Aircraft structure fatigue test protection loading device and design method thereof
By designing a loading protection ring in the aircraft structure fatigue test, the problem of damage to the test piece caused by the extension or contraction of the piston rod of the hydraulic actuator cylinder is solved, and effective protection and continuity during the test process is achieved.
Patent Information
- Application Number
- CN202510762503.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-06-09
- Publication Date
- 2025-07-22
AI Technical Summary
In the prior art In the fatigue test of aircraft structure, when the extension amount of the hydraulic actuator cylinder piston rod is too large or the shrinkage amount is too large, the test piece cannot be effectively protected, resulting in damage or long-term stopping of the test.
A fatigue test protection loading device for aircraft structures is designed, including a connecting piece, a force sensor, a hydraulic actuator, a base and a loading protection ring. The loading protection ring is used to abut between the force sensor and the cylinder when the hydraulic actuator piston rod shrinks, limiting the further shrinkage of the piston rod and avoiding damage to the test piece due to excessive shrinkage of the piston rod.
Effectively protect the test piece from damage when the piston rod of the hydraulic actuator is extended or contracted too much, avoid long-term stopping of the test, and prevent the hydraulic actuator from gradually retracting and excessive tearing of the test piece due to gravity or loss of pressure.
Smart Images
Figure CN120348479A_ABST
Abstract
Description
Technical Field
[0001] This application belongs to the technical field of aircraft structural fatigue test design, and particularly relates to an aircraft structural fatigue test protection loading device and a method for designing the same. Background Art
[0002] In aircraft structural fatigue tests, a hydraulic actuator and its connection structure are used to apply fatigue loads to the test piece, the magnitudes and directions of which change periodically or irregularly over time, such as load-bearing structures like wings, fuselages, and frame beams.
[0003] When conducting aircraft structural fatigue tests, in order to prevent the test piece from being subjected to large loads due to abnormal load application and suffering excessive deformation and damage, usually considering the maximum deformation of the test piece, a suitable hydraulic actuator and its connection structure are selected to apply fatigue loads to the test piece. When the elongation of the hydraulic actuator piston rod approaches the maximum stroke, it corresponds to the situation where the test piece undergoes the maximum deformation. This technical solution can only ensure that the test piece will not be damaged due to excessive elongation of the hydraulic actuator piston rod, and cannot ensure that the test piece will not be damaged due to excessive contraction of the hydraulic actuator piston rod. Moreover, there will be a situation where the test is stopped for a long time, and the hydraulic actuator piston rod gradually retracts due to gravity or pressure loss, excessively tearing the test piece.
[0004] In view of the existence of the above technical defects, this application is proposed. Summary of the Invention
[0005] The purpose of this application is to provide an aircraft structural fatigue test protection loading device and a method for designing the same, so as to overcome or mitigate at least one aspect of the known technical defects.
[0006] The technical solution of this application is as follows:
[0007] On the one hand, an aircraft structural fatigue test protection loading device is provided, including a connecting piece, a force measuring sensor, a hydraulic actuator, a base, and a loading protection ring;
[0008] One end of the connecting piece is used to connect with the test piece, the other end is connected to the force measuring sensor, the other end of the force measuring sensor is connected to the top of the hydraulic actuator piston rod, and the bottom of the hydraulic actuator cylinder body is connected to the base. In this way, the fatigue load of the test piece can be applied through the telescopic movement of the hydraulic actuator piston rod, and the force measuring sensor is used to monitor the magnitude of the fatigue load applied to the test piece;
[0009] The loading protection ring is sleeved on the piston rod of the hydraulic actuator and can abut between the force measuring sensor and the cylinder body of the hydraulic actuator when the piston rod of the hydraulic actuator continuously contracts.
[0010] According to at least one embodiment of the present application, in the above aircraft structure fatigue test protection loading device, when the elongation of the piston rod of the hydraulic actuator reaches the maximum stroke, the corresponding test piece is compressed and deformed close to the maximum, avoiding the situation that the test piece is damaged due to excessive elongation of the piston rod of the hydraulic actuator during the test;
[0011] When the loading protection ring abuts between the force measuring sensor and the cylinder body of the hydraulic actuator, the corresponding test piece is tensioned and deformed close to the maximum, avoiding the situation that the test piece is damaged due to excessive contraction of the piston rod of the hydraulic actuator during the test.
[0012] According to at least one embodiment of the present application, in the above aircraft structure fatigue test protection loading device, the connection between the connecting piece and the test piece, between the connecting piece and the force measuring sensor, and between the force measuring sensor and the hydraulic actuator is made by a single / double ear structure with a pin, and the hydraulic actuator can be bolted to the base through the bottom support.
