阅读说明：本技术 一种机身侧向与航向载荷联合施加装置及载荷施加方法 (Fuselage lateral and heading load combined applying device and load applying method ) 是由 郑建军 王高利 王征 张磊 郭琼 牟战云 于 2020-04-13 设计创作，主要内容包括：本申请提供了一种机身侧向与航向载荷联合施加装置,所述联合施加装置包括：加载杠杆装置,其连接于机身蒙皮表面,用于对机身蒙皮施加载荷；联合加载杠杆,其两端分别至少连接一个所述加载杠杆装置,用于平衡施加于加载杠杆装置的载荷；第一执行作动器和第二执行作动器,其近似对称的连接于所述联合加载杠杆,其中,第一执行作动器和第二执行作动器水平设置于同一水平面内。本申请提供的机身侧向与航向载荷联合施加装置相比于现有技术中的载荷施加装置来说,可实现双向加载,且是通过一套杠杆系统实现航向和侧向两种载荷的施加,减少了结构表面传载介质的粘贴量,便于结构损伤检测。(The application provides a fuselage side direction and course load jointly exert device, jointly exert the device and include: the loading lever device is connected to the surface of the fuselage skin and is used for applying load to the fuselage skin; the two ends of the combined loading lever are respectively connected with at least one loading lever device and used for balancing the load applied to the loading lever devices; and the first execution actuator and the second execution actuator are approximately symmetrically connected to the combined loading lever, wherein the first execution actuator and the second execution actuator are horizontally arranged in the same horizontal plane. Compared with a load applying device in the prior art, the lateral and heading load combined applying device for the fuselage can realize bidirectional loading, and the application of two loads, namely the heading and the lateral, is realized through one set of lever system, so that the sticking quantity of a structure surface transfer medium is reduced, and the structure damage detection is facilitated.)

1. A combined fuselage-side and heading load applicator, the combined applicator comprising:

the loading lever device is connected to the surface of the fuselage skin and is used for applying load to the fuselage skin;

the two ends of the combined loading lever are respectively connected with at least one loading lever device and used for balancing the load applied to the loading lever devices;

the first executing actuator and the second executing actuator are connected with the combined loading lever at preset included angles, and the first executing actuator and the second executing actuator are horizontally arranged in the same horizontal plane.

2. The combined fuselage lateral and heading load applicator of claim 1, further comprising:

the load measuring device comprises a first load sensor and a second load sensor, wherein the first load sensor is arranged between a first executing actuator and a combined loading lever and used for measuring the load applied by the first executing actuator, and the second load sensor is arranged between a second executing actuator and the combined loading lever and used for measuring the load applied by the second executing actuator.

3. The combined fuselage lateral and heading load applying apparatus of claim 1, wherein the lever loading apparatus comprises:

the loading device is arranged at two ends of the loading lever, and the combined loading lever is connected with the middle part of the loading lever through the adapter.

4. The combined fuselage lateral and heading load applying apparatus of claim 3, wherein there are at least two of the load transmitting devices disposed at one end of the load lever.

5. The combined fuselage lateral and heading load applying apparatus of claim 1, wherein the first actuation actuator comprises a hydraulic actuator, a load sensor, and a linkage; the second actuation actuator includes a hydraulic actuator, a load sensor, and a linkage.

6. A load application method for the fuselage lateral direction and heading load combined application device as claimed in any one of claims 1 to 5, wherein, of the loads applied by the combined application device, the heading load is:

wherein, F_1hHeading load provided for first actuator, F_2hHeading load provided for the second actuator, F_hFor the load required by the heading, an angle α is an included angle between the first execution actuator and the heading of the machine body, and an angle β is an included angle between the second execution actuator and the heading of the machine body;

the side load is:

wherein, F_1cSide load for first actuator，F_2cSide load for the second actuator, F_cThe load is required laterally;

the course and the lateral combined load are as follows:

in the formula, F₁Combined load provided to the first actuator, F₂A combined load provided to the second actuator.

