CN103487277B - A kind of multifunctional universal test-bed for light aerocraft slow test - Google Patents
A kind of multifunctional universal test-bed for light aerocraft slow test Download PDFInfo
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- CN103487277B CN103487277B CN201310474550.2A CN201310474550A CN103487277B CN 103487277 B CN103487277 B CN 103487277B CN 201310474550 A CN201310474550 A CN 201310474550A CN 103487277 B CN103487277 B CN 103487277B
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Abstract
For a multifunctional universal test-bed for light aerocraft slow test, solve the problem that existing light aerocraft slow test stand purposes is single, complicated operation, cost are high.It by main frame, be arranged on pulley blocks on pulley yoke and removable frock is formed.Above-mentioned removable frock comprises main horizontal frock, front horizontal frock, main vertical frock, auxiliary mould A, auxiliary mould B, auxiliary mould C, auxiliary mould D.Described main horizontal frock and pillar are fixed, and are arranged on main frame.The side of main frame is provided with front horizontal frock, front horizontal frock is equipped with fixture, in order to fixing head.Main vertical frock is arranged in main horizontal frock, and auxiliary mould A, auxiliary mould B, auxiliary mould C and auxiliary mould D are arranged in main vertical frock.Principal feature of the present invention is rational in infrastructure, can carry out slow test according to the different size of aircraft, different size by the frock designed by mobile to aircraft.Have the advantages that purposes is wide, cost is low, easy to operate.
Description
Technical field
The present invention relates to a kind of multifunctional universal test-bed for light aerocraft slow test, be exactly a kind of multifunctional universal test-bed for the slow test of light aerocraft housing construction, belong to field of aerospace technology.
Background technology
Along with the development of global general-use Aerobiz, the development of new model light aerocraft is also more increasing with day, and new model aircraft is before first-fly, aircaft configuration slow test is indispensable, but general aircaft configuration static testing pad can only be suitable for a kind of type, test period length, complicated operation, with high costs, be unfavorable for the development work of light aerocraft and the development of General Aviation industry.In order to shorten the light aerocraft finite element analysis cycle, reducing experimentation cost, building the General Aviation industry of saving heavy duty detergent, high-level efficiency, multiduty light aerocraft finite element analysis stand must be designed.
Summary of the invention
The present invention is for the purpose of solving the problem, and provides the light aerocraft housing construction slow test stand of a kind of multi-usage, low cost, solves the problem that existing light aerocraft slow test stand purposes is single, complicated operation, cost are high.
For achieving the above object, the technical solution used in the present invention is: a kind of multifunctional universal test-bed for light aerocraft slow test, primarily of main frame (1), is arranged on pulley blocks (16) on pulley yoke (15) and removable frock is formed.Above-mentioned removable frock comprises main horizontal frock (2), front horizontal frock (3), main vertical frock (4), auxiliary mould A(5), auxiliary mould B(6), auxiliary mould C(7), auxiliary mould D(8).Described main horizontal frock (2) is fixed with pillar (9), and is arranged on main frame (1).The side of main frame (1) is provided with front horizontal frock (3), front horizontal frock (3) is equipped with fixture (12), in order to impose restriction to aircraft forebody.Main vertical frock (4) is arranged on main horizontal frock (2), auxiliary mould A(5), auxiliary mould B(6), auxiliary mould C(7) and auxiliary mould D(8) be arranged on main vertical frock (4).The opposite side of above-mentioned main frame (1) is provided with pulley yoke (15), corresponding with front horizontal frock (3).Lead cushion block one (10) to be placed on above main horizontal frock (2), led cushion block two (11) and back-up block (13) is placed on auxiliary mould C(7) above.Above-mentioned auxiliary mould B(6) on wing body connecting pin (14) is housed.
Beneficial effect of the present invention and feature:
Principal feature of the present invention is rational in infrastructure, can carry out slow test according to the different size of aircraft, different size by the Mobile tool of design to aircraft.Have the advantages that purposes is wide, cost is low, easy to operate.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention.
Fig. 2 is full machine slow test schematic diagram.
Fig. 3 is aircraft wing structure slow test schematic diagram.
Fig. 4 is aircraft vertical fin finite element analysis schematic diagram.
Fig. 5 is the side view of Fig. 4.
