Test apparatus capable of automatically adjusting scramjet inlet lip opening angle

Abstract

The invention discloses a test apparatus capable of automatically adjusting a scramjet inlet lip opening angle. The apparatus comprises a limited fixed portion and a limited movable portion of an inlet lip, wherein the tail end of the movable portion is pivoted to the wall of an inlet channel through a pivot shaft; a leading screw; a movable nut; a connecting rod which has one end connected with the movable portion and the other part connected with the movable nut; a rotation driving mechanism which drives the leading screw to rotate to enable the movable portion to rotate relative to the pivot shaft so as to change the angle of the inlet lip; an angle sensor; and a control module, wherein a correlation relation between the rotation angle of the leading screw and the angle of the inlet lip is established in advance in the control module, according to the corresponding relation and the rotation angle, detected in real time, of the leading screw, and the rotation driving mechanism is controlled to output a certain rotation driving force, so that the real-time angle of the inlet lip can reach a specific value or change according to a specific rule, and enclosed-loop control is realized. By using the apparatus provided by the invention, the dynamic pneumatic performance of the inlet channel and the self-starting performance of the inlet channel can be obtained when the lip is continuously changed.

Description

technical field [0001] The invention relates to the field of air inlet wind tunnel tests, in particular to a test device capable of automatically adjusting the lip opening angle of a supercombustion inlet. Background technique [0002] The intake port is an important aerodynamic part of the ramjet engine, and its design form and parameters have a significant impact on the engine's operating capability and performance. Hypersonic inlets usually adopt a fixed geometry scheme, and the lip angle generally does not change during flight. However, the actual flight envelope of the inlet generally contains both the lower Mach number and the higher Mach number. The inherent characteristic of the inlet itself is that it must be self-starting at a small lip angle (that is, a small capture area) at low supersonic speeds, and a large lip angle (that is, a large capture area) is required at high supersonic speeds. Get ideal flow and compression performance. [0003] As mentioned above,...

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Problems solved by technology

[0004] In the field of intake port test, since the intake port model has been scaled down, the size has been reduced a lot, and it is often designed into different solid blocks to change the lip of the intake port. This method can only change a limited number of lips step by step. For mouth corners, each air blow can only obtain the aerodynamic performance of the air inlet at one lip angle, resulting in a huge waste of energy; at the same time, it cannot obtain the dynamic characteristics of the air inlet when the lip angle is continuously changed, and it is also impossible to obtain continuously variable lip angles. Self-starting performance of inlet port

[0005] In recent years, some designers have also tried to install a worm-worm combined motor on the intake port to drive the lip to rotate through the forward and backward movement of the worm, but this direct drive method has some disadvantages, such as the drive mechanism must be installed near the lip, which is harmful to the The flow field at the inlet of the inlet has a great influence, making the test results inaccurate

On the other hand, this method cannot install an angle sensor, that is, it cannot measure the lip angle in real time during the test, so the test system can only be controlled in an open-loop manner, and closed-loop control cannot be realized, and its anti-interference ability is poor

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