An adaptive shock rod device for drag reduction at the head of a hypersonic vehicle

Abstract

The present invention discloses an adaptive shock wave rod device for drag reduction at the head of a hypersonic vehicle. The air storage device of the adaptive shock wave rod device is communicated with a piston-type shock wave rod and a cylinder; a spherical hinge is installed inside the head of the vehicle body; the piston-type shock wave rod is fixedly connected to the spherical hinge and is located outside the vehicle body; four pressure sensors are distributed on the outer surface of the head of the vehicle body; the central position of a cross-shaped lever is movably connected to the air storage device and has four half-levers; the outer peripheral surface of the spherical hinge is hinged with four connecting rods; the other ends of the connecting rods are hinged with the half-levers; a cylinder is fixedly connected to the inner side wall of the vehicle body; the piston rod of the cylinder is hinged with the half-lever; the control system controls the air storage device to charge and discharge the cylinder and to inflate the piston-type shock wave rod. The above-mentioned adaptive shock wave rod device can simultaneously adjust the length and angle of the shock wave rod to meet the requirements of the drag reduction efficiency of the drag reduction rod at the head of the hypersonic vehicle under different working conditions.

Description

Technical Field

[0001] The present invention relates to the technical field of drag reduction for hypersonic vehicles, and particularly to an adaptive shock rod device for drag reduction at the head of a hypersonic vehicle. Background Art

[0002] Hypersonic vehicles often adopt a relatively blunt leading edge to withstand severe aerodynamic heating. The bow shock wave generated by the blunt leading edge will lead to high pressure behind the wave, and then result in a large aerodynamic drag, affecting the aerodynamic performance of the vehicle. After a large number of studies, it is found that installing a shock rod at the head of a hypersonic vehicle can push the shock wave away from the surface of the object and form a low-pressure recirculation area at the head to achieve a drag reduction effect. However, the drag reduction effect of the traditional shock rod will decrease due to the changes in the angle of attack and speed. To solve the above problems, an adaptive shock rod drag reduction device has been developed. Summary of the Invention

[0003] The present invention provides an adaptive shock rod device for drag reduction at the head of a hypersonic vehicle. The adaptive shock rod device can simultaneously adjust the length and angle of the shock rod to meet the requirements of the drag reduction efficiency of the drag reduction rod at the head of the hypersonic vehicle under different working conditions.

[0004] The present invention adopts the following specific technical solutions:

[0005] An adaptive shock rod device for drag reduction at the head of a hypersonic vehicle, the adaptive shock rod device includes an air storage device, a spherical hinge with a piston-type shock rod, a cylinder, a connecting rod, a cross-shaped lever, a pressure sensor, and a control system;

[0006] The air storage device is fixedly connected to the tail of the vehicle body and is communicated with the piston-type shock rod and the cylinder;

[0007] The spherical hinge is installed inside the head of the vehicle body;

[0008] The piston-type shock rod is fixedly connected to the spherical hinge and passes through the center position of the head of the vehicle body and exposes outside the vehicle body;

[0009] Four of the pressure sensors are evenly distributed circumferentially on the outer surface of the head of the vehicle body;

[0010] The cross-shaped lever is located inside the vehicle body, and the center position is movably connected to the air storage device and has four half-levers evenly distributed circumferentially;

[0011] Axially along the vehicle body, each of the half-levers corresponds to one of the pressure sensors;

[0012] Four link rods corresponding to each of the half levers are hinged to the outer peripheral surface of the spherical hinge; the length direction of the link rod coincides with the axial direction of the aircraft body; the other end of the link rod is hinged to the middle part of the corresponding half lever;

[0013] On the inner side wall of the aircraft body, cylinders corresponding to each of the half levers are fixedly connected; the piston rods of the cylinders extend and retract along the axial direction of the aircraft body, and the outer end of each piston rod is hinged to the corresponding half lever, so as to drive the corresponding half lever to swing through the piston rod, and thus drive the spherical hinge to rotate through the corresponding link rod to adjust the tilt angle of the piston shock rod;

[0014] The control system is connected to the pressure sensor and the gas storage device, and controls the gas storage device to charge and discharge the cylinders and charge the piston shock rod according to the pressure signal detected by the pressure sensor, so as to adjust the tilt angle and length of the piston shock rod.

