A wide-range hypersonic air intake with dual-stage continuously adjustable lip mask and throat passage, and its control and design methods.

Abstract

This invention provides a wide-range hypersonic inlet with a dual-stage continuously adjustable lip and throat, along with its control and design methods. It employs a multi-link hinged mechanism for the inlet's inner wall design and an independently adjustable lip. The throat area is cleverly controlled indirectly through a rotating arm, and the capture area is controlled by the translational lip. This allows for simultaneous and independent adjustment of the inlet's compression and capture area. The structure is stable and highly controllable, ensuring that the inlet's capture flow rate and compression performance meet specifications at various Mach numbers. This achieves good inlet start-up performance, broadens the inlet's operating range, and is also suitable for exploring the inlet's ultimate performance in wind tunnel tests.

Description

Technical Field

[0001] This invention relates to the field of hypersonic inlet design, specifically to a wide-range hypersonic inlet with dual-stage continuously adjustable lip mask and throat passage, and its control and design methods. Background Technology

[0002] The air intake is a component in an aircraft that delivers high-quality gas to the engine. As an important part of the supersonic propulsion system, designing an air intake that can operate stably while having high performance indicators is of great significance for improving the overall performance of the aircraft engine.

[0003] For wide-speed-range aircraft, the capture flow rate and compression performance at each operating point must meet requirements. Supersonic inlets generally use the maximum flight Mach number as the design state. Under this condition, the inlet performance reaches the optimal solution with unchanged geometry, and this serves as the reference profile for further design. When the Mach number is lower than the design Mach number, the increased compression shock angle leads to increased inlet overflow and decreased capture flow rate, resulting in a flow coefficient lower than the required specification. Simultaneously, the inlet compression decreases, the throat Mach number is higher, the resistance to back pressure weakens, and the supercritical state becomes more unstable. When the Mach number decreases, the self-starting contraction ratio decreases, and the throat under the design state may experience throat blockage, failing to guarantee normal inlet operation. Therefore, ensuring that the inlet capture flow rate and compression performance meet specifications under normal operating conditions is extremely important.

[0004] For traditional fixed-geometry or variable-geometry single-mechanism inlet ducts, it is difficult to simultaneously achieve both capture flow rate and compression performance. They can only meet the requirements under design conditions, making it difficult to improve performance under non-design conditions and adapt to the impact of frequent changes in operating conditions. For example, Chinese invention patent CN 107605601 A discloses a "supersonic inlet duct with synchronous adjustment of capture area and throat area." When adjusting the throat section using a four-stage linkage mechanism, a tilting groove drives the lip cover to rotate, achieving synchronous adjustment of the inlet duct throat area and capture area. However, achieving synchronous adjustment also imposes geometric constraints on the two independent adjustment mechanisms of the inlet duct. One inlet throat area can only correspond to one inlet capture area, making it impossible to study with more combinations of mechanism positions. Furthermore, it is impossible to explore the working boundaries and ultimate performance of the inlet duct during wind tunnel testing. Summary of the Invention

[0005] Purpose of the invention: The purpose of this invention is to provide a wide-range hypersonic air intake with dual-stage continuously adjustable lip mask and throat passage, as well as its control method and design method.

[0006] Technical Solution: A wide-range hypersonic inlet includes an inlet inner wall surface, a lip mask, an inlet inner channel formed by the inlet inner wall surface and the lip mask, a horizontally movable isotropic section extending rearward from the inlet inner channel, and a horizontally fixed section fixedly disposed inside the horizontally movable isotropic section. The inlet inner wall surface includes a first compression surface located at the inlet of the inlet inner channel, a second isentropic compression surface extending rearward from the first compression surface, a movable inner contraction section hinged to the rear end of the second isentropic compression surface, a movable throat section hinged to the rear end of the movable inner contraction section, and a section hinged to... The movable throat section has a movable diffuser section at its rear end; the rear end of the movable diffuser section is hinged to the horizontally movable straight section, which is slidably disposed on the horizontally fixed section; the movable throat section is provided with a throat drive module inside, which drives the movable throat section to move closer to or away from the lip mask; the lip mask includes a fixed lip mask located at the rear end of the air intake channel, a horizontally movable lip mask slidably disposed on the fixed lip mask, and a lip mask drive module connected to the horizontally movable lip mask, which drives the horizontally movable lip mask to move back and forth.