Technical Field

The application belongs to the technical field of airplane structural strength tests, and particularly relates to a device and a method for jointly applying lateral and heading loads to an airplane body.

Background

When a ground strength test of a full-size airplane structure is carried out, a load is usually applied to the airplane structure by adopting a distributed hydraulic actuator through a multipoint coordinated loading control system, the real stress of the airplane in use is simulated, and whether the strength of the structure meets the design and use requirements or not is judged by measuring the response of the structure. The test loading system generally comprises a loading system, a load sensor, a loading actuator, a rear end fixing device and the like which are connected to a test piece, and the load sensor and the loading actuator realize closed-loop control through a multi-point coordination loading control system.

For applying the lateral load of the airplane fuselage, an adhesive tape lever system is generally adopted for loading, and since the adhesive tape is made of soft canvas, the adhesive tape can only bear a single lateral tensile load, and the method cannot be realized when a compressive load is required to be applied or a lateral load and a heading load are applied simultaneously.

In the case of a loading actuator, the conventional method is to arrange a hydraulic actuator in the direction of a loading force line, and the closed-loop controllable loading is realized by a control system. In a full-size aircraft structure static test, the load size and the loading direction of different examination working conditions can be adjusted, after a loading device of the previous working condition is dismounted, the loading device required by the next working condition needs to be mounted, the mounting position needs to be changed, the loading angle needs to be adjusted, and the like, so that the accurate application of the load is realized. However, in a full-scale aircraft structure fatigue test, because all load working conditions are loaded by the same set of loading system, the installation state of loading equipment cannot be changed in real time in the test process. The traditional scheme is that a plurality of loading points are set, namely, a single forward heading loading point is set to realize the application of a forward heading load, a single backward heading loading point realizes the application of a backward load, a lateral loading point realizes the application of a single lateral direction tensile load, each loading point in the system realizes the loading requirement of one main working condition, and the system only needs to follow the operation in other unnecessary load working conditions.

However, although the existing loading mode can meet the requirement of applying the full-size airplane structure fatigue test load, the disadvantages are also obvious: firstly, a plurality of loading points are arranged, so that loading nodes are added on the surface of the airplane, the number of load transmission devices adhered to the surface of the airplane is large, and damage detection of the surface of the structure is influenced; secondly, the traditional course loading node cannot apply absolute course load due to the structural characteristics of the body, but needs to deviate from two sides by an angle, so that an unnecessary lateral load component is added while the course load is applied; thirdly, fewer loading points need to be used in each working condition, so that load application is too concentrated, and the requirement for accurate distribution and loading of structural loads is not facilitated; fourthly, the channels of the control system are increased due to the increase of the loading points, the coordination control difficulty in the test is greatly improved, the system is easy to step for waiting and even for test protection, and the high-efficiency operation of the fatigue test is not facilitated.

Disclosure of Invention

The application aims to provide a combined loading device and a loading method for lateral and heading loads of a fuselage, so as to solve any one of the problems.

In one aspect, the technical solution provided by the present application is: a combined fuselage-side and heading load applicator, the combined applicator comprising:

the loading lever device is connected to the surface of the fuselage skin and is used for applying load to the fuselage skin;

the two ends of the combined loading lever are respectively connected with at least one loading lever device and used for balancing the load applied to the loading lever devices;

first execution actuator and second execution actuator, it be certain contained angle connect in unite the loading lever, wherein, first execution actuator and second execution actuator level set up in the same horizontal plane.

In one embodiment of the present application, the joint application apparatus further comprises: the load measuring device comprises a first load sensor and a second load sensor, wherein the first load sensor is arranged between a first executing actuator and a combined loading lever and used for measuring the load applied by the first executing actuator, and the second load sensor is arranged between a second executing actuator and the combined loading lever and used for measuring the load applied by the second executing actuator.

