A cross-medium aircraft ejection device and ejection method thereof

Abstract

The present invention belongs to the field of marine engineering technology, and discloses a cross-medium aircraft ejection device and an ejection method thereof. The support frame of the ejection device is the installation body, the pulley mechanism is fixed on the support frame, the cross-medium aircraft is fixed on the pulley mechanism, the power mechanism pushes the pulley mechanism to drive the cross-medium aircraft to move and obtain the initial velocity of take-off, the buffer mechanism reduces the impact of the pulley mechanism on the support frame, the adjustment mechanism adjusts the ejection angle of the cross-medium aircraft, and the recovery mechanism recovers the support frame. The ejection method includes installing the cross-medium aircraft; adjusting the ejection angle of the cross-medium aircraft; arranging the cross-medium aircraft ejection device; launching the cross-medium aircraft; and recovering the cross-medium aircraft ejection device. The ejection device and its ejection method have a large range of initial velocities of the cross-medium aircraft; little damage to the cross-medium aircraft; compact structure, small space occupation; simple operation, good repeatability, high efficiency of repeated ejection, and engineering practical value.

Description

Technical Field

[0001] The present invention belongs to the field of marine engineering technology, and in particular relates to a cross-medium aircraft ejection device and an ejection method thereof. Background Art

[0002] With the development of the marine economy, the demand for maritime rescue and marine resource exploration is increasing.

[0003] In terms of maritime rescue, traditional rescue methods mainly rely on ships and helicopters. Ships are slow, and although helicopters are fast, there are certain risks when landing on the water and the rescue range is limited. Cross-medium aircraft can quickly reach the accident sea area and then enter the water to carry out rescue, which can greatly improve the rescue efficiency. For example, for the rescue of people who fall into the water at sea, cross-medium aircraft can directly enter the water and approach after discovering the target, reducing the rescue time.

[0004] In terms of marine resource exploration, a tool that can work in both air and water is needed. A cross-medium aircraft can carry various exploration equipment, such as seismic exploration equipment for detecting seabed oil, natural gas and other resources, and ecological monitoring equipment for marine biological resource surveys. A cross-medium aircraft can conduct preliminary surveys of large areas of sea from the air, and then enter the water for more detailed detection, providing more comprehensive data for the development of marine resources.

[0005] Currently, there is an urgent need to develop a cross-medium aircraft ejection device and an ejection method thereof. Summary of the invention

[0006] One technical problem to be solved by the present invention is to provide a cross-medium aircraft ejection device, and another technical problem to be solved by the present invention is to provide a cross-medium aircraft ejection method.

[0007] The cross-medium aircraft ejection device of the present invention comprises a support frame, a buffer mechanism, a power mechanism, an adjustment mechanism, a pulley mechanism and a recovery mechanism;

[0008] The support frame is the installation body, the pulley mechanism is fixed on the support frame, the trans-medium aircraft is fixed on the pulley mechanism, the power mechanism pushes the pulley mechanism to drive the trans-medium aircraft to move and obtain the initial velocity of take-off, the buffer mechanism is used to reduce the impact of the pulley mechanism on the support frame, the adjustment mechanism is used to adjust the ejection angle of the trans-medium aircraft, and the recovery mechanism is used to recover the support frame.

[0009] Furthermore, the frame body of the supporting frame is a rectangular frame structure welded by angle steel, square steel and tube steel, and the frame body is used to support and place all parts of the cross-medium aircraft ejection device; symmetrical guide rails are set on the left and right sides of the frame body.

[0010] Furthermore, there are two groups of buffer mechanisms, which are respectively fixed on the rear sides of the left and right sides of the support frame. Each group of buffer mechanisms includes two industrial buffers that are symmetrical up and down, and a disc spring is fixed at the front end of each industrial buffer.

[0011] Furthermore, the power mechanism drives the pulley mechanism to accelerate the movement so that the cross-medium aircraft obtains the initial velocity for take-off; it includes a fixed pulley block, a movable pulley block, a pneumatic tendon, a cylinder and a gas bottle;

[0012] In the inner cavity of the support frame, a fixed pulley block, a movable pulley block, a cylinder and a gas cylinder are fixed in sequence from back to front, and the pneumatic tendon is fixed on the upper surface of the rear section of the support frame and contacts with the pulley mechanism; the gas cylinder provides compressed gas to the cylinder and the pneumatic tendon; a steel cable is connected between the fixed pulley block and the movable pulley block, and the steel cable pulls the pulley mechanism, and the fixed pulley block and the movable pulley block are used to amplify the traction stroke of the pulley mechanism, drive the cross-medium aircraft to move and obtain the initial velocity for take-off; by adjusting the fixed pulley block and the movable pulley block, the initial velocity for the cross-medium aircraft to obtain take-off is changed.

