An aircraft launching device

Abstract

The application discloses an aircraft launching device, comprising a fixed support frame, a launching frame, a screw nut mechanism and a driving link. The rear end of the launching frame is hinged to the rear end of the fixed support frame, and the screw nut mechanism is arranged on the bottom frame of the launching frame. Since the nut is limited to rotate by the guide frame, the nut can only move forward and backward along the guide frame, can drive the lower end of the driving link to move forward and backward, and further drive the upper end of the driving link to move up and down, so as to drive the launching frame connected with the supporting rod to rotate around the hinge shaft, and further realize the pitching motion of the launching frame, and further control the launching angle of the aircraft installed on the aircraft mounting portion. The aircraft launching device has the advantages of simple structure, small space requirement of installation and layout, is beneficial to the compact layout of the aircraft, has fast motor reaction speed, has low requirement on environmental conditions, has high and adjustable rotating speed, has fast braking speed, and is beneficial to the accurate control of the launching of the aircraft.

Description

Technical Field

[0001] This application relates to the field of aircraft launching equipment technology, and in particular to an aircraft launching device. Background Technology

[0002] Existing aircraft launch devices mostly use hydraulic boosters, whose main structures include centrifugal pumps, impellers, push rods, and hydraulic cylinder assemblies with pistons. The structure is complex, requires a large installation space, and the piston moves slowly during operation, with a long braking stroke and time, which is not conducive to precise control during aircraft launch. Especially in low-temperature and high-temperature environments, the hydraulic cylinder is difficult to seal, and there is a risk of hydraulic oil leakage, which can cause the mechanism to stop moving. In addition, the maintenance cost is high and the energy consumption is large. Summary of the Invention

[0003] This application provides a spacecraft launching device that solves the technical problems of existing spacecraft launching devices, such as complex structure, large installation space, slow response time, and inability to be precisely controlled. The technical solution is as follows:

[0004] An aircraft launching device includes: a fixed support frame with a first hinge hole at its rear end; a launch frame including a base frame, a support rod fixedly connected to the rear end of the base frame, and a second hinge hole at the lower end of the support rod; the base frame and the fixed support frame are hinged together by a hinge shaft inserted into the first and second hinge holes; the launch frame is provided with multiple aircraft mounting parts for mounting aircraft whose launch direction is along the front-rear direction of the base frame; and a screw-nut mechanism disposed on the fixed support frame along the front-rear direction of the fixed support frame. On the support frame; the lead screw and nut mechanism includes a lead screw, a nut, a guide frame, and a motor and a reducer for driving the lead screw to rotate. The output shaft of the motor is connected to the input shaft of the reducer, and the output shaft of the reducer is connected to the lead screw. The housing of the motor and the housing of the reducer are both fixedly connected to the fixed support frame. The guide frame is fixedly connected to the fixed support frame, and the lead screw is arranged in a direction parallel to the front and rear of the fixed support frame. A driving connecting rod is included, with one end hinged to the nut and the other end hinged to the top of the support rod.

[0005] Optionally, the number of the aircraft mounting parts is even, the screw and nut mechanism is fixedly connected to the middle of the fixed support frame along the front-rear direction of the fixed support frame, and multiple aircraft mounting parts are symmetrically distributed on both sides of the screw and nut mechanism.

[0006] Optionally, the hinge shaft is fixedly connected to the fixed support frame; the aircraft launching device further includes a rotary encoder, which includes a fixed part and a rotating part. The fixed part is fixedly connected to the bottom frame, and the rotating part is connected to the hinge shaft, with its central axis coinciding with the central axis of the hinge shaft.

[0007] Optionally, a rear support column is provided at the middle of the rear end of the launcher, and a front support column is provided at the middle of the front end. The top ends of the rear support column and the front support column are connected by a first connecting rod, and a cover plate is hinged to each side of the first connecting rod.