Embodiment
Embodiment
With reference to Fig. 1, a kind of multifunctional universal test-bed for light aerocraft slow test, primarily of main frame 1, is arranged on pulley blocks 16 on pulley yoke 15 and removable frock is formed.Above-mentioned removable frock comprises main horizontal frock 2, front horizontal frock 3, main vertical frock 4, auxiliary mould A5, auxiliary mould B6, auxiliary mould C7, auxiliary mould D8.Described main horizontal frock 2 is fixed with pillar 9, and is arranged on main frame 1.The side of main frame 1 is provided with front horizontal frock 3, and front horizontal frock 3 is equipped with fixture 12, in order to fixing head.Main vertical frock 4 is arranged in main horizontal frock 2, and auxiliary mould A5, auxiliary mould B6, auxiliary mould C7 and auxiliary mould D8 are arranged in main vertical frock 4.The opposite side of above-mentioned main frame 1 is provided with pulley yoke 15, corresponding with front horizontal frock 3.Lead cushion block 1 to be placed on above main horizontal frock 2, lead cushion block 2 11 and back-up block 13 is placed on above auxiliary mould C7.Wing body connecting pin 14 above-mentioned auxiliary mould B6 is equipped with.
Above-mentioned multifunctional universal test-bed, main frame 1 is by 140 × 140, and the square steel tube of wall thickness 8mm is welded, and has elongated hole in many places; Removable frock is by 140 × 60, and the channel-section steel of wall thickness 8mm is welded and has elongated hole in many places, and Mobile tool uses M10 socket head cap screw and nut to fix, need pad, and pad is M10 × 30 × 2.
Full machine 18, with reference to accompanying drawing 2, is placed in test-bed 17, and applies suitable constraint by the position adjusting removable frock to full machine by the slow test of above-mentioned full machine 18.
The slow test of above-mentioned wing 19 is with reference to accompanying drawing 3, and wherein the effect of bogusware 20 is connected modes of Reality simulation situation lower wing, thus the stressing conditions reflecting wing more really applies weight in wing appropriate location.
Above-mentioned aircraft vertical fin finite element analysis, with reference to accompanying drawing 4,5, is placed on pulley blocks 16 by rope 21, loads aircraft vertical fin
With reference to Fig. 2-5, concrete test procedure:
(1) installation of testpieces.First, according to concrete dimensional requirement and the experimental test project of testpieces, adjust main horizontal frock 2, front horizontal frock 3, main vertical frock 4 and auxiliary mould A5, auxiliary mould B6, auxiliary mould C7, the position of auxiliary mould D8, simulates the restraint condition of testpieces as far as possible really.
(2) loading of testpieces.According to the stressing conditions in aircraft flight, calculate the load of load(ing) point and corresponding load(ing) point, simulate the stressing conditions of testpieces as far as possible really.
(3) load mode.The load mode of current use is that sand pocket loads, and is filled in vacuum bag by iron sand exactly and seals, be made into the sand pocket that specification is 0.5kg, 1kg, 2kg, 5kg, 10kg, by all size sand pocket independent assortment, can be combined into the weight needed for loading.Also can improve load mode, adopt hydraulic system to load, more save manual labor.
(4) measure the item.Slow test mainly obtains the strain value of monitoring point and the deflection of testpieces.
Claims (2)
1. the multifunctional universal test-bed for light aerocraft slow test, comprise main frame (1), be arranged on pulley blocks (16) on pulley yoke (15) and removable frock, it is characterized in that: described removable frock comprises main horizontal frock (2), front horizontal frock (3), main vertical frock (4), auxiliary mould A (5), auxiliary mould B (6), auxiliary mould C (7) and auxiliary mould D (8), described main horizontal frock (2) is fixed with pillar (9), and be arranged on main frame (1), the side of main frame (1) is provided with front horizontal frock (3), front horizontal frock (3) is equipped with fixture (12), in order to fixing head, main vertical frock (4) is arranged on main horizontal frock (2), auxiliary mould A (5), auxiliary mould B (6), auxiliary mould C (7) and auxiliary mould D (8) is arranged on main vertical frock (4), the opposite side of above-mentioned main frame (1) is provided with pulley yoke (15), corresponding with front horizontal frock (3), above-mentioned auxiliary mould B (6) is equipped with wing body connecting pin (14).
