A small aircraft launcher

Abstract

This invention provides a small aircraft launcher, comprising a base rotation adjustment module, a feeding and launching module, and an altitude adjustment module. The feeding and launching module is located above the altitude adjustment module and is fixed to the base rotation adjustment module. The feeding and launching module has a launching channel within it. The feeding and launching module includes a feeding and launching frame, a launching mechanism, a feeding mechanism, and a directional stabilizing mechanism. The launching mechanism, feeding mechanism, and directional stabilizing mechanism are all fixed to the launching frame. The feeding mechanism is movably connected to the rear end of the feeding and launching frame, and the launching mechanism is fixed to the front end of the feeding and launching frame. The directional stabilizing mechanism is located in the middle of the launching frame. This invention offers fast directional adjustment and high launch efficiency.

Description

Technical Field

[0001] This invention belongs to the field of robotics, and in particular relates to a small aircraft launcher. Background Technology

[0002] Darts, as a type of miniature throwing device, are increasingly popular as a form of entertainment. With the development of automated equipment, users can now utilize miniature launchers to launch darts, replacing manual throwing. These launchers can target armor plates, only half the size of an A4 sheet of paper, at distances of 16 to 20 meters, achieving long-range, high-damage attacks on buildings. The launchers can also launch objects such as badminton shuttlecocks, tennis balls, and ping-pong balls.

[0003] A patent document with Chinese patent application number 202120501413.3 and publication date of December 3, 2021, describes a utility model involving a dart-launching robot. The robot includes a frame, a launching component mounted on the frame, a launching rack, and a launching seat mounted on the launching rack via a slide rail. An elastic element is provided between the launching seat and the launching rack. A motion component is mounted on the launching rack to drive the launching seat to move along the slide rail. A feeding component is located directly above the launching rack, including a feeding plate and a cylinder mounted on the feeding plate. The projections of the cylinder and the slide rail coincide on the same horizontal plane.

[0004] However, the feeding process of this utility model uses a cylinder to push the dart into the launching seat. There is a height difference between the launching seat and the material plate, which makes it easy for the dart to fall off during the feeding process. Moreover, the alignment accuracy between the dart and the launching seat is low during the feeding process. Each feeding requires a third motor to lift the movable frame as close as possible to the material plate before pushing the dart from the material plate into the launching seat, and then readjusting the launching direction. The direction adjustment is slow and the launching efficiency is low. Summary of the Invention

[0005] The purpose of this invention is to provide a small aircraft transmitter with fast orientation adjustment and high launch efficiency.

[0006] To achieve the above objectives, a small aircraft launcher includes a base rotation adjustment module, a feeding and launching module, and an altitude adjustment module. The feeding and launching module is located above the altitude adjustment module and is fixed to the base rotation adjustment module. The feeding and launching module has a launching channel within it. The feeding and launching module includes a feeding and launching frame, a launching mechanism, a feeding mechanism, and a directional stabilizing mechanism. The launching mechanism, feeding mechanism, and directional stabilizing mechanism are all fixed to the launching frame. The feeding mechanism is movably connected to the rear end of the feeding and launching frame and is used to store the aircraft and to bring the aircraft to be launched into contact with the launching mechanism for launch. The launching mechanism is fixed to the front end of the feeding and launching mechanism, and the directional stabilizing mechanism is located in the middle of the launching frame. As shown in Figures 1 and 2, the feeding mechanism includes a feeding motor, a feeding screw coupling, a feeding head fixing component, a feeding tail fixing component, an upper hinge plate, a feeding lower hinge plate, and a feeding... The system comprises a feed pusher plate, a loading screw, and a feed screw nut. The feed head fixing component is fixed to the upper end of the feed transmitter frame. The output shaft of the feed motor is fixedly connected to one end of the feed screw coupling, and the other end of the feed screw coupling is fixedly connected to the loading screw. The other end of the loading screw passes through the feed head fixing component and connects to the feed tail fixing component. Both the feed head fixing component and the feed tail fixing component are equipped with bearings, and the loading screw rotates within the bearings. The middle part of the loading screw also passes through the feed pusher plate, and the feed pusher plate is equipped with a feed screw nut. The loading screw and the feed screw nut are movably connected. The feed pusher plate is fixedly connected to an upper hinge plate, and the other end of the upper hinge plate is movably connected to a lower hinge plate. A lower feed plate is fixed to the front side of the lower hinge plate. The lower feed plate is aligned with the launch channel. The end of the launch channel near the launch mechanism is the launch port, and the end of the launch channel near the feed mechanism is the feed inlet.

