Aircraft launching device

Abstract

The invention discloses an aircraft launching device. The aircraft launching device comprises a fixed supporting frame, a launching frame, a lead screw nut mechanism and a driving connecting rod. The rear end of the launching frame is hinged to the rear end of the fixed supporting frame, and a lead screw nut mechanism is arranged on a bottom frame of the launching frame. As the rotation of the nut is limited by the guide frame, the nut can only move back and forth along the guide frame and can drive the lower end of the driving connecting rod to move back and forth so as to drive the upper end of the driving connecting rod to move up and down, so that the launching rack connected with the supporting rod is driven to rotate around a hinge shaft, and the pitching motion of the launching rack is realized. And the launching angle of the aircraft mounted on the aircraft mounting part is further controlled. The aircraft launching device is simple in structure, small in installation and layout requirement space, beneficial to compact layout of the aircraft, high in motor response speed, low in environmental condition requirement, high in rotating speed, adjustable in rotating speed, high in braking speed and beneficial to precise control over aircraft launching.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft launch equipment, and in particular to an aircraft launch device. Background Art

[0002] Existing aircraft launching devices mostly use hydraulic boosters, the main structures of which include a centrifugal pump, an impeller, a push rod, and a hydraulic cylinder assembly with a piston. The structure is complex and requires a large space for installation. When the piston is working, the valve is slowly raised, and the braking stroke and time are long, which is not conducive to precise control during aircraft launch. Especially in low and high temperature environments, the hydraulic cylinder is difficult to seal and there is a risk of hydraulic oil leakage, which causes the mechanism to stop moving. In addition, the maintenance cost is high and the energy consumption is large. Summary of the invention

[0003] The embodiment of the present application provides an aircraft launch device, which can solve the technical problems of the aircraft launch device in the prior art, such as complex structure, large installation space, slow response time, and inability to accurately control. The technical solution is as follows:

[0004] A device for launching an aircraft, comprising: a fixed support frame, a rear end of which is provided with a first hinge hole; a launching frame, comprising a bottom frame, a rear end of the bottom frame is fixedly connected to a support rod, and a lower end of the support rod is provided with a second hinge hole; the bottom frame is hingedly connected to the fixed support frame by inserting a hinge shaft into the first hinge hole and the second hinge hole; the launching frame is provided with a plurality of aircraft mounting parts, and the aircraft mounting parts are used to mount an aircraft whose launching direction is along the front and rear direction of the bottom frame; a screw nut mechanism is arranged on the fixed support frame along the front and rear direction of the fixed support frame On the support frame; the screw and nut mechanism includes a screw, a nut, a guide frame, and a motor and a reducer for driving the screw to rotate, the output shaft of the motor is connected to the input shaft of the reducer, the output shaft of the reducer is connected to the 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 screw is arranged in a direction parallel to the front and rear direction of the fixed support frame; a driving connecting rod, one end of the driving connecting rod is hinged to the nut, and the other end is hinged to the top end of the support rod.

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

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

[0007] Optionally, a rear support column is provided in the middle of the rear end of the launch frame, and a front support column is provided in 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 on both sides of the first connecting rod.

[0008] Optionally, the aircraft launch device also includes two side panels; two rear fixing columns are respectively provided on both sides of the rear end of the launch frame, and two front fixing columns are respectively provided on both sides of the front end, and a side panel is connected to the rear fixing column and the front fixing column on the same side; the side panel 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 arranged on the cover plate, the upper locking plate has an upper locking hole, the lower locking plate is arranged on the side plate, and the lower locking plate has a lower locking hole; when the cover plate is buckled with the side plate, the upper locking hole is aligned with the lower lock buckle; when the safety pin is inserted into the upper locking hole and the lower locking hole at the same time, 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 limit block and a first guide rail and a second guide rail arranged in parallel; the first guide rail and the second guide rail are both parallel to the front and rear directions of the bottom frame; the front limit block is arranged at the front ends of the first guide rail and the second guide rail, and is used to limit the forward movement of the aircraft when installing the aircraft; a second locking assembly is arranged between the first guide rail and the second guide rail for locking or unlocking the aircraft.

