-05 | 2020-10-09 | 中国飞机强度研究所 | Large-tonnage load bearing device |
| CN111746822B (en) * | 2020-06-05 | 2023-12-22 | 中国飞机强度研究所 | Large tonnage load bearing device |
| CN113071704A (en) * | 2021-03-30 | 2021-07-06 | 中国商用飞机有限责任公司 | Test method and system for simulating wing deformation |
| CN113071704B (en) * | 2021-03-30 | 2023-02-10 | 中国商用飞机有限责任公司 | Test method and system for simulating wing deformation |
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| CN103723285B (en) | 2016-01-20 |
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