A high-speed cross-medium combined propulsion system based on rotating rockets

Abstract

The present invention discloses a high-speed cross-medium combined power system based on a rotating rocket, comprising a horizontally arranged hollow transmission shaft, the middle section of which is fixed and coaxially fitted with a rotating rocket, one end of the transmission shaft being a water inlet, and the other end being provided with an axial flow water pump connected thereto; propellant being provided in the rotating rocket; at least two nozzles being provided at the tail of the rotating rocket; an air collecting chamber and an annular afterburner being coaxially fitted on the transmission shaft and connected to each other, the air collecting chamber being connected to the rotating rocket through each nozzle; a compressed air pipe being coaxially fitted on the outside of the rotating rocket; a compressor being provided at one end of the compressed air pipe and being sealed at the other end; the compressor being fixed and coaxially fitted on the transmission shaft; a plurality of compressed air inlets being provided on the annular afterburner; and the compressed air pipe being connected to the annular afterburner through the compressed air inlets. The system solves the contradiction that existing cross-medium aircraft cannot achieve a high degree of integration of flight power and underwater power.

Description

Technical field

[0001] The present invention belongs to the technical field of aviation power devices, and in particular relates to a high-speed cross-medium combined power system based on a rotating rocket. [Background Technology]

[0002] Cross-medium aircraft are new-concept specialized aircraft capable of both airborne flight and underwater submersion. They combine the high-speed, long-range capabilities of missiles with the stealthiness of submarines. They can repeatedly switch between air and water, making it difficult for conventional enemy combat systems to respond. This creates a disruptive combat capability and will become a new growth point for future maritime combat systems.

[0003] Currently, large-scale trans-medium aircraft, such as rocket-assisted torpedoes, all utilize a rocket booster + torpedo configuration. After the boost is complete, the two separate, and the torpedo completes its mission once it enters the water and cannot re-emerge. While small trans-medium aircraft can repeatedly switch between water and air, their aerial modes often utilize propeller propulsion, which is relatively slow, significantly limiting their response speed and penetration capabilities. While ramjet / water ramjet technology can achieve high-speed travel, it requires boosters for acceleration in both air and water, limiting its use. Achieving high-speed trans-medium flight in the future will face two challenges: first, achieving a high degree of integration between flight power and underwater propulsion; second, resolving the conflict between high-speed flight and multiple trans-medium crossings. Therefore, it is necessary to design a new propulsion system suitable for high-speed trans-medium aircraft. [Summary of the invention]

[0004] The purpose of the present invention is to provide a high-speed cross-medium combined power system based on a rotating rocket to solve the problems of how to achieve a high degree of integration of flight power and underwater power in existing cross-medium aircraft, and how to solve the contradiction between high-speed flight and multiple cross-medium.

[0005] The present invention adopts the following technical solution: a high-speed cross-medium combined power system based on a rotating rocket, comprising a horizontally arranged hollow transmission shaft, a fixed middle section of the transmission shaft and a coaxially mounted rotating rocket, one end of the transmission shaft being a switchable water inlet, and the other end being provided with an axial flow water pump connected thereto; a propellant is provided in the rotating rocket; at least two nozzles are provided at the tail of the rotating rocket; each nozzle is configured to eject gas outward to generate a rotational torque to drive the rotating rocket to rotate about the transmission shaft;

[0006] It also includes a gas collecting chamber and an annular afterburner chamber coaxially sleeved on the transmission shaft and connected to each other, and the gas collecting chamber is connected to the rotating rocket through each nozzle;

[0007] It also includes a hollow compressed air pipe, which is coaxially mounted outside the rotating rocket; both ends of the compressed air pipe are sealed, and a compressor is provided at the end away from the air collecting cavity, and the compressor is fixed and coaxially mounted on the transmission shaft;

[0008] The annular afterburning chamber is provided with a plurality of compressed air inlets; the compressed air pipe is communicated with the annular afterburning chamber through the compressed air inlets.

[0009] Furthermore, at least two air inlets are provided on the wall of the compressed air pipe, close to the air inlet side of the compressor, and the air inlets are provided with openable and closable baffles.