[0013] Furthermore, the adjustment mechanism includes an adjustment support base and an electro-hydraulic push rod, the adjustment support base is fixed on the lower surface of the support frame, the electro-hydraulic push rod is fixed on the adjustment support base, the top end of the electro-hydraulic push rod is in contact with the lower surface of the cross-medium aircraft, and the ejection angle of the cross-medium aircraft is adjusted by changing the contact point position of the electro-hydraulic push rod on the lower surface of the cross-medium aircraft and the extension height of the electro-hydraulic push rod.

[0014] Furthermore, the pulley mechanism comprises a left-right symmetrical M-shaped pulley frame, the pulley frame is a frame structure, and the pulley frame slides forward and backward along the guide rail under the drive of the steel cable of the power mechanism; a stopper is arranged on the back of the pulley frame; and the left and right side frames of the pulley frame are mounted on the corresponding guide rails;

[0015] The pulley mechanism also includes flexible rollers, V-shaped rollers, a quick release mechanism and a buffer column; the flexible rollers are symmetrically distributed on the left and right, embedded in and protruding from the upper frame of the pulley rack, and are used to support the cross-medium aircraft; the V-shaped rollers are fixed in the left and right side frames of the pulley rack, contacting with the guide rails, and are used to assist the pulley rack to slide back and forth along the guide rails; the quick release mechanism is used to fix and release the cross-medium aircraft; the buffer column is fixed on the rear side surfaces of the left and right side frames of the pulley rack, corresponding one by one to the disc springs of the buffer mechanism.

[0016] Furthermore, the recovery mechanism includes a servo motor and a pulley block fixed on the ship, a steel wire rope is wound on the pulley block, a hook is installed on the steel wire rope, and the hook is hung on the pull ring of the frame body; the servo motor drives the pulley block, and the steel wire rope is released or retracted through the pulley block to achieve the release or retraction of the cross-medium aircraft ejection device.

[0017] Furthermore, the quick detachment mechanism is an electromagnet device connected to the trans-medium aircraft. When the quick detachment mechanism is powered off at the detachment point, the magnetic force disappears and the trans-medium aircraft detaches.

[0018] Furthermore, the flexible roller, the V-shaped roller and the buffer column are all made of rubber.

[0019] The cross-medium aircraft ejection method of the present invention comprises the following steps:

[0020] S10. Install the cross-medium aircraft;

[0021] A plurality of electromagnets are arranged on the lower surface of the cross-medium aircraft. When the electromagnets are energized, the cross-medium aircraft is fixed on the pulley frame of the pulley mechanism by electromagnetic suction, the quick release mechanism is locked, and the cross-medium aircraft presses the flexible roller; the wires of the electromagnets are placed across the rear section of the frame body; and the pulley frame is moved to the front end of the frame body;

[0022] S20. Adjusting the ejection angle of attack of the cross-medium aircraft;

[0023] Extending the electro-hydraulic push rod of the adjustment mechanism to adjust the trans-medium vehicle to a pre-set ejection angle of attack;

[0024] S30. Arrangement of cross-medium aircraft ejection device;

[0025] When the ship reaches the launching sea area, the recovery mechanism releases the wire rope, pushes the cross-medium vehicle ejection device into the sea, arranges it at the launching point, and releases the hook of the wire rope;

[0026] S40. Launching a cross-medium vehicle;

[0027] The gas cylinder provides compressed gas to the cylinder and the pneumatic muscle. The compressed gas pushes the cylinder to drive the pneumatic muscle to contract rapidly. The movable pulley group of the power mechanism drives the pulley frame to accelerate from front to back through the steel cable. When the preset initial speed is reached, the block set on the back of the pulley frame hits the wire, separating the positive and negative wires of the electromagnet, and the electromagnetic suction disappears. At the same time, the quick release mechanism opens, and the cross-medium aircraft is bounced off by the flexible roller and rises, avoiding the initial speed change caused by the friction between the electromagnet on the lower surface of the cross-medium aircraft and the pulley frame. The cross-medium aircraft flies to the predetermined sea area at the preset initial speed and ejection angle; the pulley frame continues to move backward, and the buffer column hits the disc spring to reduce the impact of the pulley frame on the frame body;

[0028] S50. Recover the cross-medium aircraft ejection device;

[0029] The hook of the wire rope hooks the pull ring of the frame body, the servo motor drives the pulley block to retract the wire rope, the wire rope shortens, and the hook drags the frame body supporting the frame to move toward the ship, thereby realizing the recovery of the cross-medium aircraft ejection device.

