CN104029826B - A kind of aircraft structure strength test button re-computation method - Google Patents

Abstract

The invention belongs to the button weight technology of aircraft structure strength test, be specifically related to a kind of for the button re-computation method in aircraft structure strength test.The present invention determined weight and the center of gravity of test article, test article bogusware before test article assembling, total weight and added weight is determined after installation, then calculating unit coefficient, the heavy coefficient of button and structure actual center gravity, finally carry out the button weight of full machine, test article bogusware and added weight, thus the heavy coefficient of accurate Calculation test button, reduce the heavy coefficient of test button, reduce the impact of the heavy precision of center of gravity deviation make-up of each structure member, thus by improving the heavy precision of test button, real simulation experimental engine carrying, improves test accuracy.

Description

A kind of aircraft structure strength test button re-computation method

Technical field

The invention belongs to the button weight technology of aircraft structure strength test, be specifically related to a kind of for the button re-computation method in aircraft structure strength test.

Background technology

In complete aircraft structural static/fatigue test, test load is generally the load not considering structural weight.When carrying out structure test, the weight of test article is outwardness, therefore needs the weight of test article to deduct, and namely test button is heavy.When carrying out the test of full machine, test article not only comprises test article structure, also comprises test bogusware, test loading facilities, strain-gauge, wire etc.When test button is heavy, each block construction theoretical weight usually adopting designing unit to provide and center of gravity, calculate total theoretical weight and center of gravity, after having pasted adhesive bandage, hanging up auxiliary lever, carry out actual weighing to aircraft, weigh up actual weight and center of gravity.(aircraft actual weight-bogusware weight)/theoretical construct weight, is called the heavy coefficient of button.

When button is heavy, each framing member theoretical weight is multiplied by the heavy coefficient of button, is this structure button weight values, for the deviation of actual center gravity and theoretical center of gravity, utilizes the method applying increment load, theoretical center of gravity is transferred on actual center gravity.

This button weighing method, calculates fairly simple, also can meet test requirements document.But there are some problems, as: the heavy coefficient of button is larger; The weight such as adhesive bandage, auxiliary lever is undertaken calculating by aero-structure weight distribution and detains heavy, is distributed with deviation with actual weight.

Summary of the invention

The object of the invention is: provide one accurately can realize test button heavy, test is loaded more accurate, reach the aircraft structure strength test button re-computation method of real simulation test article carrying object.

Technical scheme of the present invention is: a kind of aircraft structure strength test button re-computation method, it determined weight and the center of gravity of test article, test article bogusware before test article assembling, total weight and added weight is determined after installation, then calculating unit coefficient, the heavy coefficient of button and structure actual center gravity, finally carry out the button weight of full machine, test article bogusware and added weight.

Described aircraft structure strength test button re-computation method, specifically comprises the steps:

Step 1: test article and test article bogusware are weighed

The structural weight data of each parts of statistical test part, namely test article theoretical weight, is designated as G _li, each parts center of gravity adopts theoretical center of gravity X _i, Y _i;

Before experimental engine assembling, carry out actual weighing to each parts of test article, namely test article structure sub-unit actual weight, is designated as B _i, its center of gravity adopts theoretical center of gravity X _i, Y _i;

Before experimental engine assembling, carry out actual weighing to test article bogusware, each bogusware weight is designated as J _i, bogusware center of gravity adopts theoretical center of gravity X _ji, Y _ji;

Step 2: the complete machine after experimental engine assembling and added weight are weighed

After test unit installs into, and after having completed strain gauge adhesion, conductor configuration, complete machine is weighed, weight G _always, center of gravity X _always, Y _always;

Can calculating section in added weight, weight and center of gravity are designated as F _i, X _fi, Y _fi;

Step 3: parts coefficient n calculates

Parts coefficient n calculates: n _i=B _i/ G _li;

Step 4: the heavy coefficient k of button calculates

K=(G _always-∑ J _i-∑ F _i)/∑ B _i;

