CN-122009516-A - Tilt rotor static strength test device and method

CN122009516ACN 122009516 ACN122009516 ACN 122009516ACN-122009516-A

Abstract

The invention belongs to the technical field of testing of tilting rotors, and particularly relates to a device and a method for testing static strength of a tilting rotor. The test device comprises an angle-adjustable false piece, wherein the angle-adjustable false piece is used for simulating a tilting angle, one end of the angle-adjustable false piece is loaded with a test load, and the other end of the angle-adjustable false piece is connected with a test piece to be checked. According to the method, the false part with the adjustable angle is adopted for the static strength test of the rotor cabin in the tiltrotor aircraft, so that any angle change of the false part is realized, the load loading angle requirement during working condition assessment between a helicopter mode and a fixed wing flight mode is met, meanwhile, the complicated working condition load is optimized by adopting an optimization algorithm for the working condition load, the reasonable design of the load direction and the load size is realized, and the accurate and convenient implementation of the test load is facilitated.

Inventors

ZHOU XIN
CHEN QINGTONG
YANG LEI
Xu Dingqiang
GUO ZIQING

Assignees

中国直升机设计研究所

Dates

Publication Date: 20260512
Application Date: 20251217

Claims (10)

1. The tilting rotor static strength test device is characterized by comprising an angle-adjustable false piece, wherein the angle-adjustable false piece is used for simulating a tilting angle, one end of the angle-adjustable false piece is loaded with test load, and the other end of the angle-adjustable false piece is connected with a test piece to be checked.
2. The tilting rotor static strength test device according to claim 1, wherein the angle-adjustable dummy comprises a tilting joint 11, a screw dummy 10, a universal joint assembly, a load loading platform 6, a left tilting structure fixing seat and a right tilting structure fixing seat 1, the center of the tilting joint 11 is provided with a through hole, the universal joint assembly is fixed in the through hole, the screw dummy 10 penetrates through a threaded hole in the center of the universal joint assembly and is in threaded fit connection with the threaded hole, a double-lug structure is symmetrically fixed on the tilting joint 11, the left tilting structure fixing seat and the right tilting structure fixing seat 1 are respectively fixed at the bottom of the load loading platform 6, and the screw structure fixing seat 2 is in rotary connection with the double-lug structure and a lug structure at one end part of the screw dummy 10.
3. The tilting rotor static strength test device according to claim 1, wherein the universal joint assembly comprises a universal joint ring 3, a universal joint 4 and a flange 5, the flange 5 is fixed in the through hole through bolts, the universal joint ring 3 and the flange 5 are concentrically arranged and connected through bolts in a rotating mode, the universal joint 4 and the universal joint ring 3 are concentrically arranged and connected through bolts in a rotating mode, and a threaded through hole is formed in the center of the universal joint 4 and is connected with the screw rod dummy 10 in a threaded fit mode.
4. The tiltrotor static strength test apparatus according to claim 1, further comprising a load connector 7, wherein the load connector 7 is secured within a load aperture in a surface of the load platform 6.
5. A method for testing the static strength of a tiltrotor, which is characterized by adopting the device for testing the static strength of the tiltrotor according to any one of claims 1 to 4, and comprising the following steps: Step 1, according to dangerous load working conditions, adjusting the angle between the normal direction of the load loading platform 6 and the horizontal plane by rotating the screw rod dummy 10; step 2, predefining a plurality of load applying points on the surface of the load loading platform 6; step 3, limiting the upper and lower boundaries of each load application point according to the load of the preloaded tilting rotor wing to the load magnitude of the load application point in step 2; Step 4, establishing an objective function model within the limit range of the upper and lower boundaries of each load application point determined in the step 2 by utilizing a balance equation; And 5, calculating the applied load combination value of each load application point by using the objective function model established in the step 4 and adopting a genetic algorithm.