[0030] The trans-medium aircraft ejection device and ejection method of the present invention use a driving form of a pneumatic tendon and a cylinder in parallel combination. While ensuring sufficient driving force, the use of compressed air in the pneumatic components is reduced, which greatly reduces the overall weight of the mechanism and makes the mechanism more compact; an electromagnet is used to fix the trans-medium aircraft, which can not only ensure the relative fixation between the trans-medium aircraft and the pulley frame, but also ensure the rapid response of the trans-medium aircraft after it is separated from the pulley frame, thereby improving work efficiency; an electro-hydraulic push rod is used for support, which is convenient for adjusting the ejection angle of the trans-medium aircraft.

[0031] The cross-medium aircraft ejection device and the ejection method of the present invention have a wide range of initial velocities of the cross-medium aircraft, little damage to the cross-medium aircraft, a compact structure, and a small space occupation, and are easy to operate, have good repeatability, and high efficiency of repeated ejection. They can adapt to a variety of working conditions and have engineering practical value. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Figure 1 It is a schematic structural diagram of the cross-medium aircraft ejection device of the present invention.

[0033] In the figure, 100. supporting frame; 200. buffer mechanism; 300. power mechanism; 400. adjustment mechanism; 500. pulley mechanism; 600. recovery mechanism;

[0034] 101. Rack body; 102. Guide rail;

[0035] 201. Disc spring; 202. Industrial buffer;

[0036] 301. Pneumatic muscle; 302. Cylinder; 303. Gas cylinder;

[0037] 401.Electro-hydraulic push rod;

[0038] 501. Flexible roller; 502. V-shaped roller; 503. Quick release mechanism; 504. Buffer column. DETAILED DESCRIPTION

[0039] The present invention is described in detail below with reference to the accompanying drawings and embodiments.

[0040] Example: Figure 1 As shown, the cross-medium aircraft ejection device of this embodiment includes a support frame 100, a buffer mechanism 200, a power mechanism 300, an adjustment mechanism 400, a pulley mechanism 500 and a recovery mechanism 600;

[0041] The support frame 100 is the installation body, the pulley mechanism 500 is fixed on the support frame 100, the trans-medium aircraft is fixed on the pulley mechanism 500, the power mechanism 300 pushes the pulley mechanism 500 to drive the trans-medium aircraft to move and obtain the initial velocity of take-off, the buffer mechanism 200 is used to reduce the impact of the pulley mechanism 500 on the support frame 100, the adjustment mechanism 400 is used to adjust the ejection angle of the trans-medium aircraft, and the recovery mechanism 600 is used to recover the support frame 100.

[0042] Furthermore, the frame body 101 of the support frame 100 is a rectangular frame structure welded by angle steel, square steel and tube steel. The frame body 101 is used to support and place all components of the cross-medium aircraft ejection device; symmetrical guide rails 102 are set on the left and right sides of the frame body 101.

[0043] Furthermore, there are two groups of buffer mechanisms 200, which are respectively fixed on the rear sides of the left and right sides of the support frame 100. Each group of buffer mechanisms 200 includes two industrial buffers 202 symmetrically arranged in an upper and lower direction, and a disc spring 201 is fixed at the front end of each industrial buffer 202.

[0044] Furthermore, the power mechanism 300 drives the pulley mechanism 500 to accelerate the movement, so that the cross-medium aircraft obtains the initial velocity of take-off; it includes a fixed pulley block, a movable pulley block, a pneumatic muscle 301, a cylinder 302 and a gas bottle 303;

[0045] In the inner cavity of the support frame 100, the fixed pulley block, the movable pulley block, the cylinder 302 and the gas cylinder 303 are fixed in sequence from back to front, and the pneumatic muscle 301 is fixed on the upper surface of the rear section of the support frame 100 and is in contact with the pulley mechanism 500; the gas cylinder 303 provides compressed gas to the cylinder 302 and the pneumatic muscle 301; a steel cable is connected between the fixed pulley block and the movable pulley block, and the steel cable pulls the pulley mechanism 500. The fixed pulley block and the movable pulley block are used to amplify the traction stroke of the pulley mechanism 500, drive the cross-medium aircraft to move and obtain the initial velocity for take-off; by adjusting the fixed pulley block and the movable pulley block, the initial velocity for the cross-medium aircraft to take off is changed.