[0011] Optionally, the aircraft has a locking mouth; the second locking assembly includes: a locking pin that can be inserted into the locking mouth, the locking pin is provided with a spring retaining ring near the pin head and a retaining cap at the tail; a compression spring, which is sleeved on the locking pin; a fixing plate fixedly connected to the lower surface of the bottom frame, the fixing plate having a first pin hole, and the diameter of the first pin hole is larger than the diameter of the locking pin and smaller than the inner diameter of the compression spring, the compression spring is located between the fixing plate and the spring retaining ring; and a driving plate arranged between the fixing plate and the retaining cap, the driving plate having a second pin hole, the diameter of the second pin hole is 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 assemblies located on the same side of the screw and nut mechanism are connected as one.

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

[0014] The beneficial effects brought by the technical solution provided by the embodiment of the present application include at least:

[0015] The present application provides an aircraft launch device, comprising: a fixed support frame, a launch frame, a screw nut mechanism and a driving connecting rod. In the present application, the rear end of the launch frame is hinged to the rear end of the fixed support frame, and a screw nut mechanism is provided on the bottom frame of the launch frame. When the screw nut mechanism is started, the screw rotates. Since the nut is restricted from rotating by the guide frame, the nut can only move forward and backward along the guide frame, which can drive the lower end of the driving connecting rod to move forward and backward, and then drive the upper end of the driving connecting rod to move up and down, thereby realizing the pitch movement of the launch frame and controlling the launch angle of the aircraft installed on the aircraft mounting part. The aircraft launch device of the present application adopts a screw nut mechanism to realize the change of the pitch angle of the launch frame. Since the screw nut mechanism has a simple structure and a small installation layout space requirement, it is conducive to the compact layout of the aircraft. The power components of the screw nut mechanism are mostly motors, which have a fast response speed, low requirements on environmental conditions, high speed and adjustable speed, fast braking speed, and are conducive to the precise control of the aircraft launch. In addition, the maintenance cost of the motor and reducer is low, so the reliability is higher.

[0016] Other features and advantages of the present disclosure will be described in detail in the following detailed description. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0018] Figure 1 is a three-dimensional schematic diagram of an aircraft launching device provided by an embodiment of the present application equipped with an aircraft;

[0019] Figure 2 yes Figure 1 A in the middle is a partial enlarged view of the first locking assembly;

[0020] Figure 3 is a three-dimensional schematic diagram of the aircraft launch device provided in an embodiment of the present application with the cover plate removed;

[0021] Figure 4 yes Figure 3 Schematic diagram of the decomposition of

[0022] Figure 5 It is a three-dimensional schematic diagram of a lead screw and nut mechanism in an aircraft launching device provided in an embodiment of the present application;

[0023] Figure 6is a top view of the aircraft launch device provided in an embodiment of the present application with the cover removed;

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

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

[0026] Fig. 9 yes Figure 8 A partial enlarged view of point D in the middle;

[0027] Fig.10 It is a schematic diagram of the structure of the second locking assembly provided in an embodiment of the present application.

[0028] Description of Reference Numerals

[0029] 1-fixed support frame; 101-first hinge hole; 2-launching 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 nut mechanism; 301-screw; 302-nut; 303-guide frame; 304-motor; 305-reducer; 4-driving connecting rod; 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-stop cap; 702-compression spring; 703-fixed plate; 704-driving plate; 8-articulated shaft; 9-aircraft; 10-rotary encoder. DETAILED DESCRIPTION

[0030] The specific implementation of the present disclosure is described in detail below in conjunction with the accompanying drawings. It should be understood that the specific implementation described herein is only used to illustrate and explain the present disclosure, and is not used to limit the present disclosure.

[0031] In the present disclosure, unless otherwise specified, directional words such as "upper and lower" generally refer to the relative "upper and lower" of the corresponding components in the direction of gravity when in use, and "inside and outside" refer to the "inside and outside" relative to the contour of the corresponding components themselves. In addition, the terms "first", "second", etc. used in the present disclosure are intended to distinguish one element from another and do not have order or importance. In the following description, when referring to the drawings, unless otherwise explained, the same figure numbers in different drawings represent the same or similar elements. In the present disclosure, "front and rear" are relative to the aircraft, with "front" being the same as the launch direction of the aircraft and "rear" being the opposite to the launch direction of the aircraft.