[0007] Specifically, the throat drive module includes two rotating arms hinged at one end to the inner side of the movable throat segment, a first horizontal push rod hinged to the other end of the rotating arms, and a first drive device connected to the first horizontal push rod.

[0008] Specifically, the lip mask driving module includes a second horizontal push rod connected to the rear end of the horizontally movable lip mask and a second driving device connected to the second horizontal push rod.

[0009] Specifically, the horizontally movable straight section is slidably set and limited on the horizontally fixed section via a horizontal guide rail.

[0010] Specifically, the throat drive module further includes a first translational limiting groove, in which the first horizontal push rod is disposed.

[0011] Specifically, the lip mask driving module also includes a second translational limiting groove, and the second horizontal push rod is disposed in the second translational limiting groove.

[0012] Specifically, the two rotating arms are of equal length, and the distance between the two points where the two rotating arms are hinged to the movable throat section and the first horizontal push rod is equal.

[0013] The present invention also provides a control method for the above-mentioned wide-range hypersonic inlet, comprising the following steps:

[0014] When the flight Mach number is subsonic, the throat drive module moves the movable throat section away from the lip cover to the maximum distance, while the lip cover drive module moves the horizontally movable lip cover forward to the foremost position. At this time, the throat area and the intake capture area are both at their maximum.

[0015] When the flight Mach number increases to the intake duct start-up Mach number, the throat drive module drives the movable throat section to move closer to the lip mask, while the horizontal movable lip mask remains stationary. At this time, the throat area becomes smaller, and the intake duct capture area remains at its maximum.

[0016] As the flight Mach number increases to the design Mach number, the throat drive module drives the movable throat section to continue moving closer to the lip mask, while the lip mask drive module drives the horizontally movable lip mask to move backward. At this time, the throat area and the intake capture area decrease.

[0017] When the flight Mach number reaches the design Mach number, the movable throat section approaches the lip mask to the minimum distance, and the horizontally movable lip mask is located at the rear end. At this time, the throat area and the intake capture area are both at their minimum.

[0018] When the throat working Mach number is greater than the preset working Mach number, the throat drive module moves the movable throat section closer to the lip mask, reducing the throat area; when the throat working Mach number is less than the preset working Mach number, the throat drive module moves the movable throat section away from the lip mask, increasing the throat area; when the intake duct capture flow is less than the required flow, the lip mask drive module moves the horizontally movable lip mask forward, increasing the intake duct capture area.

[0019] The present invention also provides a design method for the above-mentioned wide-range hypersonic inlet, comprising the following steps:

[0020] Based on the aerodynamic performance requirements of the inlet, the positions of the first-stage compression surface, the second-stage isentropic compression surface, and the front lip of the horizontal movable lip are designed to obtain the reference profile of the inlet under the design Mach number condition. The reference profile under this condition is obtained by simulation verification and adjustment.

[0021] Calculate the reference flow field of the three-dimensional binary compression surface formed by the first compression surface and the second isentropic compression surface, and determine the lip coordinates of the inlet.

[0022] The intake duct performance under various operating conditions was calculated, and the corresponding positions of the movable throat section and the lip mask were obtained through simulation iteration. Specifically, when the throat operating Mach number is greater than the design Mach number, the throat drive module moves the movable throat section closer to the lip mask, reducing the throat area; when the throat Mach number is less than the design Mach number, the throat drive module moves the movable throat section away from the lip mask, increasing the throat area. This process is iterated until the throat Mach number meets the requirements, thus obtaining the optimal throat area for each operating condition.

[0023] Beneficial effects: Compared with the prior art, the significant effects of this invention are: the intake duct inner wall design with multi-link hinge mechanism and independently adjustable lip cover design can simultaneously and independently adjust the intake duct compression and capture area, and the structure is stable and highly controllable, ensuring that the intake duct capture flow and compression performance meet the target requirements under various Mach number conditions, achieving better start-up performance of the intake duct, expanding the working range of the intake duct, and is also suitable for exploring the limit performance of the intake duct in wind tunnel tests. Attached Figure Description

[0024] Figure 1 This is a schematic diagram of the overall structure of the wide-speed-range hypersonic air intake of the present invention.

[0025] Figure 2 This is a line graph showing the variation of the air intake throat area with flight Mach number in an embodiment of the present invention.

[0026] Figure 3 This is a line graph showing the variation of the inlet flow coefficient with flight Mach number in an embodiment of the present invention.