[0046] Furthermore, the adjustment mechanism 400 includes an adjustment support base and an electro-hydraulic push rod 401. The adjustment support base is fixed on the lower surface of the support frame 100. The electro-hydraulic push rod 401 is fixed on the adjustment support base. The top end of the electro-hydraulic push rod 401 contacts the lower surface of the cross-medium aircraft. The ejection angle of the cross-medium aircraft is adjusted by changing the contact point position of the electro-hydraulic push rod 401 on the lower surface of the cross-medium aircraft and the extension height of the electro-hydraulic push rod 401.

[0047] Furthermore, the pulley mechanism 500 includes a bilaterally symmetrical M-shaped pulley frame, which is a frame structure. The pulley frame slides forward and backward along the guide rail 102 under the drive of the steel cable of the power mechanism 300; a stopper is provided on the back of the pulley frame; and the left and right side frames of the pulley frame are mounted on the corresponding guide rail 102;

[0048] The pulley mechanism 500 also includes a flexible roller 501, a V-shaped roller 502, a quick release mechanism 503 and a buffer column 504; the flexible roller 501 is symmetrically distributed on the left and right sides, embedded in and protruding from the upper frame of the pulley frame, and is used to support the cross-medium aircraft; the V-shaped roller 502 is fixed in the left and right side frames of the pulley frame, in contact with the guide rail 102, and is used to assist the pulley frame to slide back and forth along the guide rail 102; the quick release mechanism 503 is used to fix and release the cross-medium aircraft; the buffer column 504 is fixed on the rear side of the left and right side frames of the pulley frame, corresponding one by one to the disc spring 201 of the buffer mechanism 200.

[0049] Furthermore, the recovery mechanism 600 includes a servo motor and a pulley block fixed on the ship, a steel wire rope is wound on the pulley block, a hook is installed on the steel wire rope, and the hook is hung on the pull ring of the frame body 101; the servo motor drives the pulley block, and the steel wire rope is released or retracted through the pulley block, thereby releasing or retracting the cross-medium aircraft ejection device.

[0050] Furthermore, the quick detachment mechanism 503 is an electromagnet device connected to the trans-medium aircraft. The quick detachment mechanism 503 is powered off at the detachment point, the magnetic force disappears, and the trans-medium aircraft detaches.

[0051] Furthermore, the flexible roller 501, the V-shaped roller 502 and the buffer column 504 are all made of rubber.

[0052] The cross-medium aircraft ejection method of this embodiment includes the following steps:

[0053] S10. Install the cross-medium aircraft;

[0054] A plurality of electromagnets are arranged on the lower surface of the cross-medium aircraft. When the electromagnets are energized, the cross-medium aircraft is fixed on the pulley frame of the pulley mechanism 500 by electromagnetic attraction, the quick release mechanism 503 is locked, and the cross-medium aircraft presses the flexible roller 501; the wires of the electromagnets are placed across the rear section of the frame body 101; and the pulley frame is moved to the front end of the frame body 101;

[0055] S20. Adjusting the ejection angle of attack of the cross-medium aircraft;

[0056] Extending the electro-hydraulic push rod 401 of the adjustment mechanism 400 to adjust the trans-medium aircraft to a preset ejection attack angle;

[0057] S30. Arrangement of cross-medium aircraft ejection device;

[0058] When the ship reaches the launching sea area, the recovery mechanism 600 releases the wire rope, pushes the cross-medium vehicle ejection device into the sea, arranges it at the launching point, and releases the hook of the wire rope;

[0059] S40. Launching a cross-medium vehicle;

