Forward separation launching device for laterally-overturned unpowered aircraft

Abstract

The invention discloses a laterally-overturned unpowered aircraft forward separation launching device which is internally provided with a barrel cover opening and locking mechanism, an ejection releasing and locking mechanism and a lateral overturning mechanism, all the mechanisms are sequentially started to work under the control of a driving transmission assembly, and the purposes that a barrel cover is ejected firstly, and then the lateral overturning mechanism is ejected are achieved; and after the barrel cover leaves a safe distance, the aircraft flies out of the barrel, and then the barrel is laterally overturned, so that the barrel is prevented from influencing a movement channel of the aircraft.

Description

Technical Field

[0001] The present invention is applied to the field of aircraft launch technology, and is mainly used to realize the rapid launch and separation of unpowered lightweight aircraft in space. Background Art

[0002] With the advancement of aerospace science and technology, and the support of China's policy of vigorously building a space power, China's space science, space technology, and space applications have experienced rapid growth. Space exploration, in particular, has entered an era of in-depth exploration. In the modern space environment, an increasing number of inflatable structures are being used in energy exploration, propulsion, communications, astronaut extravehicular activities, and planetary surface exploration. These include inflatable deployable antennas, thin-film solar sails, lightweight vehicles, and space bases. Using unpowered inflatable structures for calibration, testing, or as substitutes for real targets has become a high-value, low-cost research hotspot.

[0003] In actual work, it has been found that the initial release and separation of an unpowered inflatable structure can significantly impact the subsequent stability and reliability of an inflatable aircraft, significantly affecting its ballistic parameters and flight performance. However, due to limitations on the effective thrust and load-bearing capacity of the carrier, this lightweight inflatable aircraft lacks a built-in thrust device. Therefore, an external force must be applied during release to achieve a certain initial velocity to maintain the required flight speed. Furthermore, the cover and cylinder housing of the aircraft before and after release may also affect the aircraft's flight.

[0004] Based on the above problems, the inventors have designed a device based on the preload force of a compression spring and the rapid ejection release of an incomplete gear. Summary of the Invention

[0005] In order to overcome the above problems, the inventors have conducted intensive research and designed a sideways-flipping forward separation launch device for unpowered aircraft. The launch device is provided with a cylinder cover opening and locking mechanism, an ejection release locking mechanism and a sideways-flipping mechanism. Under the control of the drive transmission assembly, each mechanism starts to work in sequence, so that the cylinder cover is first ejected. After the cylinder cover moves to a safe distance, the aircraft flies out of the cylinder body, and then the cylinder body flips sideways to prevent the cylinder body from affecting the movement channel of the aircraft, thereby completing the present invention.

[0006] Specifically, the purpose of the present invention is to provide a sideways flipping unpowered aircraft forward separation launch device, the launch device includes a cylinder 1, the cylinder 1 includes a cylinder cover 11, a cylinder wall 12 and a bottom plate 13,

[0007] In the cylinder body 1, a cylinder cover opening and locking mechanism 2 is installed on the cylinder cover 11; the cylinder cover opening and locking mechanism 2 controls the cylinder cover 11 to pop out and detach from the cylinder wall 12;

[0008] In the cylinder 1, an ejection release locking mechanism 3 is provided at a position adjacent to the bottom plate; the ejection release locking mechanism 3 pushes the aircraft thereon, so that the aircraft is ejected and detached from the cylinder 1;

[0009] In the cylinder 1, a lateral flip mechanism 4 is installed on the bottom plate 13. After the aircraft is separated from the cylinder 1, the lateral flip mechanism 4 controls the cylinder 1 of the launch device to flip sideways.

[0010] A drive transmission assembly is provided in the ejection release locking mechanism 3 , which controls the cylinder cover opening and locking mechanism 2 , the ejection release locking mechanism 3 and the lateral flipping mechanism 4 to start working in sequence according to a predetermined time interval.

[0011] The cylinder cover opening and locking mechanism 2 includes a cylinder cover compression spring 21 installed in the cylinder wall 12.

[0012] When the cylinder cover 11 is installed on the cylinder wall 12, that is, the cylinder body 1 is closed, the top end of the cylinder cover compression spring 21 abuts against the cylinder cover 11 and is in a compressed energy storage state;

[0013] The cylinder cover opening and locking mechanism 2 further includes a cylinder cover lower panel 22 located below the cylinder cover 11. The cylinder cover 11 and the cylinder cover lower panel 22 are parallel to each other and are fixed by a connecting column.