[0027] Figure 4 This is a Mach number graph of the air intake duct in an embodiment of the present invention under Mach number 8 conditions.

[0028] Figure 5 This is a Mach number graph of the air intake duct in an embodiment of the present invention under Mach number 6.

[0029] Figure 6 This is a Mach number graph of the air intake duct in an embodiment of the present invention under Mach number 4 conditions.

[0030] Figure 7 This is a Mach number graph of the air intake duct in an embodiment of the present invention under Mach number 2 conditions. Detailed Implementation

[0031] The present invention will be further explained below with reference to the accompanying drawings and specific embodiments.

[0032] Example 1

[0033] Please see Figure 1As shown, this embodiment provides a wide-range hypersonic air intake with dual-stage continuously adjustable lip mask and throat passage, including an inner wall surface of the air intake, a lip mask, an inner channel of the air intake formed by the inner wall surface of the air intake and the lip mask, a horizontally movable straight section 15 extending rearward from the inner channel of the air intake, and a horizontally fixed section 19 fixedly disposed inside the horizontally movable straight section 15. A horizontally movable isotropic section 15 is slidably mounted on and limited by a horizontal guide rail 18 on the horizontally fixed section, and can slide back and forth along the horizontal guide rail 18. The inner wall of the intake duct includes a first compression surface 8 located at the inlet of the intake duct, a second isentropic compression surface 9 extending rearward from the first compression surface 8, a movable inner contraction section 10 hinged to the rear end of the second isentropic compression surface 9, a movable throat section 11 hinged to the rear end of the movable inner contraction section 10, and a movable diffuser section 13 hinged to the rear end of the movable throat section 11. The first compression surface 8 is used to receive the oblique shock wave 1, and the second isentropic compression surface is used to receive the isentropic compression wave 2. The rear end of the movable diffuser section 13 is hinged to the horizontally movable isotropic section 15. The lower end of the movable throat section 11 is connected to the throat drive module. In this embodiment, the throat drive module includes two rotating arms 12 hinged at one end to the lower part of the movable throat section 11, a first horizontal push rod 14 hinged to the other end of the rotating arm 12, and a first drive device 17 connected to the first horizontal push rod 14. The first horizontal push rod 14 is disposed in the first translational limiting groove 16. The lip cover includes a fixed lip cover 4 located at the rear end of the inner channel of the air intake, a horizontally movable lip cover 3 slidably disposed on the fixed lip cover 4, and a lip cover drive module connected to the horizontally movable lip cover 4. In this embodiment, the lip cover drive module includes a second horizontal push rod 5 connected to the rear end of the horizontally movable lip cover 3 and a second drive device 7 connected to the second horizontal push rod 5. The second horizontal push rod 5 is disposed in the second translational limiting groove 6.

[0034] To further explain the working principle of this embodiment, the two rotating arms 12 are of equal length, and the distance between the two points where the two rotating arms 12 are hinged to the movable throat section 11 and the first horizontal push rod 14 is equal, forming a parallelogram. When the first driving device 17 drives the first horizontal push rod 14 forward, it drives the rotating arms 12 to bring the movable throat section 11 closer to the lip cover, thereby causing the intake throat area to gradually change from the maximum to the minimum. The movable inner contraction section 10 rotates counterclockwise around the front hinge, and the movable diffuser section 13 and the horizontal movable straight section 15 move to the left accordingly, and are horizontally limited by the horizontal guide rail 18, thereby gradually reducing the intake throat area. When the second driving device 7 drives the second horizontal push rod 5 forward, it drives the horizontal movable lip cover 3 to move forward. The fixed lip cover 4 ensures that the geometric continuity of the inner surface remains unchanged during the adjustment process, thereby increasing the capture area.

[0035] In this embodiment, the driving device can be a drive motor, the horizontal push rod can be a lead screw, or the driving device can be a hydraulic device and the horizontal push rod can be a hydraulic rod. The above embodiments are only used to illustrate the solution of this embodiment and are not intended to limit its function.

[0036] Please see Figure 2-3 As shown, Figure 2 This is a line graph showing the variation of the throat area (dimensionless) of the air intake designed according to the above scheme with the flight Mach number. Figure 3 The graph shows the flow coefficient of the inlet as a function of flight Mach number. The wide-range hypersonic inlet provided in this example exhibits good performance and controllability under various flight Mach number conditions.