[0060] The gas cylinder 303 provides compressed gas to the cylinder 302 and the pneumatic muscle 301. The compressed gas pushes the cylinder 302 to drive the pneumatic muscle 301 to contract quickly. The movable pulley group of the power mechanism 300 drives the pulley frame to accelerate from front to back through the steel cable. When the preset initial speed is reached, the block set on the back of the pulley frame hits the wire, separates the positive and negative wires of the electromagnet, and the electromagnetic suction disappears. At the same time, the quick release mechanism 503 is opened, and the cross-medium aircraft is bounced off and rises by the flexible roller 501, avoiding the initial speed change caused by the friction between the electromagnet on the lower surface of the cross-medium aircraft and the pulley frame. The cross-medium aircraft flies to the predetermined sea area at the preset initial speed and ejection angle; the pulley frame continues to move backward, and the buffer column 504 hits the disc spring 201 to reduce the impact of the pulley frame on the frame body 101;

[0061] S50. Recover the cross-medium aircraft ejection device;

[0062] The hook of the wire rope hooks the pull ring of the frame body 101, and the servo motor drives the pulley block to retract the wire rope, the wire rope shortens, and the hook drags the frame body 101 supporting the frame 100 to move toward the ship, thereby realizing the recovery of the cross-medium aircraft ejection device.

[0063] Although the embodiments of the present invention have been disclosed as above, they are not limited to the applications listed in the specification and implementation modes. For those familiar with the art, all features disclosed in the present invention, or steps in all methods or processes disclosed, except for mutually exclusive features and / or steps, can be combined in any way without departing from the principles of the present invention. The present invention is not limited to the specific details and illustrations shown and described herein.

Claims

1. A cross-medium aircraft ejection device, characterized in that: The cross-medium aircraft ejection device comprises a support frame (100), a buffer mechanism (200), a power mechanism (300), an adjustment mechanism (400), a pulley mechanism (500) and a recovery mechanism (600); The support frame (100) is a mounting body, the pulley mechanism (500) is fixed on the support frame (100), the cross-medium aircraft is fixed on the pulley mechanism (500), the power mechanism (300) drives the pulley mechanism (500) to drive the cross-medium aircraft to move and obtain an initial take-off speed, the buffer mechanism (200) is used to reduce the impact of the pulley mechanism (500) on the support frame (100), the adjustment mechanism (400) is used to adjust the ejection angle of the cross-medium aircraft, and the recovery mechanism (600) is used to recover the support frame (100); The frame body (101) of the support frame (100) is a rectangular frame structure welded by angle steel, square steel and tube steel. The frame body (101) is used to support and place all parts of the cross-medium aircraft ejection device. Symmetrical guide rails (102) are arranged on the left and right sides of the frame body (101). The buffer mechanism (200) has two groups, which are respectively fixed to the rear side surfaces on the left and right sides of the support frame (100), and each group of the buffer mechanism (200) includes two industrial buffers (202) symmetrically arranged in the upper and lower parts, and a disc spring (201) is fixed at the front end of each industrial buffer (202); The power mechanism (300) drives the pulley mechanism (500) to accelerate the movement, so that the cross-medium aircraft obtains the initial velocity for take-off; it comprises a fixed pulley block, a movable pulley block, a pneumatic muscle (301), a cylinder (302) and a gas bottle (303); In the inner cavity of the support frame (100), a fixed pulley block, a movable pulley block, a cylinder (302) and a gas cylinder (303) are fixed in sequence from the back to the front; the pneumatic muscle (301) is fixed to the upper surface of the rear section of the support frame (100) and is in contact with the pulley mechanism (500); the gas cylinder (303) provides compressed gas to the cylinder (302) and the pneumatic muscle (301); a steel cable is connected between the fixed pulley block and the movable pulley block, and the steel cable pulls the pulley mechanism (500); the fixed pulley block and the movable pulley block are used to amplify the traction stroke of the pulley mechanism (500), drive the cross-medium aircraft to move and obtain an initial velocity for take-off; by adjusting the fixed pulley block and the movable pulley block, the initial velocity for the cross-medium aircraft to obtain take-off is changed; The adjustment mechanism (400) comprises an adjustment support base and an electro-hydraulic push rod (401), wherein the adjustment support base is fixed to the lower surface of the support frame (100), the electro-hydraulic push rod (401) is fixed to the adjustment support base, the top end of the electro-hydraulic push rod (401) contacts the lower surface of the cross-medium aircraft, and the ejection angle of the cross-medium aircraft is adjusted by changing the contact point position of the electro-hydraulic push rod (401) on the lower surface of the cross-medium aircraft and the extension height of the electro-hydraulic push rod (401); The pulley mechanism (500) comprises a left-right symmetrical M-shaped pulley frame, the pulley frame being a frame structure, and the pulley frame slides forward and backward along the guide rail (102) driven by the steel cable of the power mechanism (300); a stopper is provided on the back of the pulley frame; and the left and right side frames of the pulley frame are mounted on the corresponding guide rails (102); The pulley mechanism (500) further comprises a flexible roller (501), a V-shaped roller (502), a quick release mechanism (503) and a buffer column (504); the flexible rollers (501) are symmetrically distributed on the left and right sides, embedded in and protruding from the upper frame of the pulley frame, and used to support the cross-medium aircraft; the V-shaped rollers (502) are fixed in the left and right side frames of the pulley frame, contact with the guide rail (102), and are used to assist the pulley frame to slide forward and backward along the guide rail (102); the quick release mechanism (503) is used to fix and release the cross-medium aircraft; the buffer column (504) is fixed to the rear side surfaces of the left and right side frames of the pulley frame, and corresponds one-to-one to the disc springs (201) of the buffer mechanism (200).