Step 5: structure actual center gravity calculates

X=(G _alwaysx _always-∑ J _ix _ji-∑ F _ix _fi)/(G _always-∑ J _i-∑ F _i),

Y=(G _alwaysy _always-∑ J _iy _ji-∑ F _iy _fi)/(G _always-∑ J _i-∑ F _i),

Wherein, i=1,2

Step 6: button is heavy

When carrying out full machine button and being heavy, structure is according to sub-unit weight B _i× k, center of gravity X _i, Y _ideduction, after structure button heavily gathers, the center of gravity that button is heavy and the actual deviation of detaining the heavy heart of structure adjust testing non-examination position;

Each bogusware is according to the actual weight J that weighs _i, center of gravity X _jiand Y _jideduction;

Eachly calculate added weight F _i, X _fi, Y _fideduction;

In addition the weight of equipment increased also will be deducted at the trial by weighing;

When subassembly test, the heavy amount of parts button presses G _li× n × k or B _i× k, center of gravity presses X _i, Y _ideduction.

Advantage of the present invention is: machine stryctyrak test button re-computation method of the present invention calculates structure, bogusware and added weight in experimental engine by refinement, thus the heavy coefficient of accurate Calculation test button, reduce the heavy coefficient of test button, reduce the impact of the heavy precision of center of gravity deviation make-up of each structure member, thus by improving the heavy precision of test button, real simulation experimental engine carrying, improves test accuracy.

Accompanying drawing explanation

Fig. 1 is the diagram of circuit of aircraft structure strength of the present invention test button re-computation method.

Detailed description of the invention

Below by embodiment, the present invention is described further:

Refer to Fig. 1, it is the specific implementation process of aircraft structure strength of the present invention test button re-computation method, and its step is as follows:

Step 1: test article and test article bogusware are weighed

The structural weight data of each parts of statistical test part, namely test article theoretical weight, is designated as G _li, each parts center of gravity adopts theoretical center of gravity X _i, Y _i(i=1,2 ...); Wherein, described areal coordinates should be three-dimensional coordinate, coordinate parallel with the direction (Z-direction) of gravity under considering three-dimensional coordinate.

Before experimental engine assembling, carry out actual weighing to each parts of test article, namely test article structure sub-unit actual weight, is designated as B _i(i=1,2 ...), its center of gravity adopts theoretical center of gravity X _i, Y _i(i=1,2 ...);

Before experimental engine assembling, carry out actual weighing to test article bogusware, each bogusware weight is designated as J _i, bogusware center of gravity adopts theoretical center of gravity X _ji, Y _ji(i=1,2 ...); Wherein, during stryctyrak test, consider test features and manufacturing cost, some parts of experimental engine can adopt bogusware, and the simulation of these boguswares and experimental engine connection structure, for testing loading, adopt bogusware as driving engine, alighting gear.

Step 2: the complete machine after experimental engine assembling is weighed and added weight calculates

After test unit installs into, and after having completed the work such as strain gauge adhesion, conductor configuration and adhesive bandage stickup, complete machine is weighed, weight G _always, center of gravity X _always, Y _always; Test article each parts actual weight, each bogusware weight, each parts docking pts wt, the strain-gauge of stickup and the weight such as wire weight, adhesive bandage thereof is contained in this weight.Remove each parts actual weight and each bogusware weight, other weight is added weight.In added weight, have and can calculate added weight, as adhesive bandage weight, know its weight and full machine distribution, its center-of-gravity position can be calculated.Part added weight is known by calculating, can calculating section in added weight, and weight and center of gravity are designated as F _i, X _fi, Y _fi(i=1,2 ...);

Step 3: parts coefficient n calculates

Parts coefficient n calculates: n _i=B _i/ G _li;

Step 4: the heavy coefficient k of button calculates

K=(G _always-∑ J _i-∑ F _i)/∑ B _i(i=1,2 ...);

Step 5: structure actual center gravity calculates

X=(G _alwaysx _always-∑ J _ix _ji-∑ F _ix _fi)/(G _always-∑ J _i-∑ F _i),

Y=(G _alwaysy _always-∑ J _iy _ji-∑ F _iy _fi)/(G _always-∑ J _i-∑ F _i) (i=1,2 ...);

Step 6: button is heavy

When testing, the load on test article not only to be made more accurate, also will consider that engineering construction is convenient and simple.