[0014] A lock hook 23 and a spring sheet 24 are provided between the cylinder cover 11 and the cylinder cover lower panel 22;

[0015] The locking hook ring 23 is rotatable as a whole, with a locking hook 231 extending outward from its edge. The locking hook 231 is screwed into the groove 121 provided on the cylinder wall 12 to provide axial limitation for the cylinder cover opening and locking mechanism 2;

[0016] The spring piece 24 is in a deformed energy storage state, and the spring piece 24 abuts against the limit block 232 of the lock hook ring 23, and can push the limit block 232 and the lock hook ring 23 to rotate, so that the lock hook 231 is rotated out of the groove 121.

[0017] Among them, a connecting rod guide groove 122 is axially arranged on the inner side of the cylinder wall 12, and a retractable shift rod 123 is arranged in the connecting rod guide groove 122. When the shift rod 123 is extended, it abuts against the limit block 232 to prevent the lock hook ring 23 from rotating; when the shift rod 231 is retracted, the spring sheet 24 pushes the lock hook ring 23 to rotate, so that the lock hook 231 is rotated out of the groove 121, and the cylinder cover compression spring 21 pushes the cylinder cover 11 to separate from the cylinder wall 12.

[0018] The lateral turning mechanism 4 includes a gas cylinder 41 mounted on the bottom plate 13, and an air outlet 124 is provided at the bottom of the cylinder wall 12. The gas cylinder is connected to the air outlet 124 via a valve 42.

[0019] When the valve 42 is opened, the gas in the gas cylinder 41 is ejected through the gas outlet 124, causing the barrel 1 of the launch device to flip sideways; when the valve 42 is closed, the connection between the gas cylinder 41 and the gas outlet 124 is disconnected.

[0020] The ejection release locking mechanism 3 includes a push plate 31 and a mounting plate 32 that are parallel to each other. The mounting plate 32 is fixed to the cylinder wall 12. The aircraft is supported and mounted on the push plate 31. The push plate 31 can push the aircraft to slide along the cylinder wall 12.

[0021] A push plate compression spring 33 is provided between the push plate 31 and the mounting plate 32 . The push plate compression spring 33 is in a compressed energy storage state. The push plate compression spring 33 can push the push plate 31 to cause the aircraft on it to fly out of the cylinder 1 .

[0022] A pull plate 34 is provided on the push plate 31 on one side adjacent to the mounting plate 32 , a limit hole 35 is provided on the pull plate 34 , and a retractable pull rod 36 is provided at the limit hole 35 ;

[0023] When the pull rod 36 is extended, the pull rod 36 extends into the limiting through hole 35, preventing the push plate compression spring 33 from pushing the push plate 31 and the pull rod 36; when the pull rod 36 is retracted, the push plate compression spring 33 pushes the push plate 31 to move axially, causing the aircraft on the push plate 31 to fly out of the cylinder 1.

[0024] The drive transmission assembly is installed between the push plate 31 and the mounting plate 32.

[0025] The drive transmission assembly includes a motor 51, which is connected to a rotating shaft 52. The rotating shaft is connected to the gear lever 123, the pull rod 36 and the valve 42. When the rotating shaft 52 rotates, the gear lever 123, the pull rod 36 and the valve 42 start working in sequence according to a predetermined time interval.

[0026] A first driving gear 53 is provided on the rotating shaft 52. The drive transmission assembly further includes a first driven gear 54 meshing with the first driving gear 53. A first connecting rod 55 is hingedly connected to the first driven gear 54. A second connecting rod 56 is hingedly connected to the first connecting rod 55. The shift lever 123 is hingedly connected to the second connecting rod 56. The first driving gear 53 drives the first driven gear 54 to rotate to control the extension or retraction of the shift lever 123.

[0027] Preferably, the first driving gear 53 and / or the first driven gear 54 are incomplete gears, which are gears having teeth only in a partial area in the circumferential direction.

[0028] A second driving gear 57 is provided on the rotating shaft 52, and the drive transmission assembly further includes a second driven gear 58 meshing with the second driving gear 57. The pull rod 36 is hinged on the second driving gear 57, and the second driven gear 58 is driven by the second driving gear 57 to rotate to control the extension or retraction of the pull rod 36.

