A throat variable supersonic inlet and a vehicle using the same

Abstract

This invention relates to a supersonic air intake with a variable throat. The intake's constriction section is designed with a venting chamber. A throat adjustment device is installed within the venting chamber and the air body, allowing the supersonic air intake to adjust its throat area using the pressure difference between the venting chamber and the incoming air pressure. This invention utilizes the pressure difference between the venting chamber pressure and the incoming air pressure to adjust the throat area, achieving throat area adjustment without the need for additional power-assisted adjustment mechanisms. By adjusting the intake throat area, the supersonic air intake can automatically start at low incoming Mach numbers, reducing overflow losses at low Mach numbers. At high incoming Mach numbers, it can effectively decelerate and pressurize the incoming air, improving the intake's performance and demonstrating significant engineering application value.

Description

Technical Field

[0001] This invention relates to a variable throat supersonic air intake, particularly suitable for variable throat supersonic air intakes utilizing venting chamber pressure and aircraft using the device. Background Technology

[0002] The supersonic inlet is a crucial aerodynamic component of supersonic air-breathing aircraft, and its performance significantly impacts engine operating capabilities and overall performance. Constant-geometry supersonic inlets are generally designed with the maximum Mach number as the design benchmark. At maximum Mach number, to ensure inlet performance under high-Mach-number inflow conditions, the inlet's internal contraction ratio cannot be too small. However, at lower inflow Mach numbers, the inlet's internal contraction ratio required for self-starting is too large, resulting in the inlet's capture flow exceeding its throughput capacity, potentially leading to induced airflow and inability to start. This contradiction—the inlet's internal contraction ratio cannot be too small at high inflow Mach numbers, nor too large at low inflow Mach numbers—detrimentally affects the widening of the inlet's operating range. Addressing this contradiction is a critical issue that needs to be resolved for wide-range Mach-number operating inlets.

[0003] Currently, common technical approaches to adjusting the geometry of supersonic inlets include moving center cone geometry schemes, rotating lip forms, or using a power source to rotate the top plate to adjust the throat area. All of these methods require displacement sensor devices and power source devices, resulting in complex structures. Summary of the Invention

[0004] Purpose of the invention: In order to simplify the geometry adjustment device of the supersonic air intake, and to adjust the throat area of ​​the supersonic air intake by adjusting the pressure difference of the venting chamber, this invention provides a variable throat supersonic air intake and an aircraft using the device, which is used to improve the working performance and start-up problems of the wide Mach number supersonic air intake.

[0005] Technical Solution: A supersonic air intake with a variable throat area, wherein the constriction section of the air intake is designed with a venting chamber, and a throat adjustment device is installed in the venting chamber and within the air body. This allows for the adjustment of the throat area using the pressure within the venting chamber, creating a supersonic air intake with a variable geometry. This device can effectively utilize the airflow pressure within the venting chamber to adjust the throat area, forming a variable geometry air intake. The variable throat area air intake of this invention can significantly improve the performance of supersonic air intakes at a wide Mach number range.

[0006] Furthermore, the adjustment device includes: a venting chamber, a piston, a first hinge, and a second hinge; the venting chamber is connected to the throat of the air intake through a venting gap; the venting chamber is connected to the piston; the pressure in the venting chamber can be sensed in real time to drive the piston rod to move and realize the adjustment of the throat area.

[0007] Furthermore, both the first hinge and the second hinge are arranged inside the machine body, wherein the first hinge is located at the throat position; and the second hinge is located near the root of the venting chamber.

[0008] The venting slit is located on the constricted section of the air intake duct, serving as a communication channel between the venting chamber and the air intake duct.

[0009] Furthermore, the connection points between the first and second hinges and the fuselage are made of flexible materials, resulting in a smooth transition of the air intake surface.

[0010] Furthermore, a limit mechanism is provided on the piston rod of the piston to limit its maximum movement distance, thereby limiting the reduction in the intake throat area.

[0011] Furthermore, the venting slits are configured as several, the specific number of which is determined by the performance of the air intake.

[0012] The present invention also proposes a supersonic aircraft, wherein the air intake of the aircraft adopts a supersonic air intake with the throat area adjusted by the pressure of the venting chamber as described above.

[0013] Beneficial technical effects: This invention proposes an adjustable throat area device, which utilizes the pressure difference between the venting chamber pressure and the incoming flow pressure to adjust the throat area of ​​a variable geometry supersonic inlet, achieving throat area adjustment without the need for other additional power-assisted adjustment mechanisms; by adjusting the throat area of ​​the inlet, the supersonic inlet can automatically start at low incoming flow Mach numbers, reducing overflow losses at low incoming flow Mach numbers; at high incoming flow Mach numbers, it can effectively decelerate and pressurize the incoming flow, improving the working performance of the inlet, and has good engineering application value. Attached Figure Description

[0014] Figure 1 This is a schematic diagram of the structure of the present invention;

[0015] Figure 2 This is a schematic diagram illustrating the working principle of the present invention;

[0016] Among them, 1-fuselage, 2-intake lip cover, 3-venting slit, 4-venting chamber, 5-piston, 6-first hinge, 7-second hinge, 8-supersonic intake. Detailed Implementation

[0017] The technical solution of the present invention will now be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0018] Please refer to Figures 1-2As shown, this invention discloses a supersonic air intake duct that utilizes the airflow pressure of the venting chamber to adjust the throat area.

