Underwater multi-launch aircraft launching device and launching method

Abstract

The invention belongs to the technical field of aircraft underwater launching and carrying, and particularly relates to an aircraft launching device. An underwater multi-shot type aircraft launching device comprises four cabin sections and a fixing device. An aircraft launching cylinder is arranged in the first cabin section, and a bottom channel of the aircraft launching cylinder is opened and closed through an electromagnetic valve A; the second cabin section is a pressure chamber, and the airbag is mounted on the outer side of the second cabin section and communicated with an inner chamber of the second cabin section through a gas transmission pipeline; a through hole for conveying gas into the second cabin section is formed in the top of the third cabin section; a high-pressure air pump A is arranged in the third cabin section; a high-pressure air pump B is arranged in the fourth cabin section; exhaust passages are arranged at the lower part of the high-pressure air pump B, and an electromagnetic valve E for controlling a switch is arranged on each exhaust passage; the high-pressure gas tank supplies gas to the high-pressure gas pump A and the high-pressure gas pump The fixing device is used for fixing the fourth cabin section in an initial state; and after receiving the signal, releasing the fixation. The unmanned aerial vehicle has the capability of launching multiple aircrafts and is high in stability.

Description

Technical Field

[0001] The present invention belongs to the technical field of underwater launching and carrying of aircraft, and in particular relates to an aircraft launching device and a launching method. Background Art

[0002] After the aircraft launched by submarines and other vehicles determines the target, it is launched underwater and runs for a period of time before leaving the water surface and entering the air to complete the strike mission. Due to the vastness of the ocean and the strong ability of seawater to block the transmission of electromagnetic waves, it is difficult for the enemy to conduct effective targeted surveillance, so the safety requirements for aircraft launch are high. At the same time, since the aircraft is launched on submarines and other aircraft, the aircraft itself has high maneuverability, which can ensure the concealment and uncertainty of the launch.

[0003] As the launch vehicle of the aircraft, the reliability of the launch will directly affect the performance of the aircraft, thus affecting the safety of the submarine. This requires the aircraft launcher to have a fast response speed, the ability to launch multiple aircraft, and the advantages of small size and good concealment, so as to ensure the safety of the submarine at all times. Summary of the invention

[0004] The purpose of the present invention is to provide an underwater multi-launch aircraft launching device and a launching method in response to usage requirements.

[0005] A technical solution of the present invention is: an underwater multi-engine aircraft launching device, comprising: four compartments assembled in sequence and a fixing device.

[0006] An aircraft launching tube is arranged in the first compartment, and N circular holes are left at the bottom of the aircraft launching tube and N electromagnetic valves A are arranged to realize switching.

[0007] An opening corresponding to the circular hole at the bottom of the aircraft launch tube is left on the top of the second compartment; M airbags are installed on the outside of the second compartment and connected to the inner chamber of the second compartment through a gas transmission pipeline; three electromagnetic valves are provided on the gas transmission pipeline.

[0008] A through hole is provided on the top of the third compartment for conveying gas to the second compartment; a high-pressure gas pump A is provided in the third compartment.

[0009] N high-pressure air pumps B are provided in the fourth compartment; the position and arrangement of the high-pressure air pumps B correspond to the position and arrangement of the aircraft in the aircraft launch tube; an exhaust duct is provided at the lower part of the high-pressure air pump B, and each exhaust duct is provided with an electromagnetic valve E for controlling the switch.

[0010] The high-pressure gas tank supplies gas to high-pressure gas pump A and high-pressure gas pump B.

[0011] The fixing device fixes the fourth compartment in the initial state; after receiving the signal, the fixing is released.

[0012] In the above scheme, specifically:

[0013] The first compartment is assembled by a top cover and a first compartment outer shell; N aircraft launch holes are reserved on the top cover, and the aircraft launch holes are sealed by a waterproof sealing film; a first sensor for monitoring whether water is leaking from the top cover is installed at the upper end of the outer side of the first compartment outer shell, and a second sensor for monitoring water pressure is installed at the lower part of the outer side of the first compartment outer shell; an aircraft launch tube is fixedly installed in the first compartment outer shell; the aircraft launch tube is connected and fixed to the first compartment outer shell by a locating pin.