[0008] Optionally, the aircraft launching device further includes two side plates; two rear fixing posts are respectively provided on both sides of the rear end of the launcher, and two front fixing posts are respectively provided on both sides of the front end, with a side plate connected to the rear fixing post and the front fixing post on the same side; the side plate and the cover plate on the same side are locked or unlocked by a first locking assembly.

[0009] Optionally, the first locking assembly includes an upper locking plate, a lower locking plate, and a safety pin. The upper locking plate is disposed on the cover plate and has an upper locking hole. The lower locking plate is disposed on the side plate and has a lower locking hole. When the cover plate and the side plate are fastened together, the upper locking hole and the lower locking hole are aligned. When the safety pin is simultaneously inserted into the upper locking hole and the lower locking hole, the side plate and the cover plate are locked. When the safety pin is pulled out from the upper locking hole and the lower locking hole, the side plate and the cover plate are unlocked.

[0010] Optionally, each of the aircraft mounting parts includes a front limiting block and a first guide rail and a second guide rail arranged in parallel; both the first guide rail and the second guide rail are parallel to the front-rear direction of the base frame; the front limiting block is located at the front end of the first guide rail and the second guide rail, and is used to limit the forward movement of the aircraft when it is installed; a second locking component is provided between the first guide rail and the second guide rail for locking or unlocking the aircraft.

[0011] Optionally, the aircraft has a locking port; the second locking assembly includes: a locking pin that can be inserted into the locking port, the locking pin having a spring retaining ring near the pin head and a retaining cap at the tail; a compression spring sleeved on the locking pin; a fixing plate fixedly connected to the lower surface of the base frame, the fixing plate having a first pin hole, the diameter of the first pin hole being larger than the diameter of the locking pin and smaller than the inner diameter of the compression spring, the compression spring being located between the fixing plate and the spring retaining ring; and a drive plate disposed between the fixing plate and the retaining cap, the drive plate having a second pin hole, the diameter of the second pin hole being larger than the diameter of the locking pin and smaller than the diameter of the retaining cap.

[0012] Optionally, the drive plates of multiple second locking components located on the same side of the lead screw and nut mechanism are connected as one unit.

[0013] Optionally, the head of the locking pin has an inclined surface that is tilted toward the launch direction of the aircraft.

[0014] The beneficial effects of the technical solutions provided in this application include at least the following:

[0015] This application provides an aircraft launching device, including: a fixed support frame, a launcher, a screw and nut mechanism, and a drive linkage. In this application, the rear end of the launcher is hinged to the rear end of the fixed support frame, and the screw and nut mechanism is provided on the bottom frame of the launcher. When the screw and nut mechanism is activated, the screw rotates. Since the nut is restricted from rotation by the guide frame, the nut can only move back and forth along the guide frame, which can drive the lower end of the drive linkage to move back and forth, and then drive the upper end of the drive linkage to move up and down, thereby realizing the pitch motion of the launcher and controlling the launch angle of the aircraft mounted on the aircraft mounting part. The aircraft launching device of this application uses a screw and nut mechanism to realize the change of the launcher pitch angle. Since the screw and nut mechanism has a simple structure and requires little space for installation, it is conducive to the compact layout of the aircraft. The power component of the screw and nut mechanism is mostly an electric motor, which has a fast response speed, low requirements for environmental conditions, high and adjustable speed, and fast braking speed, which is conducive to the precise control of the aircraft launch. Furthermore, the maintenance cost of the motor and reducer is low, thus resulting in higher reliability.

[0016] Other features and advantages of this disclosure will be described in detail in the following detailed description section. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in the embodiments of this application, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0018] Figure 1 This is a three-dimensional schematic diagram of an aircraft launch device equipped with an aircraft, provided in an embodiment of this application.