[0007] With the above setup, when ready to launch, the aircraft is stored at the rear end of the launch channel within the feeding and launching module. The feeding mechanism within the module stores the aircraft and brings them into contact with the launch mechanism for launch. A directional stabilization mechanism, located in the middle of the launch mechanism, adjusts the feeding and launch directions of the aircraft. Therefore, multiple aircraft can be stored in the feeding mechanism awaiting launch. Overall feeding accuracy is high; the next aircraft can be immediately pushed to the launch mechanism for launch after the previous one is launched. The feeding speed is fast, and the launch efficiency is high. (The output of the feeding motor is mentioned again, but the context is unclear.) The rotation drives the feeding screw coupling to rotate, which in turn drives the loading screw to rotate, providing shock absorption and eliminating radial force inertia. The loading screw and the feeding screw nut in the feeding push plate form a screw-nut transmission. The rotation of the loading screw drives the feeding screw nut to move along the loading screw axis, thereby driving the feeding push plate to move along the loading screw axis. When the aircraft is feeding, the feeding motor drives the loading screw to rotate, and the rotation of the loading screw drives the feeding push plate to move towards the launch mechanism. The feeding push plate drives the lower feeding plate to push the aircraft along the launch channel towards the launch mechanism. The feeding process has high docking accuracy.

[0008] Furthermore, a loading optical shaft is provided on one side of the loading screw. One end of the loading optical shaft passes through the feeding head fixing member, the other end passes through the feeding tail fixing member, and the middle part passes through the feeding push plate. The loading optical shaft is connected to both the feeding head fixing member and the feeding tail fixing member by a fixing ring, and the loading optical shaft is connected to the feeding push plate by a bearing.

[0009] The above configuration includes a loading optical shaft located on one side of the loading screw to increase the stability of the movement of the feeding push plate. One end of the loading optical shaft passes through the feeding head fixing component, the other end passes through the feeding tail fixing component, and the middle part passes through the feeding push plate. The loading optical shaft is movably connected to both the feeding head fixing component and the feeding tail fixing component through a fixing ring. The loading optical shaft is connected to the feeding push plate through a bearing to improve the feeding stability.

[0010] Furthermore, the launching mechanism includes two pairs of friction wheels and corresponding acceleration motors. The friction wheels are located on both sides of the launching channel, and the acceleration motors are fixed inside the launch frame via acceleration motor mounting brackets. The friction wheels are fixedly connected to the output shaft of the acceleration motors. The acceleration motor mounting bracket includes an upper mounting plate, a lower mounting plate, and a side mounting plate. The side mounting plate is arranged perpendicular to the length direction of the launch frame. The side mounting plate has locking interfaces on both sides. The upper and lower mounting plates have locking protrusions at both ends along the length direction of the launch frame that match the locking interfaces. The upper mounting plate and the side mounting plate are detachably connected to the locking interfaces via the locking protrusions. The lower mounting plate and the side mounting plate are detachably connected to the locking interfaces via the locking protrusions. The side mounting plate has a support groove in the middle.

[0011] In the above configuration, the friction wheels are driven by independent acceleration motors, which are fixed on both sides of the launch channel inside the launcher frame. The friction wheels are fixedly connected to the output shaft of the acceleration motors. After the friction wheels are accelerated to a specified speed by the acceleration motors, the feeding pusher pushes the aircraft to be launched into the launch mechanism. The two sides of the aircraft rub against the friction wheels, and the aircraft is accelerated and launched under the action of the friction wheels. The two opposing friction wheels realize the acceleration of the aircraft. The upper and lower fixed plates are fixedly connected to the side fixed plates through snap-fit ​​protrusions and snap-fit ​​interfaces, respectively, which makes it easy to add or remove the required acceleration motors and friction wheels, thereby adjusting the launch speed of the aircraft leaving the launch port.

