CN104002988B - A kind of method that aircraft arrestment static test is implemented - Google Patents
A kind of method that aircraft arrestment static test is implemented Download PDFInfo
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- CN104002988B CN104002988B CN201410154159.9A CN201410154159A CN104002988B CN 104002988 B CN104002988 B CN 104002988B CN 201410154159 A CN201410154159 A CN 201410154159A CN 104002988 B CN104002988 B CN 104002988B
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Abstract
The invention belongs to the full-scale static test field of aircraft, relate to a kind of method that aircraft arrestment static test is implemented, its feature comprises the steps: first, determine to block main force transferring structure or the position of body in dynamic changes process process, by finite element details strength Calculation, determine test checking construction or position; The second, adopt the method for separation test part, equivalent applied load design, realize the applying of large concentrated load; 3rd, utilize the non-checking construction of test or position and replacing to be beneficial to the bogusware of load applying to increase trim position, be foundation with subassembly test data and the theory calculate having done static test, parts trim load is limited.Advantage of the present invention is: for aircraft arrestment static test practical difficulties, solve the implementation issue of test, the enforcement of warranty test and the true posting of checking construction, has again safety and operability simultaneously.
Description
Technical field
The invention belongs to the full-scale static test field of aircraft, relate to a kind of method that aircraft arrestment static test is implemented.
Background technology
The static strength of arrester hook system and body connection structure is examined in aircraft arrestment static test simultaneously, and the enforcement of test comprises applying and the trim of load.Block static test to carry out aboard, because load is comparatively large, once destroying appears in arrester hook system, whole aircraft will at moment lack of equilibrium, cause unpredictable structural failure, whether reasonable is most important in the trim of the therefore applying of test load and test.During land airplane static test examination, general Main Load direction is aircraft overload direction, take the mode of adhesive bandage distributed load during test, according to load diatibution on housing construction by loading lever and pressurized strut applied load or trim, test embodiment is ripe and easily implement.And the static test load of aircraft arrestment situation is vector load, if according to the Calculate Ways of above-mentioned overload direction load when test is implemented, the course load of aircraft is applied by adhesive bandage by mass distribution, because aircraft arrestment load is large, Aircraft Lateral tangent plane can cause arranging loading lever and pressurized strut for the limited area of course loading and vector limited space, therefore new method must be adopted to test, namely to consider the true posting situation of structure, consider the operability that test is implemented simultaneously again.
Summary of the invention:
The object of the invention is: a kind of method implemented for aircraft arrestment static test is provided, solve vector and concentrate the applying of large load and the trim problem of test, with the load-carrying capacity examining aircaft configuration to block situation.
The technical barrier that this method mainly solves: aircraft applies course and concentrate large load, conventional methods cannot meet loading requirement; Because course load is very large, bring larger difficulty to the trim of test.If it is improper that trim position is selected, trim load is excessive, may cause non-examination position premature degradation, and cause test failure.
Technical scheme of the present invention is: a kind of method solving aircraft arrestment static test and implement, its feature comprises the steps:
The first, determining to block main force transferring structure or the position of body in dynamic changes process process, by blocking load load transfer analysis and calculation of finite element strength analysis, determining test checking construction or position;
The second, adopt the method for designing of separation test part, equivalent applied load, realize the applying of large concentrated load.Concrete grammar is that load arrester hook being acted on fuselage is separated, and is separated into the connection structure test of fuselage and independent arrester hook structure test two parts by blocking test; When the connection structure of examination fuselage is tested, the arrester hook bogusware being beneficial to load applying replaces, and body is tested; When examining independent arrester hook self structure to test, fixture is examined separately, to reduce the risk tested, guarantee the safety tested;
3rd, utilize test non-checking construction or position, and design be beneficial to block load applying bogusware to replace true non-checking construction, carry out the trim of blocking load; Loading data and theoretical calculation analysis with the subassembly test doing static test is foundation, limits, finally determine the embodiment of blocking load to parts trim load.
Advantage of the present invention is: for aircraft arrestment static test practical difficulties, solve the implementation issue of test, the enforcement of warranty test and the true posting of checking construction, has again safety and operability simultaneously.
Accompanying drawing explanation
Fig. 1 blocks load load transfer analysis sketch
Detailed description of the invention
Block static test symmetry below by aircraft block the embodiment of situation and do further detailed description to this method by reference to the accompanying drawings.
First, based on blocking load load transfer analysis, determine that the main load path blocking dynamic changes process is: arrester hook load is delivered to rear body No. four fuel tank lower wall panels 4 with the form of shearing flow by arrester hook beam 5, the couple that the moment of torsion blocking load generation is formed by the shearing acting on central bay 38 frame 1,42 frame 2 and 45 frame 3 balances.