[0010] Furthermore, each nozzle is a Laval nozzle, and the direction of the force generated by each nozzle is circumferential.

[0011] Furthermore, the outlet of the axial flow water pump is connected to a water spray pipe.

[0012] Furthermore, a jet pipe is provided on the side of the annular afterburner away from the rotating rocket.

[0013] Furthermore, electrode covers are provided on both sides of the propellant, and the two electrode covers are used to connect to the positive and negative poles of the power supply respectively, wherein a plurality of air outlet holes are provided on the electrode cover close to the nozzle side.

[0014] The second technical solution adopted by the present invention is a working method of a high-speed cross-medium combined power system based on a rotating rocket, which includes the following contents:

[0015] When the high-speed cross-medium combined power system is in the three modes of before entering the water, underwater navigation and before leaving the water, the water inlet is opened and the air inlet is retracted and closed;

[0016] The water inlet introduces the sucked water or air into the housing of the axial flow water pump. The axial flow water pump accelerates the sucked water. The water spray port is used to spray out the accelerated high-speed water flow to generate thrust.

[0017] Furthermore, the following are included:

[0018] In the high-speed cross-medium combined power system in the air flight mode, the water inlet is closed and the air inlet is extended and opened;

[0019] The compressor is used to compress the air introduced through the air inlet and introduce it into the annular afterburning chamber through the compressed air inlet;

[0020] When air and gas are introduced into the annular afterburner at the same time, mixed combustion occurs and then ejected through the rear injection pipe to provide overall operating thrust.

[0021] Furthermore, the following are included:

[0022] Before entering the water, during underwater navigation, before emerging from the water and in the air flight mode, the rotating rocket always remains in a working state. The rotating rocket ejects high-speed combustion gas laterally through the side nozzle, thereby generating a circumferential rotational torque. Through its own rotation, it drives the transmission shaft to rotate, thereby driving the compressor and axial flow water pump to work.

[0023] The beneficial effects of the present invention are:

[0024] The present invention designs a new type of combined power system based on a rotary rocket suitable for high-speed cross-medium aircraft. The rotary rocket is used as the core power source. The rotation of the rotary rocket provides a power source for the axial flow pump and the compressor. Combined with the opening and closing control of the water inlet and the air inlet, the axial flow pump can be used underwater to provide power for the entire power system. In the air, the combustion of air and high-temperature combustion gas in the annular afterburner generates thrust to provide power for the entire power system. This structure provides a new power mode for high-speed underwater navigation, can achieve better propulsion efficiency, and also finds a breakthrough for the organic integration of air power and underwater power. It solves the difficult problems of high integration of air power and underwater power of high-speed cross-medium aircraft, and the contradiction between high-speed flight and multiple cross-medium. It has the advantages of zero-speed start-up in water / air medium, wide adjustable range of operating speed, flexible air / water mode switching, and excellent air flight mode performance.

[0025] The present invention proposes a new scheme for rotary rocket booster propulsion based on electronically controlled solid propulsion. That is, by adding electrode covers at both ends of the propellant, the burning rate of the propellant can be controlled by controlling the voltage, thereby controlling the operating speed of the overall combined power system. The overall combined power system has the advantages of high performance and strong maneuverability of a rotary turbine rocket, and realizes the characteristics of repeatable starting and adjustment of solid rockets, thereby improving the adjustment ability and adaptability of the power system.

Brief Description of the Drawings

[0026] Figure 1 This is a longitudinal cross-sectional schematic diagram of a high-speed cross-medium combined power system based on a rotating rocket according to the present invention;

[0027] Figure 2 This is a schematic diagram of the three-dimensional structure of a high-speed cross-medium combined power system based on a rotating rocket according to the present invention;

[0028] Figure 3 This is a schematic diagram of the three-dimensional structure of the rotating rocket of the present invention;

[0029] Figure 4 for Figure 3 Side view of

[0030] Figure 5This is a schematic diagram of the working mode of a high-speed cross-medium combined power system based on a rotating rocket in the air;

[0031] Figure 6 This is a schematic diagram of the operation of a high-speed cross-medium combined power system based on a rotating rocket in underwater diving mode according to the present invention.

