CN104002988A - Method for implementing aircraft arresting static test - Google Patents

Abstract

The invention belongs to the field of full-scale aircraft static test and relates to a method for implementing aircraft arresting static test. The method for implementing the aircraft arresting static test includes that step 1, confirming a main power transmission structure or part of the aircraft body when transmitting arresting load, and confirming a test structure or part through finite element detail strength calculation and analysis; step 2, separating a test piece and applying load in an equivalent mode to apply large concentrated load; step 3, using the structure or part not to be tested in the test and using an artificial piece convenient for applying load to increase a balancing part, and defining the component balancing load according to the test data of the component which has taken part in the static test and the theoretical calculation. The method for implementing the aircraft arresting static test solves the test implementation problems according to the aircraft arresting static test implementation difficulty, is capable of guaranteeing the real load transmission of the test (test structure) and has safety and maneuverability.

Description

A kind of method that aircraft arrestment static test is implemented

Technical field

The invention belongs to the full-scale static test of aircraft field, 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 of load and trim.Blocking static test carries out aboard, because load is larger, once destroying appears in arrester hook system, whole aircraft will be at moment lack of equilibrium, cause unpredictable structural failure, thus the trim that applies and test of test load whether reasonable is most important.During land airplane static test examination, general Main Load direction is aircraft overload direction, during test, take the mode of adhesive bandage distributed load, according to load, be distributed on housing construction and pass through to load lever and pressurized strut applied load or trim, test embodiment maturation and easily implement.And the static test load of aircraft arrestment situation is vector load, if tested while implementing according to the Calculate Ways of above-mentioned overload direction load, the course load of aircraft is applied by adhesive bandage by mass distribution, because the area that aircraft arrestment load is large, Aircraft Lateral tangent plane can load for course is limited and vector limited space causes arranging loading lever and pressurized strut, therefore must adopt new method to test, to consider the true posting situation of structure, consider again the operability that test is implemented simultaneously.

Summary of the invention:

The object of the invention is: a kind of method of implementing for aircraft arrestment static test is provided, solves the trim problem that applies and test that vector is concentrated large load, to examine aircaft configuration to block the load-carrying capacity of situation.

The technical barrier that this method mainly solves: apply course on aircraft 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 that non-examination position destroys in advance, causes test failure.

Technical scheme of the present invention is: a kind of method that solves aircraft arrestment static test enforcement, its feature comprises the steps:

The first, determine main force transferring structure or the position of blocking body in load transmittance process, by blocking load power transmission analysis and calculation of finite element strength, analyze, determine test checking construction or position;

The second, the method for designing of employing separation test part, equivalent applied load, realizes applying of large concentrated load.Concrete grammar is arrester hook to be acted on to the load separation of fuselage, by blocking, tests connection structure test and the independent arrester hook structure test two parts that are separated into fuselage; When the connection structure of examination fuselage is tested, arrester hook replaces with the bogusware that is beneficial to load applying, on body, tests; While examining independent arrester hook self structure test, on fixture, examine separately, to reduce the risk of test, guarantee the safety of test;

The 3rd, utilize non-checking construction or the position of test, and design is beneficial to the bogusware that blocks load applying and replaces true non-checking construction, block the trim of load; By subassembly test loading data and the theoretical calculation analysis of doing static test, be foundation, parts trim load is limited, final definite embodiment of blocking load.

Advantage of the present invention is: for aircraft arrestment static test practical difficulties, solved the implementation issue of test, the enforcement of warranty test is the true posting of checking construction, has again safety and operability simultaneously.

Accompanying drawing explanation

Fig. 1 blocks load power transmission to analyze sketch

The specific embodiment

Below by aircraft, block the embodiment that static test symmetry blocks situation and by reference to the accompanying drawings this method done to further detailed description.

First, based on blocking load power transmission, analyze, determine that the main power transmission route block load transmission is: arrester hook beam 5 is delivered to No. four fuel tank lower wall panels 4 of rear body by arrester hook load with the form of shearing flow, block moment of torsion that load produces and carry out balance by the couple that acts on the shearing of central bay 38 frame 1,42 frames 2 and 45 frames 3 and form.

The second, in order to test safe and reliable the carrying out of energy, the load that arrester hook is acted on to fuselage by mechanics equivalence is separated, by blocking, tests connection structure test and the independent arrester hook structure test two parts that are separated into fuselage; While examining the connection structure of fuselage, arrester hook replaces with the bogusware that is beneficial to load applying, on body, tests; During examination arrester hook self structure, on fixture, examine separately;

The 3rd, for realizing the large load trim in course, while examining the connection structure of fuselage, non-examination position wing and driving engine adopt bogusware to carry out trim, its trim load is calculated as foundation according to other test figuress and the theory that have completed, trim load is limited, and wherein false outer wing balancing load is that 120000N is less than its limit load 150000N; Wig motivation balancing load is 180000N not, is less than its limit load 200000N, and the load equalization scheme that finally definite symmetry is blocked situation sees the following form.

Symmetry is blocked situation balance scheme

Claims (1)

1. the method that aircraft arrestment static test is implemented, its feature comprises the steps:

The first, determine main force transferring structure or the position of blocking body in load transmittance process, by blocking load power transmission analysis and calculation of finite element strength, analyze, determine test checking construction or position;

The second, the method for designing of employing separation test part, equivalent applied load, realizes applying of large concentrated load.Concrete grammar is arrester hook to be acted on to the load separation of fuselage, by blocking, tests connection structure test and the independent arrester hook structure test two parts that are separated into fuselage; When the connection structure of examination fuselage is tested, arrester hook replaces with the bogusware that is beneficial to load applying, on body, tests; While examining independent arrester hook self structure test, on fixture, examine separately, to reduce the risk of test, guarantee the safety of test;

The 3rd, utilize non-checking construction or the position of test, and design is beneficial to the bogusware that blocks load applying and replaces true non-checking construction, block the trim of load; By subassembly test loading data and the theoretical calculation analysis of doing static test, be foundation, parts trim load is limited, final definite embodiment of blocking load.