Horizontal single-degree-of-freedom follow-up restraint device for static fatigue test of airplane structure
By designing a horizontal single-degree of freedom follow-up constraint device for static fatigue test of aircraft structures, using the combined constraints of follow-up slide plate and articulated joints, the additional constraint problem caused by insufficient stiffness of the constraint point in the prior art is solved, and more accurate and safe test results are achieved.
Patent Information
- Application Number
- CN202510211510.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-02-25
- Publication Date
- 2025-05-27
AI Technical Summary
In the static/fatigue test of existing aircraft structures, the horizontal direction constraints mostly use the hinge constraints of two-force rods and columns. When the stiffness of the constraint point is small, additional constraints will occur in other directions, affecting the test results and safety.
A single degree of freedom follow-up constraint device for horizontal direction of static fatigue test aircraft structure is designed, including a fixed constraint plate, a follow-up slide plate, a connecting rod and a hinged joint. Through the sliding of the follow-up slide plate in the sliding cavity and the rotation of the hinged joint, a single degree of freedom constraint on the aircraft is achieved, and additional constraints on other directions are avoided.
It effectively avoids additional constraints in other directions, ensures the accuracy of load-bearing and load monitoring feedback at each constraint point, and improves the accuracy and safety of the test judgment.
Smart Images
Figure CN120043752A_ABST
Abstract
Description
Technical Field
[0001] The present application belongs to the technical field of static fatigue testing of aircraft structures, and in particular relates to a single-degree-of-freedom follow-up constraint device in a horizontal direction for static fatigue testing of aircraft structures. Background Art
[0002] In static / fatigue tests of aircraft structures, the aircraft is usually constrained in the form of six-degree-of-freedom static constraints. Generally, three vertical constraints and three horizontal constraints are selected to constrain the aircraft's pitch, yaw, roll, vertical displacement, lateral displacement and heading displacement.
[0003] At present, the most common form of horizontal constraint for aircraft is to use two-force rods and columns for hinged constraints. When the stiffness of the constraint point is small and a large deformation occurs during the test loading process, additional constraints in other directions will be generated, thereby affecting the load on each constraint point and the load monitoring feedback, which in turn affects the judgment of the test and the test assessment, making it difficult to obtain accurate test results and even causing danger.
[0004] This application is proposed in view of the above-mentioned technical defects. Summary of the invention
[0005] The purpose of the present application is to provide a horizontal single-degree-of-freedom follow-up restraint device for static fatigue testing of aircraft structures, so as to overcome or alleviate at least one of the known technical defects.
[0006] The technical solution of this application is:
[0007] A single-degree-of-freedom follow-up restraint device in a horizontal direction for a static fatigue test of an aircraft structure comprises a fixed restraint plate, a follow-up slide plate, a connecting rod, and an articulated joint;
[0008] The fixed restraining plate is fixed on the ground, and has a sliding cavity inside, a side wall on one side has a protruding hole connected to the sliding cavity, and an edge has a strip groove;
[0009] The follower slide plate is arranged in the slide cavity, and is inlaid with a plurality of steel balls. The follower slide plate can slide in the slide cavity through the contact between the steel balls and the inner wall of the slide cavity;
[0010] There are four steel balls, which are distributed on the four corners of the follower slide.
[0011] One end of the connecting rod is connected to the follower slide plate, and the other end extends out from the extension hole and is connected to the hinge joint; a gap is left between the connecting rod and the extension hole;
[0012] The connection between the connecting rod and the follower slide plate is a detachable connection;
[0013] The articulated joint is hinged to the aircraft, and is articulated with the aircraft's landing gear through a single-ear and double-ear structure with a joint bearing.
[0014] According to at least one embodiment of the present application, in the horizontal direction single-degree-of-freedom follow-up restraint device for the static fatigue test of the aircraft structure, the fixed restraint plate is fixed to the ground through columns and is arranged vertically along the X-axis, Y-axis or Z-axis of the aircraft.
[0015] According to at least one embodiment of the present application, in the horizontal direction single-degree-of-freedom follow-up restraint device for the static fatigue test of the aircraft structure, the protruding hole on the fixed restraint plate is a circular hole.
[0016] According to at least one embodiment of the present application, in the horizontal direction single-degree-of-freedom follow-up restraint device for the static fatigue test of the aircraft structure, a force sensor is arranged between the connecting rod and the hinge joint.
[0017] According to at least one embodiment of the present application, in the horizontal direction single-degree-of-freedom follow-up restraint device for the static fatigue test of the aircraft structure, the hinge joint and the force sensor are connected by threads.
[0018] According to at least one embodiment of the present application, in the horizontal direction single-degree-of-freedom follow-up restraint device for the static fatigue test of the aircraft structure, a screw rod is arranged between the connecting rod and the force sensor, and both ends of the screw rod are screwed on the connecting rod and the force sensor.
