A power generation mechanism based on a hypersonic aircraft

Abstract

This utility model discloses a power generation mechanism based on a hypersonic aircraft, including a fan shroud (1) rotatably connected to the nose of the aircraft. The surface of the fan shroud (1) is provided with a flow guide protrusion (2). A permanent magnet (3) is fixedly connected to the inner side of the fan shroud (1). A generator stator (4) of the aircraft is fixedly connected to the inner side of the permanent magnet (3). A capacitor (5) is connected to the outer side of the generator stator (4). The flow guide protrusion (2) is used to drive the fan shroud (1) to rotate under wind force during the flight of the aircraft. After rotation, the fan shroud (1) drives the permanent magnet (3) to cut the generator stator (4), causing the generator stator (4) to generate current. The generator stator (4) is used to transmit the generated current to the capacitor (5) for energy storage. This utility model has the characteristics of small size and strong applicability.

Description

Technical Field

[0001] This utility model relates to a hypersonic aircraft, and more particularly to a power generation mechanism based on a hypersonic aircraft. Background Technology

[0002] Currently, most hypersonic vehicles use batteries as their power source for their nose-mounted fuses. In operation, the hypersonic vehicle is mounted on the missile's nose, and the missile carries it through the atmosphere at hypersonic speeds. When the warhead hits the ground, the batteries power the main control circuit module in the vehicle's nose, which then triggers the fuse, causing the munitions in the propellant magazine to explode.

[0003] However, this power supply method has its drawbacks. On the one hand, the size of the battery limits the size of the hypersonic vehicle, requiring an increase in the size of the vehicle's nose to accommodate the battery, thus increasing drag during flight. On the other hand, the battery has stringent requirements for its operating environment, being greatly affected by factors such as humidity, temperature, and salinity. This results in relatively limited storage for the hypersonic vehicle and high maintenance costs, hindering its widespread deployment across different regions.

[0004] Therefore, a small-sized and highly adaptable hypersonic aircraft power generation mechanism is needed. Utility Model Content

[0005] The purpose of this invention is to provide a power generation mechanism based on a hypersonic aircraft. It features small size and wide applicability.

[0006] The technical solution of this utility model is as follows: A power generation mechanism based on a hypersonic aircraft includes a fan shroud rotatably connected to the head of the aircraft. The surface of the fan shroud is provided with a flow guide protrusion. A permanent magnet is fixedly connected to the inner side of the fan shroud. A generator stator of the aircraft is fixedly connected to the inner side of the permanent magnet. A capacitor is connected to the outside of the generator stator. The guide protrusion is used to drive the fan cover to rotate under the action of wind force during the flight of the aircraft; The fan cover is used to drive the permanent magnet to cut the generator stator after rotation, so that the generator stator generates current. The generator stator is used to transmit the generated current to the capacitor for energy storage.

[0007] In the aforementioned power generation mechanism based on a hypersonic aircraft, a central shaft is rotatably connected to the inner side of the fan shroud via a bearing, the central shaft is fixedly connected to the head of the aircraft, and the generator stator is fixedly connected to the outside of the central shaft.

[0008] In the aforementioned power generation mechanism based on a hypersonic aircraft, a rotary switch base and a rectifier bridge housing are respectively provided on the upper and lower sides of the fan cover, and the rotary switch base and the rectifier bridge housing are fixedly connected to both ends of the central shaft.

[0009] In the aforementioned power generation mechanism based on a hypersonic aircraft, a rectifier circuit board is fixedly connected to the inner side of the rectifier bridge housing, and the output terminal of the generator stator is connected to a capacitor via the rectifier circuit board. The rectifier circuit board is used to rectify the current generated by the generator stator.

[0010] In the aforementioned power generation mechanism based on a hypersonic aircraft, a power management housing is fixedly connected to the lower end of the rectifier bridge housing. The power management housing contains a step-down module and a main control circuit module, and the capacitor is connected to the step-down module and the main control circuit module in sequence.

[0011] In the aforementioned power generation mechanism based on a hypersonic aircraft, a rotary switch intermediate seat is fixedly connected to the upper end of the rotary switch base, a rotary switch circuit board is fastened between the rotary switch intermediate seat and the rotary switch base, an operating knob is rotatably connected to the upper end of the rotary switch intermediate seat, and a rotary switch that cooperates with the rotary switch circuit board is fixedly connected to the inner side of the operating knob.

[0012] In the aforementioned power generation mechanism based on a hypersonic aircraft, the power management housing is fixedly connected to a projectile base at the end away from the rectifier bridge housing. The projectile base is equipped with an electromechanical actuator and a propellant magazine. The electromechanical actuator is externally connected to a main control circuit module and is used to trigger the explosion of the ammunition in the propellant magazine.

