System and method for measuring flight attitude and surface temperature of ultra-high-speed aircraft

A technology of surface temperature and flight attitude, applied in measurement devices, instruments, etc., can solve problems such as inability to combine aircraft, and achieve the effect of accurate characterization

Pending Publication Date: 2020-05-29
ZHEJIANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The surface temperature can only be measured separately through the sensor measurement, and it cannot be combined with the attitude of the aircraft

Method used

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  • System and method for measuring flight attitude and surface temperature of ultra-high-speed aircraft
  • System and method for measuring flight attitude and surface temperature of ultra-high-speed aircraft
  • System and method for measuring flight attitude and surface temperature of ultra-high-speed aircraft

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Embodiment

[0057] see figure 1 The system for measuring the flight attitude and surface temperature of the ultra-high-speed aircraft of the present embodiment includes a double-pulse laser 1, a spatial filter, a beam expander 3, an ultra-high-speed aircraft 4, a first beam splitter 5, an aircraft attitude measurement module, and an aircraft surface Temperature measurement module, timing control module and calculation module.

[0058] The spatial filter includes a focusing lens 201 and an aperture 202 . The aircraft attitude measurement module includes a neutral attenuator 601 , a narrowband filter 602 , a second beam splitter 603 , a hologram recording camera 604 and a hologram recording camera 605 . The aircraft surface temperature measurement module includes a third beam splitter 701 , a narrowband filter 702 , a lens 703 , a thermal radiation image recording camera 704 , a narrowband filter 705 , a lens 706 and a thermal radiation image recording camera 707 .

[0059] A double-pulse...

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Abstract

The invention discloses a system and a method for measuring the flight attitude and surface temperature of an ultra-high-speed aircraft, and belongs to the technical field of ultra-high-speed aircrafttest parameter measurement. The system comprise a laser for illuminating the ultra-high-speed aircraft, a collimation and beam expanding device used for improving the uniformity of a light source, the ultra-high-speed aircraft which simulates the shape of a rocket, a first beam splitter which is used for splitting ultra-high-speed aircraft signal light into two beams, an aircraft attitude measurement module used for receiving the signal light emitted after the laser irradiates the aircraft and measuring attitude parameters of the aircraft, an aircraft surface temperature measuring module which is used for receiving the radiation light generated after a head of the ultra-high-speed aircraft is pneumatically heated and measuring the aircraft surface temperature, a time sequence control module used for controlling the laser to emit light and receiving CCD synchronous exposure of the signal light; and a calculation module used for obtaining attitude parameters and surface temperature of the aircraft, wherein one beam of the two beams is received by the aircraft attitude measurement module, and the other beam is received by the aircraft surface temperature measurement module.

Description

technical field [0001] The invention relates to the technical field of ultra-high-speed aircraft test parameter measurement, in particular to a system and method for measuring the flight attitude and surface temperature of an ultra-high-speed aircraft. Background technique [0002] With the development of aerospace technology, the speed of aircraft is getting higher and higher, and the frequency of going to and from space is increasing. The shape of the ultra-high-speed aircraft is precisely designed, and the aerodynamic parameters under different attitudes are quite different. Developing aircraft attitude measurement technology, simulating the space environment, and carrying out ground tests of ultra-high-speed aircraft are of great significance to the design and attitude control of aircraft. When the aircraft flies at super high speed, due to the viscous stagnation of the high-speed airflow on the surface of the aircraft, a large amount of frictional heat is generated, fo...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01D21/02
CPCG01D21/02
Inventor 薛志亮吴学成周永刚吴迎春姚龙超
Owner ZHEJIANG UNIV
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