[0019] The present application has at least the following beneficial technical effects:
[0020] A horizontal direction single-degree-of-freedom follow-up restraint device for the static fatigue test of the aircraft structure is provided. The fixed effect of the fixed restraint plate can be utilized to realize the restraint of a single degree of freedom of the aircraft's heading displacement, lateral displacement or vertical displacement. At the same time, the sliding of the follow-up sliding plate in the sliding cavity of the fixed restraint plate and the rotation effect of the hinge joint hinged with the aircraft are utilized to release the degrees of freedom of the aircraft in other directions, avoiding the generation of additional constraints in other directions. In this way, in the static / fatigue test of the aircraft structure, the loading of each restraint point and the load monitoring feedback can be avoided from being affected, which is conducive to the judgment of the test and obtaining accurate test results, and avoiding danger. Description of the Drawings
[0021] Figure 1 is a schematic diagram of the cooperation between the horizontal direction single-degree-of-freedom follow-up restraint device for the static fatigue test of the aircraft structure provided by the embodiment of the present application and the aircraft;
[0022] Figure 2 is an assembly schematic diagram of the horizontal direction single-degree-of-freedom follow-up restraint device for the static fatigue test of the aircraft structure provided by the embodiment of the present application;
[0023] Wherein:
[0024] 1 - Fixed constraint plate; 2 - Follow-up slide plate; 3 - Steel ball; 4 - Connecting rod; 5 - Hinge joint; 6 - Aircraft; 7 - Force sensor; 8 - Screw; 9 - Spherical plain bearing.
[0025] To better illustrate this embodiment, some contents of the drawings will be omitted, enlarged or reduced, which are only for illustrative purposes and should not be construed as a limitation to this application. Detailed implementation manners
[0026] To make the technical solutions and their advantages of this application clearer, the technical solutions of this application will be further described clearly and completely below in conjunction with the 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 rather than 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.
[0027] 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 field 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 listed after this word and their equivalents, without excluding other related concepts.
[0028] In addition, the words indicating directions used in the description of this application are only used to represent 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.
[0029] A horizontal single-degree-of-freedom follow-up constraint device for aircraft structural static fatigue tests, as Figure 1 - Figure 2 shown, includes a fixed constraint plate 1, a follow-up slide plate 2, a connecting rod 4, and a hinge joint 5.
[0030] The fixed constraint plate 1 can be fixed to the ground through columns.
[0031] The fixed constraint plate 1 has a sliding cavity inside, and one side wall has an extension hole communicating with the sliding cavity. The extension hole can be a circular hole.
[0032] The follow-up slide plate 2 is arranged in the sliding cavity and can slide in the sliding cavity.
[0033] To facilitate the installation of the follower slide plate 2 into the sliding cavity, a strip-shaped groove can be designed on one edge of the fixed restraint plate 1. During installation, the follower slide plate 2 can be placed into the sliding cavity through the strip-shaped groove.
[0034] To reduce the sliding resistance of the follower slide plate 2 in the sliding cavity, multiple steel balls 3 can be embedded in the follower slide plate 2. By contacting the inner wall of the sliding cavity with the steel balls 3 and utilizing the rolling of the steel balls 3, the sliding resistance in the sliding cavity can be reduced.
[0035] Specifically, it can be designed that the number of steel balls 3 embedded in the follower slide plate 2 is four, which are distributed at the four corner parts of the follower slide plate 2.
[0036] One end of the connecting rod 4 is connected to the follower slide plate 2, and the other end extends out from the protruding hole and is connected to the articulated joint 5. A gap is left between the connecting rod 4 and the protruding hole to adapt to the sliding design of the follower slide plate 2 in the sliding cavity.
[0037] To avoid interference with the installation of the follower slide plate 2 into the sliding cavity, the connection between the connecting rod 4 and the follower slide plate 2 can be designed as a detachable connection, specifically a threaded connection. When installing the follower slide plate 2 into the sliding cavity, the connecting rod 4 can be first unscrewed from the follower slide plate 2. After installing the follower slide plate 2 into the sliding cavity, the connecting rod 4 can be threadedly connected to the follower slide plate 2 through the protruding hole.
[0038] The articulated joint 5 is hinged to the aircraft 6, specifically it can be hinged to the landing gear of the aircraft 6, and is hinged to the landing gear through a single-double ear structure and a spherical plain bearing 9.