The second, safe and reliablely can carry out to test, by mechanic equivalent, arrester hook being acted on the load separation of fuselage, test will be blocked and be separated into the connection structure test of fuselage and independent arrester hook structure test two parts; When examining the connection structure of fuselage, the arrester hook bogusware being beneficial to load applying replaces, and body is tested; Examine separately on fixture during examination arrester hook self structure;
3rd, for realizing the large load trim in course, when examining the connection structure of fuselage, non-examination position wing and driving engine adopt bogusware to carry out trim, its trim load is foundation according to other test figuress completed and theory calculate, limit trim load, wherein false outer wing balancing load is that 120000N is less than its limit load 150000N; The non-180000N of wig motivation balancing load, is less than its limit load 200000N, finally determines that the load equalization scheme that symmetry blocks situation sees the following form.
Symmetry blocks situation balance scheme
Claims (1)
1. a method for aircraft arrestment static test enforcement, its feature comprises the steps:
The first, determining to block main force transferring structure or the position of body in dynamic changes process process, by blocking load load transfer analysis and calculation of finite element strength analysis, determining test checking construction or position;
Second, adopt the method for designing of separation test part, equivalent applied load, realize the applying of large concentrated load, concrete grammar is that load arrester hook being acted on fuselage is separated, and is separated into the connection structure test of fuselage and independent arrester hook structure test two parts by blocking test; When the connection structure of examination fuselage is tested, the arrester hook bogusware being beneficial to load applying replaces, and body is tested; When examining independent arrester hook self structure to test, fixture is examined separately, to reduce the risk tested, guarantee the safety tested;
3rd, utilize test non-checking construction or position, and design be beneficial to block load applying bogusware to replace true non-checking construction, carry out the trim of blocking load; Loading data and theoretical calculation analysis with the subassembly test doing static test is foundation, limits, finally determine the embodiment of blocking load to parts trim load.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410154159.9A CN104002988B (en) | 2014-04-17 | 2014-04-17 | A kind of method that aircraft arrestment static test is implemented |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410154159.9A CN104002988B (en) | 2014-04-17 | 2014-04-17 | A kind of method that aircraft arrestment static test is implemented |
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| Publication Number | Publication Date |
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| CN104002988A CN104002988A (en) | 2014-08-27 |
| CN104002988B true CN104002988B (en) | 2015-12-02 |
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Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105300679B (en) * | 2015-11-13 | 2018-04-03 | 哈尔滨工业大学 | A kind of arrester hook falls warship simulation test device |
| CN108860657B (en) * | 2018-05-18 | 2021-10-29 | 西北工业大学 | Aircraft arresting test device and aircraft arresting load transfer simulation equipment |
| CN108896316B (en) * | 2018-06-05 | 2020-07-14 | 西安航天动力测控技术研究所 | Safety test device for checking full-size solid engine under action of large extrusion force |
| CN109543262A (en) * | 2018-11-09 | 2019-03-29 | 中国直升机设计研究所 | Helicopter Main Reducer bogusware and its design method |
| 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 |
| CN111539134B (en) * | 2019-12-25 | 2023-10-20 | 中国航空工业集团公司西安飞机设计研究所 | Processing method of large-curvature aircraft panel |
| CN112591135A (en) * | 2020-11-03 | 2021-04-02 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft static test load loading method |
| CN116698471B (en) * | 2023-08-07 | 2023-11-07 | 四川腾盾科技有限公司 | Static strength test method for aircraft control surface |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2002193196A (en) * | 2000-12-26 | 2002-07-10 | Honda Motor Co Ltd | Load applying method to fuselage structure of aircraft |
| GB0608744D0 (en) * | 2006-05-03 | 2006-06-14 | Airbus Uk Ltd | Landing Gear Ground Test |
| JP4969492B2 (en) * | 2008-02-28 | 2012-07-04 | 三菱重工業株式会社 | Test load loading method and test load loading mechanism |
| CN102288400B (en) * | 2011-05-31 | 2013-04-24 | 中国航空动力机械研究所 | Stirring tube driving speed reducer static test device |
| CN102928293B (en) * | 2012-10-26 | 2015-01-28 | 重庆交通大学 | Dynamic and static testing system and method for multifunctional wharf structure |
| CN102991726A (en) * | 2012-12-10 | 2013-03-27 | 中国飞机强度研究所 | Loading system and method for airplane structure test |
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