[0013] According to at least one embodiment of the present application, in the above aircraft structure fatigue test protection loading device, the loading protection ring includes an arc-shaped metal shell;
[0014] There are two arc-shaped metal shells, which are connected to form a complete ring structure and sleeved on the piston rod of the hydraulic actuator. When the contraction of the piston rod of the hydraulic actuator is excessive, the two ends directly abut between the force measuring sensor and the cylinder body of the hydraulic actuator, restricting further contraction of the piston rod of the hydraulic actuator;
[0015] The two sides of the two arc-shaped metal shells are fitted and assembled in the form of a boss and a groove, and are axially connected by bolts.
[0016] According to at least one embodiment of the present application, in the above aircraft structure fatigue test protection loading device, the loading protection ring includes a plastic lining;
[0017] There are two plastic linings, which are connected to the inner sides of the two arc-shaped metal shells, directly contact the piston rod of the hydraulic actuator, and have a smooth surface.
[0018] According to at least one embodiment of the present application, in the above aircraft structure fatigue test protection loading device, the plastic lining is adhesively connected to the arc-shaped metal shell.
[0019] On the other hand, a design method for an aircraft structure fatigue test protection loading device is provided, which is used to design the above aircraft structure fatigue test protection loading device, including:
[0020] According to the distance between the base and the test piece and the maximum deformation of the test piece under the ballast, select the connecting piece, force measuring sensor, and hydraulic actuator with appropriate sizes, so that when the piston rod elongation of the hydraulic actuator reaches the maximum stroke, the corresponding test piece undergoes ballast deformation close to the maximum;
[0021] According to the maximum deformation of the test piece under the tensile load, design the length of the loading protection ring, so that when the loading protection ring abuts between the force measuring sensor and the cylinder body of the hydraulic actuator, the corresponding test piece undergoes tensile load deformation close to the maximum.
[0022] The present application has at least the following beneficial technical effects:
[0023] Provide an aircraft structure fatigue test protection loading device and a method for designing it. During the test, on the basis of avoiding the test piece being damaged due to excessive elongation of the piston rod of the hydraulic actuator, further design a loading protection ring sleeved on the piston rod of the hydraulic actuator, which can abut between the force measuring sensor and the cylinder body of the hydraulic actuator when the piston rod of the hydraulic actuator continuously contracts, thereby avoiding the situation that the test piece is damaged due to excessive contraction of the piston rod of the hydraulic actuator during the test, and avoiding the situation that the hydraulic actuator gradually retracts due to gravity or pressure loss and excessively tears the test piece during a long-term stop of the test. Description of the Drawings
[0024] Figure 1 is a schematic diagram of the aircraft structure fatigue test protection loading device provided by the embodiment of the present application;
[0025] Figure 2 is a schematic diagram of the loading protection ring provided by the embodiment of the present application;
[0026] Figure 3 is a schematic diagram of the disassembled loading protection ring provided by the embodiment of the present application;
[0027] Wherein:
[0028] 1 - connecting piece; 2 - force measuring sensor; 3 - hydraulic actuator; 4 - base; 5 - loading protection ring; 6 - test piece;
[0029] 51 - arc-shaped metal shell; 52 - plastic lining.
[0030] For better illustration of this embodiment, some contents in the drawings will be omitted, enlarged or reduced, and are only for illustrative purposes and cannot be construed as a limitation to the present application. Detailed Embodiments
[0031] To make the technical solution of this application and its advantages clearer, the following will further clearly and completely describe the technical solution of this application in conjunction with the accompanying drawings. It can be understood that the specific embodiments described herein are only partial embodiments of this application, which are only used to explain this application and not to limit this application. It should be noted that for the convenience of description, only the parts related to this application are shown in the drawings, and other related parts can refer to the general design.
[0032] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application should have the ordinary meanings understood by those of ordinary skill in the art to which this application belongs. The "including" used in the description of this application means that the concept appearing before this word covers the concepts and their equivalents listed after this word, without excluding other related concepts.
[0033] In addition, the words indicating directions used in the description of this application are only used to indicate relative directions or positional relationships. When the absolute position of the object being described changes, its relative positional relationship may also change accordingly. It should also be noted that unless otherwise clearly specified and limited, the words such as "installation" and "connection" used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium. Those skilled in the art can understand their specific meanings in this application according to the specific situation.
[0034] An aircraft structure fatigue test protection loading device, as Figure 1 shown, includes a connecting piece 1, a force measuring sensor 2, a hydraulic actuator 3, a base 4, and a loading protection ring 5.