[0015] Furthermore, the gas storage device is communicated with the piston shock rod through a first gas pipeline;

[0016] The gas storage device is separately communicated with each cylinder through a second gas pipeline.

[0017] Furthermore, an air inlet channel penetrating through the center of the sphere is provided inside the spherical hinge;

[0018] The air inlet channel forms a part of the first gas pipeline.

[0019] Furthermore, the inside of the spherical hinge is filled with a light material, and the air inlet channel is formed by surrounding the light material.

[0020] Furthermore, the light material is carbon fiber composite material or aluminum alloy.

[0021] Furthermore, the gas storage device has independent gas sources corresponding to and communicated with the piston shock rod and the cylinders one by one.

[0022] Furthermore, the four hinge points on the outer peripheral surface of the spherical hinge form a hinge plane, and the hinge plane passes through the center of the sphere of the spherical hinge and is perpendicular to the axial direction of the piston shock rod.

[0023] Furthermore, the gas storage device is provided with a boss for connecting the cross-shaped lever.

[0024] Beneficial effects:

[0025] 1. The adaptive shock rod device of the present invention installs pressure sensors, spherical hinges, and piston-type shock rods at the head of the aircraft body. The pressure changes at the head are detected by four pressure sensors. The control system controls the air storage device to charge and discharge air from the cylinder. The piston rod of the cylinder drives the cruciform lever to swing through expansion and contraction, thereby driving the spherical hinge to rotate through the connecting rod, realizing the adjustment of the inclination angle of the shock rod. At the same time, the control system can also control the air storage device to inflate the piston-type shock rod, realizing stepless adjustment of the length of the shock rod, thereby reducing the head resistance of the aircraft. Therefore, the above-mentioned adaptive shock rod device can achieve head drag reduction of hypersonic aircraft to meet the requirements of the drag reduction efficiency of the head drag reduction rod of hypersonic aircraft under different working conditions.

[0026] 2. The air storage device of the adaptive shock rod device of the present invention is separately connected to the piston-type shock rod and the cylinder through different air pipelines, so that the air charging and discharging of each cylinder are independent of and do not interfere with the inflation of the piston-type shock rod, improving the accuracy and reliability of control. Moreover, the air storage device has independent air sources corresponding to the piston-type shock rod and the cylinder one by one, which can further avoid the inflation interference of each cylinder and the piston-type shock rod.

[0027] 3. The adaptive shock rod device of the present invention is provided with an air inlet passage passing through its spherical center inside the spherical hinge, which can directly inject gas into the piston-type shock rod through the inside of the spherical hinge, reducing the gas carrying amount. At the same time, the inside of the spherical hinge is filled with lightweight materials, reducing the weight of the spherical hinge. The inside of the air storage device is divided into three parts, and the air charging and discharging of the cylinder do not interfere with the inflation of the piston-type shock rod. Description of the Drawings

[0028] Figure 1 is the overall external structure schematic diagram of the adaptive shock rod device of the present invention;

[0029] Figure 2 is Figure 1 the cross-sectional view of the adaptive shock rod device in

[0030] Figure 3 the structural schematic diagram when the piston-type shock rod is in the extended state;

[0031] Figure 4 is the schematic diagram of the angle change of the piston-type shock rod with the change of the angle of attack;

[0032] Figure 5 is the assembly structure schematic diagram of the cruciform lever and the air storage device.