[0013] Compared with the prior art, this utility model has the following characteristics: (1) The present invention, through the combined arrangement of the fan cover, permanent magnet and generator stator, enables the fan cover to be driven by the wind to rotate the permanent magnet during the flight of the aircraft, thereby cutting the magnetic field lines of the generator stator on the inner side, so that the generator stator generates current and stores it through the capacitor; and with the above combination, the present application can use the above structure to generate electricity instead of the battery, thereby effectively reducing the size of the aircraft's nose and improving its applicability; (2) By limiting the fan cover installation structure, on the one hand, the fan cover used to drive the permanent magnet to rotate can be made into an integrated structure with the aircraft shell, thereby simplifying the aircraft structure and facilitating the assembly by the operators; on the other hand, the fan cover can be installed and positioned by using the central axis, ensuring the installation stability of the fan cover on the aircraft and preventing the rotary switch base and rectifier bridge shell on both sides from hindering the rotation of the fan cover, thereby improving the operational stability of this utility model. (3) By limiting the installation structure of the main control circuit module, the main control circuit module can also be installed at the tail end of the aircraft, thereby better protecting the main control circuit module from damage when the warhead hits the ground and improving the operational stability of the main control circuit module. Therefore, this utility model has the characteristics of small size and strong applicability. Attached Figure Description

[0014] Figure 1 This is a schematic diagram of the structure of this utility model; Figure 2 yes Figure 1 A magnified view from direction A; Figure 3 This is the outline drawing of this utility model.

[0015] The labels in the attached diagram are as follows: 1-Fan cover, 2-Guide boss, 3-Permanent magnet, 4-Generator stator, 5-Capacitor, 6-Bearing, 7-Central shaft, 8-Rotary switch base, 9-Rectifier bridge housing, 10-Rectifier circuit board, 11-Power management housing, 12-Step-down module, 13-Main control circuit module, 14-Rotary switch intermediate seat, 15-Rotary switch circuit board, 16-Operating knob, 17-Rotary switch, 18-Projectile base, 19-Electromechanical actuator, 20-Medical cartridge. Detailed Implementation

[0016] The present invention will be further described below with reference to the accompanying drawings and embodiments, but this should not be construed as limiting the present invention.

[0017] Example. A power generation mechanism based on a hypersonic aircraft, configured as follows: Figure 1 As shown, it includes a fan shroud 1 rotatably connected to the head of the aircraft. The surface of the fan shroud 1 is provided with a flow guide protrusion 2. A permanent magnet 3 is fixedly connected to the inner side of the fan shroud 1. A generator stator 4 of the aircraft is fixedly connected to the inner side of the permanent magnet 3. A winding coil that matches the permanent magnet 3 is wound around the outside of the generator stator 4. A capacitor 5 is connected to the outside of the generator stator 4. The guide protrusion 2 is used to drive the fan cover 1 to rotate under the action of wind force during the flight of the aircraft; The fan cover 1 is used to drive the permanent magnet 3 to cut the generator stator 4 after rotation, so that the generator stator 4 generates current. The generator stator 4 is used to transmit the current to the capacitor 5 for energy storage after generating the current.

[0018] The inner side of the fan cover 1 is rotatably connected to the central shaft 7 via the bearing 6. The central shaft 7 is fixedly connected to the head of the aircraft. The generator stator 4 is fixedly connected to the outside of the central shaft 7 and is distributed vertically offset from the bearing 6.

[0019] The upper and lower sides of the fan cover 1 are respectively provided with a knob switch base 8 and a rectifier bridge housing 9. The outer surfaces of the knob switch base 8 and the rectifier bridge housing 9 are flush with the outer surface of the fan cover 1. The two ends of the central shaft 7 are fixedly connected to the knob switch base 8 and the rectifier bridge housing 9.

[0020] A rectifier circuit board 10 is fixedly connected to the inner side of the rectifier bridge housing 9. The output terminal of the generator stator 4 is connected to a capacitor 5 via the rectifier circuit board 10. The rectifier circuit board 10 is used to rectify the current generated by the generator stator 4.

[0021] The lower end of the rectifier bridge housing 9 is fixedly connected to a power management housing 11. The power management housing 11 is equipped with a step-down module 12 and a main control circuit module 13. The capacitor 5 is externally connected to the step-down module 12 and the main control circuit module 13. The rectifier circuit board 10 and the capacitor 5 are interconnected through the step-down module 12. The upper end of the power management housing 11 is provided with an opening for wires to pass through.

[0022] The upper end of the rotary switch base 8 is fixedly connected to a rotary switch intermediate seat 14. A rotary switch circuit board 15 is fastened between the rotary switch intermediate seat 14 and the rotary switch base 8. An operation knob 16 is rotatably connected to the upper end of the rotary switch intermediate seat 14. A rotary switch 17 is fastened to the inner side of the operation knob 16. The rotary switch 17 and the rotary switch circuit board 15 are interconnected via contacts and springs. The rotary switch 17 can change the control circuit on the rotary switch circuit board 15 by rotating the switching contacts, thereby realizing the switching of aircraft functions.