In an embodiment of the present application, the lever loading device includes: the loading device is arranged at two ends of the loading lever, and the combined loading lever is connected with the middle part of the loading lever through the adapter.

In one embodiment of the present application, the number of the load transfer devices provided at one end of the load lever is at least two.

In one embodiment of the present application, the first actuation actuator comprises a hydraulic actuator, a load sensor; the second execution actuator comprises a hydraulic actuator and a load sensor.

On the other hand, the technical scheme provided by the application is as follows: a load application method for the fuselage lateral direction and heading load combined application device comprises the following steps of:

wherein, F_1hHeading load provided for first actuator, F_2hHeading load provided for the second actuator, F_hFor the load required by the heading, an angle α is an included angle between the first execution actuator and the heading of the machine body, and an angle β is an included angle between the second execution actuator and the heading of the machine body;

the side load is:

wherein, F_1cSide load for the first actuator, F_2cSide load for the second actuator, F_cThe load is required laterally;

the course and the lateral combined load are as follows:

in the formula, F₁Combined load provided to the first actuator, F₂A combined load provided to the second actuator.

The application provides a fuselage side direction and course load joint application device and load application method, compare the load application device among the prior art, but two-way loading on one hand, system function has been expanded, on the other hand, one set of lever system realizes the application of two kinds of loads of course and side direction, the volume of pasting of the structure surface load transfer medium has been reduced, be convenient for structure damage to detect, on the other hand, the pure course load is applyed and is had no additional lateral component, the loading is more accurate, on the other hand, the distribution of loading point is more reasonable, the load distribution is more even, better satisfy the experimental needs, on the other hand, actuator along with the operation in the loading system reduces, be convenient for experimental control, the high-efficient operation of favourable experiment.

Drawings

In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.

FIG. 1 is a schematic view of a co-application device of the present application.

Reference numerals:

1-loading lever device, 11-load transmission device, 12-loading lever;

2-a combined loading lever;

3-a first load sensor;

4-a second load sensor;

5-a first execution actuator;

6-second actuator.

Detailed Description

In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.

In the aspect of load application in a ground strength test of a full-size airplane structure, the load application requirements in the test can be met, and the number of sticking nodes on the surface of the airplane is not increased too much; the lateral/heading load required in the test can be accurately applied, and the structure cannot bear the unnecessary lateral load component.

As shown in fig. 1, the present application firstly provides an applying device for fuselage lateral and heading load combined loading, the applying device mainly comprises: the lever loading device 1, the combined loading lever 2, the first actuator 5 and the second actuator 6. The loading lever arrangement 1 is connected to the fuselage skin surface in order to apply a load to the fuselage skin, wherein the loading lever arrangement 1 can be connected to the fuselage skin, for example, by means of gluing or riveting. Two ends of the combined loading lever 2 are respectively connected with at least one loading lever device, and the loading lever devices play a role in balancing loads applied to the loading lever devices 1. The first and second actuators 5, 6 are connected approximately symmetrically to the middle of the loading lever 1, while the first and second actuators 5, 6 are arranged horizontally in the same horizontal plane.

It should be noted that the rear ends of the first and second actuating actuators 5/6 are secured to a load support structure (not shown) and that load transfer is achieved by mounting mechanical linkages in appropriate locations.

In the present application, the joint application device further comprises: a first load sensor 3 and a second load sensor 4, the first load sensor 3 being arranged between the first actuator 5 and the load lever 2 for measuring the load exerted by the first actuator, and the second load sensor 4 being arranged between the second actuator 6 and the load lever 2 for measuring the load exerted by the second actuator 6.

In the present application, the loading lever device 1 comprises at least two load transferring devices 11 and a loading lever 12, wherein the load transferring devices 11 are distributed at two ends of the loading lever 12, and the end part of the combined loading lever 2 is connected to the middle part of the loading lever 12 through an adapter.