[0035] One end of the connecting piece 1 is used to connect with the test piece 6, the other end is connected to the force measuring sensor 2, the other end of the force measuring sensor 2 is connected to the top of the piston rod of the hydraulic actuator 3, and the bottom of the cylinder body of the hydraulic actuator 3 is connected to the base 4 and fixed on the ground or other fixed structures. In this way, the fatigue load of the test piece 6 can be loaded by the telescopic movement of the piston rod of the hydraulic actuator 3, and the force measuring sensor 2 is used to monitor the magnitude of the fatigue load applied to the test piece 6.
[0036] Between the connecting piece 1 and the test piece 6, between the connecting piece 1 and the force measuring sensor 2, and between the force measuring sensor 2 and the hydraulic actuator 3, they can be connected by pins through single or double ear structures, and the hydraulic actuator 3 can be connected to the base 4 by bolts through the bottom support.
[0037] In order to avoid the situation that the test piece 6 is damaged due to excessive elongation of the piston rod of the hydraulic actuator 3 during the test, appropriate-sized connecting parts 1, load cells 2, and hydraulic actuators 3 can be selected according to the distance between the base 4 and the test piece 6 and the maximum deformation of the test piece 6, so that when the elongation of the piston rod of the hydraulic actuator 3 reaches the maximum stroke, the corresponding deformation of the test piece 6 is close to the maximum. This deformation refers to the deformation of the test piece 6 under the action of the load.
[0038] The loading protection ring 5 is sleeved on the piston rod of the hydraulic actuator 3. When the piston rod of the hydraulic actuator 3 continuously contracts, it can abut between the load cell 2 and the cylinder body of the hydraulic actuator 3, avoiding the situation that the test piece 6 is damaged due to excessive contraction of the piston rod of the hydraulic actuator 3 during the test, and avoiding the situation that the piston rod of the hydraulic actuator 3 gradually retracts due to gravity or loss of pressure during a long-term test stop, over-tearing the test piece 6.
[0039] The length of the loading protection ring 5 can be designed according to the maximum deformation of the test piece 6, so that when the loading protection ring 5 abuts between the load cell 2 and the cylinder body of the hydraulic actuator 3, the corresponding deformation of the test piece 6 is close to the maximum. This deformation refers to the deformation of the test piece 6 under the action of the tensile load.
[0040] The loading protection ring 5 can be specifically designed to include an arc-shaped metal shell 51 and a plastic lining 52, as Figures 2 - 3 shown.
[0041] There are two arc-shaped metal shells 51, which are connected to form an integral ring structure and sleeved on the piston rod of the hydraulic actuator 3. When the contraction of the piston rod of the hydraulic actuator 3 is excessive, the two ends directly abut between the load cell 2 and the cylinder body of the hydraulic actuator 3, restricting further contraction of the piston rod of the hydraulic actuator 3, and requiring sufficient strength to ensure the protection effect on the test piece 6.
[0042] It can be designed that the two sides of the two arc-shaped metal shells 51 are fitted and assembled in the form of bosses and grooves, and connected axially by bolts, so that it can be conveniently disassembled and assembled. Without disassembling the connecting parts 1, load cells 2, hydraulic actuators 3, and base 4, it can be conveniently installed on the piston rod of the hydraulic actuator 3 and can be installed on the piston rods of different hydraulic actuators 3 according to needs.
[0043] There are two plastic linings 52, which are connected to the inner sides of the two arc-shaped metal shells 51. Specifically, they can be adhesively connected and directly contact the piston rod of the hydraulic actuator 3. The surface is required to be smooth and does not hinder the telescopic movement of the piston rod of the hydraulic actuator 3, so that the retraction and extension of the piston rod of the hydraulic actuator 3 are not affected.
[0044] The aircraft structure fatigue test protection loading device disclosed in the above embodiments can avoid the test piece 6 from being damaged due to excessive elongation of the piston rod of the hydraulic actuator 3 during the test. On this basis, a loading protection ring 5 is further designed to be sleeved on the piston rod of the hydraulic actuator 3, which can be abutted between the force sensor 2 and the cylinder body of the hydraulic actuator 3 when the piston rod of the hydraulic actuator 3 continuously contracts, so as to avoid the situation that the test piece 6 is damaged due to excessive contraction of the piston rod of the hydraulic actuator 3 during the test, and to avoid the situation that the hydraulic actuator 3 gradually retracts due to gravity or pressure loss and excessively tears the test piece 6 when the test is stopped for a long time.
[0045] The aircraft structure fatigue test protection loading device disclosed in the above embodiments, when applied in the test, can effectively protect the test piece 6 from being damaged when the elongation and contraction amounts of the piston rod of the actuator 3 are too large, and can avoid the situation that the hydraulic actuator 3 gradually retracts due to gravity or pressure loss and excessively tears the test piece 6 when the test is stopped for a long time. The specific design can be carried out with reference to the following method:
[0046] According to the distance between the base 4 and the test piece 6 and the maximum deformation amount of the test piece 6 under the load, select the connecting piece 1, the force sensor 2, and the hydraulic actuator 3 with appropriate sizes, so that when the elongation amount of the piston rod of the hydraulic actuator 3 reaches the maximum stroke, the deformation of the test piece 6 under the load is close to the maximum.