[0037] Example 2

[0038] This embodiment provides a control method for a wide-speed-range hypersonic inlet as described in Embodiment 1, including the following steps:

[0039] When the flight Mach number is subsonic, the first horizontal push rod is pushed to the rear end, causing the movable throat section to move away from the lip cover to the maximum distance. At the same time, the second horizontal push rod is pushed forward, causing the horizontal movable lip cover to move forward to the front end. At this time, the throat area and the intake capture area are both at their maximum.

[0040] When the flight Mach number increases to the intake duct start-up Mach number, the first horizontal push rod is pushed forward, causing the movable throat section to move closer to the lip. The horizontal movable lip remains stationary. At this time, the throat area becomes smaller, the intake duct capture area remains at its maximum, the compression increases, and the compression performance of the intake duct is improved.

[0041] As the flight Mach number increases to the design Mach number, the first horizontal push rod moves forward, causing the movable throat section to continue to move closer to the lip. At the same time, the second horizontal push rod moves backward, causing the horizontal movable lip to move backward. At this time, the throat area and the intake capture area decrease, thereby ensuring that the intake has high compression performance under the premise of the intake starting state.

[0042] When the flight Mach number reaches the design Mach number, the movable throat section approaches the lip mask to the minimum distance, and the horizontally movable lip mask is located at the rear end. At this time, the throat area and the intake capture area are both at their minimum.

[0043] When the throat working Mach number is greater than the preset working Mach number, the first horizontal push rod moves forward, causing the movable throat section to move closer to the lip, thus reducing the throat area; when the throat working Mach number is less than the preset working Mach number, the first horizontal push rod moves backward, causing the movable throat section to move away from the lip, thus increasing the throat area; when the intake duct capture flow rate is less than the required flow rate, the second horizontal push rod moves forward, causing the horizontal movable lip to move forward, thus increasing the intake duct capture area, and adjusting the throat area as needed to ensure the intake duct compression efficiency.

[0044] Example 3

[0045] This embodiment provides a design method for a wide-speed-range hypersonic inlet as described in Embodiment 1, including the following steps:

[0046] Based on the aerodynamic performance requirements of the inlet, the positions of the first-stage compression surface, the second-stage isentropic compression surface, and the front lip of the horizontal movable lip cover are designed to obtain the reference profile of the inlet under the design Mach number condition. The reference profile under this condition is obtained through simulation iteration adjustment.

[0047] Calculate the reference flow field of the three-dimensional binary compression surface formed by the first compression surface and the second isentropic compression surface, and determine the lip coordinates of the inlet to ensure that the capture area of ​​the inlet meets the standard.

[0048] The intake manifold performance under different operating conditions is calculated. When the Mach number of the throat is greater than expected, i.e. the compression is too small, the first horizontal push rod is pushed forward to reduce the throat area and increase the compression. Conversely, the first horizontal push rod is pushed backward to increase the throat area and decrease the compression. The optimal mechanism position for each operating condition is finally obtained by using Fluent simulation software for simulation iteration.

[0049] Example 4

[0050] This embodiment uses the design method of Embodiment 3 to design a wide-speed-range hypersonic inlet as described in Embodiment 1, and employs the control method described in Embodiment 2 to perform simulation calculations under typical operating conditions. The simulation results under typical operating conditions are presented. Please refer to [link / reference]. Figure 4-7 The above Mach number graphs are for the air intake in this embodiment when the incoming Mach number is 8, 6, 4 and 2 respectively. As can be seen from the above Mach number graphs, the air intake can work normally under each tested Mach number condition, meet the requirements for wide speed range ultra-high speed operation, and verify the feasibility of the overall solution of the present invention.

Claims

1. A wide-range hypersonic air intake with dual-stage continuously adjustable lip mask and throat passage, characterized in that, The system includes an inner wall surface of the intake duct, a lip shield, an inner intake duct channel formed by the inner wall surface of the intake duct and the lip shield, a horizontally movable isotropic section (15) extending rearward from the inner intake duct channel, and a horizontally fixed section (19) fixedly disposed inside the horizontally movable isotropic section (15). The inner wall surface of the intake duct includes a first compression surface (8) located at the entrance of the inner intake duct channel, a second isentropic compression surface (9) extending rearward from the first compression surface (8), a movable inner contraction section (10) hinged to the rear end of the second isentropic compression surface (9), a movable throat section (11) hinged to the rear end of the movable inner contraction section (10), and a movable throat section (11) hinged to the rear end of the movable throat section (11). Movable diffuser section (13); the rear end of the movable diffuser section (13) is hinged to the horizontal movable straight section (15), and the horizontal movable straight section (15) is slidably disposed on the horizontal fixed section (19); the movable throat section (11) is provided with a throat drive module inside, and the throat drive module drives the movable throat section (11) to move closer to or away from the lip mask; the lip mask includes a fixed lip mask (4) located at the rear end of the air intake channel, a horizontal movable lip mask (3) slidably disposed on the fixed lip mask (4), and a lip mask drive module connected to the horizontal movable lip mask (4), and the lip mask drive module drives the horizontal movable lip mask (4) to move back and forth.