In the embodiment shown on the right, as shown in fig. 1, the loading lever device 1 has two load transfer devices 11, which are respectively arranged at two ends of a loading lever 12, and form a combined loading lever form with double loading holes; in the embodiment shown on the left, the loading lever arrangement 1 has four load-transferring devices 11, two of which are arranged in groups at each end of a loading lever 12, forming a combined loading lever form with four loading holes.

It should be noted that the loading device 11 may be a hard structure, such as a disk made of metal, or a soft structure, such as a disk made of rubber. In order to achieve non-stress concentration of the load, when the loading device 11 is of a hard structure, a flexible rubber pad or the like may be provided between the loading device and the aircraft body.

In the present application, the first or second actuator needs to provide a linear load, which can be realized by a mechanism or a device for realizing a telescopic function, such as a hydraulic actuator, a linear motor, and the like.

As shown in figure 1, a plurality of load transfer devices 11 are combined into a whole in a loading lever device 1 by adhering the load transfer devices 11 to proper positions of the lateral structure surface of the airplane body, so that uniform load distribution is realized, a combined loading lever 2 is the final lever of the loading lever device 1 and is provided with two load applying nodes which can simultaneously transfer loads to two execution actuators 5/6, a first load sensor 3, a first execution actuator 5, a second load sensor 4 and a second execution actuator 6 respectively form two groups of closed loop loading systems, load application is respectively carried out by a coordinated loading control system, the loading force line of the first load sensor 3 and the first execution actuator 5 forms an included angle α with the airplane body heading, the loading force line of the second load sensor 4 and the second execution actuator 6 forms an included angle β with the airplane body heading, and independent or combined loading of the airplane body heading and the lateral actuators can be realized by respectively or jointly controlling the first execution actuator/second execution actuator.

In order to load the lateral and heading loads of the fuselage, as shown in fig. 1, the loading lever device 1 needs to apply the heading load and the lateral load of the fuselage, the loads needed to be applied by the two execution actuators under a single main load can be respectively obtained by force vector decomposition according to a geometric relationship, and under the condition that both the two loads need to be applied, the two loads can be simultaneously applied by force composition in a superposition manner, so that the loading purpose of double loads in two directions is achieved.

For pure course load F_hThe force resolution from the geometric relationship is given by the following formula:

F_1hcos(α)+F_2hcos(β)＝F_h

F_1hsin(α)+F_2hsin(β)＝0

the formula can be arranged to obtain:

for pure side load F_cThe force resolution from the geometric relationship is given by the following formula:

F_1csin(α)+F_2csin(β)＝F_c

F_1ccos(α)-F_2ccos(β)＝0

the formula can be arranged to obtain:

when the heading and the side load need to be applied simultaneously, the force composition principle has the following formula:

in the above formula, F_1hHeading load provided for first actuator, F_2hHeading load provided for the second actuator, F_hFor the load required by the heading, α angle is the included angle between the first execution actuator and the heading of the machine body, β angle is the included angle between the second execution actuator and the heading of the machine body, F_1cSide load for the first actuator, F_2cSide load for the second actuator, F_cThe load is required laterally; f₁Combined load provided to the first actuator, F₂Combined load provided to the second actuator

Two sets of closed-loop control systems which can be respectively controlled are constructed through the first load sensor 3, the first execution actuator 5, the second load sensor 4 and the second execution actuator 6, and corresponding loads are respectively and independently applied by the control systems according to the calculation results.

Compared with a load applying device in the prior art, the device and the method for applying the load to the lateral direction and the heading load of the airplane body jointly can realize bidirectional loading, expand system functions, realize the application of two loads of the heading and the lateral direction by one set of lever system, reduce the sticking amount of a load transfer medium on the surface of a structure, facilitate the detection of structural damage, apply pure heading load without additional lateral component, realize more accurate loading, realize more reasonable distribution of loading points, realize more uniform load distribution, better meet the test requirement, reduce the actuators which follow the operation in a loading system, facilitate test control and facilitate the efficient operation of the test.

The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.