[0029] Preferably, the second driving gear 57 and / or the second driven gear 58 are incomplete gears, which are gears having teeth only in a partial area in the circumferential direction.

[0030] A cam 59 is provided on the rotating shaft 52 . When the tip of the cam 59 rotates downward, it touches and squeezes the valve 42 , so that the valve 42 changes from a closed state to an open state.

[0031] The beneficial effects of the present invention include:

[0032] (1) The device for launching a sideways flipping unpowered aircraft forward separation provided by the present invention is designed to meet the launch requirements of unpowered lightweight aircraft in space. The device utilizes the compression preload of a spring to achieve rapid release of the aircraft and impart a high initial velocity to the aircraft. At the same time, a gas jet is used to propel the launch device to sideways flip and separation.

[0033] (2) According to the sideways flipping unpowered aircraft forward separation launch device provided by the present invention, except for a few load-bearing parts, the rest of the device can be made of lightweight materials, and has the advantages of light weight, small size, and reusability. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] Figure 1 A schematic diagram showing the working process structure of the device for forward separation and launching of a sideways-flipped unpowered aircraft in this application;

[0035] Figure 2 A schematic diagram showing the overall structure of the forward separation launch device for a sideways-flipped unpowered aircraft in this application;

[0036] Figure 3 A schematic diagram showing the structure of the upper cover opening and locking mechanism of the forward separation launch device of the sideways-flipped unpowered aircraft in this application;

[0037] Figure 4 A schematic diagram showing the structure of the locking hook on the forward separation launch device of the sideways-flipped unpowered aircraft in this application;

[0038] Figure 5 A schematic diagram showing the structure of the upper cover of the forward separation launch device of the sideways-flipped unpowered aircraft in the present application when axially locked;

[0039] Figure 6 A schematic diagram showing the structure of the ejection release and locking mechanism on the forward separation launch device of the sideways-flipped unpowered aircraft in this application;

[0040] Figure 7 A schematic diagram showing the structure of the upper push plate and the pull rod of the forward separation launch device of the sideways flipped unpowered aircraft in this application;

[0041] Figure 8 A schematic diagram showing the structure of the lateral flipping mechanism on the forward separation launch device of the lateral flipping unpowered aircraft in this application;

[0042] Description of Reference Numerals

[0043] 1-Cylinder

[0044] 11-Cylinder cover

[0045] 12-cylinder wall

[0046] 121-Groove

[0047] 122-connecting rod guide groove

[0048] 123-gear lever

[0049] 124-vent

[0050] 13-base plate

[0051] 2-Cylinder cover opening and locking mechanism

[0052] 21-Cylinder cover compression spring

[0053] 22-Cylinder cover lower panel

[0054] 23-Lock hook

[0055] 231-Lock hook

[0056] 232-Limit Block

[0057] 24-spring

[0058] 3-Ejection release locking mechanism

[0059] 31-Push Plate

[0060] 32-Mounting plate

[0061] 33-Push plate compression spring

[0062] 34-Pull plate

[0063] 35-Limiting through hole

[0064] 36-Tie rod

[0065] 4-Side flip mechanism

[0066] 41-gas cylinder

[0067] 42-Valve

[0068] 51-Motor

[0069] 52-Shaft

[0070] 53-First driving gear

[0071] 54-First driven gear

[0072] 55-First connecting rod

[0073] 56-Second connecting rod

[0074] 57-Second driving gear

[0075] 58-Second driven gear

[0076] 59-Cam

[0077] 6-Aircraft DETAILED DESCRIPTION

[0078] The present invention will be described in further detail below with reference to the accompanying drawings and examples, through which the features and advantages of the present invention will become more clearly understood.

[0079] The word "exemplary" is used exclusively herein to mean "serving as an example, example, or illustration." Any embodiment described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments. Although various aspects of the embodiments are shown in the drawings, the drawings are not necessarily drawn to scale unless otherwise indicated.

[0080] The present invention provides a sideways flipping unpowered aircraft forward separation launch device, such as Figure 1 and Figure 2 As shown in FIG, the launch device includes a cylinder 1, and the cylinder 1 includes a cylinder cover 11, a cylinder wall 12 and a bottom plate 13.

