High-speed cross-medium combined power system based on rotating rocket

Abstract

The high-speed cross-medium combined power system based on the rotating rocket comprises a horizontally-arranged hollow transmission shaft, the middle section of the transmission shaft is fixedly and coaxially sleeved with the rotating rocket, one end of the transmission shaft is a water inlet, and the other end of the transmission shaft is provided with an axial flow water pump communicating with the transmission shaft; propellants are arranged in the rotating rockets; at least two spray pipes are arranged at the tail part of the rotating rocket; the gas collecting cavity and the annular afterburning chamber are coaxially arranged on the transmission shaft in a sleeving mode and communicate with each other, and the gas collecting cavity communicates with the rotating rocket through the spray pipes; the compressed air pipe is coaxially arranged outside the rotating rocket in a sleeving manner; one end of the compressed air pipe is provided with a compressor, and the other end is sealed; the gas compressor is fixedly and coaxially sleeved on the transmission shaft; a plurality of compressed air inlets are formed in the annular afterburning chamber; and the compressed air pipe is communicated with the annular afterburning chamber through the compressed air inlet. The contradiction that an existing cross-medium aircraft cannot achieve high fusion of flight power and underwater power is solved.

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 refers to a new concept special aircraft that can fly in the air and dive underwater. It has the advantages of high speed and long range of missile weapons and good concealment of submarines. It can realize repeated switching of water / air medium, making it difficult for the enemy's conventional combat system to cope with it, forming a subversive combat capability, and becoming a new combat power growth point in the future maritime combat system.

[0003] At present, large-scale cross-medium aircraft, such as rocket-assisted torpedoes, all adopt the structure of rocket booster + torpedo. After the boost is completed, the two are separated. The torpedo enters the water once to complete the mission and cannot get out of the water again. Although small cross-medium aircraft can realize repeated switching between water / air media, their air modes mostly use propeller propulsion, which has a low speed, and the response speed and penetration capability are greatly limited. Although ramjet / water ramjet can achieve high-speed navigation, boosters are required for acceleration in both air and water, and their use is limited. In the future, the realization of high-speed cross-medium flight will face two difficulties: one is how to achieve a high degree of integration of flight power and underwater power; the other is how to solve the contradiction between high-speed flight and multiple cross-medium. Therefore, it is necessary to design a new power system suitable for high-speed cross-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, so as 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 scheme: a high-speed cross-medium combined power system based on a rotating rocket, comprising a horizontally arranged hollow transmission shaft, the middle section of the transmission shaft is fixed and coaxially mounted with a rotating rocket, one end of the transmission shaft is a switchable water inlet, and the other end is provided with an axial flow water pump connected thereto; propellant is arranged in the rotating rocket; at least two nozzles are arranged at the tail of the rotating rocket; each nozzle is used to spray out combustion gas to generate a rotational torque to drive the rotating rocket to rotate about the transmission shaft;

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

[0007] It also includes a hollow compressed air pipe, which is coaxially sleeved outside the rotating rocket; both ends of the compressed air pipe are sealed, and a compressor is arranged at one end away from the air collecting cavity, and the compressor is fixed and coaxially sleeved 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 arranged on the pipe 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 type 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 with 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 respectively used to connect to the positive and negative electrodes of the power supply, 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 contracted and closed;

[0016] The water inlet guides the sucked water or air into the housing of the axial flow water pump, and 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] Further, 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 will occur and then ejected through the rear jet pipe to provide overall operating thrust.

[0021] Further, the following are included:

[0022] The rotating rocket always remains in a working state before entering the water, sailing underwater, before emerging from the water and in the air flight mode. The rotating rocket ejects high-speed combustion gas laterally through the side nozzle to generate 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 rotating rocket suitable for high-speed cross-medium aircraft. The rotating rocket is used as the core power source. The rotation of the rotating rocket provides a power source for the axial flow water pump and the compressor. Combined with the opening and closing control of the water inlet and the air inlet, the axial flow water pump can be used underwater to provide power for the overall 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 overall power system. This structure provides a new power mode for underwater high-speed navigation, which can obtain better propulsion efficiency and find a breakthrough for the organic integration of air power and underwater power. It solves the 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 switching of air / water mode, and excellent air flight mode performance.

[0025] The present invention proposes a new scheme of rotary rocket booster propulsion based on electronically controlled solid propulsion, namely, 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 adjustability of a solid rocket, thereby improving the adjustment capability and adaptability of the power system.

Brief Description of the Drawings

[0026] Figure 1 It 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 It is a three-dimensional structural schematic diagram of a high-speed cross-medium combined power system based on a rotating rocket of the present invention;

[0028] Figure 3 It 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 5It 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 The present invention is a schematic diagram of a high-speed cross-medium combined power system based on a rotating rocket working in an underwater diving mode.