[0032] Existing aircraft launching devices mostly use hydraulic boosters, the main structures of which include a centrifugal pump, an impeller, a push rod, and a hydraulic cylinder assembly with a piston. The structure is complex and requires a large space for installation. When the piston is working, the valve is slowly raised, and the braking stroke and time are long, which is not conducive to precise control during aircraft launch. Especially in low and high temperature environments, the hydraulic cylinder is difficult to seal and there is a risk of hydraulic oil leakage, which causes 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, the present application provides an aircraft launching device, comprising: a fixed support frame 1, a launching frame 2, a screw nut mechanism 3 and a driving connecting rod 4.

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

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

[0036] refer to Figure 3 The launcher 2 is provided with a plurality of aircraft mounting parts 6, and the aircraft mounting parts 6 are used to mount the aircraft 9 whose launching direction is along the front-rear direction of the bottom frame 201. Figures 3 to 7 , the screw nut mechanism 3 is arranged on the fixed support frame 1 along the front and rear direction of the fixed support frame 1.

[0037] refer to Figure 5The lead screw 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 housing of the motor 304 and the housing of 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 front-to-back direction parallel to the fixed support frame 1; the driving connecting rod 4, one end of the driving connecting rod 4 is hinged to the nut 302, and the other end is hinged to the top end of the support rod 202.

[0038] In the embodiment of the present application, the rear end of the launcher 2 is hinged to the rear end of the fixed support frame 1, and a screw nut mechanism 3 is provided on the bottom frame 201 of the launcher 2. When the screw nut mechanism 3 is started, the screw 301 rotates, and since the nut 302 is restricted from rotating by the guide frame 303, the nut 302 can only move forward and backward along the guide frame 303, which can drive the lower end of the driving connecting rod 4 to move forward and backward, and then drive the upper end of the driving connecting rod 4 to move up and down. Since the upper end of the driving connecting rod 4 is hinged to the upper end of the support rod 202, when the upper end of the driving connecting rod 4 moves up and down, the launcher 2 connected to the support rod 202 can be driven to rotate around the hinge shaft 8, thereby realizing the pitch movement of the launcher 2, and then controlling the launch angle of the aircraft 9 installed on the aircraft mounting portion 6. The aircraft launching device of the present application adopts a screw-nut mechanism 3 to realize the change of the pitch angle of the launching frame 2. Since the screw-nut mechanism 3 has a simple structure and requires a small space for installation and layout, it is conducive to the compact layout of the aircraft 9. The power component of the screw-nut mechanism 3 is mostly a motor 304, which has a fast response speed, low requirements on environmental conditions, high and adjustable speed, and fast braking speed, which is conducive to the precise control of the launch of the aircraft 9. In addition, the maintenance cost of the motor 304 and the reducer 305 is low, and thus the reliability is higher.

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

[0040] In the examples of this application, reference is made to Figure 3 and Figure 4, the hinge shaft 8 is fixedly connected to the fixed support frame 1. The aircraft launch device may further include a rotary encoder 10, which includes a fixed portion and a rotating portion, wherein the fixed portion is fixedly connected to the bottom frame 201, and the rotating portion is connected to the hinge shaft 8 and its central axis coincides with the central axis of the hinge shaft 8. The rotary encoder 10 can obtain the rotation angle of the launch frame 2 in real time, so that the rotation degree of the launch frame 2 relative to the fixed support frame 1 can be obtained in real time, thereby facilitating the operator to accurately control the launch angle.

[0041] In the examples of this application, reference is made to Figure 3 and Figure 4 A rear support column 203 is provided at the middle of the rear end of the launcher 2, and a front support column 204 is provided at the middle of the 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, and a cover plate 206 is hinged on both sides of the first connecting rod 205. In this embodiment, two cover plates 206 are hinged on the top of the support frame by the first connecting rod 205, so as to protect the aircraft 9 from dust and rain damage, and also prevent direct sunlight from shining on the aircraft 9.