[0081] In the cylinder body 1, a cylinder cover opening and locking mechanism 2 is installed on the cylinder cover 11; the cylinder cover opening and locking mechanism 2 controls the cylinder cover 11 to pop out and detach from the cylinder wall 12;

[0082] In the cylinder 1, an ejection release locking mechanism 3 is provided at a position adjacent to the bottom plate; the ejection release locking mechanism 3 pushes the aircraft thereon, so that the aircraft is ejected and detached from the cylinder 1;

[0083] In the cylinder 1, a lateral flip mechanism 4 is installed on the bottom plate 13. After the aircraft is separated from the cylinder 1, the lateral flip mechanism 4 controls the cylinder 1 of the launch device to flip sideways.

[0084] The ejection release locking mechanism 3 is provided with a drive transmission assembly, which controls the cylinder cover opening and locking mechanism 2, the ejection release locking mechanism 3 and the lateral flipping mechanism 4 to start working in sequence at a predetermined time interval. The time interval can be set according to actual needs.

[0085] In a preferred embodiment, Figure 3 、 Figure 4 and Figure 5 As shown in , the cylinder cover opening and locking mechanism 2 includes a cylinder cover compression spring 21 installed in the cylinder wall 12. A blind hole for installing the cylinder cover compression spring 21 is opened on the cylinder wall 12. When the cylinder cover compression spring 21 is compressed to the limit position, it can be completely embedded in the blind hole;

[0086] When the cylinder cover 11 is installed on the cylinder wall 12, that is, the cylinder body 1 is closed, the top end of the cylinder cover compression spring 21 abuts against the cylinder cover 11 and is in a compressed energy storage state;

[0087] The cylinder cover opening and locking mechanism 2 further includes a cylinder cover lower panel 22 located below the cylinder cover 11. The cylinder cover 11 and the cylinder cover lower panel 22 are parallel to each other and are fixed by a connecting column, so that the cylinder cover lower panel 22 and the cylinder cover 11 are an integral structure and can be ejected together and separated from the cylinder body;

[0088] A lock hook 23 and a spring sheet 24 are provided between the cylinder cover 11 and the cylinder cover lower panel 22;

[0089] The locking hook ring 23 is rotatable as a whole, with its rotation center preferably set on the axis of the cylinder body. A locking hook 231 extends outward from its edge. By screwing the locking hook 231 into the groove 121 provided on the cylinder wall 12, an axial limit is provided for the cylinder cover opening and locking mechanism 2. The groove 121 is provided on the cylinder wall 12 near the cylinder cover 11. There is only one degree of freedom between the groove and the locking hook 231. The locking hook 231 can only enter and exit the groove when it rotates. The cross-sectional dimension of the locking hook 231 is slightly smaller than or substantially equal to the cross-sectional dimension of the groove. The axial direction in this application refers to the length direction of the cylinder wall.

[0090] The spring piece 24 is in a deformed energy storage state and abuts against the limit block 232 of the lock hook ring 23, which can push the limit block 232 and the lock hook ring 23 to rotate, so that the lock hook 231 is rotated out of the groove 121. The limit block 232 is fixed to the bottom of the lock hook ring, and the two rotate synchronously.

[0091] Preferably, a connecting rod guide groove 122 is axially arranged on the inner side of the cylinder wall 12, and the connecting rod guide groove 122 is close to the cylinder wall 12 and does not interfere with the sliding of the aircraft; a retractable shift rod 123 is arranged in the connecting rod guide groove 122, and when the shift rod 123 is extended, it abuts against the limit block 232 to prevent the lock hook ring 23 from rotating; when the shift rod 231 is retracted, there is no longer a mechanism to prevent the lock hook ring 23 from rotating, and the spring sheet 24 pushes the lock hook ring 23 to rotate, so that the lock hook 231 is rotated out of the groove 121, and the cylinder cover compression spring 21 pushes the cylinder cover 11 to separate from the cylinder wall 12.

[0092] In a preferred embodiment, Figure 8 As shown in , the lateral flip mechanism 4 includes a gas cylinder 41 mounted on the bottom plate 13, and an air outlet 124 is opened at the bottom of the cylinder wall 12, and the gas cylinder is connected to the air outlet 124 through a valve 42;

[0093] When the valve 42 is opened, the gas in the gas cylinder 41 is ejected through the gas outlet 124, causing the barrel 1 of the launch device to flip sideways; when the valve 42 is closed, the connection between the gas cylinder 41 and the gas outlet 124 is disconnected.

