A hypersonic vehicle head drag reduction and heat reduction adaptive device

Abstract

The application provides a hypersonic vehicle head drag reduction and heat reduction adaptive device, which combines a drag reduction and heat reduction device of an aerodynamic rod and a sweat cooling device; when the vehicle is in supersonic flight, the aerodynamic rod pushes the shock wave away from the wall surface of the nose cone front edge to achieve the effect of drag reduction, reduces the pressure and heat flow at the nose cone front edge, and makes the sweat cooling medium more easily flow out of the ceramic-based porous material, thereby solving the problem of low stagnation point cooling efficiency in sweat cooling; the cooling medium water is in liquid state in the connecting pipeline, the coolant micropore storage tank and the internal cavity of the nose cone shell, enters the ceramic-based porous material, absorbs heat in the ceramic-based porous material, is warmed and phase-changed, flows out of the porous material, then continues to flow downstream, and forms an air film on the surface of the nose cone shell area, thereby achieving the effect of heat reduction; and with the change of the incoming flow pressure, the aerodynamic rod can be self-adaptively adjusted in the length of extension to adjust the effect of drag reduction, and the sweat cooling can also be self-adaptively adjusted in the flow of the coolant to adjust the effect of heat reduction.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of drag reduction and heat reduction of hypersonic vehicles, and particularly relates to a drag reduction and heat reduction adaptive device for the head of a hypersonic vehicle. BACKGROUND

[0002] In recent years, hypersonic flight technology has attracted widespread attention from countries around the world due to its great strategic significance. In hypersonic flight, the vehicle often faces severe aerodynamic heating and shock wave drag, which can cause surface ablation of the vehicle and even damage the aerodynamic structure, posing a serious challenge to the design of hypersonic vehicles. Therefore, drag reduction and heat reduction design is particularly important in the field of hypersonic flight. The common drag reduction and heat reduction techniques can be divided into active control and passive control, and the principle of both is basically to change the shock wave intensity or boundary layer state to achieve drag reduction and heat reduction, including energy delivery, windward cavity, sweat cooling, reverse jet flow, aerodynamic rod and their combination techniques.

[0003] Sweat cooling has been proven to be a highly potential active thermal protection method, which has the advantages of strong cooling capacity, small amount of coolant, and high system stability. However, when numerical simulation and experimental research are conducted on the nose cone model, it is found that due to the extremely uneven spatial distribution of heat flow and pressure on the surface of the nose cone, the coolant is difficult to flow out from the stagnation point with high pressure and high heat flow, resulting in unsatisfactory cooling effect in the stagnation point area.

[0004] The aerodynamic rod is favored by a large number of researchers due to its simple structure and obvious drag reduction effect. Installing an aerodynamic rod on the head of a hypersonic blunt body vehicle can push the bow shock wave away from the surface, significantly reducing the pressure on the wall surface of the blunt body. However, while the aerodynamic rod reduces the surface pressure, its heat reduction effect is not ideal, which limits the application of the aerodynamic rod. SUMMARY

[0005] Therefore, the present application aims to provide a drag reduction and heat reduction adaptive device for the head of a hypersonic vehicle, which can adaptively adjust the drag reduction effect by combining the aerodynamic rod with sweat cooling, and solve the problem of low cooling efficiency in the stagnation point area. The drag reduction and heat reduction adaptive device for the head of a hypersonic vehicle comprises an aerodynamic rod (1), a ceramic-based porous material (2), a nose cone shell (3), a barrel-shaped base (4), a positioning pin mechanism (5), a connecting rod mechanism (6), a piston (7), a hydraulic mechanism (8), a connecting pipeline (9), and a coolant micropore storage tank (10).

[0006] The whole of the nose cone shell (3) is a cylindrical structure, the head part is inwardly contracted to form a nose cone structure, the end of the head part is provided with an opening, and a ceramic-based porous material (2) is arranged in the opening; the tail part of the nose cone shell (3) is open and coaxially sleeved on the outside of a barrel-shaped base (4) fixed on the head part of the aircraft; the inside of the barrel-shaped base (4) is provided with a positioning pin mechanism (5), and a groove is arranged on the inner wall of the tail part of the nose cone shell (3); in the initial state, the positioning pin mechanism (5) protrudes out of the outer wall surface of the barrel-shaped base (4) and is clamped in the groove of the nose cone shell (3); in the working state, the positioning pin mechanism (5) is retracted into the barrel-shaped base (4), and the nose cone shell (3) can move axially forward and backward along the outer wall surface of the barrel-shaped base (4) under the action of an external force.