[0023] The central shaft 7 has a cylindrical structure with wiring holes on its inner side. A wiring tube is provided inside the power management housing 11 on one side of the capacitor 5 and the step-down module 12. The wiring tube is not shown in the figure. The upper end of the wiring tube is connected to the central shaft 7, and the lower end of the wiring tube is connected to the main control circuit module 13. The connecting wire of the rotary switch circuit board 15 extends through the wiring holes and wiring tube to the bottom of the step-down module 12 and connects to the main control circuit module 13, thereby transmitting the control signal to the main control circuit module 13.

[0024] The operation knob 16 has a marking line on its outside, and the knob switch middle seat 14 has four marking lines on its outside, corresponding to the four function positions of collision, proximity explosion, delay and standby. By rotating the operation knob 16 to align the marking line with any of the marking lines on the knob switch middle seat 14, the four different positions can be switched.

[0025] The power management housing 11 has a projectile base 18 fixedly connected to the end away from the rectifier bridge housing 9. The projectile base 18 is equipped with an electromechanical actuator 19 and a cartridge 20. The cartridge 20 is filled with ammunition. The electromechanical actuator 19 is externally connected to the main control circuit module 13 and is used to trigger the explosion of the ammunition in the cartridge 20.

[0026] The working principle of this invention is as follows: The hypersonic vehicle is mounted on the missile's nose cone, and operators select the missile's functions by rotating the control knob 16. After launch, the missile carries the hypersonic vehicle and achieves hypersonic flight within the atmosphere. During flight, wind power drives the guide vane 2 and fan shroud 1 to rotate at high speed, thereby driving the generator stator 4 to generate electricity. The electrical energy generated by the generator stator 4 is first rectified by the rectifier circuit board 10, then stepped down by the voltage reduction module 12, and finally charged and stored in the capacitor 5. The capacitor 5 supplies power to the electromechanical actuator 19 through the main control circuit module 13, enabling the electromechanical actuator 19 to subsequently trigger the fuse, causing the ammunition in the propellant magazine 20 to explode.

Claims

1. A power generation mechanism based on a hypersonic aircraft, characterized in that: The fan cover (1) is rotatably connected to the head of the aircraft. The surface of the fan cover (1) is provided with a flow guide boss (2). A permanent magnet (3) is fixedly connected to the inner side of the fan cover (1). A generator stator (4) of the aircraft is fixedly connected to the inner side of the permanent magnet (3). A capacitor (5) is connected to the outside of the generator stator (4). The guide boss (2) is used to drive the fan cover (1) to rotate under the action of wind force during the flight of the aircraft; The fan cover (1) is used to drive the permanent magnet (3) to cut the generator stator (4) after rotation, so that the generator stator (4) generates current. The generator stator (4) is used to transmit the current to the capacitor (5) for energy storage after the current is generated.

2. The power generation mechanism based on a hypersonic aircraft according to claim 1, characterized in that: The inner side of the fan cover (1) is rotatably connected to the central shaft (7) via the bearing (6), the central shaft (7) is fixedly connected to the head of the aircraft, and the generator stator (4) is fixedly connected to the outside of the central shaft (7).

3. The power generation mechanism based on a hypersonic aircraft according to claim 2, characterized in that: The upper and lower sides of the fan cover (1) are respectively provided with a rotary switch base (8) and a rectifier bridge housing (9), and the two ends of the central shaft (7) are fixedly connected to the rotary switch base (8) and the rectifier bridge housing (9).

4. The power generation mechanism based on a hypersonic aircraft according to claim 3, characterized in that: A rectifier circuit board (10) is fixedly connected to the inner side of the rectifier bridge housing (9). The output terminal of the generator stator (4) is connected to a capacitor (5) via the rectifier circuit board (10). The rectifier circuit board (10) is used to rectify the current generated by the generator stator (4).

5. A power generation mechanism based on a hypersonic aircraft according to claim 3, characterized in that: The lower end of the rectifier bridge housing (9) is fixedly connected to a power management housing (11). The power management housing (11) is provided with a step-down module (12) and a main control circuit module (13). The capacitor (5) is connected to the step-down module (12) and the main control circuit module (13) in sequence.

6. A power generation mechanism based on a hypersonic aircraft according to claim 3, characterized in that: The upper end of the rotary switch base (8) is fixedly connected to the rotary switch intermediate seat (14), and the rotary switch circuit board (15) is fastened between the rotary switch intermediate seat (14) and the rotary switch base (8). The upper end of the rotary switch intermediate seat (14) is rotatably connected to the operating knob (16), and the inner side of the operating knob (16) is fixedly connected to the rotary switch (17) that cooperates with the rotary switch circuit board (15).

7. A power generation mechanism based on a hypersonic aircraft according to claim 5, characterized in that: The power management housing (11) is fixedly connected to a projectile base (18) at the end away from the rectifier bridge housing (9). The projectile base (18) is provided with an electromechanical actuator (19) and a cartridge (20). The electromechanical actuator (19) is externally connected to the main control circuit module (13) and is used to trigger the explosion of the ammunition in the cartridge (20).

Images