2. The wide-speed-range hypersonic inlet according to claim 1, characterized in that: The throat drive module includes two rotating arms (12) with one end hinged to the inner side of the movable throat section (11), a first horizontal push rod (14) hinged to the other end of the rotating arm (12), and a first drive device (17) connected to the first horizontal push rod (14).

3. The wide-speed-range hypersonic inlet according to claim 1, characterized in that: The lip mask driving module includes a second horizontal push rod (5) connected to the rear end of the horizontally movable lip mask (3) and a second driving device (7) connected to the second horizontal push rod (5).

4. The wide-speed-range hypersonic inlet according to claim 1, characterized in that: The horizontal movable straight section (15) is slidably set and limited on the horizontal fixed section via the horizontal guide rail (18).

5. The wide-speed-range hypersonic inlet according to claim 2, characterized in that: The throat drive module also includes a first translational limiting groove (16), and the first horizontal push rod (14) is disposed in the first translational limiting groove (16).

6. The wide-speed-range hypersonic inlet according to claim 3, characterized in that: The lip mask driving module also includes a second translational limiting groove (6), and the second horizontal push rod (5) is disposed in the second translational limiting groove (6).

7. The wide-speed-range hypersonic inlet according to claim 2, characterized in that: The two rotating arms (12) are of equal length, and the distance between the two points where the two rotating arms (12) are hinged to the movable throat section (11) and the first horizontal push rod (14) is equal.

8. A control method for a wide-speed-range hypersonic inlet according to any one of claims 1-7, characterized in that, Includes the following steps: When the flight Mach number is subsonic, the throat drive module moves the movable throat section away from the lip cover to the maximum distance, while the lip cover drive module moves the horizontally movable lip cover forward to the foremost position. At this time, the throat area and the intake capture area are both at their maximum. When the flight Mach number increases to the intake duct start-up Mach number, the throat drive module drives the movable throat section to move closer to the lip mask, while the horizontal movable lip mask remains stationary. At this time, the throat area becomes smaller, and the intake duct capture area remains at its maximum. As the flight Mach number increases to the design Mach number, the throat drive module drives the movable throat section to continue moving closer to the lip mask, while the lip mask drive module drives the horizontally movable lip mask to move backward. At this time, the throat area and the intake capture area decrease. When the flight Mach number reaches the design Mach number, the movable throat section approaches the lip mask to the minimum distance, and the horizontally movable lip mask is located at the rear end. At this time, the throat area and the intake capture area are both at their minimum.

9. The control method for a wide-range hypersonic inlet according to claim 8, characterized in that: The control method further includes: When the throat working Mach number is greater than the preset working Mach number, the throat drive module moves the movable throat section closer to the lip mask, reducing the throat area; when the throat Mach number is less than the preset working Mach number, the throat drive module moves the movable throat section away from the lip mask, increasing the throat area; when the intake duct capture flow is less than the required flow, the lip mask drive module moves the horizontally movable lip mask forward, increasing the intake duct capture area.

10. A design method for a wide-speed-range hypersonic inlet according to any one of claims 1-7, characterized in that, Includes the following steps: Based on the aerodynamic performance requirements of the intake duct, the positions of the first-stage compression surface, the second-stage isentropic compression surface, and the front lip of the horizontal movable lip cover (3) are designed to obtain the intake duct reference profile under the design Mach number condition. The reference profile under this condition is obtained by simulation verification and adjustment. Calculate the reference flow field of the three-dimensional binary compression surface formed by the first compression surface and the second isentropic compression surface, and determine the lip coordinates of the inlet. The performance of the intake duct under different operating conditions is calculated, and the positions of the movable throat section and the lip mask corresponding to each operating condition are obtained through simulation iteration.

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