6. The method for testing the static strength of the tilting rotor according to claim 5, wherein the dangerous working conditions comprise a helicopter mode, an angle between a normal direction of the load loading platform 6 and a horizontal plane is 90 degrees, a fixed wing mode, an angle between the normal direction of the load loading platform 6 and the horizontal plane is 0 degree, and a transition mode, and an angle between the normal direction of the load loading platform 6 and the horizontal plane is 0 degree to 90 degrees.
7. The method according to claim 5, wherein in the step2, the specific process of predefining a plurality of load application points comprises: The projection point of the rotor center point on the load loading platform 6 is selected as one load point, and the rest load points are determined according to the loaded aperture size, so that the aperture size that the loading aperture is not smaller than 1.5 times of the edge distance of the load loading platform 6 is required to be ensured, and the loading aperture is ensured not to be subjected to shearing damage.
8. The method according to claim 5, wherein in the step 3, the defining of the upper and lower boundaries of each load applying point comprises: the lower boundary of each load applying point is determined according to the minimum load which can be implemented by a load loading system of a laboratory, namely F min ≤F System and method for controlling a system min ; The upper boundary meets a principle that the maximum shearing stress and the maximum normal stress of a local structure of the load loading platform 6 under the condition of considering at least 2 times of safety factors are respectively calculated according to the aperture and the edge distance of a loading hole on the load loading platform, and then the equivalent stress is calculated according to a fourth strength theory, wherein the equivalent stress is ensured to be less than or equal to the strength limit of the material, namely The calculation formula is as follows: , , wherein In order for the shear stress to be a high shear stress, In order to load the load, Is the diameter of the aperture of the tube, The maximum positive stress is applied to the steel plate, In order to load the thickness of the platform, For the equivalent stress calculated according to the fourth intensity theory, Is the strength limit for loading the platform material.
9. The method for testing the static strength of the tiltrotor according to claim 5, wherein in the step 4, the specific process of establishing the objective function model includes: the first step of establishing an equivalent load balance equation of the load and the moment at the center of the rotor according to the coordinate value of a predefined load applying point, wherein the balance equation is as follows: ∑FXi =∑PX.........................................................(1) ∑FYi =∑PY......................................................(2) ∑FZi =∑PZ.........................................................(3) ∑Y1i ×FZi +∑Z1i ×FYi =∑MX..............................(4) ∑Z1i ×FXi +∑X1i ×FZi =∑MY..............................(5) ∑X1i ×FYi +∑Y1i ×FXi =∑MZ..............................(6) Wherein F Xi 、F Yi 、F Zi is the load at the load loading point, X 1i 、Y 1i 、Z 1i is the coordinate value of the dummy loading point, i is the serial number of the loading point, and ΣPX, ΣPY, ΣPZ, ΣMX, ΣMY, ΣMZ are the equivalent load and the equivalent moment at the center of the rotor; The second step carries out matrixing expression on the established equivalent load balance equation, wherein the equation set comprises a coefficient matrix A and a constraint vector b, a basis is provided for subsequent calculation, and matrixing expression is as follows: A×Fi=b a is a coefficient matrix of coordinate values of dummy loading points, fi is a vector formed by loading of loading points, and b is a constraint vector formed by equivalent load and equivalent moment at the center of a rotor wing; thirdly, vectorizing the upper and lower boundaries of each load applying point, wherein the upper and lower boundary vectors are as follows: Lb=[F1_min ... Fi_min ... Fn_min] Lu=[F1_max ... Fi_ max ... Fn_max] lb is a vector of a lower limit of a load value at a load loading point, and Lu is a vector of an upper limit of the load value at the load loading point; Determining an objective function, wherein the objective function is a residual error of an equivalent load balance equation set, and the objective function is as follows: 。
10. The method for testing the static strength of the tiltrotor according to claim 5, wherein in the step 5, the method specifically comprises the following steps: firstly, a script function is newly built in MATLAB, a genetic algorithm is selected as an optimization tool, an adaptability function of the algorithm is an objective function established in the step four, a constraint equation is an equivalent balance equation established in the step four, boundary conditions are upper and lower boundary vectors established in the step four, and then, load combination values applied by all load application points are optimized and solved.