[0014] The second compartment is a pressure chamber, comprising an outer shell of the second compartment assembled with the outer shell of the first compartment; an opening corresponding to the circular hole at the bottom of the aircraft launch tube is reserved on the top of the outer shell of the second compartment; a third sensor for monitoring internal pressure is provided inside the outer shell of the second compartment; M airbags are installed on the outside of the second compartment and connected to the outer shell of the second compartment through a gas transmission pipeline; the gas transmission pipeline is divided into: a first horizontal section connected to the outer shell of the second compartment, a third vertical section connected to the airbag, and a second inclined section connecting the first horizontal section and the third vertical section; an electromagnetic valve B is provided on the first horizontal section, and an electromagnetic valve C and an electromagnetic valve D are provided on the third vertical section; a fourth sensor for monitoring pressure is installed in the airbag.

[0015] The third compartment includes a third compartment outer shell assembled with the second compartment outer shell; a through hole is provided on the top of the third compartment outer shell for conveying gas to the second compartment outer shell; a main power supply, an aircraft launch control device, a gyroscope and a high-pressure air pump A are provided inside the third compartment outer shell.

[0016] The fourth compartment is assembled by the fourth compartment outer shell and the fourth compartment base; the fourth compartment outer shell is assembled with the third compartment outer shell; N exhaust ducts cooperating with the high-pressure air pump B are provided on the fourth compartment base, and each exhaust duct is provided with an electromagnetic valve E for controlling the switch; an antenna for wireless communication with the submarine is provided on the fourth compartment base.

[0017] The high-pressure gas tank is installed on the outside of the third and fourth compartments and is used to supply gas to high-pressure gas pumps A and B.

[0018] The fixing device includes: a limit base, in which a piston limit device and a limit rod whose movement is controlled by an air pump are arranged; one end of the limit rod passes through a through hole on the base of the fourth compartment to fix the fourth compartment; the fixing device is also provided with a power supply and a control device, and a waterproof socket for connecting and communicating with the optical fiber on the submarine.

[0019] Another technical solution of the present invention is: an underwater multi-launch aircraft launching method, based on the launching device as described above, which includes: releasing the aircraft launcher, floating the aircraft launcher, and launching the aircraft and stabilizing the aircraft.

[0020] The submarine communicates with fixed installations via fiber optics and remotely with aircraft launchers via antennas.

[0021] The steps to release the aircraft are as follows:

[0022] When the aircraft is in the initial state, the N solenoid valves A located on the aircraft launch tube are in a closed state, the solenoid valves B, C and D located on the gas transmission pipeline are all in a closed state, and the solenoid valve E located at the exhaust duct at the base of the fourth compartment is in a closed state.

[0023] After receiving the launch command, the release step is executed.

[0024] A1. The aircraft launch control device sends a command to the high-pressure air pump A located in the third compartment to inflate the second compartment.

[0025] A2. When the third sensor detects that the pressure in the pressure chamber is greater than the set value of the water pressure at the water depth, all valves on the gas transmission pipeline are opened.

[0026] A3. When the fourth sensor detects that the pressure in the air bag is greater than the set value of the water pressure at the water depth, the second valve from bottom to top on the gas transmission pipeline is closed.

[0027] A4. The power supply and control device inside the fixing device sends instructions to the air pump to control the piston limit device and the limit rod to retract, thereby releasing the lock on the fourth compartment.

[0028] A5. The aircraft launcher floats up under the action of buoyancy and is released.

[0029] After the release is completed, the floating steps are also included:

[0030] B1. During the ascent, the launch control device of the aircraft reads the data of the second sensor to monitor the water pressure in real time, and at the same time controls the third valve from bottom to top on the gas transmission pipeline to deflate, thereby controlling the pressure in the airbag and the water pressure to always remain constant.

[0031] B2. When the pressure in the pressure chamber is higher than seventy percent of the maximum pressure that the outer shell of the second compartment can withstand, the aircraft launch control device controls the first valve from bottom to top on the gas transmission pipeline to deflate.

[0032] B3. The aircraft launch control device obtains the height of the aircraft launcher from the water surface through the data of the second sensor. When the aircraft launcher floats to the set height from the water surface, the aircraft launch control device opens all the electromagnetic valves E on the exhaust duct of the base of the fourth compartment, and controls the high-pressure air pump B located in the fourth compartment to exhaust air into the exhaust duct of the fourth compartment at a pressure greater than the current water depth and water pressure, thereby accelerating the surfacing of the aircraft launcher under the action of the recoil force.

[0033] B4. After the first sensor identifies that the first compartment has emerged from water, close all electromagnetic valves E on the exhaust duct at the base of the fourth compartment, as well as the high-pressure air pump B, to complete the ascent.