[0012] Furthermore, the base rotation adjustment module includes a base, a frustum turntable, a rotation adjustment motor, a motor mounting plate, a drive gear, and a rack plate. The frustum turntable is rotatably connected to the base. The rotation adjustment motor and the frustum turntable are fixedly connected through the motor mounting plate. The lower end of the motor mounting plate is fixedly connected to the upper end of the frustum turntable. The rotation adjustment motor is fixed to the upper surface of the motor mounting plate. The output shaft of the rotation adjustment motor passes through the motor mounting plate and is fixedly connected to the drive gear. The rack plate is fixed to the lower end of the base. The drive gear meshes with the rack plate. The rotation adjustment motor drives the drive gear to rotate and meshes with the rack plate. Since the rack plate is fixed to the base and the rotation adjustment motor is fixed to the motor mounting plate, the meshing of the drive gear and the rack plate drives the frustum turntable to rotate on the base.

[0013] In the above configuration, the output of the rotary adjustment motor rotates, driving the drive gear to rotate. The drive gear meshes with the rack plate, so the drive gear moves along the arc of the rack plate. At the same time, the movement of the drive gear drives the rotary adjustment motor to move, and the rotary adjustment motor drives the motor fixing plate, which is fixedly connected to the rotary adjustment motor, to rotate. Meanwhile, the frustum turntable, which is fixedly connected to the motor fixing plate, rotates on the base along the circumference of the frustum turntable. The rotating structure is simple and reliable.

[0014] Furthermore, the height adjustment module includes a height adjustment motor, a height adjustment lead screw, a height adjustment lead screw coupling, a lead screw seat, an adjustment lead screw nut, a lead screw nut seat, a linear guide, a linear guide slider, a linkage fixing plate, support rods, and a support frame. The lower end of the support frame is fixedly connected to the upper end of the frustum turntable. The linkage fixing plate is slidably disposed at the front end of the support frame. Support rods are provided on both sides of the upper end of the linkage fixing plate. The lower ends of the support rods are rotatably connected to the linkage fixing plate, and the upper ends of the support rods are rotatably connected to the lower front end of the transmitter frame. The rear end of the support frame is rotatably connected to the lower rear end of the transmitter frame. The height adjustment motor is located in the middle of the support frame. The height adjustment motor is fixedly connected to the middle of the upper end of the height motor fixing plate. The two sides of the upper end of the height motor fixing plate are fixedly connected to the lower ends of both sides of the support frame. The output end of the height adjustment motor is connected to the height adjustment lead screw coupling. One end is connected to a height-adjusting lead screw coupling, and the other end is connected to a height-adjusting lead screw. The other end of the height-adjusting lead screw is movably connected to a bearing inside a lead screw seat. The lead screw seat is fixed to a support frame. The middle part of the height-adjusting lead screw passes through a lead screw nut seat at the lower end of a linkage fixing plate. An adjusting lead screw nut is provided in the lead screw nut seat, and the height-adjusting lead screw is movably connected to the adjusting lead screw nut. Linear rails are provided on both sides of the support frame, and linear rail sliders are provided on both sides of the lower end of the linkage fixing plate. The lower end of the linear rail slider is provided with a sliding groove corresponding to the linear rail. The output end of the height-adjusting motor is in the same direction as the length direction of the linear rail. Pulley fixing plates are also provided at both the front and rear ends of the support frame. Pulley fixing plates are provided with pulleys. Arc guide rails corresponding to the pulleys are provided on the base. A shock-absorbing plate is provided between the arc guide rails and the pulley fixing plates as a support.

[0015] With the above settings, when adjusting the launch altitude, the height adjustment motor drives the output end to rotate, which in turn drives the height adjustment lead screw coupling to rotate. The lead screw coupling drives the height adjustment lead screw to rotate, and the height adjustment lead screw and the adjusting lead screw nut form a lead screw-nut transmission. The adjusting lead screw nut moves axially along the height adjustment lead screw nut, thus driving the linkage fixing plate on the lead screw nut seat to move along the length of the linear guide. When the linkage fixing plate moves, it drives the support rod on the linkage fixing plate to move. When the support rod moves, it drives the front part of the launch frame to move. Since the rear part of the launch frame is movably connected to the rear part of the support frame, the height of the front part of the launch frame changes when the rear part of the launch frame is movably connected, thereby adjusting the launch altitude. The height adjustment method is simple and reliable. During rotation, the bullseye wheels located at the front and rear ends of the support frame slide along the arc guide rail on the base. The bullseye wheels at the front and rear ends of the support frame can provide sufficient support force for the support frame. The shock-absorbing plate can provide a preload force when the pulley rotates and when the aircraft is launched, which is used to counteract the recoil force during launch and the pressure during rotation.