[0033] Among them, 1 - aircraft body, 2 - piston shock rod, 3 - pressure sensor, 4 - gas storage device, 5 - spherical hinge, 6 - cylinder, 7 - connecting rod, 8 - cross-shaped lever, 9 - first gas pipeline, 10 - second gas pipeline, 21 - piston, 41 - boss, 51 - air inlet, 52 - hinge point, 61 - piston rod, 81 - half lever Detailed implementation manner

[0034] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0035] As Figure 1 and Figure 2 shown in the structure, this embodiment provides an adaptive shock rod device for drag reduction at the head of a hypersonic aircraft. The adaptive shock rod device is installed on the aircraft body 1 and includes a gas storage device 4, a spherical hinge 5 with a piston shock rod 2, a cylinder 6, a connecting rod 7, a cross-shaped lever 8, a pressure sensor 3, and a control system; for the convenience of description, in this embodiment, the end where the spherical hinge 5 is installed in Figure 1 is defined as the head of the aircraft body 1, and the end where the gas storage device 4 is installed is the tail of the aircraft body 1. Taking Figure 1 the free end of the piston shock rod 2 in as the front end and the end of the piston shock rod 2 connected to the spherical hinge 5 as the rear end. Similarly, the end of the connecting rod 7 connected to the spherical hinge 5 is the front end and the end connected to the cross-shaped rod is the rear end;

[0036] The gas storage device 4 is fixedly installed at the tail of the aircraft body 1 and is communicated with the piston shock rod 2 and the cylinder 6; the gas storage device 4 is used to store high-pressure gas and provide gas for the cylinder 6 and the piston shock rod 2, and at the same time provide an installation basis for the cross-shaped lever 8; the gas storage device 4 and the piston shock rod 2 can be communicated through the first gas pipeline 9;

[0037] The spherical hinge 5 is installed inside the head of the aircraft body 1; the spherical hinge 5 includes a sphere and four hinge points 52 arranged on the outer peripheral surface of the sphere; the front end of the sphere is in shape fit with the aircraft body 1 to realize the rotation of the sphere;

[0038] The piston shock rod 2 is fixedly connected to the spherical hinge 5 and passes through the center position of the head of the aircraft body 1 and exposes outside the aircraft body 1; as Figure 2 and Figure 3As shown, a piston is provided inside the piston shock rod 2. The gas delivered into the piston shock rod 2 through the gas storage device 4 can push the piston 21 to move forward, enabling the elongation of the piston shock rod 2. Figure 3 It is a schematic structural diagram of the piston shock rod 2 in the extended state. Figure 4 It is a schematic structural diagram of the piston shock rod 2 in the tilted state driven by the cylinder 6.

[0039] As Figure 1 shown, four pressure sensors 3 are evenly distributed along the circumferential direction on the outer surface of the head of the aircraft body 1. The pressure sensors 3 can measure the pressure values at the corresponding positions of the aircraft body 1.

[0040] As Figure 2 、 Figure 3 and Figure 5 shown, the cross-shaped lever 8 is located inside the aircraft body 1, is movably connected to the gas storage device 4 at the central position, and has four half-levers 81 evenly distributed along the circumferential direction. The four half-steel rod structures are the same and are opposite to the positions of the four pressure sensors 3. To facilitate the cross-shaped lever 8 to swing with the central connection point as the fulcrum, the gas storage device 4 is provided with a boss 41 for connecting the cross-shaped lever 8 at the end facing the cross-shaped lever 8. The cross-shaped lever 8 can swing freely through the boss 41 protruding from the front end face of the gas storage device 4, avoiding the front end face of the gas storage device 4 restricting the swing of the cross-shaped lever 8. Along the axial direction of the aircraft body 1, each half-lever 81 corresponds to a pressure sensor 3 one by one. Through the half-lever 81 corresponding to the pressure sensor 3, the connecting rod 7 connected to the half-lever 81, the piston rod 61, and the ball hinge 5, it is convenient to adjust the resistance of the corresponding part.

[0041] As Figure 2 and Figure 3 shown in the structure, four connecting rods 7 corresponding to each half-lever 81 are hinged to the outer peripheral surface of the spherical hinge 5. The length direction of the connecting rod 7 coincides with the axial direction of the aircraft body 1. The other end of the connecting rod 7 is hinged to the middle of the corresponding half-lever 81. The four hinge points 52 on the outer peripheral surface of the spherical hinge 5 form a hinge plane, and the hinge plane passes through the center of the spherical hinge 5 and is perpendicular to the axial direction of the piston shock rod 2.

