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Method for designing hypersonic internal parallel three-channel air inlet channel adjusting mechanism

A hypersonic, adjusting mechanism technology, applied in mechanical equipment, gas turbine devices, jet propulsion devices, etc., can solve the problems of increased design difficulty and structural complexity of air intake control, and achieves light weight, simple and practical structure, and solves the problem of starting effect of the problem

Active Publication Date: 2018-12-28
XIAMEN UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Although the TriJet engine can effectively solve the relay problem of the dual-channel TBCC, its inherent three-channel structural layout increases the structural complexity, and the intake control between different modes increases the design difficulty

Method used

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  • Method for designing hypersonic internal parallel three-channel air inlet channel adjusting mechanism
  • Method for designing hypersonic internal parallel three-channel air inlet channel adjusting mechanism
  • Method for designing hypersonic internal parallel three-channel air inlet channel adjusting mechanism

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Embodiment Construction

[0025] The following embodiments will further illustrate the present invention in conjunction with the accompanying drawings.

[0026] Such as figure 1 with 2 As shown, the hypersonic internal parallel three-channel inlet includes an external pressure section 2, a rotating shaft 3, a splitter section 4, a turbine channel 9, a rocket channel 8, a ram channel 7, and a partition 5 between the turbine channel and the rocket channel , the partition plate 6 between the rocket channel and the stamping channel, the baffle plate groove 18 on the wall surface of the air inlet. Such as image 3 As shown, the hypersonic internal parallel three-channel inlet adjustment mechanism includes a rotating shaft 3, a main splitter plate 11, a motor 12, a baffle plate 13, a driving rack 14, a driven rack 15, an auxiliary splitter plate 16 and a rotary spring 10, Wherein, the main splitter plate 11 , the driving rack 14 is connected with the baffle plate 13 , and the auxiliary splitter plate 16 i...

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Abstract

The invention relates to a hypersonic flight vehicle, in particular to a method for designing a hypersonic internal parallel three-channel air inlet channel adjusting mechanism. The shape and the position of a hypersonic internal parallel three-channel air inlet channel, the shape and the length of a flow distribution plate, a driving rack, a driven rack and a baffle, the specific position and a fixing mode of the adjusting mechanism in the air inlet channel, a power scheme of the adjusting mechanism and a rotating mode of the flow distribution plate are designed. The flight vehicle has turbine, rocket and stamping working modes; air incoming flow needs to enter different channels so as to meet the requirements of the corresponding working modes; a gear is driven by a motor to drive the flow distribution plate to rotate for adjusting the conversion among the modes; the problem of starting under a wide Mach number is solved; the structure is simple and practical; and the weight is light. The flow distribution plate is divided into a main flow distribution plate and an auxiliary flow distribution plate; during transfer, the baffle plays a role of supporting the driving rack, and airflow is prevented from entering a dead zone above the main flow distribution plate; and the auxiliary flow distribution plate ensures the natural transition of the air flow in a rocket channel, so that the air flow is relatively smooth, and the loss is relatively small.

Description

technical field [0001] The invention relates to a hypersonic aircraft, in particular to a design method for a hypersonic internal parallel three-channel inlet regulating mechanism. Background technique [0002] The existing power systems of various types of aircraft, including piston engines, turbojet engines, ramjet engines and rocket engines, all have their own operating ranges and performance advantages and disadvantages. Combining the characteristics of the above engines, in order to obtain a wider working range and better performance, researchers have proposed turbine-based combined cycle engines (abbreviated as TBCC), air turbine rocket / ramjet combined cycle engines ( ATR for short) and rocket-based combined cycle engine (RBCC for short) and other combined cycle power systems, and a large number of researches and experiments have been carried out (Zhang Mengzheng, Li Ping, Chen Zukui. Challenges and prospects of combined cycle power systems[J]. Rocket Propulsion, 2009...

Claims

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Application Information

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IPC IPC(8): F02C7/057
Inventor 尤延铖楚国庆邱若凡张旭
Owner XIAMEN UNIV
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