[0032] Among them, 1. Water inlet; 2. Nozzle; 3. Air inlet; 4. Compressed air pipe; 5. Rotating rocket; 6. Gas collecting chamber; 7. Compressed air inlet; 8. Annular afterburner; 9. Water spray pipe; 10. Axial flow water pump; 11. Drive shaft; 12. Compressor; 13. Jet pipe, 14. Propellant, 15. Electrode cover, 16. Air outlet. [Specific implementation method]

[0033] The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.

[0034] The present invention discloses a high-speed cross-medium combined power system based on a rotating rocket, such as Figure 1 and Figure 2 As shown, it includes a horizontally arranged hollow transmission shaft 11, the middle section of the transmission shaft 11 is fixed and coaxially mounted with a rotating rocket 5, one end of the transmission shaft 11 is a switchable water inlet 1, and the other end is provided with an axial flow water pump 10 connected thereto; a propellant such as a hydroxylamine nitrate-based electronically controlled fuel-rich propellant is provided in the rotating rocket 5; Figure 3 and Figure 4 As shown, at least two nozzles 2 are provided at the tail of the rotating rocket 5; each nozzle 2 is used to eject gas outward to generate a rotational torque to drive the rotating rocket 5 to rotate about the transmission shaft 11;

[0035] It also includes an air collecting chamber 6 and an annular afterburning chamber 8 which are coaxially mounted on the transmission shaft 11 and are interconnected. The air collecting chamber 6 is connected to the rotating rocket 5 through each nozzle 2. Both the air collecting chamber 6 and the annular afterburning chamber 8 are hollow cylindrical structures.

[0036] It also includes a hollow compressed air pipe 4, which is coaxially mounted on the outside of the rotating rocket 5; both ends of the compressed air pipe 4 are sealed, and a compressor 12 is set at the end away from the air collecting chamber 6. The compressor 12 is fixed and coaxially mounted on the transmission shaft 11.

[0037] The annular afterburning chamber 8 is provided with a plurality of compressed air inlets 7 ; the compressed air pipe 4 is connected to the annular afterburning chamber 8 through the compressed air inlets 7 .

[0038] The rotating rocket 5 is used to burn the fuel therein to generate high-speed combustion gas, and eject the high-speed combustion gas laterally through the nozzle 2, thereby generating a circumferential rotational torque to drive the rotating rocket 5; the transmission shaft 11 is used to rotate with the rotating rocket 5 and simultaneously drive the compressor 12 and the axial flow water pump 10 to rotate;

[0039] The high-speed combustion gas generated by the rotating rocket 5 enters the annular afterburner 8 through the nozzle 2 and the gas collecting cavity 6. The compressed air pipe 4 is used to pass the gas sucked by the compressor 12 through the interior of the compressed air pipe 4 and the compressed air inlet 7 into the annular afterburner 8. The annular afterburner 8 is used to mix the high-speed combustion gas and compressed air entering therein for secondary combustion to generate thrust.

[0040] The transmission shaft 11 is used to flow water entering from the water inlet 1 into the housing of the axial flow water pump 10 through the transmission shaft 11 and then be discharged after being accelerated by the axial flow water pump 10 to generate thrust.

[0041] In some embodiments, at least two air inlets 3 are provided on the wall of the compressed air pipe 4, near the air inlet side of the compressor 12, and an openable and closable baffle is provided on the air inlet 3. The air inlet 3 is used to inhale air when the baffle is open.

[0042] At least two air inlets 3 are provided on the compressed air pipe 4, near the air inlet side of the compressor 12. Each air inlet 3 is provided with an openable and closable flap. When the air inlet 3 is open, it is used to take in air. When entering the underwater navigation phase, the flap is closed to stop taking in air.

[0043] In some embodiments, each nozzle 2 is a Laval nozzle, and the direction of the force generated by each nozzle 2 is circumferential.