[0019] Figure 2 yes Figure 1 A magnified view of the first locking component at point A in the middle;

[0020] Figure 3 This is a three-dimensional schematic diagram of the aircraft launch device provided in the embodiments of this application after the cover plate has been removed;

[0021] Figure 4 yes Figure 3 A schematic diagram of the decomposition process;

[0022] Figure 5 This is a three-dimensional schematic diagram of the lead screw and nut mechanism in the aircraft launch device provided in the embodiments of this application;

[0023] Figure 6This is a top view of the aircraft launch device provided in this application embodiment after the cover plate has been removed;

[0024] Figure 7 yes Figure 6 Sectional view at point BB;

[0025] Figure 8 yes Figure 6 Sectional view at CC;

[0026] Figure 9 yes Figure 8 A magnified view of a section at point D;

[0027] Figure 10 This is a schematic diagram of the structure of the second locking component provided in the embodiments of this application.

[0028] Explanation of reference numerals in the attached figures

[0029] 1-Fixed support frame; 101-First hinge hole; 2-Launch frame; 201-Bottom frame; 202-Support rod; 2021-Second hinge hole; 203-Rear support column; 204-Front support column; 205-First connecting rod; 206-Cover plate; 207-Side plate; 208-Rear fixed column; 209-Front fixed column; 3-Screw and nut mechanism; 301-Screw; 302-Nut; 303-Guide frame; 304-Motor; 305-Reducer; 4-Drive linkage; 5-First locking assembly; 501-Upper locking plate; 502-Lower locking plate; 503-Safety pin; 6-Aircraft mounting part; 601-Front limit block; 602-First guide rail; 603-Second guide rail; 7-Second locking assembly; 701-Locking pin; 7011-Spring retaining ring; 7012-Retaining cap; 702-Compression spring; 703-Fixing plate; 704-Drive plate; 8-Hinge shaft; 9-Aircraft; 10-Rotary encoder. Detailed Implementation

[0030] The specific embodiments of this disclosure will be described in detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are for illustration and explanation only and are not intended to limit this disclosure.

[0031] In this disclosure, unless otherwise stated, directional terms such as "upper" and "lower" generally refer to the relative positions of the corresponding components in their operational state relative to each other in the direction of gravity, while "inner" and "outer" refer to their relative positions relative to the contours of the corresponding components themselves. Furthermore, the terms "first," "second," etc., used in this disclosure are for distinguishing one element from another and do not imply sequentiality or importance. In the following description, when referring to the accompanying drawings, unless otherwise explained, the same reference numerals in different drawings denote the same or similar elements. In this disclosure, "front" and "rear" are relative to the aircraft; "front" refers to the direction of launch of the aircraft, and "rear" refers to the direction of launch opposite to the direction of launch.

[0032] Existing aircraft launch devices mostly use hydraulic boosters, whose main structures include centrifugal pumps, impellers, push rods, and hydraulic cylinder assemblies with pistons. The structure is complex, requires a large installation space, and the piston moves slowly during operation, with a long braking stroke and time, which is not conducive to precise control during aircraft launch. Especially in low-temperature and high-temperature environments, the hydraulic cylinder is difficult to seal, and there is a risk of hydraulic oil leakage, which can cause the mechanism to stop moving. In addition, the maintenance cost is high and the energy consumption is large.

[0033] refer to Figures 1 to 10 As shown, this application provides an aircraft launching device, including: a fixed support frame 1, a launch frame 2, a lead screw and nut mechanism 3, and a drive linkage 4.

[0034] Among them, reference Figure 3 and Figure 4 The rear end of the fixed support frame 1 is provided with a first hinge hole 101; the fixed support frame 1 can be the frame of the transport vehicle or a fixed frame supported on the ground.

[0035] The launcher 2 includes a base frame 201, and a support rod 202 is fixedly connected to the rear end of the base frame 201. The lower end of the support rod 202 is provided with a second hinge hole 2021. The base frame 201 and the fixed support frame 1 are hinged by inserting a hinge shaft 8 into the first hinge hole 101 and the second hinge hole 2021.

