A load applying device for fuselage panel frame
A fuselage panel and application device technology, applied in the direction of aircraft component testing, etc., can solve the problems of inability to apply fuselage panel frame loads, restricting the selection of fuselage panel structures and verification tests, etc., and achieves convenient processing and installation. , low cost, overcoming the effect of small loading space
Active Publication Date: 2022-03-29
CHINA AIRPLANT STRENGTH RES INST
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Problems solved by technology
However, the test device at this stage is still unable to apply the frame load of the fuselage panel, which seriously restricts the selection and verification test of the fuselage panel structure in the development of civil aircraft.
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[0028] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the invention. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below ...
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The invention discloses a load applying device for a fuselage wall plate frame, which belongs to the technical field of aircraft structure strength tests. The device includes a skeleton, a guide loading plate and an actuator, wherein the skeleton is in a semicircular structure, and the two ends are respectively fixed on the two straight sides of the fuselage panel frame, and close to the two ends The position of the upper part is provided with a lever fulcrum; two guide loading plates are respectively arranged at the two lever fulcrums, any guide loading plate includes a middle part and two end parts, and the middle part is rotatably set on the lever fulcrum, One end is connected to the tensile load application point of the fuselage panel, and the other end is hinged to the output shaft of the actuator; the bases of the two actuators are butted together. The fuselage panel frame load applying device of the invention is easy to process and install parts, has low cost, can apply tensile loads along the tangent direction of the fuselage panel frame, equal in size and opposite in direction, and overcomes the difficulty of narrow loading space.
Description
technical field [0001] The invention belongs to the aircraft structure strength test technology, in particular to a fuselage wall frame load applying device. Background technique [0002] Internal pressure load is a very important repetitive load, which has a great influence on the fatigue and damage tolerance characteristics of the fuselage structure. Many pieces of fuselage panel internal pressure load tests are planned in the development of civil aircraft. The fuselage panels are assembled from skins, stringers and frames. When the fuselage panel bears the internal pressure load, the skin and the girder deform outward together, part of the internal pressure load is borne by the circumferential tension of the skin, and the rest is transmitted to the frame by the girder and the skin, and the frame bears it, resulting in a frame The hoop tension, so the fuselage panel frame load needs to be applied during the test. However, the test device at this stage is still unable to ...
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IPC IPC(8): B64F5/60
CPCB64F5/60
Inventor 臧伟锋董迪党堃米晓红
Owner CHINA AIRPLANT STRENGTH RES INST