[0016] Furthermore, the directional stabilization mechanism includes side limiting plates, side limiting brackets, an upper guide rail, and a lower guide rail. The side limiting plates are vertically spaced and fixed on both sides of the launch channel, extending from the feed inlet of the launch channel to the middle of the launch channel. The side limiting plates are fixed together by limiting fixing plates. The limiting fixing plates are L-shaped plates, with four or more limiting protrusions at one end. The limiting protrusions engage with the limiting grooves on the side limiting plates. The side limiting plates near the feed inlet have an end that tilts outwards. The device is angled, with the side limiting brackets fixed to both sides of the launch channel, connected to the side limiting plates, and extending to one end of the launch mechanism. The upper guide rail is fixed to the upper side of the launch channel, with one side of the upper guide rail fixed to the lower end of the feeding tail fixing component and the other side of the upper guide rail fixed to one end of the launch port. The lower guide rail is fixed to the lower side of the launch channel, with one end of the lower guide rail fixed to one end of the feeding port and the other end of the lower guide rail fixed to one end of the launch port. The side limiting plates, side limiting brackets, upper guide rails, and lower guide rails are in contact with the fuselage of the aircraft.

[0017] The above configuration, with the side limiting plate, side limiting bracket, upper guide rail, and lower guide rail fitting snugly against the aircraft's fuselage, ensures stable launch direction. The smooth surfaces of the side limiting plate, side limiting bracket, upper guide rail, and lower guide rail reduce friction. The side limiting plate, with its end angled outwards near the feed inlet, creates a larger opening in the feed inlet direction, facilitating feeding. After feeding, the material is guided by the lower guide rail. The upper guide rail, located near the launch port, and the upper and lower guide rails, limit the aircraft's entry into the launch port from the vertical direction of the launch channel, allowing the aircraft to enter the launch port more effectively and reliably.

[0018] Furthermore, the feeding launcher frame is provided with two or more micro switches spaced apart on one side, and a micro switch trigger is provided on the side of the feeding pusher plate near the micro switches. The interval length of the micro switches is the same as the length of the aircraft. Each time the feeding pusher plate pushes an aircraft forward, the micro switch trigger touches a micro switch.

[0019] With the above setup, when the feeding pusher pushes the aircraft to feed the launch mechanism, each time an aircraft is pushed into the launch mechanism, the micro switch component on the side of the feeding pusher closest to the micro switch contacts the micro switch. The micro switch connects to and sends a start signal to the acceleration motor of the launch mechanism. The acceleration motor starts and accelerates the friction wheel, thereby launching the aircraft to be launched. The trigger switch realizes automatic feeding and automatic launch.

[0020] Furthermore, the feeding transmitter frame is also equipped with an infrared aiming device, which is located at the upper end of the emission port and emits infrared laser light to illuminate the emission port direction.

[0021] The above settings allow you to adjust the firing direction of the launch port and use the infrared laser emitted by the infrared sight to determine the firing direction. This makes it easy to observe whether the launch point is aligned with the target location and achieve long-range target hits.

[0022] In the above structure, when the aircraft is ready for launch, it is stored at the rear end of the launch channel within the feeding and launch module. Side limiting plates and brackets are installed on both sides of the feeding mechanism in the launch channel to conform to the aircraft and limit the feeding direction. Upper and lower guide rails are installed on the upper and lower sides of the launcher mechanism in the launch channel to conform to the aircraft and limit the launch direction. In the base rotation adjustment module, the output of the rotation adjustment motor rotates, driving the drive gear to rotate. The drive gear meshes with the rack plate and moves along the arc of the rack plate. This movement of the drive gear drives the rotation adjustment motor, simultaneously causing the motor fixing plate and the frustum turntable, which are fixedly connected to the rotation adjustment motor, to rotate on the base along the circumference of the frustum turntable. In the height adjustment module, the output of the height adjustment motor drives the height adjustment screw coupling to rotate, which in turn drives the height adjustment screw to rotate. The height adjustment screw and the adjusting screw nut form a screw-nut transmission. The adjusting screw nut moves axially along the height adjustment screw nut, causing the linkage fixing plate on the screw nut seat to move along the length of the linear guide. The movement of the linkage fixing plate drives the linkage fixing plate... The support rod on the fixed plate moves, which in turn moves the front of the launcher frame. Since the rear of the launcher frame is connected to the rear of the support frame via a movable connection, the height of the front of the launcher frame changes even when the rear pin is fixed, thus adjusting the launch height and direction quickly. The output of the feeding motor in the feeding launch module rotates, driving the feeding screw coupling to rotate. This coupling, in turn, drives the loading screw to rotate. The rotation of the loading screw causes the feeding screw nut to move axially along the loading screw, which in turn moves the feeding push plate towards the launch mechanism. The feeding optical axis located on one side of the feeding screw increases the stability of the feeding push plate. The feeding push plate drives the lower feeding plate to push the aircraft along the launch channel towards the launch mechanism. In the launch mechanism, the friction wheel is accelerated to a specified speed by the acceleration motor. The feeding push plate pushes the aircraft to be launched into the launch mechanism. The two sides of the aircraft rub against the friction wheel. Under the action of the friction wheel, the aircraft is accelerated and launched. The overall feeding speed is fast. After the previous aircraft is launched, the next aircraft can be pushed to the launch mechanism for launch immediately. The launch efficiency is high. Attached Figure Description

