Design Method of Adjusting Mechanism for tbcc Parallel Nozzles Embedded in Partition

A technology of nozzle adjustment and design method, which is applied to machines/engines, jet propulsion devices, etc., can solve the problems of occupation, large aircraft space, and long tail nozzles, and achieves compact space layout, simple structural design, and good thrust performance. Effect

Active Publication Date: 2019-08-27
XIAMEN UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] For hypersonic aircraft, in order to obtain high thrust efficiency when cruising with a large drop pressure ratio, the tail nozzle is usually designed to be relatively long, which takes up a large amount of aircraft space

Method used

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  • Design Method of Adjusting Mechanism for tbcc Parallel Nozzles Embedded in Partition
  • Design Method of Adjusting Mechanism for tbcc Parallel Nozzles Embedded in Partition
  • Design Method of Adjusting Mechanism for tbcc Parallel Nozzles Embedded in Partition

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Embodiment Construction

[0019] The following embodiments will further illustrate the present invention in conjunction with the accompanying drawings.

[0020] The TBCC tail nozzle involved in the present invention is a unilateral expansion parallel nozzle, such as figure 1 As shown, the upper passage is the tail nozzle of the turbine passage, and the lower passage is the tail nozzle of the ram passage. There are partitions and adjustment mechanisms between the passages. The adjustment plate of the adjustment mechanism is rotated to control the throat size and switch of the turbine passage. figure 2 with 3 They are two typical working states of TBCC combined engine tail nozzle. TBCC has multiple working states in the actual voyage. Parallel nozzles need to adapt to different outlet airflow states. By rotating the position of the adjustment plate, the maximum thrust performance can be obtained. TBCC As the flight Mach number increases, the upper channel of the parallel nozzle, that is, the throat of ...

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PUM

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Abstract

The invention relates to TBCC parallel spraying pipes, in particular to a design method of a TBCC parallel spray pipe adjusting mechanism buried in a separation plate. The structure of a motion component is designed, and the adjusting mechanism is composed of an adjusting plate, a connecting rod, an acting barrel and a rotary pair. The acting barrel is arranged in the separation plate, and can move left and right along a rail. The connecting rod, the adjusting plate and the acting barrel are connected through hinges, and the connecting rod, the acting barrel and the rotary pair are located onthe same plane. When the acting barrel move leftwards along the rail, the connecting rod is driven to rotate clockwise, and meanwhile the adjusting plate rotate anticlockwise with the rotary pair as the center, that is, the adjusting plate deflects upwards. When the acting barrel moves rightwards along the rail, the connecting rod is driven to rotate anticlockwise, and meanwhile the adjusting plate rotate clockwise with the rotary pair as the center, that is, the adjusting plate deflects downwards. During the straight reciprocating motion of the acting barrel, reciprocating circumferential swinging of the adjusting plate is achieved. The number of the acting barrel needed by the mechanism is calculated according to the stress state of the mechanism, and a corresponding acting barrel distributing scheme is given.

Description

technical field [0001] The invention relates to a TBCC parallel nozzle, in particular to a design method for a TBCC parallel nozzle regulating mechanism embedded in a partition. Background technique [0002] Hypersonic flight is known as the third "revolution" in aviation history after propeller propulsion flight and jet propulsion flight, and it is the commanding height of aerospace technology in the 21st century. Since the 1950s, various countries have launched a series of hypersonic research programs. Scramjet is the best power choice for hypersonic aircraft because of its simple structure and no need to carry oxidant itself. However, a hypersonic vehicle cannot independently complete the entire mission process from horizontal take-off to hypersonic flight by scramjet engine alone, and must rely on other types of power to help it complete the entire process from take-off to hypersonic flight. Therefore, hypersonic power systems need to integrate scramjet engines, turboj...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K1/11
Inventor 陈荣钱黄阳灿产世宁苏茂禄尤延铖
Owner XIAMEN UNIV
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