[0034] After the ascent is completed, the launch step is also included:

[0035] After receiving the command to launch the aircraft from the submarine, the aircraft launch control device controls the high-pressure air pump A located in the third compartment to inflate the second compartment. When the pressure in the pressure compartment reaches 70% of the maximum pressure that the compartment can withstand, the aircraft launch control device controls the electromagnetic valve A located at the bottom of the aircraft launch tube to open the electromagnetic valve A corresponding to the aircraft to be launched, and the aircraft is ejected out of the tube under the action of the high-pressure gas.

[0036] While opening the electromagnetic valve A, the corresponding electromagnetic valve E and high-pressure air pump B on the exhaust duct of the fourth compartment base are controlled to open, so as to achieve the stabilization of the launcher's attitude by exhausting the air; after the launch is completed, the electromagnetic valve A, electromagnetic valve E and high-pressure air pump B are closed.

[0037] During the ascent and waiting for launch, the attitude of the aircraft launcher is obtained by detecting the gyroscope data; when the attitude of the aircraft launcher is unstable, the exhaust speed of the high-pressure air pump B is increased or decreased to stabilize the attitude of the aircraft launcher during the ascent.

[0038] Beneficial effects:

[0039] (1) The present invention enables the aircraft launch device to have the ability to launch multiple aircraft, and at the same time has the ability to launch a single aircraft in sequence and multiple aircraft simultaneously. It can launch aircraft according to actual combat needs, greatly increasing the penetration capability of the aircraft.

[0040] (2) The present invention accelerates the surfacing speed of the aircraft launch device by means of the launch device airbag and bottom exhaust, thereby increasing the launch response speed during combat and improving the actual confrontation capability of submarines; before the aircraft launch device surfaces to prepare for launch, the stability of the aircraft launch device's posture can be increased by exhausting air from the bottom, ensuring that the posture of the aircraft launch device before the aircraft is launched can meet the launch requirements of the aircraft.

[0041] (3) In the present invention, when a single or multiple aircraft are launched, a recoil force will be generated that affects the stability of the launch device, causing the launch device to be unstable or even overturned. The present invention can control the bottom exhaust to ensure that the launch device is always in a relatively stable posture during the launch of the aircraft, thereby greatly improving the reliability of the aircraft launch. BRIEF DESCRIPTION OF THE DRAWINGS

[0042] Figure 1 is a cross-sectional view of the present invention;

[0043] Figure 2 is a top view of the top cover of the present invention;

[0044] Figure 3 It is a top cross-sectional view of the high-pressure gas tank of the present invention;

[0045] Figure 4 This is a view of the base of the fourth compartment in the present invention;

[0046] Among them: 1-top cover, 2-fourth sensor, 3-first sensor, 4-first compartment outer shell, 5-aircraft launch tube, 6-locating pin, 7-aircraft, 8-second sensor, 9-airbag, 10-electromagnetic valve A, 11-third sensor, 12-electromagnetic valve C, 13-second compartment outer shell, 14-third compartment outer shell, 15-main power supply, 16-high-pressure air pump B, 17-electromagnetic valve E, 18-limit base, 19-piston limit device, 20-limit rod, 21-fourth compartment base, 22-power supply and control device, 23-waterproof sealing membrane, 24-electromagnetic valve D, 25-electromagnetic valve B, 26-gas transmission pipeline, 27-aircraft launch control device, 28-gyroscope, 29-high-pressure air pump A, 30-high-pressure gas tank, 31-fourth compartment outer shell, 32-antenna, 33-air pump, 34-fixing device, 35-waterproof socket. DETAILED DESCRIPTION

[0047] The present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments.

[0048] Example 1

[0049] See attached Figure 1 This embodiment provides an underwater multi-engine aircraft launching device, including: four compartments assembled in sequence and a fixing device 34.

[0050] See attached Figure 2The first compartment is assembled by a top cover 1 and a first compartment outer shell 4; 6 aircraft launch holes are reserved on the top cover 1, and the aircraft launch holes are sealed by a waterproof sealing film 23; a first sensor 3 for monitoring whether water is discharged from the top cover 1 is installed at the upper end of the outer side of the first compartment outer shell 4, and a second sensor 8 for monitoring water pressure is installed at the lower part of the outer side of the first compartment outer shell 4; an aircraft launch tube 5 is fixedly installed in the first compartment outer shell 4; the aircraft launch tube 5 is connected and fixed to the first compartment outer shell 4 by a positioning pin 6, and 6 round holes are reserved at the bottom of the aircraft launch tube 5 and 6 electromagnetic valves A10 are provided to realize the opening and closing of the bottom of the launch tube.