[0023] Figure 1 This is a schematic diagram of the structure of a small aircraft transmitter according to the present invention.

[0024] Figure 2 This is an exploded view of the fuel supply and launch module of the aircraft in this invention.

[0025] Figure 3 This is an exploded view of the feeding mechanism in this invention.

[0026] Figure 4 A schematic diagram of the base rotation adjustment module in this invention.

[0027] Figure 5 An exploded view of the base rotation adjustment module in this invention.

[0028] Figure 6 This is a schematic diagram of the height adjustment module in this invention.

[0029] Figure 7 This is an exploded view of the height adjustment module in this invention.

[0030] Figure 8 This is a schematic diagram of the structure of the base of the present invention after rotation.

[0031] Figure 9 This is a schematic diagram of the structure after height adjustment according to the present invention.

[0032] Figure 10 This is a schematic diagram of the structure connecting the side limiting plate, side limiting bracket, side fixing plate, upper guide rail, lower guide rail, friction wheel, acceleration motor and motor fixing frame in this invention.

[0033] Figure 11 This is a schematic diagram of the friction wheel, acceleration motor, and motor mounting bracket in this invention.

[0034] Figure 12 This is an exploded view of the friction wheel, the acceleration motor, and the motor mounting bracket in this invention.

[0035] Figure 13 This is a front view of the side fixing plate in this invention.

[0036] Figure 14 This is a front view of the limiting and fixing plate in this invention. Detailed Implementation

[0037] The present invention will now be described in further detail with reference to the accompanying drawings and specific embodiments.

[0038] like Figure 1-14As shown, a small aircraft launcher is used to launch a small aircraft 1. The small aircraft launcher includes a base rotation adjustment module 2, a feeding and launching module 3, and an altitude adjustment module 4. The feeding and launching module 3 is located above the altitude adjustment module 4, and the altitude adjustment module 4 is fixed on the base rotation adjustment module 2. The feeding and launching module 3 has a launching channel 5 inside. The feeding and launching module 3 includes a feeding and launching frame 31, a launching mechanism 32, a feeding mechanism 33, and a directional stabilizing mechanism 34. The launching mechanism 32, the feeding mechanism 33, and the directional stabilizing mechanism 34 are all fixed on the launching frame 31. The feeding mechanism 33 is movably connected to the rear end of the feeding and launching frame 31 and is used to store the aircraft 1 and to make the aircraft 1 to be launched contact with the launching mechanism 32 and launch it. The launching mechanism 32 is fixed to the front end of the feeding and launching mechanism 31, and the directional stabilizing mechanism 34 is located in the middle of the launching frame 32.

