Design method of axial symmetry adjustable ultrasonic air inlet way based on flexible center body

A design method and air intake technology, applied in computing, mechanical equipment, sustainable transportation, etc., can solve the problem that the design method has not been published.

Active Publication Date: 2017-08-25
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Application Information

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Problems solved by technology

However, the relevant design method for this type of axisy

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  • Design method of axial symmetry adjustable ultrasonic air inlet way based on flexible center body
  • Design method of axial symmetry adjustable ultrasonic air inlet way based on flexible center body
  • Design method of axial symmetry adjustable ultrasonic air inlet way based on flexible center body

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Embodiment

[0059] Such as figure 2 As shown, an axisymmetric supersonic inlet based on a flexible central body with a working Mach number ranging from 2.0 to 3.0, the inlet capture diameter is 100 mm, two-stage external compression cones are used, and the airflow deflection angles are 11° and 13° respectively , the initial angle of the lip cover is 10°, and the design of the flexible central body is adopted. The throat height of the inlet is 14.3mm when the inlet works at Mach 2.0, and the throat height of the inlet is 8.5mm when the inlet is at Mach 3.0. The comparative axisymmetric inlets have the same external compression and capture diameters, while the throat height is fixed at 14.3 mm. Table 1 compares the recovery of the critical total pressure at the outlet of the two inlets when they work at Mach numbers 2.0 and 3.0. It can be seen that after the introduction of the flexible central body design, the total pressure recovery coefficient of the inlet port at Mach number 3.0 has b...

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Abstract

The invention discloses a design method of an axial symmetry adjustable ultrasonic air inlet way based on a flexible center body. The throat deformation amount under different flight Mach numbers of the axial symmetry adjustable ultrasonic air inlet way is determined, and the flexible center body with a braided fabric reinforcing layer is designed; according to the actual flight Mach number range and the flow needs of the air inlet way, the air inlet way throat control needs under different work Mach numbers are rapidly determined, and the corresponding throat deformation amount of an air inlet way center body under the different work Mach numbers is determined; the flexible center body with a nylon wire reinforcing layer wound in a one-way manner is designed, it is ensured that under the maximum inflation pressure, the flexible layer can deform to the needed diameter, the flexible center body diameter deformation condition corresponding to different inflation pressures is obtained, and through the inflation pressure, the axial symmetry adjustable ultrasonic air inlet way with the adjustable air inlet way throat can be accurately adjusted. Through the method, the effective adjustment of the axial symmetry air inlet way throat is achieved, and on the basis of not losing the low capturing characteristics, the property of the air inlet way is obviously improved.

Description

technical field [0001] The invention relates to the design field of a supersonic axisymmetrically adjustable inlet port, in particular to a design method of an axisymmetrically supersonic adjustable inlet port based on a flexible central body. Background technique [0002] The air inlet is an important part of the propulsion system of a supersonic vehicle, and its total static pressure recovery characteristics, flow capture characteristics and resistance characteristics directly affect the working efficiency and operation capability of the propulsion system. At present, it is generally believed that the total pressure recovery coefficient of the intake port has the most direct influence on the thrust of the engine, and every 1% increase in the total pressure recovery coefficient corresponds to a 1.5% increase in engine thrust. However, in order to ensure the starting performance at low Mach number, conventionally designed fixed-geometry supersonic inlets generally have a thr...

Claims

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Application Information

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IPC IPC(8): F02C7/042F02C7/057G06F17/50
CPCF02C7/042F02C7/057G06F30/17Y02T90/00
Inventor 张悦谭慧俊李博王子运刘亚洲盛发家
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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