[0044] In some embodiments, the outlet of the axial flow water pump 10 is connected to a water spray pipe 9 .

[0045] In some embodiments, a jet pipe 13 is provided on the side of the annular afterburner 8 away from the rotating rocket 5 .

[0046] In some embodiments, electrode covers 15 are installed on either side of the propellant 14. These two electrode covers 15 are used to connect to the positive and negative poles of a power source, respectively. The electrode cover 15 near the nozzle 2 is provided with multiple air outlets 16. The propellant 14 is cylindrical, and the electrode covers 15 are cylindrical caps that clamp onto the ends of the propellant, providing both voltage and securing the propellant. By adjusting the voltage between the two electrode covers 15, the combustion rate of the propellant can be controlled, ultimately regulating the operating speed of the entire combined power system.

[0047] The present invention provides a working method of a high-speed cross-medium combined power system based on a rotating rocket, which includes the following contents:

[0048] like Figure 6As shown, when the high-speed cross-medium combined power system is in the three modes of before entering the water, underwater navigation and before leaving the water, the water inlet 1 is opened and the air inlet 3 is retracted and closed;

[0049] The water inlet 1 introduces the sucked water or air into the housing of the axial flow water pump 10. The axial flow water pump 10 accelerates the sucked water. The water outlet 9 is used to spray out the accelerated high-speed water flow to generate thrust.

[0050] In the underwater navigation mode of the high-speed cross-medium combined power system, the air inlet 3 shrinks and closes; when no air is introduced into the annular afterburner 8, mixed combustion does not occur, and the annular afterburner 8 discharges the high-temperature combustion gas therein through the jet pipe 13.

[0051] In some embodiments, the following are included:

[0052] like Figure 5 As shown, in the high-speed cross-medium combined power system in the air flight mode, the water inlet 1 is closed and the air inlet 3 is extended and opened;

[0053] The compressor 12 is used to compress the air introduced through the air inlet 3 and introduce it into the annular afterburning chamber 8 through the compressed air inlet 7;

[0054] When air and fuel gas are introduced into the annular afterburner 8 at the same time, mixed combustion will occur and then ejected through the rear injection pipe 13 to provide overall operating thrust.

[0055] In some embodiments, the following are included:

[0056] Before entering the water, while sailing underwater, before emerging from the water, and in the air, the rotating rocket 5 remains in operation. It ejects high-speed combustion gas laterally through its side nozzle 2, generating a circumferential rotational torque. Its own rotation drives the transmission shaft, thereby driving the compressor 12 and axial-flow water pump 10. Simultaneously, the combustion gas produced by the rotating rocket 5 is introduced into the annular afterburner 8.

[0057] The present invention designs a new type of combined power system based on a rotary rocket suitable for high-speed cross-medium aircraft. The rotary rocket is used as the core power source. The rotation of the rotary rocket provides a power source for the axial flow pump and the compressor. Combined with the opening and closing control of the water inlet and the air inlet, the axial flow pump can be used underwater to provide power for the entire power system. In the air, the combustion of air and high-temperature combustion gas in the annular afterburner generates thrust to provide power for the entire power system. This structure provides a new power mode for high-speed underwater navigation, can achieve better propulsion efficiency, and also finds a breakthrough for the organic integration of air power and underwater power. It solves the difficult problems of high integration of air power and underwater power of high-speed cross-medium aircraft, and the contradiction between high-speed flight and multiple cross-medium. It has the advantages of zero-speed start-up in water / air medium, wide adjustable range of operating speed, flexible air / water mode switching, and excellent air flight mode performance.

[0058] The present invention proposes a new scheme for rotary rocket booster propulsion based on electronically controlled solid propulsion. That is, by adding electrode covers at both ends of the propellant, the burning rate of the propellant can be controlled by controlling the voltage, thereby controlling the operating speed of the overall combined power system. The overall combined power system has the advantages of high performance and strong maneuverability of a rotary turbine rocket, and realizes the characteristics of repeatable starting and adjustment of solid rockets, thereby improving the adjustment ability and adaptability of the power system.