[0042] In the examples of this application, reference is made to Figures 1 to 4 As shown, in order to further strengthen the protection of the aircraft 9, the aircraft 9 protection device can also include two side panels 207; two rear fixing columns 208 are respectively provided on both sides of the rear end of the launcher 2, and two front fixing columns 209 are respectively provided on both sides of the front end, and a side panel 207 is connected to the rear fixing column 208 and the front fixing column 209 on the same side; the side panel 207 and the cover plate 206 on the same side are locked or unlocked by the first locking assembly 5.

[0043] In the examples 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 arranged on the cover plate 206 and has an upper locking hole. The lower locking plate 502 is arranged on the side plate 207 and has a lower locking hole. When the cover plate 206 and the side plate 207 are buckled, the upper locking hole is aligned with the lower locking buckle. When the safety pin 503 is inserted into the upper locking hole and the lower locking hole at the same time, the side plate 207 and the cover plate 206 are locked. When the safety pin 503 is pulled out of the upper locking hole and the lower locking hole, the side plate 207 and the cover plate 206 are unlocked. In this case, the cover plate 206 and the side plate 207 are locked by the first locking assembly 5, so as to 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 examples of this application, reference is made to Figure 6As shown, each aircraft mounting portion 6 may include a front limit 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 and rear directions of the bottom frame 201; the front limit block 601 is arranged 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 installing the aircraft 9; a second locking assembly 7 for locking or unlocking the aircraft 9 is arranged 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 can facilitate the operator to install the aircraft 9 on the aircraft installation 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 installation part 6 and push the aircraft 9 forward to install the aircraft 9 in place and reliably lock it, which saves the installation time of the aircraft 9 and simplifies the steps of installing the aircraft 9.

[0045] In the examples 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 driving 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 stop cap 7012 is provided at the tail; the compression spring 702 is sleeved on the locking pin 701. The fixing plate 703 is fixedly connected to the lower surface of the bottom frame 201, and 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, and the compression spring 702 is located between the fixing plate 703 and the spring retaining ring 7011. The driving plate 704 is arranged between the fixing plate 703 and the stop cap 7012, and the driving plate 704 has a second pin hole, and the diameter of the second pin hole is larger than the diameter of the locking pin 701 and smaller than the diameter of the stop cap 7012. In this way, in a free state, the head of the locking pin 701 can protrude from the upper surface of the bottom frame 201 and be inserted into the locking port to lock the aircraft 9. When the aircraft 9 needs to be taken out, a downward force is applied to the driving plate 704. Since the diameter of the second pin hole on the driving plate 704 is larger than the diameter of the locking pin 701 and smaller than the diameter of the blocking cap 7012, the driving 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 taken out.

[0046] In the examples of this application, reference is made to Fig. 9 and Fig.10 As shown, the driving plates 704 of the plurality of second locking assemblies 7 on the same side of the screw nut mechanism 3 are connected as one. In this way, the synchronous linkage of the plurality of locking pins 701 can be achieved, thereby achieving the synchronous unlocking of the plurality of aircrafts 9.

[0047] In the embodiment of the present application, the head of the locking pin 701 has an inclined surface inclined toward the launch direction of the aircraft 9. In this way, when the aircraft 9 is installed on the aircraft installation part 6, when the operator pushes the aircraft 9 forward, the aircraft 9 can squeeze the locking pin 701 and squeeze the locking pin 701 into the lower surface of the launcher 2. When the aircraft 9 moves forward to the position, 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 the present disclosure are described in detail above in conjunction with the accompanying drawings; however, the present disclosure is not limited to the specific details in the above embodiments. Within the technical concept of the present disclosure, a variety of simple modifications can be made to the technical solution of the present disclosure, and these simple modifications all fall within the protection scope of the present disclosure.

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

[0050] In addition, various embodiments of the present disclosure may be arbitrarily combined, and as long as they do not violate the concept of the present disclosure, they should also be regarded as the contents disclosed by the present disclosure.