[0047] According to the maximum deformation amount of the test piece 6 under the tensile load, design the length of the loading protection ring 5 so that when the loading protection ring 5 abuts between the force sensor 2 and the cylinder body of the hydraulic actuator 3, the deformation of the test piece 6 under the tensile load is close to the maximum.
[0048] So far, the technical solution of the present application has been described in combination with the preferred embodiments shown in the drawings. Those skilled in the art should understand that the protection scope of the present application is obviously not limited to these specific embodiments. Without departing from the principle of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the protection scope of the present application.
Claims
1. An aircraft structure fatigue test protection loading device, characterized in that, It includes a connecting piece (1), a force measuring sensor (2), a hydraulic actuator (3), a base (4), and a loading protection ring (5); One end of the connecting piece (1) is used to connect with the test piece (6), the other end is connected to the force measuring sensor (2), the other end of the force measuring sensor (2) is connected to the top of the piston rod of the hydraulic actuator (3), and the bottom of the cylinder body of the hydraulic actuator (3) is connected to the base (4). In this way, through the expansion and contraction of the piston rod of the hydraulic actuator (3), the fatigue load of the test piece (6) can be loaded, and the force measuring sensor (2) is used to monitor the magnitude of the fatigue load applied to the test piece (6); The loading protection ring (5) is sleeved on the piston rod of the hydraulic actuator (3) and can abut between the force measuring sensor (2) and the cylinder body of the hydraulic actuator (3) when the piston rod of the hydraulic actuator (3) continuously contracts.
2. The aircraft structure fatigue test protection loading device according to claim 1, wherein When the elongation of the piston rod of the hydraulic actuator (3) reaches the maximum stroke, the compression deformation of the test piece (6) is close to the maximum, avoiding the situation that the test piece (6) is damaged due to excessive elongation of the piston rod of the hydraulic actuator (3) during the test; When the loading protection ring (5) abuts between the force measuring sensor (2) and the cylinder body of the hydraulic actuator (3), the tensile deformation of the test piece (6) is close to the maximum, avoiding the situation that the test piece (6) is damaged due to excessive contraction of the piston rod of the hydraulic actuator (3) during the test.
3. The aircraft structure fatigue test protection loading device according to claim 2, wherein Between the connecting piece (1) and the test piece (6), between the connecting piece (1) and the force measuring sensor (2), and between the force measuring sensor (2) and the hydraulic actuator (3), they are connected by pins through single and double ear structures, and the hydraulic actuator (3) can be connected to the base (4) by bolts through the bottom support.
4. The aircraft structure fatigue test protection loading device according to claim 3, wherein The loading protection ring (5) includes an arc-shaped metal shell (51); There are two arc-shaped metal shells (51), which are connected to form an integral ring structure and are sleeved on the piston rod of the hydraulic actuator (3). When the contraction of the piston rod of the hydraulic actuator (3) is excessive, the two ends directly abut between the force measuring sensor (2) and the cylinder body of the hydraulic actuator (3), restricting further contraction of the piston rod of the hydraulic actuator (3); The two sides of the two arc-shaped metal shells (51) are assembled by means of bosses and grooves and are connected axially by bolts.
5. The aircraft structure fatigue test protection loading device according to claim 4, wherein The loading protection ring (5) includes a plastic lining (52); There are two plastic linings (52), which are connected to the inner sides of the two arc-shaped metal shells (51), directly contact the piston rod of the hydraulic actuator (3), and have a smooth surface.
6. The aircraft structure fatigue test protection loading device according to claim 5, wherein The plastic lining (52) is adhesively connected to the arc-shaped metal shell (51).
7. A design method for a protection loading device for aircraft structure fatigue tests, which is used to design the protection loading device for aircraft structure fatigue tests described in claim 1, characterized in that, It includes: According to the distance between the base (4) and the test piece (6) and the maximum deformation of the test piece (6) under ballast, select the connecting piece (1), force measuring sensor (2), and hydraulic actuator (3) with appropriate sizes, so that when the piston rod elongation of the hydraulic actuator (3) reaches the maximum stroke, the deformation of the test piece (6) under ballast is close to the maximum; According to the maximum deformation of the test piece (6) under ballast, design the length of the loading protection ring (5), so that when the loading protection ring (5) abuts between the force measuring sensor (2) and the cylinder body of the hydraulic actuator (3), the deformation of the test piece (6) under tensile load is close to the maximum.