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Rotary VTOL Nozzle Based on Quasi-Axisymmetric Throat Offset Aerodynamic Vectoring Nozzle and Its Design Method

A vector nozzle, vertical take-off and landing technology, applied in design optimization/simulation, computer-aided design, calculation, etc., can solve the problems of complex nozzle structure, difficult maintenance, difficult control, etc., to reduce the number of parts and make adjustments complicated The effect of degree, small size and less mechanical structure

Active Publication Date: 2022-01-18
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The structure of the traditional STOL / VTOL nozzle is complex, and the mode switching process is difficult to control and difficult to maintain

Method used

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  • Rotary VTOL Nozzle Based on Quasi-Axisymmetric Throat Offset Aerodynamic Vectoring Nozzle and Its Design Method
  • Rotary VTOL Nozzle Based on Quasi-Axisymmetric Throat Offset Aerodynamic Vectoring Nozzle and Its Design Method
  • Rotary VTOL Nozzle Based on Quasi-Axisymmetric Throat Offset Aerodynamic Vectoring Nozzle and Its Design Method

Examples

Experimental program
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Effect test

Embodiment

[0079] Rotating VTOL nozzle based on a throat-offset aerodynamic vectoring nozzle for a typical configuration.

[0080] Figure 8a , Figure 8b What the two figures show is the specific embodiment of the aerodynamic vectoring nozzle using the mechanically disturbed throat displacement type. The ratio of the minor axis to the major axis of the conical surface of this configuration m=b D / a D =b E / a E =0.85, α=arc cos0.85=58.21°. in, Figure 8a Shown is the internal flow field of a nozzle with no disturbance applied near the throat. It can be seen that the airflow of the present invention turns to about 50 degrees at this time, thus vertical take-off and landing cannot be realized. However, when the spoiler that controls the bowing direction is stretched out, the vector nozzle produces a larger angle of airflow deflection.

[0081] Therefore, the present invention further optimizes the value of m for a specific configuration by further optimizing the design, and in the...

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Abstract

The invention discloses a rotary vertical take-off and landing nozzle based on a quasi-axisymmetry throat offset type aerodynamic vector nozzle and a design method thereof. The rotating vertical take-off and landing nozzle includes a fixed cylinder section, a first rotating cylinder section, and a second rotating cylinder section; the front end of the first rotating cylinder section can be rotatably connected The actuating end of the rotary driving mechanism is connected; the front end of the second rotating cylinder section can be rotatably connected with the tail of the first rotating cylinder section, and is connected with the actuating end of the second rotating driving mechanism. In the level flight mode, the inner flow channel of the nozzle is a typical quasi-axisymmetric throat offset aerodynamic vectoring nozzle with double throat structure, through active and passive aerodynamic disturbance or mechanical disturbance near one throat. In the vertical take-off and landing mode, through the rotation of the first and second rotating cylinder segments, the outlet of the nozzle becomes inclined downward, and under the disturbance near the first throat, the airflow at the outlet of the nozzle is more than 90° turn.

Description

technical field [0001] The invention designs a rotary vertical take-off and landing nozzle based on a quasi-axisymmetry throat offset aerodynamic vectoring nozzle and a design method thereof, and belongs to the technical field of advanced thrust vectoring nozzles of aero-engines. Background technique [0002] With the development of science and technology and the urgent needs of practical applications, short-distance / vertical take-off and landing aircraft have once again entered people's field of vision. The structure of the traditional ST / VTOL nozzle is complex, and the mode switching process is difficult to control and difficult to maintain. Therefore, it is necessary to develop a STOL / VTOL exhaust system with simple structure, light weight, good performance, and meeting the needs of high-speed flight. [0003] At present, the fluid thrust vectoring nozzle has gradually become the research focus and research focus of various countries due to its simple structure and light...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K1/00F02K1/78G06F30/15G06F30/28G06F113/08G06F119/14
CPCF02K1/004F02K1/78G06F30/15G06F30/28G06F2113/08G06F2119/14
Inventor 黄帅徐惊雷宋光韬潘睿丰张玉琪陈匡世曹明磊成前
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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