[0039] like Figure 2 and Figure 3 As shown, the feeding mechanism 33 includes a feeding motor 331, a feeding screw coupling 332, a feeding head fixing member 333, a feeding tail fixing member 334, an upper hinge plate 335, a feeding lower hinge plate 336, a feeding push plate 337, a loading screw 338, and a feeding screw nut 339. The feeding head fixing member 333 is fixed to the upper end of the feeding transmitter frame 31. The output shaft of the feeding motor 331 is fixedly connected to one end of the feeding screw coupling 332, and the other end of the feeding screw coupling 332 is fixedly connected to the loading screw 338. The other end of the loading screw 338 passes through the feeding head fixing member 333 and is connected to the feeding head fixing member 334. The tail fixing member 334 is connected, and the feeding head fixing member 333 and the feeding tail fixing member 334 are both equipped with bearings. The loading screw 338 rotates in the bearing. The middle part of the loading screw 338 also passes through the feeding push plate 337. The feeding push plate 337 is equipped with a feeding screw nut 339. The loading screw 338 and the feeding screw nut 339 are movably connected. The feeding push plate 337 is fixedly connected to an upper hinge plate 335. The other end of the upper hinge plate 335 is movably connected to a lower hinge plate 336. The front side of the lower hinge plate 336 is fixed with a lower feeding plate 330. The lower feeding plate 330 extends into the launching channel 5.

[0040] With the above setup, multiple aircraft 1 are stored at intervals at the rear end of the launch channel 5 within the feeding and launching module 3 during launch preparation. The feeding mechanism 33 within the feeding and launching module 3 is used to store the aircraft 1 and to bring the aircraft 1 to be launched into contact with the launching mechanism 32 for launch. The directional stabilization mechanism 34 is located in the middle of the launching mechanism 32 to adjust the feeding direction and launch direction of the aircraft 1. Therefore, multiple aircraft 1 can be stored in the feeding mechanism 33 and wait for the launching mechanism 32 to launch them. The overall feeding accuracy is high. After the previous aircraft 1 is launched, the next aircraft 1 can be immediately pushed to the launching mechanism 32 for launch. The feeding speed is fast and the launch efficiency is high. The output end of the feeding motor 331 rotates to drive the feeding screw coupling 33. 2. Rotation: The feeding screw 338 is driven to rotate via the feeding screw coupling 332, providing shock absorption and eliminating radial force inertia. The feeding screw 338 and the feeding screw nut 339 in the feeding push plate 337 form a screw-nut transmission. The rotation of the feeding screw 338 drives the feeding screw nut 339 to move axially along the feeding screw 338, thereby driving the feeding push plate 337 to move axially along the feeding screw 338. When the aircraft 1 is feeding, the feeding motor 331 drives the feeding screw 338 to rotate. The rotation of the feeding screw 338 drives the feeding push plate 337 to move towards the launch mechanism 32. The feeding push plate 337 drives the lower feeding plate 330 to push the aircraft 1 along the launch channel 5 towards the launch mechanism 32. The feeding process has high docking accuracy.

[0041] like Figure 2 and Figure 3 As shown, a loading optical shaft 351 is also provided on one side of the loading screw 338. One end of the loading optical shaft 351 passes through the feeding head fixing member 333, the other end passes through the feeding tail fixing member 334, and the middle part passes through the feeding push plate 337. The loading optical shaft 351 is movably connected to the feeding head fixing member 333 and the feeding tail fixing member 334 through a fixing ring 352. The loading optical shaft 351 is connected to the feeding push plate 337 through a bearing.

[0042] The above configuration includes a loading optical shaft 351 located on one side of the loading screw 338 to increase the stability of the movement of the feeding push plate. One end of the loading optical shaft 351 on one side of the loading screw 338 passes through the feeding head fixing member 333, the other end passes through the feeding tail fixing member 334, and the middle part passes through the feeding push plate 337. The loading optical shaft 351 is movably connected to the feeding head fixing member 333 and the feeding tail fixing member 334 through a fixing ring 352. The loading optical shaft 351 is connected to the feeding push plate 337 through a bearing. By setting the loading optical shaft 351 on one side of the loading screw 337, the loading screw 337 drives the feeding push plate 337 to move for guidance, thereby improving the stability of the feeding.