[0051] The second compartment is a pressure chamber, including a second compartment outer shell 13 assembled with the first compartment outer shell 4; an opening corresponding to the bottom circular hole of the aircraft launch tube 5 is reserved on the top of the second compartment outer shell 13; a third sensor 11 for monitoring the internal pressure is arranged in the second compartment outer shell 13; four air bags 9 are installed outside the second compartment and connected to the second compartment outer shell 13 through four gas transmission pipelines 26; the material of the air bag 9 is a composite material composed of nylon mesh as a matrix and rubber. The gas transmission pipeline 26 is divided into: a first horizontal section connected to the second compartment outer shell 13, a third vertical section connected to the air bag 9, and a second inclined section connecting the first horizontal section and the third vertical section; an electromagnetic valve B25 is arranged in the first horizontal section, and an electromagnetic valve C12 and an electromagnetic valve D24 are arranged in the third vertical section; a fourth sensor 2 for monitoring the pressure is installed in the air bag 9.

[0052] The third compartment comprises a third compartment outer shell 14 assembled with the second compartment outer shell 13; a through hole is provided at the top of the third compartment outer shell 14 for conveying gas into the second compartment outer shell 13; a main power supply 15, an aircraft launch control device 27, a gyroscope 28 and a high-pressure air pump A29 are provided in the third compartment outer shell 14.

[0053] See attached Figure 3 The high-pressure gas tank 30 is installed on the outside of the third compartment and the fourth compartment to supply gas to the high-pressure gas pump A29 and the high-pressure gas pump B16.

[0054] See attached Figure 4 The fourth compartment is assembled by the fourth compartment outer shell 31 and the fourth compartment base 21; the fourth compartment outer shell 31 is assembled with the third compartment outer shell 14; six high-pressure air pumps B16 are arranged in the fourth compartment; the positions and order of the high-pressure air pumps B16 correspond to the positions and order of the aircraft 7 in the aircraft launch tube 5; Figure 1As shown, aircraft 7 is aircraft 1#, and the counterclockwise rotation is aircraft 2#, 3#, 4#, 5#, and 6#. The high-pressure air pump 16 located in the fourth compartment is air pump 1#, and the counterclockwise rotation is air pump 2#, 3#, 4#, 5#, and 6#. Six exhaust ducts matching the high-pressure air pump B16 are provided on the base 21 of the fourth compartment, and each exhaust duct is provided with an electromagnetic valve E17 for controlling the switch; an antenna 32 for wireless communication with the submarine is provided on the base 21 of the fourth compartment.

[0055] The fixing device 34 fixes the fourth compartment in the initial state; after receiving the signal, the fixing is released. The fixing device 34 includes: a limiting base 18, in which a piston limiting device 19 and a limiting rod 20 are provided, the movement of which is controlled by an air pump 33; one end of the limiting rod 20 passes through a through hole on the fourth compartment base 21 to fix the fourth compartment; the fixing device 34 is also provided with a power supply and control device 22, and a waterproof socket 35 for connecting and communicating with the optical fiber on the submarine.

[0056] Embodiment 2:

[0057] This embodiment provides a method for launching an underwater multi-launch aircraft. Based on the launching device as described in Embodiment 1, the launching method comprises: releasing the aircraft launcher, floating the aircraft launcher, and launching the aircraft and stabilizing the aircraft.

[0058] The submarine communicates with the fixed device 34 via optical fiber and remotely communicates with the aircraft launch device via antenna 32.

[0059] The steps to release the aircraft are as follows:

[0060] When the aircraft is in the initial state, the N solenoid valves A10 located on the aircraft launch tube 5 are in a closed state, the solenoid valves B25, C12 and D24 located on the gas transmission pipeline 26 are all in a closed state, and the solenoid valve E17 located at the exhaust duct of the fourth compartment base 21 is in a closed state.

[0061] After receiving the launch command, the release step is executed.

[0062] A1. The aircraft launch control device 27 sends a command to the high-pressure air pump A29 located in the third compartment to inflate air into the second compartment.

[0063] A2. When the third sensor 11 detects that the pressure in the pressure chamber is greater than the set value of the water pressure at the water depth, all valves on the gas transmission pipeline 26 are opened.

