Truss type structure loading test platform
A technology of loading test and truss, which is applied in the direction of the launching device, can solve the problems that have not been found in literature or data, and achieve the effects of reducing the arm of force, enhancing the stability of the structure, and increasing the strength
Pending Publication Date: 2022-06-03
XIAN SPACE ENGINE CO LTD
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Problems solved by technology
No relevant literature or materials have been found on a loading test platform that can withstand large-scale loading tests and can be docked with different devices to be tested
Method used
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[0033] The features and advantages of the present invention will become clearer and clearer through the detailed description of the present invention below.
[0034] The word "exemplary" is used exclusively herein to mean "serving as an example, embodiment, or illustration." Any embodiment described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments. While various aspects of the embodiments are shown in the drawings, the drawings are not necessarily drawn to scale unless otherwise indicated.
[0035] like figure 1 and figure 2 As shown, it is a loading test platform for a truss structure of the present invention. The structure is used to perform a static test on the device under inspection to verify the strength and reliability of the device under inspection. The device under inspection cooperates with the loading test platform of the present invention. It can simulate the missile launch environment. The loading tes...
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The invention discloses a truss type structure loading test platform which comprises an oil cylinder seat and a bottom beam. The upper end of the oil cylinder seat is used for placing the loading oil cylinder, and the lower end is fixedly connected with the bottom beam; the bottom beam comprises an integral type cross beam, a sectional type cross beam, an integral type reinforcing beam and a sectional type reinforcing beam; the sectional type cross beam comprises a first cross beam section and a second cross beam section, the first cross beam section and the second cross beam section are connected to the two sides of the integral type cross beam respectively and are perpendicular to the integral type cross beam, and the integral type cross beam and the sectional type cross beam form a cross-shaped structure; the integral type reinforcing beam is fixed below the sectional type cross beam, the sectional type reinforcing beam is fixed below the integral type cross beam, and the sectional type reinforcing beam comprises a first section of reinforcing beam and a second section of reinforcing beam which are located on the two sides of the integral type reinforcing beam respectively; the detected device is fixedly installed on the bottom beam. The device is simple in structure and convenient to disassemble, can meet the requirements of large-scale loading tests, and has universality for static tests of various detected devices.
Description
technical field [0001] The invention belongs to the technical field of large-scale loading tests, and in particular relates to a truss-type structure loading test platform. Background technique [0002] In order to simulate the real loading situation of the missile on the launcher, a corresponding test platform is required, which can withstand the self-weight of the missile, and also needs to be consistent with the interfaces of various tested devices. Since the missile itself is quite heavy, and for safety reasons, there must be a corresponding safety factor, so the test platform is required to have sufficient strength and rigidity to approximate a rigid structure; in addition, in order to better simulate the working environment of the launch silo, The test platform is required to be detachable. No relevant literature or information on a loading test platform that can withstand large-scale loading tests and can be docked with different devices to be tested has yet been fou...
Claims
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Login to View More IPC IPC(8): F41F1/00
CPCF41F1/00
Inventor 许桐晔范文强段立立董飞李华杜疆许静
Owner XIAN SPACE ENGINE CO LTD