When carrying out subassembly test, do not carry out the button weight of complete machine, only button is carried out to examination parts and weigh.The heavy amount of parts button presses G _li× n × k or B _i× k, center of gravity presses X _i, Y _ideduction.

When carrying out full machine button and being heavy:

Structure is according to sub-unit weight B _i, center of gravity X _i, Y _ideduction, structure button heavy general by upwards initiatively load(ing) point or counterbalancing weight point deduct, namely multiple load(ing) point distributes button heavy amount, ensures that the heavy amount of each parts button and center of gravity and parts actual weight and center of gravity are consistent.

After structure button heavily gathers, the heavy amount × k of structure button is that structure is real claims calculated weight, and the deviation (eccentricity) that the heavy heart of structure button and structure reality claim to calculate center of gravity adjusts testing non-examination position;

Bogusware is the non-examination position of test, and in order to short form test, each bogusware is according to the actual weight J that weighs _i, center of gravity X _jiand Y _jideduction;

Eachly calculate added weight F _i, X _fi, Y _fideduction;

In addition the weight of equipment increased also will be deducted at the trial by weighing.

The present invention determined weight and the center of gravity of test article, test article bogusware before test article assembling in sum, total weight and added weight is determined after installation, then calculating unit coefficient, the heavy coefficient of button and structure actual center gravity, finally carry out the button weight of full machine, test article bogusware and added weight, thus the heavy coefficient of accurate Calculation test button, reduce the heavy coefficient of test button, reduce the impact of the heavy precision of center of gravity deviation make-up of each structure member, thus by improving the heavy precision of test button, real simulation experimental engine carrying, improves test accuracy.

Claims (1)

1. an aircraft structure strength test button re-computation method, it is characterized in that, weight and the center of gravity of test article, test article bogusware was determined before test article assembling, total weight and added weight is determined after installation, then calculating unit coefficient, the heavy coefficient of button and structure actual center gravity, finally carry out the button weight of full machine, test article bogusware and added weight, specifically comprise the steps:

Step 1: test article and test article bogusware are weighed

The structural weight data of each parts of statistical test part, namely test article theoretical weight, is designated as G _li, each parts center of gravity adopts theoretical center of gravity X _i, Y _i;

Before experimental engine assembling, carry out actual weighing to each parts of test article, namely test article structure sub-unit actual weight, is designated as B _i, its center of gravity adopts theoretical center of gravity X _i, Y _i;

Before experimental engine assembling, carry out actual weighing to test article bogusware, each bogusware weight is designated as J _i, bogusware center of gravity adopts theoretical center of gravity X _ji, Y _ji;

Step 2: the complete machine after experimental engine assembling and added weight are weighed

After test unit installs into, and after having completed strain gauge adhesion, conductor configuration, complete machine is weighed, weight G _always, center of gravity X _always, Y _always;

Can calculating section in added weight, weight and center of gravity are designated as F _i, X _fi, Y _fi;

Step 3: parts coefficient n calculates

Parts coefficient n calculates: n _i=B _i/ G _li;

Step 4: the heavy coefficient k of button calculates

K=(G _always-Σ J _i-Σ F _i)/Σ B _i;

Step 5: structure actual center gravity calculates

X=(G _alwaysx _always-Σ J _ix _ji-Σ F _ix _fi)/(G _always-Σ J _i-Σ F _i),

Y=(G _alwaysy _always-Σ J _iy _ji-Σ F _iy _fi)/(G _always-Σ J _i-Σ F _i),

Wherein, i=1,2

Step 6: button is heavy

When carrying out full machine button and being heavy, structure is according to sub-unit weight B _i× k, center of gravity X _i, Y _ideduction, after structure button heavily gathers, the center of gravity that button is heavy and the actual deviation of detaining the heavy heart of structure adjust testing non-examination position;

Each bogusware is according to the actual weight J that weighs _i, center of gravity X _jiand Y _jideduction;

Eachly calculate added weight F _i, X _fi, Y _fideduction;

In addition the weight of equipment increased also will be deducted at the trial by weighing;

When subassembly test, the heavy amount of parts button presses G _li× n × k or B _i× k, center of gravity presses X _i, Y _ideduction.