[0064] A3. When the fourth sensor 2 detects that the pressure in the air bag 9 is greater than the set value of the water pressure at the water depth, the second valve from bottom to top on the gas transmission pipeline 26 is closed.

[0065] A4. The power supply and control device 22 inside the fixing device 34 sends a command to the air pump 33 to control the piston limit device 19 and the limit rod 20 to retract, thereby releasing the lock on the fourth compartment.

[0066] A5. The aircraft launcher floats up under the action of buoyancy and is released.

[0067] After the release is completed, the floating steps are also included:

[0068] B1. During the ascent, the aircraft launch control device 27 reads the data of the second sensor 8 to monitor the water pressure in real time, and at the same time controls the third valve from bottom to top on the gas transmission pipeline 26 to deflate, thereby controlling the pressure in the airbag 9 and the water pressure to always remain constant.

[0069] B2. When the pressure in the pressure chamber is higher than seventy percent of the maximum pressure that the outer shell 13 of the second compartment can withstand, the aircraft launch control device 27 controls the first valve from bottom to top on the gas transmission pipeline 26 to deflate.

[0070] B3. The aircraft launch control device 27 obtains the height of the aircraft launcher from the water surface through the data of the second sensor 8. When the aircraft launcher floats to the set height from the water surface, the aircraft launch control device 27 opens all the electromagnetic valves E17 on the exhaust duct of the fourth compartment base 21, and controls the high-pressure air pump B16 located in the fourth compartment to exhaust air into the exhaust duct of the fourth compartment at a pressure greater than the current water depth and water pressure, thereby accelerating the surfacing of the aircraft launcher under the action of the recoil force.

[0071] B4. After the first sensor 3 identifies that the first compartment has emerged from the water, all electromagnetic valves E17 and the high-pressure air pump B16 on the exhaust duct of the fourth compartment base 21 are closed to complete the buoyancy.

[0072] After the ascent is completed, the launch step is also included:

[0073] After receiving the aircraft launch command from the submarine, the aircraft launch control device 27 controls the high-pressure air pump A29 located in the third compartment to inflate the second compartment. When the pressure in the pressure compartment reaches 70% of the maximum pressure that the compartment can withstand, the aircraft launch control device 27 controls the electromagnetic valve A10 located at the bottom of the aircraft launch tube 5 to open the electromagnetic valve A10 corresponding to the aircraft 7 to be launched, and the aircraft 7 is ejected out of the tube under the action of the high-pressure gas.

[0074] While opening the solenoid valve A10, the corresponding solenoid valve E17 and high-pressure air pump B16 on the exhaust duct of the fourth compartment base 21 are controlled to open, so as to achieve the stability of the launcher's attitude by exhausting the air; after the launch is completed, the solenoid valve A10, the solenoid valve E17 and the high-pressure air pump B16 are closed.

[0075] During the ascent and waiting for launch, the attitude of the aircraft launcher is obtained by detecting the data of the gyroscope 28; when the attitude of the aircraft launcher is unstable, the exhaust speed of the high-pressure air pump B16 is increased or decreased to stabilize the attitude of the aircraft launcher during the ascent.

[0076] Embodiment 3:

[0077] On the basis of embodiments 1 and 2, the specific working process of an underwater multi-engine aircraft launching device is as follows:

[0078] First, the aircraft launch device receives the aircraft equipment launch command sent by the submarine. The launch control device 27 sends a command to the high-pressure air pump A29 located in the third compartment to inflate the pressure chamber. When the pressure in the pressure chamber is greater than a certain value of the water pressure at the water depth, all valves on all airbags that are the same as the airbag 9 are opened. The launch control device 27 monitors the pressure data in the fourth sensor 2. When the air pressure inside the airbag 9 is greater than a certain value of the water pressure at the water depth, the electromagnetic valves C12 on all gas transmission pipelines 26 are closed. After all electromagnetic valves C12 are closed, the power supply and control device 22 inside the aircraft launcher fixture 34 sends a command to the air pump 33 to control the piston limit device 19 to contract, drive the limit rod 20 to disengage, release the lock of the aircraft launcher by the fixture 34, and the aircraft launcher floats up under the action of buoyancy, completing the release operation of the aircraft launcher.