[0019] like Figures 1-2 As shown, the supersonic air intake that uses the airflow pressure of the venting chamber to adjust the throat area and the aircraft using the air intake include a fuselage 1, a supersonic air intake 8, an air intake lip 2, a venting chamber 4, a venting slot 3, a piston 5, a first hinge 6, and a second hinge 7.

[0020] An aircraft employs an air intake designed as described above. At low incoming Mach numbers, the position of piston 5 in the throat area is the initial position. At this time, the supersonic air intake 8 is relatively small in contraction, and the airflow capacity of the air intake can support the flow rate captured by the air intake. The air intake can achieve self-starting. When the aircraft accelerates, the back pressure at the air intake outlet increases, and the air intake enters a subcritical state. The pressure in the constricted section of the air intake increases, and the airflow enters the venting chamber 4 through the venting slot 3. The pressure P in the venting chamber increases, causing piston 5 to move downward, i.e., along the Y-axis (here, the incoming flow direction is defined as the X-axis, and the direction perpendicular to the X-axis is the Y-axis). This pushes the first hinge 6 downward, thereby causing the throat to contract and changing the throat area. In specific implementation, a second hinge 7 is also provided between the first hinge 6 and the venting chamber 4 to facilitate the adjustment of the throat area. After changing the throat area, the aircraft speed increases, the Mach number of the incoming flow increases, the throat area decreases, and the intake duct contraction ratio increases, which can better decelerate and pressurize the incoming flow and improve the working performance of the intake duct.

[0021] With the structure designed in this invention, the size of the air intake throat area changes with pressure when the aircraft changes its flight state, achieving self-adaptation. Under acceleration, the air intake throat area decreases, the contraction ratio increases, and the compression performance is improved, enabling the aircraft to fly across a wide speed range.

[0022] In the structure designed in this invention, the area before the second hinge 7 is a fixed geometry compression surface, while the area between the first hinge 6 and the second hinge 7 is a variable geometry compression surface. During acceleration, the back pressure in the intake increases, and the piston rod moves downward under force, causing the first hinge 6 to move vertically downward, which reduces the throat height and area. At this time, the compression surface between the first hinge 6 and the second hinge 7 undergoes corresponding deformation, and the angle of the compression surface increases, which is more conducive to high Mach number flight.

[0023] Furthermore, in the specific design, the venting chamber is an irregularly shaped cavity, and its shape can be adjusted according to the structural distribution within the fuselage. For example... Figure 2 In this configuration, P acts on the pressure plate. The cavity beneath the pressure plate is not a sealed container and has an outlet, which facilitates the piston's operation. The pressure plate area s cannot be too small; its specific area is affected by the aircraft's flight status.

[0024] The above specific embodiments or examples are only used to explain the technical solutions of the present invention and are not intended to limit the present application. Parts not described in detail are considered to be conventional technical means or common knowledge in the field. Those skilled in the art should understand that, based on the design concept of the present application, it is possible to make adaptive modifications to the technical solutions described in the foregoing embodiments or to make equivalent substitutions for some or all of the technical features. These modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the various embodiments of the present invention.

Claims

1. A supersonic air intake with a variable throat, characterized in that, The intake duct constriction section is designed with a venting chamber. A throat adjustment device is installed in the venting chamber and inside the machine body to adjust the throat area of ​​the supersonic intake duct using the pressure of the venting chamber. The adjustment device includes a venting chamber and a piston. The venting chamber is connected to the intake duct throat through a venting slit. The venting chamber is conductive to the piston. The pressure in the venting chamber can be sensed in real time to drive the piston rod to move and adjust the throat area. The adjustment device also includes a first hinge and a second hinge. The first hinge and the second hinge are both arranged inside the machine body. The first hinge is located at the throat position, and the second hinge is located near the root of the venting chamber.

2. The variable throat supersonic air intake as described in claim 1, characterized in that, The first and second hinges are made of flexible material at the connection points with the fuselage, which allows for a smooth transition of the air intake surface.

3. The variable throat supersonic air intake as described in claim 1, characterized in that, The piston rod of the piston is equipped with a limit mechanism to limit its maximum movement distance, thereby limiting the reduction in the intake throat area.

4. The variable throat supersonic air intake as described in claim 1, characterized in that, The venting slit is located on the constricted section of the air intake duct, serving as a channel connecting the venting chamber and the air intake duct.

5. The variable throat supersonic air intake as described in claim 4, characterized in that, The venting slits are configured as several, the specific number of which is determined by the performance of the air intake.

6. A supersonic aircraft, characterized in that, The air intake of the aircraft adopts a supersonic air intake with a variable throat as described in any one of claims 1-5.

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