[0036] refer to Figure 3 The launcher 2 is equipped with multiple aircraft mounting sections 6, which are used to mount aircraft 9 whose launch direction is along the front-rear direction of the base frame 201. (Reference) Figures 3 to 7 The lead screw and nut mechanism 3 is mounted on the fixed support frame 1 along the front-rear direction of the fixed support frame 1.

[0037] refer to Figure 5The lead screw and nut mechanism 3 includes a lead screw 301, a nut 302, a guide frame 303, and a motor 304 and a reducer 305 for driving the lead screw 301 to rotate. The output shaft of the motor 304 is connected to the input shaft of the reducer 305, and the output shaft of the reducer 305 is connected to the lead screw 301. The housings of the motor 304 and the reducer 305 are both fixedly connected to the fixed support frame 1. The guide frame 303 is fixedly connected to the fixed support frame 1, and the lead screw 301 is arranged in a direction parallel to the front and rear of the fixed support frame 1. A drive link 4 is included, with one end hinged to the nut 302 and the other end hinged to the top of the support rod 202.

[0038] In this embodiment, the rear end of the launcher 2 is hinged to the rear end of the fixed support frame 1, and a screw and nut mechanism 3 is provided on the bottom frame 201 of the launcher 2. When the screw and nut mechanism 3 is activated, the screw 301 rotates. Since the nut 302 is restricted from rotating by the guide frame 303, the nut 302 can only move back and forth along the guide frame 303, which can drive the lower end of the drive link 4 to move back and forth, thereby driving the upper end of the drive link 4 to move up and down. Since the upper end of the drive link 4 is hinged to the upper end of the support rod 202, when the upper end of the drive link 4 moves up and down, it can drive the launcher 2 connected to the support rod 202 to rotate around the hinge axis 8, thereby realizing the pitch motion of the launcher 2, and thus controlling the launch angle of the aircraft 9 mounted on the aircraft mounting part 6. The launch device of this application uses a screw and nut mechanism 3 to realize the pitch angle change of the launcher 2. Since the screw and nut mechanism 3 has a simple structure and requires little space for installation, it is conducive to the compact layout of the aircraft 9. The power components of the screw and nut mechanism 3 are mostly motors 304, which have fast response speed, low requirements for environmental conditions, high speed and adjustable speed, and fast braking speed, which is conducive to the precise control of the launch of the aircraft 9. In addition, the motors 304 and the reducers 305 have low maintenance costs, thus having higher reliability.

[0039] In the embodiments of this application, reference is made to Figure 3 and Figure 4 The number of aircraft mounting parts 6 can be even. The screw and nut mechanism 3 is fixedly connected to the middle of the fixed support frame 1 along the front-rear direction. Multiple aircraft mounting parts 6 are symmetrically distributed on both sides of the screw and nut mechanism 3. In this way, the launcher 2 is subjected to relatively uniform force, which is beneficial to the precise control of the aircraft 9. In other embodiments, if the number of aircraft mounting parts 6 is an odd number greater than 1, it can be achieved by changing the structural form of the drive link 4. For example, the drive link 4 can be made into two sub-drive links 4, which are located on both sides of the middle aircraft mounting part 6.

[0040] In the embodiments of this application, reference is made to Figure 3 and Figure 4The hinge shaft 8 is fixedly connected to the fixed support frame 1. The aircraft launch device may also include a rotary encoder 10, which includes a fixed part and a rotating part. The fixed part is fixedly connected to the base frame 201, and the rotating part is connected to the hinge shaft 8, with its central axis coinciding with the central axis of the hinge shaft 8. The rotary encoder 10 can acquire the rotation angle of the launcher 2 in real time. Thus, the degree of rotation of the launcher 2 relative to the fixed support frame 1 can be acquired in real time, facilitating precise control of the launch angle by the operator.