[0079] After the release operation of the aircraft launcher is completed, the aircraft launcher floats up under the action of buoyancy. During the floating process, the water pressure will gradually decrease. In order to ensure the constant volume of the airbag 9 and thus ensure smooth floating, it is necessary to control the pressure in the airbag 9 and the water pressure difference to remain constant. The specific implementation method is: during the ascent, the launch control device 27 in the aircraft launcher reads the data of the second sensor 8 to monitor the water pressure in real time, and controls the electromagnetic valve D24 on the gas transmission pipeline 26 to deflate, and controls the pressure in the airbag 9 and the water pressure to always maintain a constant value through deflation. During the floating process, if the pressure in the pressure chamber is higher than 70% of the maximum pressure that the second cabin shell can withstand, the launch control device 27 controls the electromagnetic valve B 25 on the gas transmission pipeline 26 to deflate to prevent the pressure in the pressure chamber from being too high and damaging the cabin.

[0080] The launch control device 27 can obtain the height of the aircraft launcher from the water surface through the data of the second sensor 8. When the aircraft launcher floats to a height of 10 meters from the water surface, the aircraft launch control device 27 opens all electromagnetic valves E17 on the exhaust duct of the fourth compartment base 21, and controls the high-pressure air pump B16 located in the fourth compartment to exhaust air to the exhaust duct of the fourth compartment at a pressure greater than the current water depth water pressure, thereby accelerating the buoyancy of the aircraft launcher under the action of the recoil force; while buoying, the launch control device 27 detects the data of the gyroscope 28. When the attitude of the aircraft launcher is unstable, the exhaust speed is increased or decreased by controlling part of the high-pressure air pumps B16 in the fourth compartment to stabilize the attitude of the aircraft launcher during the buoyancy process. For example, when the launch control device 27 detects that the aircraft launcher is tilted toward the direction of the 1# aircraft during the buoyancy process, the launch control device 27 controls the 4# high-pressure air pump located in the fourth compartment to reduce the exhaust speed to return the attitude of the aircraft launcher to the normal state. After the aircraft launcher returns to the normal state, the exhaust speed of the 4# high-pressure air pump is restored to normal. Through the above operations, the aircraft launcher floating operation is completed.

[0081] After the first sensor 3 located at the upper end of the outer side of the first compartment outer shell 4 recognizes that the top cover 1 of the aircraft launcher is out of water, all electromagnetic valves E17 and the high-pressure air pump B16 on the exhaust duct of the fourth compartment base 21 are closed.

[0082] After receiving the aircraft launch command from the submarine, the aircraft launch control device 27 controls the high-pressure air pump A29 located in the third compartment to inflate the second compartment. When the pressure in the pressure compartment reaches 70% of the maximum pressure that the compartment can withstand, the aircraft launch control device 27 controls the electromagnetic valve A10 located at the bottom of the aircraft launch tube 5 to open the electromagnetic valve A10 corresponding to the aircraft 7 to be launched, and the aircraft 7 is ejected out of the tube under the action of high-pressure gas; while opening the electromagnetic valve A10, the electromagnetic valve E17 and the high-pressure air pump B16 on the exhaust duct of the corresponding fourth compartment base 21 are controlled to open, and the launcher posture is stabilized by exhausting air; after the launch is completed, the electromagnetic valve A10, the electromagnetic valve E17 and the high-pressure air pump B16 are closed. Taking the launch of aircraft #1 as an example, the aircraft launch control device 27 controls the high-pressure air pump A29 in the third compartment to inflate the pressure cabin. After the pressure in the pressure cabin reaches 70% of the maximum pressure that the compartment can withstand, the aircraft launch control device 27 controls the electromagnetic valve A10 on the launch tube 5 to open. At the same time, the aircraft launch control device 27 controls the high-pressure air pump B16 (air pump #1) and electromagnetic valve E17 in the fourth compartment to open, and the high-pressure gas discharge generates a recoil force to offset the reverse force in the aircraft launch process to stabilize the aircraft launcher posture, and complete the launch of aircraft #1. After the launch of aircraft #1 is completed and the posture is stable, the aircraft launch control device 27 controls the closing of the electromagnetic valve 17 and the high-pressure air pump 16 (air pump #1). Subsequently, according to combat needs, the launch of the remaining aircraft is completed or the launch is stopped according to the above process. After the aircraft launcher cover 1 is out of water, if the launch aircraft command from the submarine is not received temporarily, the aircraft launch control device 27 will constantly monitor the launcher's attitude information through the gyroscope 28. If the launch conditions are bad and cause the launcher to become unstable, the exhaust will be exhausted through part of the bottom exhaust channel to control the launcher's attitude stability.

