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Measuring device and system for simulated weight loss unloading force of spacecraft antenna

A technology for simulating weightlessness and measuring devices, which is applied to measuring devices, force/torque/work measuring instruments, instruments, etc., can solve the problems of deformation of the measured parts, affecting the measurement and research of thermal deformation of spacecraft antennas, and achieve the reduction of unloading The effect of extreme force and deformation prevention

Inactive Publication Date: 2018-06-08
西安诺伊传感技术有限公司
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  • Abstract
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Problems solved by technology

[0004] The extreme value of the unloading force between the measuring device and the measured object is large during the measurement of the existing measuring device, which will cause deformation of the measured object, and the deformation caused by the unloading force will affect the thermal deformation measurement and research of the spacecraft antenna

Method used

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  • Measuring device and system for simulated weight loss unloading force of spacecraft antenna
  • Measuring device and system for simulated weight loss unloading force of spacecraft antenna
  • Measuring device and system for simulated weight loss unloading force of spacecraft antenna

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Embodiment Construction

[0036] The present invention will be further described in detail below in conjunction with the accompanying drawings, which are explanations rather than limitations of the present invention.

[0037] see Figure 1-7 , a spacecraft antenna simulation weightlessness unloading force measuring device, is characterized in that, comprises pressure sensor 3, elastic element 5, mount 6 and pressure measurement display instrument 9; Pressure sensor 3 lower ends connect elastic element 5, and elastic element is arranged on installation On the seat 6; the pressure sensor 3 is also connected to the pressure measurement and display instrument 9.

[0038] A sleeve is arranged above the mounting seat 6 , and a sensor connecting piece 4 sliding along the axial direction of the sleeve is arranged in the sleeve, and the sensor connecting piece 4 is arranged between the pressure sensor 3 and the elastic element 5 .

[0039] The sensor connector 4 is configured in a rod shape, and the center axi...

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Abstract

The invention discloses a measuring device and system for a simulated weight loss unloading force of a spacecraft antenna, and belongs to the field of unloading force measurement. The measuring devicecomprises a pressure sensor, an elastic element, a soleplate and a pressure measuring and displaying instrument, the lower end of the pressure sensor is connected to the elastic element, and the elastic element is arranged on the soleplate; and the pressure sensor is also connected to the pressure measuring and displaying instrument. When a tested piece presses the sensor, the elastic element canbuffer a pressure on the sensor, and the extreme value of the unloading force is reduced; and deformation of the tested piece can be prevented during measurement, and the spacecraft antenna is protected.

Description

technical field [0001] The invention belongs to the field of unloading force measurement, in particular to a space vehicle antenna simulated weightless unloading force measurement device and a measurement system thereof. Background technique [0002] During the in-orbit working phase of the spacecraft antenna, under the action of space thermal load, the reflector surface will produce a corresponding deformation, that is, thermal deformation, and thermal deformation is one of the important factors affecting the radio frequency performance of the antenna, especially for antennas that are more sensitive to thermal deformation Even more so. In order to accurately evaluate the influence of the reflector's on-orbit thermal deformation on the antenna's RF performance, it is necessary to conduct a thermal deformation test on the reflector, and then take corresponding measures to reduce the risk of the antenna's on-orbit RF performance deterioration due to thermal deformation. [00...

Claims

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Application Information

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IPC IPC(8): G01L5/00
CPCG01L5/00
Inventor 王馨晨柏宏武韦学勇朱文英刘博学
Owner 西安诺伊传感技术有限公司
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