2. The cross-medium aircraft ejection device according to claim 1, characterized in that: The recovery mechanism (600) comprises a servo motor and a pulley block fixed on the ship, a steel wire rope is wound around the pulley block, a hook is installed on the steel wire rope, and the hook is hung on a pull ring of the frame body (101); the servo motor drives the pulley block, and the steel wire rope is released or retracted through the pulley block, thereby releasing or retracting the cross-medium aircraft ejection device.

3. The cross-medium aircraft ejection device according to claim 1, characterized in that: The quick detachment mechanism (503) is an electromagnet device connected to the trans-medium aircraft. When the quick detachment mechanism (503) is powered off at the detachment point, the magnetic force disappears and the trans-medium aircraft detaches.

4. The cross-medium aircraft ejection device according to claim 1, characterized in that: The flexible roller (501), the V-shaped roller (502) and the buffer column (504) are all made of rubber.

5. A method for launching a cross-medium aircraft, which is used in the cross-medium aircraft launching device according to any one of claims 1 to 4, characterized in that: The following steps are involved: S10. Install the cross-medium aircraft; A plurality of electromagnets are arranged on the lower surface of the cross-medium aircraft. When the electromagnets are energized, the cross-medium aircraft is fixed to the pulley frame of the pulley mechanism (500) by electromagnetic suction, the quick release mechanism (503) is locked, and the cross-medium aircraft is pressed against the flexible roller (501); the wires of the electromagnets are placed across the rear section of the frame body (101); and the pulley frame is moved to the front end of the frame body (101); S20. Adjusting the ejection angle of attack of the cross-medium aircraft; Extending the electro-hydraulic push rod (401) of the adjustment mechanism (400) to adjust the cross-medium aircraft to a preset ejection attack angle; S30. Arrangement of cross-medium aircraft ejection device; When the ship reaches the launching sea area, the recovery mechanism (600) releases the steel wire rope, pushes the cross-medium aircraft ejection device into the sea, arranges it at the launching point, and releases the hook of the steel wire rope; S40. Launching a cross-medium vehicle; The gas cylinder (303) provides compressed gas to the gas cylinder (302) and the pneumatic muscle (301). The compressed gas pushes the gas cylinder (302) to drive the pneumatic muscle (301) to contract rapidly. The movable pulley group of the power mechanism (300) drives the pulley frame to move from front to back at an accelerated speed through the steel cable. When the preset initial speed is reached, the block provided on the back of the pulley frame hits the wire, separating the positive and negative wires of the electromagnet, and the electromagnetic suction force disappears. At the same time, the quick release mechanism (503) opens, and the cross-medium aircraft is ejected by the flexible roller (501) and rises, avoiding the initial speed change caused by the friction between the electromagnet on the lower surface of the cross-medium aircraft and the pulley frame. The cross-medium aircraft flies to the predetermined sea area at the preset initial speed and ejection angle. The pulley frame continues to move backward, and the buffer column (504) hits the disc spring (201) to reduce the impact of the pulley frame on the frame body (101). S50. Recover the cross-medium aircraft ejection device; The hook of the wire rope hooks the pull ring of the frame body (101), and the servo motor drives the pulley block to retract the wire rope, the wire rope shortens, and the hook drags the frame body (101) supporting the frame (100) toward the ship, thereby realizing the recovery of the cross-medium aircraft ejection device.

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