[0041] In the embodiments of this application, reference is made to Figure 3 and Figure 4 The launcher 2 has a rear support column 203 at the middle of its rear end and a front support column 204 at the middle of its front end. The tops of the rear support column 203 and the front support column 204 are connected by a first connecting rod 205. A cover plate 206 is hinged to each side of the first connecting rod 205. In this embodiment, the two cover plates 206 hinged above the support frame by the first connecting rod 205 can protect the aircraft 9 from dust and rain damage, and also prevent direct sunlight from hitting the aircraft 9.

[0042] In the embodiments of this application, reference is made to Figures 1 to 4 As shown, in order to further enhance the protection of the aircraft 9, the protective device for the aircraft 9 may also include two side plates 207; two rear fixing posts 208 are respectively provided on both sides of the rear end of the launcher 2, and two front fixing posts 209 are respectively provided on both sides of the front end. A side plate 207 is connected to the rear fixing post 208 and the front fixing post 209 on the same side; the side plate 207 and the cover plate 206 on the same side are locked or unlocked by the first locking assembly 5.

[0043] In the embodiments of this application, reference is made to Figure 1 and Figure 2 As shown, the first locking assembly 5 includes an upper locking plate 501, a lower locking plate 502, and a safety pin 503. The upper locking plate 501 is disposed on the cover plate 206 and has an upper locking hole. The lower locking plate 502 is disposed on the side plate 207 and has a lower locking hole. When the cover plate 206 and the side plate 207 are fastened together, the upper locking hole and the lower locking hole are aligned. When the safety pin 503 is simultaneously inserted into the upper locking hole and the lower locking hole, the side plate 207 and the cover plate 206 are locked. When the safety pin 503 is pulled out from the upper locking hole and the lower locking hole, the side plate 207 and the cover plate 206 are unlocked. In this case, locking the cover plate 206 and the side plate 207 by the first locking assembly 5 can prevent the cover plate 206 and the side plate 207 from separating or shaking during the transportation of the aircraft launch device.

[0044] In the embodiments of this application, reference is made to Figure 6As shown, each aircraft mounting section 6 may include a front limiting block 601 and a first guide rail 602 and a second guide rail 603 arranged in parallel; the first guide rail 602 and the second guide rail 603 are both parallel to the front-rear direction of the base frame 201; the front limiting block 601 is located at the front end of the first guide rail 602 and the second guide rail 603, and is used to limit the forward movement of the aircraft 9 when it is installed; a second locking component 7 for locking or unlocking the aircraft 9 is provided between the first guide rail 602 and the second guide rail 603. In this embodiment, the first guide rail 602 and the second guide rail 603 are arranged in parallel, which facilitates the operator to install the aircraft 9 onto the aircraft mounting part 6. Since the front limit block 601 can limit the forward movement of the aircraft 9, and the second locking device can limit the backward movement of the aircraft 9 and has a locking function, the operator does not need special training. He only needs to place the aircraft 9 on the aircraft mounting part 6 and push the aircraft 9 forward to install the aircraft 9 in place and lock it reliably, which saves the installation time of the aircraft 9 and simplifies the steps of installing the aircraft 9.