[0043] like Figure 2 , Figure 11 and Figure 12 As shown, in this embodiment, the launching mechanism 32 includes two pairs of friction wheels 321 and corresponding acceleration motors 322. The friction wheels 321 are located on both sides of the launching channel 5. The acceleration motors 322 are fixed inside the launching frame 31 by acceleration motor mounting brackets 323. The friction wheels 321 are fixedly connected to the output shaft of the acceleration motors 322. The acceleration motor mounting brackets 323 include an upper mounting plate 324, a lower mounting plate 325, and a side mounting plate 326. The upper mounting plate 324 and the lower mounting plate 325 are respectively connected to the upper and lower ends of the side mounting plate 326. In this embodiment, there are two side mounting plates 326, which are located on both sides of the upper mounting plate 324 and the lower mounting plate 325 and are connected to the upper mounting plate 326. The upper fixing plate 324 and the lower fixing plate 325 are connected to form a fixing frame. An acceleration motor 322 is fixedly connected to the upper fixing plate 324. The side fixing plate 326 is set perpendicular to the length direction of the transmitter frame 31. The side fixing plate 326 has a snap-fit ​​interface 3261 on both sides. The upper fixing plate 324 and the lower fixing plate 325 have snap-fit ​​protrusions 3262 at both ends along the length direction of the transmitter frame 31 that match the snap-fit ​​interface 3261. The upper fixing plate 324 and the side fixing plate 3262 are fixedly connected to the snap-fit ​​interface 3261 through the snap-fit ​​protrusion 3262. The lower fixing plate 325 and the side fixing plate 326 are detachably connected to the snap-fit ​​interface 3261 through the snap-fit ​​protrusion 3262. The side fixing plate 326 has a support groove 3263 in the middle.

[0044] In the above configuration, the friction wheels 321 are driven by independent acceleration motors 322. The acceleration motors 322 are fixed on both sides of the launch channel 5 inside the launcher frame 31. The friction wheels 321 are fixedly connected to the output shaft of the acceleration motors 322. After the friction wheels 321 are accelerated to a specified speed by the acceleration motors 322, the feeding push plate 337 pushes the aircraft 1 to be launched into the launch mechanism 32. The two sides of the aircraft 1 rub against the friction wheels 321. Under the action of the friction wheels 321, the aircraft 1 is accelerated and launched. The two opposing friction wheels 321 realize the acceleration of the aircraft 1. The upper fixing plate 324 and the lower fixing plate 325 are detachably connected to the side fixing plate 3262 through the snap-fit ​​protrusion 3262 and the snap-fit ​​interface 3261, respectively, so as to facilitate the addition and reduction of the required acceleration motors 322 and friction wheels 321, thereby adjusting the launch speed of the aircraft 1 from the launch port.

[0045] like Figure 4 and Figure 5As shown, the base rotation adjustment module 2 includes a base 21, a frustum turntable 22, a rotation adjustment motor 23, a motor fixing plate 28, a drive gear 25, and a rack plate 26. The frustum turntable 22 is rotatably connected to the base 21. The rotation adjustment motor 23 and the frustum turntable 22 are fixedly connected through the motor fixing plate 28. The lower end of one side of the motor fixing plate 28 is fixedly connected to the upper end of the frustum turntable 22. The rotation adjustment motor 23 is fixed to the upper surface of the motor fixing plate 28. The output shaft of the rotation adjustment motor 23 passes through the motor fixing plate 28 and is fixedly connected to the drive gear 25. The rack plate 26 is fixed to the lower end of the base 21. The drive gear 25 meshes with the rack plate 26. The rotation adjustment motor 23 drives the drive gear 25 to rotate and mesh with the rack plate 26. Since the rack plate 26 is fixed to the base 21 and the rotation adjustment motor 23 is fixed to the motor fixing plate 28, the meshing of the drive gear 25 and the rack plate 26 drives the frustum turntable 22 to rotate on the base 21.

[0046] In the above configuration, the output of the rotary adjustment motor 23 rotates, driving the drive gear 25 to rotate. The drive gear 25 meshes with the rack plate 25. Therefore, the drive gear 25 moves along the arc of the rack plate 25. At the same time, the movement of the drive gear 25 drives the rotary adjustment motor 23 to move. Simultaneously, the rotary adjustment motor 23 drives the motor fixing plate 28, which is fixedly connected to the rotary adjustment motor 23, to rotate. At the same time, the frustum turntable 22, which is fixedly connected to the motor fixing plate 28, rotates on the base 21 along the circumference of the frustum turntable 22. The rotating structure is simple and reliable.

[0047] like Figure 13 As shown, two parallel protruding pillars 32631 are also provided in the middle of the support groove 3263. The two protruding pillars 32631 form a first groove 32632, and a second groove 32633 is formed on both sides of the first groove 32632. With the above arrangement, when the aircraft 1 enters the launch port, the bottom of the aircraft 1 contacts the two protruding pillars 32631 to support the aircraft. The flight fins on both sides of the aircraft are accommodated by the second groove 32622 to achieve a guiding function, so that the aircraft can smoothly enter the launch port.