[0094] In a preferred embodiment, Figure 6 and Figure 7 As shown in , the ejection release locking mechanism 3 includes a push plate 31 and a mounting plate 32 parallel to each other. The mounting plate 32 is fixed to the cylinder wall 12. The aircraft 6 is supported and mounted on the push plate 31. The push plate 31 can push the aircraft 6 to slide along the cylinder wall 12 and push the aircraft out of the cylinder.

[0095] A push plate compression spring 33 is provided between the push plate 31 and the mounting plate 32. The push plate compression spring 33 is in a compressed energy storage state. The push plate compression spring 33 can push the push plate 31 to make the aircraft on it fly out of the cylinder 1. Preferably, at least 3 push plate compression springs 33 can be provided and evenly distributed to provide a sufficiently large initial speed for the aircraft. Accordingly, a sleeve for installing the push plate compression spring 33 is provided between the push plate 31 and the mounting plate 32 to provide guide, limit and protection for the push plate compression spring 33.

[0096] Preferably, if Figure 7 As shown in FIG, a pull plate 34 is provided on the push plate 31 on one side adjacent to the mounting plate 32. A limit hole 35 is provided on the pull plate 34, and a retractable pull rod 36 is provided at the limit hole 35. Two pull plates 34 can be provided, which are symmetrically distributed.

[0097] When the pull rod 36 is extended, the pull rod 36 extends into the limiting through hole 35, preventing the push plate compression spring 33 from pushing the push plate 31 and the pull rod 36; when the pull rod 36 is retracted, the push plate compression spring 33 pushes the push plate 31 to move axially, causing the aircraft on the push plate 31 to fly out of the cylinder 1.

[0098] In a preferred embodiment, Figure 6 As shown in , the drive transmission assembly is installed between the push plate 31 and the mounting plate 32, and the drive transmission assembly includes a motor 51, and the motor 51 is connected to a rotating shaft 52, and the rotating shaft 52 rotates synchronously with the motor;

[0099] The rotating shaft is connected to the lever 123, the pull rod 36, and the valve 42. When the rotating shaft 52 rotates, the lever 123, the pull rod 36, and the valve 42 are activated in sequence at predetermined time intervals. This arrangement allows the motor 51 to sequentially control the lever 123, the pull rod 36, and the valve 42 by simply receiving a start signal and rotating a certain angle, thereby achieving the three actions of ejecting the lid, ejecting the aircraft, and flipping the barrel sideways. This reduces the impact of external interference on the control of the three actions and ensures stable and reliable time intervals between the three actions.

[0100] Preferably, a first driving gear 53 is provided on the rotating shaft 52, and the drive transmission assembly further includes a first driven gear 54 meshing with the first driving gear 53, a first connecting rod 55 is hingedly connected to the first driven gear 54, and a second connecting rod 56 is hingedly connected to the first connecting rod 55, and the shift lever 123 is hingedly connected to the second connecting rod 56, and the first driving gear 53 drives the first driven gear 54 to rotate to control the extension or retraction of the shift lever 123;

[0101] Preferably, the first driving gear 53 and / or the first driven gear 54 are incomplete gears, which are gears having teeth only in a partial area in the circumferential direction.

[0102] Preferably, a second driving gear 57 is provided on the rotating shaft 52, and the drive transmission assembly further includes a second driven gear 58 meshing with the second driving gear 57. The pull rod 36 is hinged on the second driving gear 57, and the second driven gear 58 is driven by the second driving gear 57 to rotate to control the extension or retraction of the pull rod 36.

[0103] Preferably, the second driving gear 57 and / or the second driven gear 58 are incomplete gears, which are gears having teeth only in a partial area in the circumferential direction.

[0104] Preferably, a cam 59 is provided on the rotating shaft 52 , and the tip of the cam 59 touches and squeezes the valve 42 when rotating downward, so that the valve 42 is changed from a closed state to an open state.

[0105] In the present application, by setting the number of teeth on the above-mentioned incomplete gears, the initial phases of several groups of incomplete gears and the orientation angles of the cam tips, the barrel cover opening locking mechanism 2, the ejection release locking mechanism 3 and the lateral flipping mechanism 4 are started and operated in sequence at predetermined time intervals.