[0007] The hydraulic mechanism (8) is fixed at the end surface of the barrel-shaped base (4); the inside of the main cavity of the hydraulic mechanism (8) is filled with a liquid working medium, and the main cavity extends a plurality of piston cavities, one of which extends to the head part along the central axis of the nose cone shell (3), the tail part of the pneumatic rod (1) is arranged in the piston cavity and serves as a piston and can move forward and backward under the pressure of the liquid working medium; the pneumatic rod (1) extends its head part along the axial direction of the nose cone shell (3), and the head part is provided with a spherical disc; each of the other piston cavities of the main cavity is connected with a connecting rod mechanism (6), one end of the connecting rod mechanism (6) enters the piston cavity and serves as a piston, and the other end is connected to the inner wall surface of the nose cone shell (3).

[0008] A partition plate (11) is arranged at a position close to the head part in the inside of the nose cone shell (3), so as to form an independent cavity in the space of the head part; a sleeve (12) is arranged in the middle of the partition plate (11), and a cylindrical coolant micropore storage tank (10) is arranged in the inside of the sleeve (12); the pneumatic rod (1) extends out of the nose cone shell (3) through the central through hole of the sleeve (12) and the coolant micropore storage tank (10); one end of the connecting pipeline (9) is fixed on the barrel-shaped base (4), and the other end is fixed on the coolant micropore storage tank (10).

[0009] A plurality of micro through holes are arranged on the outer wall surface of the coolant micropore storage tank (10), and the connecting pipeline (9) sends the coolant coming from the barrel-shaped base (4) into the coolant micropore storage tank (10); in the initial state, the sleeve (12) is completely sleeved on the outside of the coolant micropore storage tank (10) and covers the micro through hole region.

[0010] Preferably, in addition to the piston cavity of the central axis, the cavity further comprises four piston cavities, and each piston cavity is connected with a connecting rod mechanism (6); the four piston cavities are symmetrically and uniformly distributed around the central axis.

[0011] The present application has the following beneficial effects:

[0012] The application provides a hypersonic aircraft head drag reduction and heat reduction adaptive device, which combines a drag reduction and heat reduction device of a pneumatic rod and sweating cooling, when the aircraft flies at a supersonic speed, the pneumatic rod pushes the shock wave of the nose cone front edge away from the wall surface to achieve the effect of reducing the drag, reduces the pressure and heat flow at the nose cone front edge, and makes the sweating cooling medium more easily flow out of the ceramic-based porous material, thereby solving the problem of low stagnation cooling efficiency in sweating cooling.

[0013] The cooling medium water is in a liquid state in the connecting pipeline, the coolant micropore storage tank and the internal cavity of the nose cone shell, is absorbed heat in the ceramic-based porous material after entering the ceramic-based porous material, is phase changed after being heated, flows out of the porous material, then continues to flow downstream, and forms an air film on the surface of the nose cone shell area, thereby achieving the effect of reducing heat.

[0014] Moreover, with the change of the incoming flow pressure, the pneumatic rod can adaptively adjust the extension length to adjust the drag reduction effect, and the sweating cooling can also adaptively adjust the coolant flow to adjust the heat reduction effect. BRIEF DESCRIPTION OF DRAWINGS

[0015] Figure 1 FIG. 1 is a structural schematic view of a hypersonic aircraft head drag reduction and heat reduction adaptive device according to the application.

[0016] Figure 2 FIG. 2 is a structural sectional view of a hypersonic aircraft head drag reduction and heat reduction adaptive device according to the application.

[0017] In the drawings, 1 is a pneumatic rod, 2 is a ceramic-based porous material, 3 is a nose cone shell, 4 is a barrel-shaped base, 5 is a positioning pin mechanism, 6 is a connecting rod mechanism, 7 is a piston, 8 is a hydraulic mechanism, 9 is a connecting pipeline, 10 is a coolant micropore storage tank, 11 is a partition plate, and 12 is a sleeve. DETAILED DESCRIPTION

[0018] The application will be described in detail below with reference to the drawings and examples.

[0019] According to the advantages and disadvantages and complementarity of the sweating cooling and the pneumatic rod structure, the application provides a hypersonic aircraft head drag reduction and heat reduction adaptive device, that is, the two cooling structures are combined, the pneumatic rod structure is used to reduce the heat flow and pressure near the stagnation point, and the problem of low stagnation cooling efficiency in sweating cooling is solved. Moreover, with the change of the incoming flow pressure, the pneumatic rod can adaptively adjust the extension length to adjust the drag reduction effect, and the sweating cooling can also adaptively adjust the coolant flow to adjust the heat reduction effect.

[0020] The hypersonic aircraft head drag reduction and heat reduction adaptive device according to the application comprises a pneumatic rod 1, a ceramic-based porous material 2, a nose cone shell 3, a barrel-shaped base 4, a positioning pin mechanism 5, a connecting rod mechanism 6, a piston 7, a hydraulic mechanism 8, a connecting pipeline 9 and a coolant micropore storage tank 10.