[0039] For the horizontal single-degree-of-freedom follow-up restraint device for the static fatigue test of the aircraft structure disclosed in the above embodiments, to perform horizontal restraint on the aircraft, the following method can be referred to:
[0040] When restraining the heading displacement of the aircraft, the fixed restraint plate 1 can be set to be vertically fixed along the X-axis of the aircraft. In this way, the fixed effect of the fixed restraint plate 1 can be utilized to achieve the restraint of the aircraft's heading displacement. At the same time, the sliding of the follower slide plate 2 in the sliding cavity of the fixed restraint plate 1 and the rotational effect of the hinge between the articulated joint 5 and the aircraft 6 can be utilized to release the degrees of freedom of the aircraft in its direction and avoid generating additional constraints in other directions;
[0041] When restraining the lateral displacement of the aircraft, the fixed restraint plate 1 can be set to be vertically fixed along the Y-axis of the aircraft. In this way, the fixed effect of the fixed restraint plate 1 can be utilized to achieve the restraint of the aircraft's lateral displacement. At the same time, the sliding of the follower slide plate 2 in the sliding cavity of the fixed restraint plate 1 and the rotational effect of the hinge between the articulated joint 5 and the aircraft 6 can be utilized to release the degrees of freedom of the aircraft in other directions and avoid generating additional constraints in other directions;
[0042] When restricting the vertical displacement of the aircraft, the fixed restraint plate 1 can be set to be vertically fixed along the Z-axis of the aircraft. In this way, the fixing effect of the fixed restraint plate 1 can be utilized to achieve the restraint of the vertical displacement of the aircraft. At the same time, the sliding of the follower slide plate 2 in the sliding cavity of the fixed restraint plate 1 and the rotational effect of the hinge joint 5 hinged to the aircraft 6 can be utilized to release the degrees of freedom of the aircraft in other directions and avoid generating additional constraints in other directions.
[0043] The horizontal single-degree-of-freedom follow-up restraint device for the aircraft structure static and fatigue test disclosed in the above embodiment can utilize the fixing effect of the fixed restraint plate 1 to achieve the restraint of a single degree of freedom of the aircraft's heading displacement, lateral displacement or vertical displacement. At the same time, the sliding of the follower slide plate 2 in the sliding cavity of the fixed restraint plate 1 and the rotational effect of the hinge joint 5 hinged to the aircraft 6 are utilized to release the degrees of freedom of the aircraft in other directions and avoid generating additional constraints in other directions. In this way, in the aircraft structure static / fatigue test, it is possible to avoid affecting the loading of each restraint point and the load monitoring feedback, which is conducive to the judgment of the test, obtain accurate test results, and avoid danger.
[0044] In order to be able to perform force detection, a force sensor 7 can be provided between the connecting rod 4 and the hinge joint 5, and it is designed that the hinge joint 5 and the force sensor 7 are connected by threads for easy disassembly.
[0045] In addition, in order to facilitate the connection between the horizontal single-degree-of-freedom follow-up restraint device for the aircraft structure static and fatigue test and the aircraft and have a self-adaptation function in terms of distance, a screw rod 8 can be provided between the connecting rod 4 and the force sensor 7. Both ends of the screw rod 8 are screwed onto the connecting rod 4 and the force sensor 7. In this way, by turning the screw rod 8, the depth of the screw hole of the screw rod 8 on the connecting rod 4 and the force sensor 7 can be adjusted, and the distance between the hinge joint 5 and the aircraft 6 can be adjusted, so as to connect the hinge joint 5 to the aircraft 6.
[0046] So far, the technical solutions of the present application have 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 fall within the protection scope of the present application.
Claims
1. A single-degree-of-freedom follow-up restraint device in the horizontal direction for static fatigue test of aircraft structure, characterized in that: It comprises a fixed restraining plate (1), a follower slide plate (2), a connecting rod (4), and an articulated joint (5); The fixed restraining plate (1) is fixed on the ground, and has a sliding cavity therein, a side wall on one side has a protruding hole connected to the sliding cavity, and an edge has a strip groove; The follower slide plate (2) is arranged in the slide cavity and is inlaid with a plurality of steel balls (3). The steel balls (3) are in contact with the inner wall of the slide cavity and can slide in the slide cavity. The number of the steel balls (3) is four and they are distributed on the four corners of the follower slide plate (2); One end of the connecting rod (4) is connected to the follower slide plate (2), and the other end extends out from the extension hole and is connected to the hinge joint (5); a gap is left between the connecting rod (4) and the extension hole; The connection between the connecting rod (4) and the follower slide plate (2) is a detachable connection; The articulated joint (5) is articulated to the aircraft (6), and is articulated to the landing gear of the aircraft (6) through a single-ear and double-ear structure in cooperation with a joint bearing (9).
2. The horizontal single-degree-of-freedom follow-up restraint device for static fatigue test of aircraft structure according to claim 1 is characterized in that: The fixed restraint plate (1) is fixed to the ground via a column and is arranged vertically along the X-axis, Y-axis or Z-axis of the aircraft (6).
3. The horizontal single-degree-of-freedom follow-up restraint device for static fatigue test of aircraft structure according to claim 2, characterized in that: The protruding hole on the fixed restraining plate (1) is a circular hole.
4. The horizontal single-degree-of-freedom follow-up restraint device for static fatigue test of aircraft structure according to claim 3, characterized in that: A force sensor (7) is arranged between the connecting rod (4) and the hinge joint (5).
5. The horizontal single-degree-of-freedom follow-up restraint device for static fatigue test of aircraft structure according to claim 4, characterized in that: The articulated joint (5) and the force sensor (7) are connected via threads.
6. The horizontal single-degree-of-freedom follow-up restraint device for static fatigue test of aircraft structure according to claim 5, characterized in that: A screw rod (8) is arranged between the connecting rod (4) and the force sensor (7), and two ends of the screw rod (8) are screwed onto the connecting rod (4) and the force sensor (7).