Claims

1. An aircraft launching device, characterized in that: include: A fixed support frame (1), the rear end of which is provided with a first hinge hole (101); A launching frame (2) comprises a bottom frame (201), the rear end of the bottom frame (201) being fixedly connected to a support rod (202), the lower end of the support rod (202) being provided with a second hinge hole (2021); the bottom frame (201) is hingedly connected to the fixed supporting frame (1) by inserting a hinge shaft (8) into the first hinge hole (101) and the second hinge hole (2021); the launching frame (2) is provided with a plurality of aircraft mounting parts (6), the aircraft mounting parts (6) being used to mount an aircraft (9) whose launching direction is along the front-rear direction of the bottom frame (201); A lead screw and nut mechanism (3) is arranged on the fixed support frame (1) along the front-to-back direction of the fixed support frame (1); the lead screw and nut mechanism (3) comprises 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) being connected to the input shaft of the reducer (305), the output shaft of the reducer (305) being connected to the lead screw (301), the housing of the motor (304) and the housing of the reducer (305) being both fixedly connected to the fixed support frame (1); the guide frame (303) being fixedly connected to the fixed support frame (1), and the lead screw (301) being arranged along the front-to-back direction parallel to the fixed support frame (1); A driving connecting rod (4), one end of which is hinged to the nut (302), and the other end of which is hinged to the top end of the supporting rod (202).

2. The aircraft launching device according to claim 1, characterized in that: The number of the aircraft mounting parts (6) is an even number, the screw nut mechanism (3) is fixedly connected to the middle part of the fixed support frame (1) along the front-rear direction of the fixed support frame (1), and the plurality of 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 launching device also includes a rotary encoder (10), which includes a fixed part and a rotating part, wherein the fixed part is fixedly connected to the bottom frame (201), and the rotating part is connected to the hinge shaft (8) and its central axis coincides with the central axis of the hinge shaft (8).

4. The aircraft launching device according to claim 1, characterized in that: A rear support column (203) is provided in the middle of the rear end of the launch frame (2), and a front support column (204) is provided in the middle of the front end. The top ends of the rear support column (203) and the front support column (204) are connected via a first connecting rod (205), and a cover plate (206) is hingedly connected to both sides of the first connecting rod (205).

5. The aircraft launching device according to claim 4, characterized in that: The aircraft launching device also includes two side panels (207); Two rear fixing columns (208) are respectively arranged on both sides of the rear end of the launch frame (2), and two front fixing columns (209) are respectively arranged on both sides of the front end, and a side plate (207) is connected to the rear fixing column (208) and the front fixing column (209) on the same side; The side plate (207) and the cover plate (206) on the same side are locked or unlocked by a first locking assembly (5).

6. The aircraft launching device according to claim 5, characterized in that: The first locking assembly (5) comprises an upper locking plate (501), a lower locking plate (502) and a safety pin (503); the upper locking plate (501) is arranged on the cover plate (206), the upper locking plate (501) has an upper locking hole, the lower locking plate (502) is arranged on the side plate (207), and the lower locking plate (502) has a lower locking hole; When the cover plate (206) and the side plate (207) are buckled together, the upper locking hole is aligned with the lower locking buckle; When the safety pin (503) is inserted into the upper locking hole and the lower locking hole at the same time, 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.

7. The aircraft launching device according to claim 1, characterized in that: Each of the aircraft installation parts (6) comprises a front limit 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 bottom frame (201); the front limit block (601) is arranged 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 the aircraft (9) 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 assembly (7) comprises: A lock pin (701) that can be inserted into the locking opening, wherein the lock pin (701) 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 lock pin (701); A fixing plate (703) fixedly connected to the lower surface of the bottom frame (201), the fixing plate (703) having 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), and the compression spring (702) is located between the fixing plate (703) and the spring retaining ring (7011); and a driving plate (704) disposed between the fixing plate (703) and the blocking cap (7012), wherein the driving plate (704) has a second pin hole, wherein the diameter of the second pin hole is larger than the diameter of the locking pin (701) and smaller than the diameter of the blocking cap (7012).

9. The aircraft launching device according to claim 8, characterized in that: The driving plates (704) of the plurality of second locking assemblies (7) located on the same side of the screw nut mechanism (3) are connected as one body.

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 inclined toward the launching direction of the aircraft (9).

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