[0106] The working process of the forward separation launch device of the sideways flipping unpowered aircraft includes:

[0107] When the aircraft needs to be released, an electrical signal is sent to the motor; after receiving the electrical signal, the motor starts to rotate, driving the first driving gear, the second driving gear and the cam to rotate through the rotating shaft.

[0108] The first driving gear rotates to drive the gear lever to move downward, the circumferential restrictions of the cylinder cover and the lock hook ring are unlocked, the lock hook ring rotates circumferentially under the action of the preload force of the spring sheet, and the cylinder cover is pushed outward and separated under the action of the preload force of the cylinder cover compression spring.

[0109] After the cylinder cover is opened, the second driving gear starts to engage, driving the pull rod to be pulled out of the limit through hole of the pull plate, and the push plate and the aircraft on it are pushed outward under the action of the push plate compression spring; when the push plate compression spring reaches the free length, the push plate no longer moves outward, and the aircraft continues to move forward at a certain speed under the action of inertia.

[0110] After the aircraft pops out of the tube, the cam rotates to open the gas bottle valve, and the gas in the gas bottle is ejected outward along the outlet hole, causing the launch device to flip outward and avoid the movement channel of the aircraft.

[0111] The present invention has been described above with reference to preferred embodiments, but these embodiments are merely exemplary and serve only as illustrations. On this basis, various replacements and improvements can be made to the present invention, all of which fall within the scope of protection of the present invention.

Claims

1. A sideways flipping unpowered aircraft forward separation launch device, characterized in that: The launching device comprises a cylinder (1), wherein the cylinder (1) comprises a cylinder cover (11), a cylinder wall (12) and a bottom plate (13). In the cylinder body (1), a cylinder cover opening and locking mechanism (2) is installed on the cylinder cover (11); the cylinder cover (11) is controlled by the cylinder cover opening and locking mechanism (2) to pop out and detach from the cylinder wall (12); In the cylinder (1), an ejection release locking mechanism (3) is provided at a position adjacent to the bottom plate; the ejection release locking mechanism (3) pushes the aircraft thereon, so that the aircraft is ejected and detached from the cylinder (1); In the cylinder (1), a lateral flipping mechanism (4) is installed on the bottom plate (13). After the aircraft is separated from the cylinder (1), the cylinder (1) of the launch device is controlled to flip sideways by the lateral flipping mechanism (4). A drive transmission assembly is provided in the ejection release locking mechanism (3), and the drive transmission assembly controls the cylinder cover opening locking mechanism (2), the ejection release locking mechanism (3) and the lateral flipping mechanism (4) to start working in sequence at predetermined time intervals.

2. The forward separation and launching device for a sideways flipping unpowered aircraft according to claim 1, characterized in that: The cylinder cover opening and locking mechanism (2) comprises a cylinder cover compression spring (21) installed in the cylinder wall (12). When the cylinder cover (11) is installed on the cylinder wall (12), that is, when the cylinder body (1) is closed, the top end of the cylinder cover compression spring (21) abuts against the cylinder cover (11) and is in a compressed energy storage state; The cylinder cover opening and locking mechanism (2) further comprises a cylinder cover lower panel (22) located below the cylinder cover (11); the cylinder cover (11) and the cylinder cover lower panel (22) are parallel to each other and are fixed via a connecting column. A lock hook (23) and a spring sheet (24) are provided between the cylinder cover (11) and the cylinder cover lower panel (22); The locking hook ring (23) is rotatable as a whole, and a locking hook (231) extends outward from its edge. By screwing the locking hook (231) into the groove (121) provided on the cylinder wall (12), an axial limit is provided for the cylinder cover to open the locking mechanism (2); The spring sheet (24) is in a deformed energy storage state, and the spring sheet (24) abuts against the limit block (232) of the lock hook ring (23), and can push the limit block (232) and the lock hook ring (23) to rotate, so that the lock hook (231) is rotated out of the groove (121).