[0021] The nose cone shell 3 is a cylindrical structure with its head tapering inward to form a nose cone. An opening is located at the end of the head, within which a ceramic-based porous material 2 is placed. The tail of the nose cone shell 3 is an open structure, coaxially fitted onto the outside of a barrel-shaped base 4 fixed to the nose of the aircraft. The nose cone shell 3 can move axially back and forth along the outer wall of the barrel-shaped base 4. A positioning pin mechanism 5 is located inside the barrel-shaped base 4. A groove is provided on the inner wall of the tail of the nose cone shell 3. In the initial state, the positioning pin mechanism 5 extends out of the outer wall of the barrel-shaped base 4 and engages in the groove of the nose cone shell 3, fixing the nose cone shell 3 and preventing axial movement relative to the barrel-shaped base 4. In the working state, the positioning pin mechanism 5 retracts into the barrel-shaped base 4, allowing the nose cone shell 3 to move axially back and forth along the outer wall of the barrel-shaped base 4 under external force.

[0022] The bottom of the hydraulic mechanism 8 is fixed on one end face of the barrel-shaped base 4 and the nose cone housing 3. The main cavity of the hydraulic mechanism 8 is filled with liquid working fluid. Five piston chambers extend from the outside of the main cavity. One of the piston chambers extends towards the head along the central axis of the nose cone housing 3. The tail of the pneumatic rod 1 is set in the piston chamber and acts as a piston, which can move back and forth under the pressure of the liquid working fluid. The pneumatic rod 1 extends out of the opening of its head along the axial direction of the nose cone housing 3 and is provided with a spherical disk at its end. When the pneumatic rod 1 is fully retracted, the disk can fit against the outer wall of the ceramic-based porous material 2.

[0023] Each of the other four piston chambers is connected to a linkage mechanism 6. One end of the linkage mechanism 6 enters the piston chamber as a piston, and the other end is connected to the inner wall of the nose cone housing 3. The four piston chambers are symmetrically and evenly distributed around the central axis of the nose cone housing 3.

[0024] When the nose cone housing 3 moves forward relative to the barrel base 4, it drives one end of the four linkage mechanisms 6 to move, causing one end of the linkage mechanism 6, which acts as a piston, to move inward along the piston cavity. This causes the liquid working medium in the main cavity to be squeezed, thus squeezing the working medium into the axial piston cavity, and finally pushing the piston at the tail of the pneumatic rod 1 to extend the pneumatic rod 1 outward.

[0025] A partition 11 is located inside the nose cone housing 3 near the head, forming an independent cavity for the head. A sleeve 12 is located in the middle of the partition 11, which houses a cylindrical microporous coolant reservoir 10. The pneumatic rod 1 extends out of the nose cone housing 3 through the sleeve 12 and the central through-hole of the microporous coolant reservoir 10. One end of the connecting pipe 9 is fixed to the barrel-shaped base 4, and the other end is fixed to the microporous coolant reservoir 10.

[0026] The outer wall surface of the coolant micro-porous storage tank 10 is provided with a series of micro-holes, and the connecting pipeline 9 sends the coolant coming from the barrel-shaped base 4 into the coolant micro-porous storage tank 10; in the initial state, the sleeve 12 is completely sleeved outside the coolant micro-porous storage tank 10, covering all the micro-hole areas, and the coolant cannot flow out; in the working state, the nose cone shell 3 slides backward, and the sleeve 12 also slides backward, and the coolant micro-porous storage tank 10 gradually exposes part of the micro-holes, so that the liquid coolant can flow out, enter the independent cavity in the head of the nose cone shell 3, and finally flow out of the ceramic-based porous material 2.

[0027] In subsonic flight, the nose cone shell 3 is close to the front edge of the barrel-shaped base 4 and is fixed by the positioning pin mechanism 5; the aerodynamic rod 1 does not protrude, and the aerodynamic disc is tightly attached to the outer wall surface of the ceramic-based porous material 2; the coolant micro-porous storage tank 10 is completely blocked, and no coolant flows out.

[0028] In supersonic flight, the control positioning pin mechanism 5 is retracted, and the aerodynamic force generated by the high dynamic pressure of the incoming flow acting on the wall surface of the nose cone shell 3 makes the nose cone shell 3 slide downstream along the outer wall surface of the barrel-shaped base 4; at the same time, the nose cone shell 3 drives the aerodynamic rod 1 to protrude upstream through the connecting rod mechanism 6 and the hydraulic mechanism 8 to achieve the effect of drag reduction, and the coolant micro-porous storage tank 10 also gradually leaks the micro-holes, so that the coolant can pass through and flow out of the ceramic-based porous material 2 to achieve the effect of heat reduction.