[0032] Among them, 1. water inlet; 2. nozzle; 3. air inlet; 4. compressed air pipe; 5. rotating rocket; 6. air collecting cavity; 7. compressed air inlet; 8. annular afterburner chamber; 9. water spray pipe; 10. axial flow water pump; 11. transmission shaft; 12. compressor; 13. jet pipe, 14. propellant, 15. electrode cover plate, 16. air outlet. [Specific implementation method]

[0033] The present invention is 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 comprises 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; the rotating rocket 5 is provided with a propellant such as hydroxylamine nitrate-based electrically controlled fuel-rich propellant; 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 afterburner 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 afterburner 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 arranged at the end away from the air collecting chamber 6, and the compressor 12 is fixed and coaxially mounted on the transmission shaft 11.

[0037] A plurality of compressed air inlets 7 are provided on the annular afterburning chamber 8 ; the compressed air pipe 4 is connected to the annular afterburning chamber 8 via the compressed air inlet 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 rotation torque to drive itself to rotate; the transmission shaft 11 is used to rotate with the rotating rocket 5, and at the same time 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 into the annular afterburner 8 through the inside of the compressed air pipe 4 and the compressed air inlet 7 in sequence; 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 allow water entering from the water inlet 1 to flow 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 opened.

[0042] At least two air inlets 3 are provided on the compressed air pipe 4, near the air inlet side of the compressor 12, and the air inlet 3 is provided with an openable and closable baffle; the air inlet 3 is used to inhale air in the open state. When entering the underwater navigation stage, the baffle is closed to stop inhaling air.

[0043] In some embodiments, each nozzle 2 is a Laval type 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 provided on both sides of the propellant 14, and the two electrode covers 15 are used to connect the positive and negative electrodes of the power supply respectively, wherein the electrode cover 15 near the nozzle 2 is provided with a plurality of air outlets 16. The propellant 14 is a cylindrical structure, and the electrode cover 15 is a cylindrical cover structure, which is stuck at both ends of the propellant, and can provide voltage and fix the propellant. By adjusting and controlling the voltage between the two electrode covers 15, the combustion speed of the propellant can be controlled, and finally the operation speed of the overall combined power system can be adjusted.

[0047] The present invention provides a working method of a high-speed cross-medium combined power system based on a rotating rocket, which comprises 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 contracted and closed;

[0049] The water inlet 1 guides the sucked water or air into the housing of the axial flow water pump 10, and the axial flow water pump 10 accelerates the sucked water. The water spray port 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 chamber 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, in underwater navigation, before leaving the water and in the air flight mode, the rotating rocket 5 always keeps working. 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. At the same time, the combustion gas generated by the rotating rocket 5 will be introduced into the annular afterburner 8.

[0057] The present invention designs a new type of combined power system based on a rotating rocket suitable for high-speed cross-medium aircraft. The rotating rocket is used as the core power source. The rotation of the rotating rocket provides a power source for the axial flow water pump and the compressor. Combined with the opening and closing control of the water inlet and the air inlet, the axial flow water pump can be used underwater to provide power for the overall 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 overall power system. This structure provides a new power mode for underwater high-speed navigation, which can obtain better propulsion efficiency and find a breakthrough for the organic integration of air power and underwater power. It solves the 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 switching of air / water mode, and excellent air flight mode performance.

[0058] The present invention proposes a new scheme of rotary rocket booster propulsion based on electronically controlled solid propulsion, namely, 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 adjustability of a solid rocket, thereby improving the adjustment capability 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 a rotating rocket (5) is fixedly mounted in the middle section of the transmission shaft (11) and coaxially mounted thereon, wherein 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 is arranged in the rotating rocket (5); at least two nozzles (2) are arranged at the tail of the rotating rocket (5); each nozzle (2) is used to eject combustion gas outwards to generate a rotational torque to drive the rotating rocket (5) to rotate about the transmission shaft (11); It also comprises a gas collecting chamber (6) and an annular afterburning chamber (8) which are coaxially sleeved on the transmission shaft (11) and are 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 arranged at one end thereof away from the air collecting chamber (6); 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) via the compressed air inlets (7).

2. A high-speed cross-medium combined power system based on a rotating rocket as claimed in claim 1, characterized in that: At least two air inlets (3) are arranged on the wall of the compressed air pipe (4) and on the air inlet side close to the compressor (12), and the air inlet (3) is provided with an openable and closable baffle.

3. A high-speed cross-medium combined power system based on a rotating rocket as described in claim 1 or 2, 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.

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

5. 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).

6. A high-speed cross-medium combined power system based on a rotating rocket as claimed in claim 3, characterized in that: Electrode cover plates (15) are provided on both sides of the propellant (14), and the two electrode cover plates (15) are respectively used to connect to the positive electrode and the negative electrode of the power supply, wherein the electrode cover plate (15) close to the nozzle (2) is provided with a plurality of air outlet holes (16).

7. A working method of a high-speed cross-medium combined power system based on a rotating rocket, characterized in that: A high-speed cross-medium combined power system based on a rotating rocket according to any one of claims 1 to 6, comprising the following contents: 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 contracted 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, and the water spray port (9) is used to spray out the accelerated high-speed water flow to generate thrust.

8. The working method according to claim 7, 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 chamber (8) at the same time, mixed combustion occurs and then ejected through the rear jet pipe (13) to provide overall operating thrust.

9. The working method according to claim 7 or 8, 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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