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Rudderpost heat sealing test device

A test device and heat sealing technology, which is applied in the direction of measuring devices, testing of mechanical parts, testing of machine/structural parts, etc., can solve the problem of no experience to follow, rudder shaft heat sealing test without arc heating ground simulation test, etc. problem, to achieve the effect of increasing the range

Active Publication Date: 2015-12-23
CHINA ACAD OF AEROSPACE AERODYNAMICS
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  • Abstract
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  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The arc heating test equipment has become the preferred heating equipment due to its advantages of realistic simulated gas composition, wide parameter adjustment range, and long-term heating. However, no special arc heating ground simulation test has been conducted for the heat sealing test of the rudder shaft, so there is no experience to follow

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  • Rudderpost heat sealing test device
  • Rudderpost heat sealing test device

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Embodiment Construction

[0013] Such as figure 1 As shown, the rudder shaft heat seal test device includes an arc heater 1, a supersonic nozzle 2, a conduit 3, a water-cooling cap tooling 4 and a rudder shaft model 5.

[0014] The nozzle 2 is located between the arc heater 1 and the duct 3, and is used to accelerate the high temperature and high pressure air heated by the arc heater 1 to form a supersonic airflow; the duct 3 and the water-cooling cap tooling 4 and the rudder shaft model with the rudder base plate 5 Direct connection, its function is to simulate the outflow by internal flow, limit the expansion of high-temperature air flow, increase the test simulation parameters, and improve the test simulation ability; the water-cooling cap tooling 4 plays the role of protecting the rudder shaft model 5, and is on the rudder base plate of the rudder shaft model Air flow channels are formed on the surface. Among them, the supersonic nozzle 2 is a Laval nozzle, and when the upstream and downstream reach a...

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Abstract

A rudderpost heat sealing test device provided by the present invention comprises an arc heater, a supersonic nozzle, a conduit, a water cooling cap tooling and a rudderpost model. The supersonic nozzle is connected between the arc heater and the conduit and is used to accelerate the high-temperature high-pressure air heated by the arc heater to from a supersonic air flow, and the conduit is directly connected with the water cooling cap tooling and the rudderpost model with a rudder substrate, thereby forming an air flow channel. According to the present invention, the rudderpost heat sealing test device of the arc heater is designed by depending on an arc heating ground test device, tightly combining the special structure of a rudderpost and the special demands of the test, and taking a conduit test technology as the reference, thereby realizing the effects of limiting the high-temperature air flow expansion, and improving the test simulation capability.

Description

Technical field [0001] The invention relates to a device for conducting heat-sealing ground simulation test of a high-speed aircraft rudder shaft, belonging to the field of aircraft ground simulation test devices. Background technique [0002] After decades of development, various high-temperature heat-sealing components have been widely used in space shuttles, X-37B, HTV-2, X-51 and other aircraft. Among them, the high-temperature and long-term heat sealing of the rudder shaft section and movable parts It is the weak link of the thermal protection system. Due to the swing of the rudder during flight, the heating environment of the entire rudder shaft area belongs to unsteady gap heating. The rudder and its components and the supersonic high-temperature air flow produce strong shock boundary layer interference effects. The flow field in the rudder shaft area is very complicated. It is difficult to evaluate the performance and design of the rudder shaft high-temperature heat-seal...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M13/00
Inventor 陈连忠张骞杨忠凯
Owner CHINA ACAD OF AEROSPACE AERODYNAMICS