[0045] In the embodiments of this application, reference is made to Figures 8 to 10 As shown, the aircraft 9 has a locking port; the second locking assembly 7 may include: a locking pin 701, a compression spring 702, a fixing plate 703, and a drive plate 704. The locking pin 701 can be inserted into the locking port, and a spring retaining ring 7011 is provided near the pin head of the locking pin 701, and a retaining cap 7012 is provided at the tail end; the compression spring 702 is sleeved on the locking pin 701. The fixing plate 703 is fixedly connected to the lower surface of the base frame 201, and the fixing plate 703 has a first pin hole, the diameter of which is larger than the diameter of the locking pin 701 but smaller than the inner diameter of the compression spring 702, with the compression spring 702 located between the fixing plate 703 and the spring retaining ring 7011. The drive plate 704 is disposed between the fixing plate 703 and the retaining cap 7012, and the drive plate 704 has a second pin hole, the diameter of which is larger than the diameter of the locking pin 701 but smaller than the diameter of the retaining cap 7012. In this way, in the free state, the head of the locking pin 701 can protrude from the upper surface of the base frame 201 and insert into the locking hole to lock the aircraft 9. When it is necessary to remove the aircraft 9, a downward force is applied to the drive plate 704. Since the diameter of the second pin hole on the drive plate 704 is larger than the diameter of the locking pin 701 and smaller than the diameter of the stop cap 7012, the drive plate 704 can drive the locking pin 701 downward. When the head of the locking pin 701 is located on the upper surface of the launcher 2, the aircraft 9 can be unlocked and removed.

[0046] In the embodiments of this application, reference is made to Figure 9 and Figure 10 As shown, the drive plates 704 of multiple second locking components 7 located on the same side of the lead screw and nut mechanism 3 are connected as one unit. In this way, the synchronous linkage of multiple locking pins 701 can be realized, thereby realizing the synchronous unlocking of multiple aircraft 9.

[0047] In the embodiments of this application, the head of the locking pin 701 has an inclined surface that is tilted towards the launch direction of the aircraft 9. Thus, when the aircraft 9 is installed on the aircraft mounting part 6, the aircraft 9 can squeeze the locking pin 701 when the operator pushes the aircraft 9 forward, and the locking pin 701 is squeezed into the lower surface of the launcher 2. When the aircraft 9 moves forward into place, the locking pin 701 can automatically insert into the locking port of the aircraft 9 under the restoring force of the compression spring 702 to lock the aircraft 9.

[0048] The preferred embodiments of this disclosure have been described in detail above with reference to the accompanying drawings. However, this disclosure is not limited to the specific details of the above embodiments. Within the scope of the technical concept of this disclosure, various simple modifications can be made to the technical solutions of this disclosure, and these simple modifications all fall within the protection scope of this disclosure.

[0049] It should also be noted that the various specific technical features described in the above embodiments can be combined in any suitable manner without contradiction. To avoid unnecessary repetition, this disclosure will not describe the various possible combinations separately.

[0050] Furthermore, various different embodiments of this disclosure can be combined in any way, as long as they do not violate the spirit of this disclosure, they should also be regarded as the content disclosed in this disclosure.

Claims

1. A spacecraft launching device, characterized in that, include: A fixed support frame (1) is provided with a first hinge hole (101) at its rear end. The launcher (2) includes a base frame (201), a support rod (202) is fixedly connected to the rear end of the base frame (201), and a second hinge hole (2021) is provided at the lower end of the support rod (202); the base frame (201) and the fixed support frame (1) are hinged by inserting a hinge shaft (8) into the first hinge hole (101) and the second hinge hole (2021); the launcher (2) is provided with a plurality of aircraft mounting parts (6), and the aircraft mounting parts (6) are used to mount aircraft (9) whose launch direction is along the front and rear direction of the base frame (201); A lead screw and nut mechanism (3) is arranged on the fixed support frame (1) along the front-back direction of the fixed support frame (1); the lead screw and nut mechanism (3) includes a lead screw (301), a nut (302), a guide frame (303), and a motor (304) and a reducer (305) for driving the lead screw (301) to rotate. The output shaft of the motor (304) is connected to the input shaft of the reducer (305), and the output shaft of the reducer (305) is connected to the lead screw (301). The housings of the motor (304) and the reducer (305) are both fixedly connected to the fixed support frame (1); the guide frame (303) is fixedly connected to the fixed support frame (1), and the lead screw (301) is arranged along the front-back direction parallel to the fixed support frame (1); A drive link (4) is hinged at one end to the nut (302) and at the other end to the top of the support rod (202).