[0029] In a certain incoming flow dynamic pressure state, the aerodynamic forces acting on the nose cone shell 3 and the aerodynamic rod 1 interact with each other and reach a balanced state when the aerodynamic rod 1 protrudes by a suitable distance; in the balanced state, if disturbed, the protruding distance of the aerodynamic rod 1 becomes longer or the nose cone shell 3 slides downstream, according to the theory of aerodynamics, the aerodynamic force acting on the nose cone shell 3 will decrease, but the aerodynamic force acting on the aerodynamic rod 1 will basically remain unchanged, which leads to an unbalanced force, and further makes the aerodynamic rod 1 slide downstream, that is, the protruding distance of the aerodynamic rod 1 becomes shorter, and finally returns to the balanced state again, and vice versa. When the incoming flow dynamic pressure changes, according to the theory of aerodynamics, the protruding distance of the aerodynamic rod 1 will also change to achieve a balanced state to adjust the effect of drag reduction, at the same time, the sleeve position in the internal cavity of the head of the nose cone shell 3 will move, and the number of micro-holes exposed by the coolant micro-porous storage tank 10 will change, thereby controlling the flow of the sweat cooling coolant to adjust the effect of heat reduction.

[0030] In summary, the above is only a preferred embodiment of the present application, and is not used to limit the protection scope of the present application. Any modification, equivalent replacement, improvement, etc. made within the spirit and principles of the present application shall be included in the protection scope of the present application.

Claims

1. A hypersonic vehicle head drag reduction and heat reduction adaptive device, characterized in that, The device comprises a pneumatic rod (1), a ceramic-based porous material (2), a nose cone shell (3), a barrel base (4), a positioning pin mechanism (5), a connecting rod mechanism (6), a piston (7), a hydraulic mechanism (8), a connecting pipeline (9) and a coolant micro-porous storage tank (10). The nose cone shell (3) is in a cylindrical structure, with the head part inwardly contracted to form a nose cone structure, and an opening is arranged at the end of the head part, in which the ceramic-based porous material (2) is arranged; the tail part of the nose cone shell (3) is open and coaxially sleeved with the outside of the barrel base (4) fixed to the head part of the aircraft; the inside of the barrel base (4) is provided with the positioning pin mechanism (5), and a groove is arranged on the inner wall of the tail part of the nose cone shell (3); in the initial state, the positioning pin mechanism (5) extends out of the outer wall surface of the barrel base (4) and is clamped in the groove of the nose cone shell (3); in the working state, the positioning pin mechanism (5) is retracted into the barrel base (4), and the nose cone shell (3) can move axially forward and backward along the outer wall surface of the barrel base (4) under the action of external force. The bottom of the hydraulic mechanism (8) is fixed on the end surface of the barrel base (4); the inside of the main cavity of the hydraulic mechanism (8) is filled with liquid working medium, and the main cavity extends out of multiple piston cavities, one of which extends to the head part along the central axis of the nose cone shell (3), the tail part of the pneumatic rod (1) is arranged in the piston cavity and serves as a piston, which can move forward and backward under the pressure of the liquid working medium; the pneumatic rod (1) extends out of the head part along the axial direction of the nose cone shell (3), and the head part is provided with a spherical disc; each of the other piston cavities of the main cavity is connected with a connecting rod mechanism (6), one end of the connecting rod mechanism (6) enters the piston cavity and serves as a piston, and the other end is connected to the inner wall surface of the nose cone shell (3). A partition plate (11) is arranged at a position close to the head part inside the nose cone shell (3), so as to form an independent cavity in the space of the head part; a sleeve (12) is arranged in the middle of the partition plate (11), and a cylindrical coolant micro-porous storage tank (10) is arranged in the inside of the sleeve (12); the pneumatic rod (1) extends out of the nose cone shell (3) through the central through hole of the sleeve (12) and the coolant micro-porous storage tank (10); one end of the connecting pipeline (9) is fixed on the barrel base (4), and the other end is fixed on the coolant micro-porous storage tank (10). A plurality of micro holes are arranged on the outer wall surface of the coolant micro-porous storage tank (10), and the connecting pipeline (9) sends the coolant from the barrel base (4) into the coolant micro-porous storage tank (10); in the initial state, the sleeve (12) is completely sleeved on the outside of the coolant micro-porous storage tank (10) and covers the micro hole area.

2. A drag-reducing and heat-reducing self-adapting device combining pneumatic rod and transpiration cooling according to claim 1, characterized in that, In addition to the piston cavity of the central axis, the cavity comprises four piston cavities, each of which is connected with a connecting rod mechanism (6); the four piston cavities are symmetrical and uniformly distributed around the central axis.

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