[0042] As Figure 2 and Figure 3As shown in the structure, cylinders 6 corresponding to each semi-lever 81 are fixedly connected to the inner side wall of the aircraft body 1; the gas storage device 4 can be separately communicated with each cylinder 6 through a second gas pipeline 10; the piston rod 61 of the cylinder 6 expands and contracts along the axial direction of the aircraft body 1, and the outer end of each piston rod 61 is hinged to the corresponding semi-lever 81, and is used to drive the corresponding semi-lever 81 to swing through the piston rod 61, so as to drive the spherical hinge 5 to rotate through the corresponding connecting rod 7 to adjust the tilt angle of the piston shock rod 2;

[0043] The control system is connected to the pressure sensor 3 and the gas storage device 4, and controls the gas storage device 4 to charge and discharge the cylinder 6 and inflate the piston shock rod 2 according to the pressure signal detected by the pressure sensor 3, so as to adjust the tilt angle and length of the piston shock rod 2.

[0044] The above-mentioned adaptive shock rod device is used for drag reduction at the head of a hypersonic aircraft. The working principle is as follows: during the flight of a hypersonic aircraft, the piston shock rod 2 forms a certain angle of attack with the oncoming flow, resulting in a pressure difference at the head of the aircraft. After the pressure sensor 3 detects the pressure difference, the control system controls the gas storage device 4 to charge and discharge the corresponding cylinder 6. The gas in the gas storage device 4 enters or exits the cylinder 6 through the second gas pipeline 10, realizing the telescopic movement of the piston rod 61 in the cylinder 6. Furthermore, the piston rod 61 drives the cross-shaped lever 8 and the connecting rod 7 to drive the spherical hinge 5 to deflect through the cross-shaped lever 8, so that the angle of the piston shock rod 2 changes and aligns with the oncoming flow direction; during the flight of a hypersonic aircraft, the resistance increases and the head pressure rises. After the pressure sensor 3 detects the pressure increase, the control system controls the gas storage device 4 to discharge gas and inflate the piston shock rod 2. The gas is injected into the piston shock rod 2 through the first gas pipeline 9, pushing the piston inside the shock rod to move, so that the shock rod realizes a length change, thereby reducing the flight resistance.

[0045] The above-mentioned adaptive shock rod device installs a pressure sensor 3, a spherical hinge 5 and a piston shock rod 2 at the head of the aircraft body 1. The control system controls the gas storage device 4 to charge and discharge the cylinder 6 by detecting the pressure change at the head through four pressure sensors 3. The piston rod 61 of the cylinder 6 expands and contracts to drive the cross-shaped lever 8 to swing, and then drives the spherical hinge 5 to rotate through the cross-shaped lever 8 and the connecting rod 7 in sequence, realizing the adjustment of the tilt angle of the shock rod; at the same time, the control system can also control the gas storage device 4 to inflate the piston shock rod 2, realizing the stepless adjustment of the length of the shock rod, thereby reducing the head resistance of the aircraft; therefore, the above-mentioned adaptive shock rod device can adjust the length and angle of the shock rod at the same time, realizing drag reduction at the head of a hypersonic aircraft to meet the requirements of the drag reduction efficiency of the drag reduction rod at the head of a hypersonic aircraft under different working conditions.

[0046] Meanwhile, the gas storage device 4 is separately and independently connected to the piston shock rod 2 and the cylinders 6 through different gas pipelines, so that the gas charging and discharging of each cylinder 6 and the gas charging of the piston shock rod 2 are independent of each other and do not interfere with each other, improving the accuracy and reliability of control. Moreover, the gas storage device 4 has independent gas sources that are in one-to-one correspondence with the piston shock rod 2 and the cylinders 6, which can further avoid the gas charging interference between each cylinder 6 and the piston shock rod 2.

[0047] In addition, in order to achieve further independent gas supply control, the gas storage device 4 also has independent gas sources that are in one-to-one correspondence with the piston shock rod 2 and the cylinders 6, that is, the gas storage device 4 has five independent gas sources that are in one-to-one correspondence with the piston shock rod 2 and the four cylinders 6, such as: five gas storage tanks.