Claims

1. A high-speed cross-medium combined power system based on a rotating rocket, characterized in that: The invention comprises a horizontally arranged hollow transmission shaft (11), wherein the middle section of the transmission shaft (11) is fixed and coaxially sleeved with a rotating rocket (5), one end of the transmission shaft (11) is a switchable water inlet (1), and the other end is provided with an axial flow water pump (10) connected thereto; propellant is provided in the rotating rocket (5); at least two nozzles (2) are provided at the tail of the rotating rocket (5); each nozzle (2) is used to eject gas outwards to generate a rotational torque to drive the rotating rocket (5) to rotate about the transmission shaft (11); It also includes a gas collecting chamber (6) and an annular afterburning chamber (8) coaxially sleeved on the transmission shaft (11) and arranged in communication with each other, wherein the gas collecting chamber (6) is in communication with the rotating rocket (5) through each of the nozzles (2); It also includes a hollow compressed air pipe (4) which is coaxially sleeved outside the rotating rocket (5); both ends of the compressed air pipe (4) are sealed, and a compressor (12) is provided at one end thereof away from the air collecting chamber (6), and the compressor (12) is fixed and coaxially sleeved on the transmission shaft (11); The annular afterburning chamber (8) is provided with a plurality of compressed air inlets (7); the compressed air pipe (4) is connected to the annular afterburning chamber (8) through the compressed air inlets (7); At least two air inlets (3) are provided on the wall of the compressed air pipe (4) and on the air inlet side close to the compressor (12), and an openable and closable baffle is provided on the air inlet (3).

2. A high-speed cross-medium combined power system based on a rotating rocket as claimed in claim 1, characterized in that: Each of the nozzles (2) is a Laval-type nozzle, and the direction of the force generated by each of the nozzles (2) is circumferential.

3. A high-speed cross-medium combined power system based on a rotating rocket as claimed in claim 1 or 2, characterized in that: The outlet of the axial flow water pump (10) is connected to a water spray pipe (9).

4. A high-speed cross-medium combined power system based on a rotating rocket as claimed in claim 3, characterized in that: A jet pipe (13) is provided on the side of the annular afterburning chamber (8) away from the rotating rocket (5).

5. A high-speed cross-medium combined power system based on a rotating rocket as claimed in claim 4, characterized in that: Electrode covers (15) are provided on both sides of the propellant (14), and the two electrode covers (15) are respectively used to connect to the positive electrode and the negative electrode of the power supply, wherein the electrode cover (15) close to the nozzle (2) is provided with a plurality of air outlet holes (16).

6. A method for operating a high-speed cross-medium combined power system based on a rotating rocket, characterized in that: A high-speed cross-medium combined propulsion system based on a rotating rocket according to claim 5, comprising the following: When the high-speed cross-medium combined power system is in the three modes of before entering the water, underwater navigation and before leaving the water, the water inlet (1) is opened and the air inlet (3) is retracted and closed; The water inlet (1) guides the sucked water or air into the housing of the axial flow water pump (10). The axial flow water pump (10) accelerates the sucked water. The water spray pipe (9) is used to spray out the accelerated high-speed water flow to generate thrust.

7. The working method according to claim 6, characterized in that: Includes the following: When the high-speed cross-medium combined power system is in an air flight mode, the water inlet (1) is closed and the air inlet (3) is extended and opened; The compressor (12) is used to compress the air introduced through the air inlet (3) and introduce the air into the annular afterburning chamber (8) through the compressed air inlet (7); When air and fuel gas are introduced into the annular afterburner (8) at the same time, mixed combustion occurs and is ejected through the rear injection pipe (13) to provide overall operating thrust.

8. The working method according to claim 6 or 7, characterized in that: Includes the following: Before entering the water, in underwater navigation, before emerging from the water, and in the air flight mode, the rotating rocket (5) always maintains a working state. The rotating rocket (5) ejects high-speed combustion gas laterally through the side nozzle (2) to generate a circumferential rotation torque. Through its own rotation, it drives the transmission shaft to rotate, thereby driving the compressor (12) and the axial flow water pump (10) to work.

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