[0083] Although the present invention has been described in detail above by general description and specific embodiments, it is obvious to those skilled in the art that some modifications or improvements can be made to the present invention. Therefore, these modifications or improvements made without departing from the spirit of the present invention all belong to the scope of protection claimed by the present invention.

Claims

1. An underwater multi-launch aircraft launching device, comprising: Four compartments and a fixing device (34) assembled in sequence along the axial direction are characterized in that: An aircraft launch tube (5) is provided in the first compartment, and N circular holes are left at the bottom of the aircraft launch tube (5) and N electromagnetic valves A (10) are provided to realize opening and closing; An opening corresponding to the circular hole at the bottom of the aircraft launch tube (5) is reserved at the top of the second compartment; M air bags (9) are installed on the outside of the second compartment and are connected to the inner chamber of the second compartment through a gas transmission pipeline (26); three electromagnetic valves are provided on the gas transmission pipeline (26); A through hole for conveying gas to the second compartment is provided on the top of the third compartment; a high-pressure gas pump A (29) is provided in the third compartment; N high-pressure air pumps B (16) are arranged in the fourth compartment; the positions and order of the high-pressure air pumps B (16) correspond to the positions and order of the aircraft (7) in the aircraft launch tube (5); an exhaust duct is arranged at the lower part of the high-pressure air pump B (16), and each exhaust duct is provided with an electromagnetic valve E (17) for controlling the switch; The high-pressure gas tank (30) supplies gas to the high-pressure gas pump A (29) and the high-pressure gas pump B (16); The fixing device (34) fixes the fourth compartment in an initial state and releases the fixation after receiving a signal.

2. The underwater multiple-engine aircraft launching device according to claim 1, characterized in that: The first compartment is assembled from a top cover (1) and a first compartment outer shell (4); N aircraft launch holes are left on the top cover (1), and the aircraft launch holes are sealed by a waterproof sealing film (23); a first sensor (3) for monitoring whether water is coming out of the top cover (1) is installed on the upper end of the outer side of the first compartment outer shell (4), and a second sensor (8) for monitoring water pressure is installed on the lower part of the outer side of the first compartment outer shell (4); an aircraft launch tube (5) is fixedly installed inside the first compartment outer shell (4); The second compartment is a pressure chamber, comprising a second compartment outer shell (13) assembled with the first compartment outer shell (4); an opening corresponding to the bottom circular hole of the aircraft launch tube (5) is reserved at the top of the second compartment outer shell (13); a third sensor (11) for monitoring internal pressure is arranged in the second compartment outer shell (13); M airbags (9) are installed on the outside of the second compartment and are connected to the second compartment outer shell (13) through a gas transmission pipeline (26); the gas transmission pipeline (26) is divided into: a first horizontal section connected to the second compartment outer shell (13), a third vertical section connected to the airbags (9), and a second inclined section connecting the first horizontal section and the third vertical section; an electromagnetic valve B (25) is arranged on the first horizontal section, and an electromagnetic valve C (12) and an electromagnetic valve D (24) are arranged on the third vertical section; a fourth sensor (2) for monitoring pressure is installed in the airbag (9); The third compartment comprises a third compartment outer shell (14) assembled with the second compartment outer shell (13); a through hole for conveying gas into the second compartment outer shell (13) is provided at the top of the third compartment outer shell (14); a main power supply (15), an aircraft launch control device (27), a gyroscope (28) and a high-pressure air pump A (29) are provided in the third compartment outer shell (14); The fourth compartment is composed of a fourth compartment outer shell (31) and a fourth compartment base (21); the fourth compartment outer shell (31) is assembled with the third compartment outer shell (14); N exhaust passages matched with a high-pressure air pump B (16) are provided on the fourth compartment base (21), and each exhaust passage is provided with an electromagnetic valve E (17) for controlling the switch; an antenna (32) for wireless communication with a submarine is provided on the fourth compartment base (21); A high-pressure gas tank (9) is installed outside the third compartment and the fourth compartment, and is used to supply gas to the high-pressure gas pump A (29) and the high-pressure gas pump B (16); The fixing device (34) comprises: a limiting base (18), wherein a piston limiting device (19) and a limiting rod (20) are arranged inside the limiting base (18), and the piston limiting device (19) whose movement is controlled by an air pump (33); one end of the limiting rod (20) passes through a through hole on the fourth compartment base (21) to fix the fourth compartment; the fixing device (34) is also provided with a power supply and control device (22), and a waterproof socket (35) for connecting and communicating with an optical fiber on a submarine.