3. The forward separation launch device for a sideways flipping unpowered aircraft according to claim 2, characterized in that: A connecting rod guide groove (122) is axially arranged on the inner side of the cylinder wall (12), and a retractable shift rod (123) is arranged in the connecting rod guide groove (122). When the shift rod (123) is extended, it abuts against the limit block (232) to prevent the lock hook ring (23) from rotating; when the shift rod (231) is retracted, the spring sheet (24) pushes the lock hook ring (23) to rotate, so that the lock hook (231) is rotated out of the groove (121), and the cylinder cover compression spring (21) pushes the cylinder cover (11) to separate from the cylinder wall (12).

4. The forward separation launch device for a sideways flipping unpowered aircraft according to claim 1, characterized in that: The lateral turning mechanism (4) comprises a gas cylinder (41) mounted on a bottom plate (13), an air outlet (124) is provided at the bottom of the cylinder wall (12), and the gas cylinder is connected to the air outlet (124) via a valve (42); When the valve (42) is opened, the gas in the gas cylinder (41) is ejected through the gas outlet (124), causing the barrel (1) of the launch device to flip sideways; when the valve (42) is closed, the connection between the gas cylinder (41) and the gas outlet (124) is disconnected.

5. The forward separation and launching device for a sideways flipping unpowered aircraft according to claim 1, characterized in that: The ejection release locking mechanism (3) comprises a push plate (31) and a mounting plate (32) which are parallel to each other, wherein the mounting plate (32) is fixed to the cylinder wall (12), and the aircraft is supported and mounted on the push plate (31), and the push plate (31) is capable of pushing the aircraft to slide along the cylinder wall (12); A push plate compression spring (33) is provided between the push plate (31) and the mounting plate (32). The push plate compression spring (33) is in a compressed energy storage state. The push plate compression spring (33) can push the push plate (31) to make the aircraft on it fly out of the cylinder (1).

6. The forward separation and launching device for a sideways-flipping unpowered aircraft according to claim 5, characterized in that: A pull plate (34) is provided on the push plate (31) at a side adjacent to the mounting plate (32); a limit hole (35) is provided on the pull plate (34); and a retractable pull rod (36) is provided at the limit hole (35); When the pull rod (36) is extended, the pull rod (36) extends into the limiting through hole (35), preventing the push plate compression spring (33) from pushing the push plate (31) and the pull rod (36); when the pull rod (36) is retracted, the push plate compression spring (33) pushes the push plate (31) to move axially, so that the aircraft on the push plate (31) flies out of the cylinder (1).

7. The forward separation and launching device for a sideways-flipping unpowered aircraft according to claim 5, characterized in that: The drive transmission assembly is installed between the push plate (31) and the mounting plate (32). The drive transmission assembly includes a motor (51), a rotating shaft (52) is connected to the motor (51), and the rotating shaft is connected to a shift lever (123), a pull rod (36) and a valve (42). When the rotating shaft (52) rotates, the shift lever (123), the pull rod (36) and the valve (42) start to work in sequence according to a predetermined time interval.

8. The forward separation and launching device for a sideways-flipping unpowered aircraft according to claim 7, characterized in that: A first driving gear (53) is provided on the rotating shaft (52), and the drive transmission assembly further comprises a first driven gear (54) meshed with the first driving gear (53), a first connecting rod (55) is hinged on the first driven gear (54), a second connecting rod (56) is hinged on the first connecting rod (55), and the shift rod (123) is hinged on the second connecting rod (56), and the first driving gear (53) drives the first driven gear (54) to rotate to control the shift rod (123) to extend or retract; Preferably, the first driving gear (53) and / or the first driven gear (54) are incomplete gears, and the incomplete gears are gears with teeth provided in only a partial area in the circumferential direction.

9. The forward separation and launching device for a sideways-flipping unpowered aircraft according to claim 7, characterized in that: A second driving gear (57) is provided on the rotating shaft (52), and the drive transmission assembly further comprises a second driven gear (58) meshed with the second driving gear (57). The pull rod (36) is hinged on the second driving gear (57), and the second driven gear (58) is driven to rotate by the second driving gear (57) to control the extension or retraction of the pull rod (36); Preferably, the second driving gear (57) and / or the second driven gear (58) are incomplete gears, and the incomplete gears are gears with teeth provided in only a partial area in the circumferential direction.

10. The forward separation and launching device for a sideways-flipping unpowered aircraft according to claim 7, characterized in that: A cam (59) is provided on the rotating shaft (52). When the tip of the cam (59) rotates downward, it touches and squeezes the valve (42), so that the valve (42) changes from a closed state to an open state.

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