2. The aircraft launching device according to claim 1, characterized in that, The number of the aircraft mounting parts (6) is even. The screw nut mechanism (3) is fixedly connected to the middle of the fixed support frame (1) in the front-back direction. Multiple aircraft mounting parts (6) are symmetrically distributed on both sides of the screw nut mechanism (3).

3. The aircraft launching device according to claim 1, characterized in that, The hinge shaft (8) is fixedly connected to the fixed support frame (1); The aircraft launch device also includes a rotary encoder (10), which includes a fixed part and a rotating part. The fixed part is fixedly connected to the base frame (201), and the rotating part is connected to the hinge shaft (8) with its central axis coinciding with the central axis of the hinge shaft (8).

4. The aircraft launching device according to claim 1, characterized in that, The launcher (2) has a rear support column (203) at the middle of its rear end and a front support column (204) at the middle of its front end. The top ends of the rear support column (203) and the front support column (204) are connected by a first connecting rod (205). A cover plate (206) is hinged to each side of the first connecting rod (205).

5. The aircraft launching device according to claim 4, characterized in that, The aircraft launch device also includes two side plates (207). The launcher (2) has two rear fixing posts (208) on both sides of the rear end and two front fixing posts (209) on both sides of the front end. A side plate (207) is connected to the rear fixing post (208) and the front fixing post (209) on the same side. The side plate (207) and the cover plate (206) on the same side are locked or unlocked by the first locking assembly (5).

6. The aircraft launching device according to claim 5, characterized in that, The first locking assembly (5) includes an upper locking plate (501), a lower locking plate (502) and a safety pin (503). The upper locking plate (501) is disposed on the cover plate (206) and has an upper locking hole. The lower locking plate (502) is disposed on the side plate (207) and has a lower locking hole. When the cover plate (206) is engaged with the side plate (207), the upper locking hole is aligned with the lower locking hole; When the safety pin (503) is inserted into both the upper and lower locking holes, the side plate (207) and the cover plate (206) are locked; when the safety pin (503) is pulled out from both the upper and lower locking holes, the side plate (207) and the cover plate (206) are unlocked.

7. The aircraft launching device according to claim 1, characterized in that, Each of the aircraft mounting parts (6) includes a front limiting block (601) and a first guide rail (602) and a second guide rail (603) arranged in parallel; the first guide rail (602) and the second guide rail (603) are both parallel to the front-rear direction of the base frame (201); the front limiting block (601) is located at the front end of the first guide rail (602) and the second guide rail (603) and is used to limit the forward movement of the aircraft (9) when it is installed; A second locking assembly (7) for locking or unlocking the aircraft (9) is provided between the first guide rail (602) and the second guide rail (603).

8. The aircraft launching device according to claim 7, characterized in that, The aircraft (9) has a locking port; The second locking component (7) includes: A locking pin (701) that can be inserted into the locking port is provided with a spring retaining ring (7011) near the pin head and a retaining cap (7012) at the tail. A compression spring (702) is sleeved on the locking pin (701); A fixing plate (703) is fixedly connected to the lower surface of the bottom frame (201). The fixing plate (703) has a first pin hole, and the diameter of the first pin hole is larger than the diameter of the locking pin (701) and smaller than the inner diameter of the compression spring (702). The compression spring (702) is located between the fixing plate (703) and the spring retaining ring (7011). And a drive plate (704) disposed between the fixed plate (703) and the stop cap (7012), the drive plate (704) having a second pin hole, the diameter of the second pin hole being larger than the diameter of the locking pin (701) and smaller than the diameter of the stop cap (7012).

9. The aircraft launching device according to claim 8, characterized in that, The drive plates (704) of the multiple second locking components (7) located on the same side of the lead screw and nut mechanism (3) are connected as one unit.

10. The aircraft launching device according to claim 8 or 9, characterized in that, The head of the locking pin (701) has an inclined surface that is tilted toward the launch direction of the aircraft (9).

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