2. a kind of multifunctional universal test-bed for light aerocraft slow test as claimed in claim 1, it is characterized in that: cushion block one (10) has been led in being placed with above of main horizontal frock (2), cushion block two (11) and back-up block (13) have been led in being placed with above of auxiliary mould C (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310474550.2A CN103487277B (en) | 2013-10-11 | 2013-10-11 | A kind of multifunctional universal test-bed for light aerocraft slow test |
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| CN201310474550.2A CN103487277B (en) | 2013-10-11 | 2013-10-11 | A kind of multifunctional universal test-bed for light aerocraft slow test |
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| CN103487277A CN103487277A (en) | 2014-01-01 |
| CN103487277B true CN103487277B (en) | 2015-11-04 |
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| CN201310474550.2A Expired - Fee Related CN103487277B (en) | 2013-10-11 | 2013-10-11 | A kind of multifunctional universal test-bed for light aerocraft slow test |
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Families Citing this family (10)
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| CN103808505B (en) * | 2014-03-06 | 2016-04-13 | 哈尔滨工业大学 | Wing static loading experiment device |
| CN105444999B (en) * | 2014-08-06 | 2018-04-13 | 北京航空航天大学 | A kind of static(al) suitable for miniature self-service captain's straight wing tests loading method |
| CN106742052B (en) * | 2016-11-29 | 2019-01-22 | 中国直升机设计研究所 | A kind of helicopter body slow test suspension |
| CN109827722A (en) * | 2019-01-25 | 2019-05-31 | 苏州为鹿测试技术有限公司 | The full machine intensity of fixed wing aircraft and modal test frame system |
| CN109827723A (en) * | 2019-01-25 | 2019-05-31 | 苏州为鹿测试技术有限公司 | The full machine intensity of fixed wing aircraft and modal test flexible support system |
| CN110146265A (en) * | 2019-05-19 | 2019-08-20 | 北京航空航天大学 | A kind of static force loading device being suitable for small drone wing |
| CN110239742B (en) * | 2019-05-29 | 2022-11-01 | 陕西飞机工业（集团）有限公司 | Method for combining two-model airplane with static test |
| CN110346098A (en) * | 2019-07-05 | 2019-10-18 | 傅明尧 | A kind of wing slow test hanging apparatus |
| CN218382145U (en) * | 2022-09-19 | 2023-01-24 | 峰飞航空科技(昆山)有限公司 | Wing static load strength test frame |
| CN117151698B (en) * | 2023-10-30 | 2023-12-29 | 西安航宇创通装备制造有限公司 | Comprehensive information processing system based on data analysis |
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| CN1731124A (en) * | 2005-07-04 | 2006-02-08 | 浙江大学 | Test bench for testing flight performance of small-sized helicopter |
| 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 |
| CN203534842U (en) * | 2013-10-11 | 2014-04-09 | 沈阳航空航天大学 | Multifunctional universal test bed for static test on light airplane |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| JPH07295819A (en) * | 1994-04-27 | 1995-11-10 | Fuji Heavy Ind Ltd | Fault diagnostic device |
| KR100488257B1 (en) * | 2002-11-26 | 2005-05-06 | 한국항공우주연구원 | Weight Counterbalance System for Air-ship Structure test |
| US8493324B2 (en) * | 2008-01-10 | 2013-07-23 | Symax Technology Co., Ltd. | Apparatus and method generating interactive signal for a moving article |
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1731124A (en) * | 2005-07-04 | 2006-02-08 | 浙江大学 | Test bench for testing flight performance of small-sized helicopter |
| 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 |
| CN203534842U (en) * | 2013-10-11 | 2014-04-09 | 沈阳航空航天大学 | Multifunctional universal test bed for static test on light airplane |
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Effective date of registration: 20160721 Address after: 110133 Liaoning city of Shenyang province Shenbei New Area Po Road No. 83 Patentee after: LIAONING RUIXIANG GENERAL AVIATION CO., LTD. Patentee after: Shenyang Aerospace University Patentee after: Liaoning General Aviation Academy Address before: 110136 Shenbei New Area, Shenyang Province, moral, South Street, No. 37, No. Patentee before: Shenyang Aerospace University Patentee before: Liaoning General Aviation Academy |
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