Description

Tilt rotor static strength test device and method The invention belongs to the technical field of testing of tilting rotors, and particularly relates to a device and a method for testing static strength of a tilting rotor. Background The tilting rotorcraft is a special-configuration aircraft with the functions of vertical take-off and landing of a helicopter and high-speed flight of a fixed-wing aircraft, a power propulsion system of the tilting rotorcraft is a rotor cabin or a nacelle which can be tilted generally, and the structure can realize the conversion between a helicopter mode and a fixed-wing flight mode, so that the switching of flight modes is realized. The unique working mode makes the structure, particularly the connection area of the tilting structure and the wings and the fuselage of the tilting structure bear complex and significantly different load environments in two flight modes, and extremely high requirements are placed on the design and strength verification of the tilting structure of the tilting gyroplane. The static strength test is used as a ground test means for verifying the bearing capacity of the aircraft structure and ensuring the most direct and indispensable flight safety, and the rationality of the test method is directly related to the accuracy and reliability of the verification result. At present, static strength test technology is relatively mature for a conventional fixed wing aircraft or helicopter, however, for static strength test of a tilting structure of the tilting rotorcraft, challenges are faced in (1) simulating two distinct load working conditions of a helicopter state and a fixed wing state in the same test, wherein the load size, direction and action point are extremely variable, the coordination application difficulty is high, (2) simulating the boundary condition of the aerial load and realizing high-precision and synchronous application of complex loads (such as combination of tension, torque, thrust and bending moment) of key components such as a wing cabin and the like, and (3) if a traditional single global loading scheme is adopted, huge support and loading systems possibly need to be adjusted for covering all critical working conditions for multiple times, and the test period is long and the cost is high. Disclosure of Invention The invention aims to provide a tilting rotor static strength test device and a tilting rotor static strength test method, which aim at adopting an angle-adjustable false part for a tilting rotor cabin static strength test in a tilting rotor aircraft so as to meet the working condition assessment from a helicopter mode to a fixed wing flight mode, and simultaneously, optimize complex working condition loads by adopting an optimization algorithm aiming at the working condition loads so as to realize reasonable design of the loads and facilitate accurate implementation of test loads. According to the first aspect of the invention, the invention provides a tilting rotor static strength test device which comprises an angle-adjustable false piece, wherein the angle-adjustable false piece is used for simulating a tilting angle, one end of the angle-adjustable false piece is loaded with a test load, and the other end of the angle-adjustable false piece is connected with a test piece to be checked. In one possible embodiment, the angle-adjustable dummy comprises a tilting joint 11, a screw dummy 10, a universal joint assembly, a load loading platform 6, a left tilting structure fixing seat and a right tilting structure fixing seat 1 and a screw structure fixing seat 2, wherein a through hole is formed in the center of the tilting joint 11, the universal joint assembly is fixed in the through hole, the screw dummy 10 penetrates through a threaded hole in the center of the universal joint assembly to be in threaded fit connection with the threaded hole, double-lug structures are symmetrically fixed on the tilting joint 11, and the left tilting structure fixing seat and the right tilting structure fixing seat 1 and the screw structure fixing seat 2 are respectively fixed at the bottom of the load loading platform 6 and are in rotary connection with the double-lug structures and lug structures at one end of the screw dummy 10. In one possible embodiment, the universal joint assembly comprises a universal joint ring 3, a universal joint 4 and a flange 5, wherein the flange 5 is fixed in the through hole through bolts, the universal joint ring 3 and the flange 5 are concentrically arranged and connected through bolts in a rotating mode, the universal joint 4 and the universal joint ring 3 are concentrically arranged and connected through bolts in a rotating mode, a threaded through hole is formed in the center of the universal joint 4, and the threaded through hole is connected with the screw rod dummy 10 in a threaded fit mode. In one possible embodiment, the load device further comprises a load joint 7, wherein the load joint 7 is fixe