[0048] In a specific embodiment, such as Figure 2 and Figure 3 shown, the spherical hinge 5 has an air inlet passage 51 passing through its center of the sphere; the air inlet passage 51 forms a part of the first gas pipeline 9; the spherical hinge 5 is filled with a light material, and the air inlet passage 51 is formed by surrounding with the light material. The light material can be a carbon fiber composite material or an aluminum alloy.

[0049] Since the adaptive shock rod device is provided with an air inlet passage 51 passing through its center of the sphere inside the spherical hinge 5, the gas can be directly injected into the piston shock rod 2 through the inside of the ball hinge, reducing the gas carrying amount; at the same time, the inside of the ball hinge is filled with a light material, reducing the weight of the ball hinge; the inside of the gas storage device 4 is divided into three parts, and the gas charging and discharging of the cylinder 6 and the gas charging of the piston shock rod 2 do not interfere with each other.

[0050] Obviously, those skilled in the art can make various changes and modifications to the embodiments of the present invention without departing from the spirit and scope of the present invention. Thus, if these modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalent technologies, the present invention is also intended to include these changes and modifications.

Claims

1. An adaptive shock rod device for drag reduction at the head of a hypersonic vehicle, characterized in that It includes a gas storage device, a spherical hinge with a piston-type shock rod, a cylinder, a connecting rod, a cross-shaped lever, a pressure sensor, and a control system; The gas storage device is fixedly connected to the tail of the aircraft body and is communicated with the piston-type shock rod and the cylinder; The spherical hinge is installed inside the head of the aircraft body; The piston-type shock rod is fixedly connected to the spherical hinge, passes through the central position of the head of the aircraft body and exposes outside the aircraft body; Four of the pressure sensors are evenly distributed along the circumferential direction on the outer surface of the head of the aircraft body; The cross-shaped lever is located inside the aircraft body, and its central position is movably connected to the gas storage device and has four half-levers evenly distributed along the circumferential direction; Axially along the aircraft body, each of the half-levers corresponds to one of the pressure sensors; Four connecting rods corresponding to each of the half-levers are hinged to the outer peripheral surface of the spherical hinge; the length direction of the connecting rod coincides with the axial direction of the aircraft body; the other end of the connecting rod is hinged to the middle of the corresponding half-lever; Cylinders corresponding to each of the half-levers are fixedly connected to the inner side wall of the aircraft body; the piston rod of the cylinder expands and contracts along the axial direction of the aircraft body, and the outer end of each piston rod is hinged to the corresponding half-lever, so as to drive the corresponding half-lever to swing through the piston rod, thereby driving the spherical hinge to rotate through the corresponding connecting rod to adjust the tilt angle of the piston-type shock rod; The control system is connected to the pressure sensor and the gas storage device, and controls the gas storage device to charge and discharge the cylinder and inflate the piston-type shock rod according to the pressure signal detected by the pressure sensor, so as to adjust the tilt angle and length of the piston-type shock rod.

2. The adaptive shock rod device according to claim 1, characterized in that, The gas storage device is communicated with the piston-type shock rod through a first gas pipeline; The gas storage device is separately communicated with each of the cylinders through a second gas pipeline.

3. The adaptive shock rod device according to claim 2, characterized in that, The spherical hinge has an air inlet passage passing through its center of the sphere; The air inlet passage forms a part of the first gas pipeline.

4. The adaptive shock rod device according to claim 3, characterized in that, The spherical hinge is filled with a light material, and the air inlet passage is formed by surrounding with the light material.

5. The adaptive shock rod device according to claim 4, characterized in that, The light material is a carbon fiber composite material or aluminum alloy.

6. The adaptive shock rod device according to any one of claims 1-5, characterized in that, The gas storage device has independent gas sources corresponding to the piston-type shock rod and the cylinder in a one-to-one manner.

7. The adaptive shock rod device according to any one of claims 1-5, characterized in that, Four hinge points on the outer peripheral surface of the spherical hinge form a hinge plane, and the hinge plane passes through the center of the sphere of the spherical hinge and is perpendicular to the axial direction of the piston-type shock rod.

8. The adaptive shock rod device according to any one of claims 1-5, characterized in that, The gas storage device is provided with a boss for connecting the cross-shaped lever.

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