3. A method for launching an underwater multi-engine aircraft, based on the launching device according to claim 2, characterized in that: Including the release steps of the aircraft; When the aircraft is in an initial state, the N electromagnetic valves A (10) located on the launch tube (5) of the aircraft are in a closed state, the electromagnetic valve B (25), the electromagnetic valve C (12) and the electromagnetic valve D (24) located on the gas transmission pipeline (26) are all in a closed state, and the electromagnetic valve E (17) located at the exhaust duct of the fourth compartment base (21) is in a closed state; After receiving the launch command, the release step is executed; A1. The aircraft launch control device (27) issues a command to the high-pressure air pump A (29) located in the third compartment to inflate the second compartment; A2. When the third sensor (11) detects that the pressure in the pressure chamber is greater than the set value of the water pressure at the water depth, all valves on the gas transmission pipeline (26) are opened; A3. When the fourth sensor (2) detects that the pressure in the air bag (9) is greater than the set value of the water pressure at the water depth, the second valve from bottom to top on the gas transmission pipeline (26) is closed; A4. The power supply and control device (22) inside the fixing device (34) sends a command to the air pump (33) to control the piston limit device (19) and the limit rod (20) to retract, thereby releasing the lock on the fourth compartment; A5. The aircraft launcher floats up under the action of buoyancy and is released.

4. The underwater multi-engine aircraft launching method as claimed in claim 3, characterized in that: After the release is completed, it also includes a floating step; B1. During the ascent, the aircraft launch control device (27) reads the data of the second sensor (8) to monitor the water pressure in real time, and at the same time controls the third valve from bottom to top on the gas transmission pipeline (26) to release air, thereby controlling the pressure inside the airbag (9) and the water pressure to always maintain a constant value through the release of air; B2. When the pressure in the pressure chamber is higher than 70 percent of the maximum pressure that the outer shell (13) of the second compartment section can withstand, the aircraft launch control device (27) controls the first valve from bottom to top on the gas transmission pipeline (26) to release air; B3. The aircraft launch control device (27) obtains the height of the aircraft launcher from the water surface through the data of the second sensor (8). When the aircraft launcher floats up to a set height from the water surface, the aircraft launch control device (27) opens all the electromagnetic valves E (17) on the exhaust duct of the fourth compartment base (21), and controls the high-pressure air pump B (16) located in the fourth compartment to exhaust air into the exhaust duct of the fourth compartment at a pressure greater than the current water depth pressure, thereby accelerating the buoyancy of the aircraft launcher under the action of the recoil force; B4. After the first sensor (3) identifies that the first compartment has emerged from the water, all the electromagnetic valves E (17) on the exhaust duct of the fourth compartment base (21) and the high-pressure air pump B (16) are closed to complete the buoyancy.

5. The underwater multi-engine aircraft launching method according to claim 4, characterized in that: After the ascent is completed, the launching step is also included; After receiving the aircraft launch command from the submarine, the aircraft launch control device (27) controls the high-pressure gas pump A (29) located in the third compartment to inflate the second compartment. When the pressure in the pressure compartment reaches 70% of the maximum pressure that the compartment can withstand, the aircraft launch control device (27) controls the electromagnetic valve A (10) located at the bottom of the aircraft launch tube (5) to open the electromagnetic valve A (10) corresponding to the aircraft (7) to be launched, and the aircraft (7) is ejected out of the tube under the action of the high-pressure gas. When the electromagnetic valve A (10) is opened, the electromagnetic valve E (17) and the high-pressure air pump B (16) on the corresponding exhaust duct of the fourth compartment base (21) are controlled to open, so as to achieve the stability of the launcher posture by exhausting air; after the launch is completed, the electromagnetic valve A (10), the electromagnetic valve E (17) and the high-pressure air pump B (16) are closed.

6. The underwater multi-engine aircraft launching method according to claim 4 or 5, characterized in that: During the floating process and the process of waiting for launch, the launcher attitude of the aircraft is obtained by detecting the data of the gyroscope (28); When the attitude of the aircraft launcher is unstable, the attitude of the aircraft launcher is stabilized during the floating process by increasing or decreasing the exhaust speed of the high-pressure air pump B (16).

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