[0048] like Figure 6 and Figure 7As shown, the height adjustment module 4 includes a height adjustment motor 41, a height adjustment lead screw 42, a height adjustment lead screw coupling 43, a lead screw seat 44, an adjustment lead screw nut 45, a lead screw nut seat 46, a linear guide 47, a linear guide slider 48, a linkage fixing plate 49, support rods 40, and a support frame 27. The lower end of the support frame 27 is fixedly connected to the upper end of the frustum turntable 22. The linkage fixing plate 49 is slidably disposed at the front end of the support frame 27. Support rods 40 are provided on both sides of the upper end of the linkage fixing plate 49. The lower end of the support rod 40 is rotatably connected to the linkage fixing plate 49. The upper end of the support rod 40 is rotatably connected to the lower front end of the transmitter frame 31. The rear end of the support frame 27 is rotatably connected to the lower rear end of the transmitter frame 31. The height adjustment motor 41 is located in the middle of the support frame 27. The height adjustment motor 41 is fixedly connected to the middle upper end of the height motor fixing plate 410. The upper sides of the height motor fixing plate 410 are fixedly connected to the lower ends of both sides of the support frame 40. The output end of the height adjustment motor 41 is connected to one end of the height adjustment screw coupling 43. The other end of the height adjusting screw coupling 43 is connected to the height adjusting screw 42. The other end of the height adjusting screw 42 is movably connected to a bearing inside the screw seat 44. The screw seat 44 is fixed on the support frame 27. The middle part of the height adjusting screw 42 passes through the screw nut seat 46 at the lower end of the linkage fixing plate 49. The screw nut seat 46 is provided with an adjusting screw nut 45. The height adjusting screw 42 is movably connected to the adjusting screw nut 45. Linear rails 47 are provided on both sides of the support frame 27. The linkage fixing plate 49... The lower end of the support frame 27 is provided with linear guide sliders 48 on both sides. The lower end of the linear guide sliders 48 is provided with a slide groove 480 corresponding to the linear guide 47. The output end of the height adjustment motor 41 is in the same direction as the length direction of the linear guide 47. The front and rear ends of the support frame 27 are also provided with pulley fixing plates 240. The pulley fixing plates 240 are provided with pulleys 24. The base 21 is provided with arc guide rails 29 corresponding to the pulleys 24. A shock-absorbing plate 290 is provided between the arc guide rails 29 and the pulley fixing plates 240 as a support.

[0049] With the above settings, when adjusting the launch height, the height adjustment motor 41 drives the output end to rotate, which in turn drives the height adjustment screw coupling 43 to rotate. The height adjustment screw coupling 43 drives the height adjustment screw 42 to rotate. The height adjustment screw 42 and the adjustment screw nut 45 form a screw-nut transmission. The adjustment screw nut 45 moves axially along the height adjustment screw 42 nut, thus driving the linkage fixing plate 49 on the screw nut seat 46 to move along the length direction of the linear guide 47. When the linkage fixing plate 49 moves, it drives the support rod 40 on the linkage fixing plate 49 to move. The movement of the support rod 40 drives the front part of the transmitter frame 31 to move. Because the rear of the launcher frame 31 is movably connected to the rear of the support frame 27, the height of the front of the launcher frame 31 can be changed when the rear of the launcher frame 31 is movably connected, thereby adjusting the launch height. The height adjustment method is simple and reliable. When rotating, the bullseye wheels 24 located at the front and rear ends of the support frame 27 slide along the arc guide rail on the base 21. The bullseye wheels 24 at the front and rear ends of the support frame 27 can provide sufficient support force for the support frame 27. The shock-absorbing plate 290 can provide a preload force when the pulley 24 rotates and when the aircraft 1 is launched, which is used to counteract the recoil force during launch and the pressure during rotation.

[0050] like Figure 10 and Figure 14 As shown, the directional stabilizing mechanism 34 includes side limiting plates 341, side limiting brackets 342, upper guide rails 343, and lower guide rails 344. The side limiting plates 341 are vertically spaced and fixed on both sides of the launch channel 5, extending from the feed inlet of the launch channel 5 to the middle of the launch channel 5. The side limiting plates 341 are fixed together by limiting fixing plates 327. The limiting fixing plates 327 are L-shaped plates, and one end of the limiting fixing plates 327 is provided with four or more limiting protrusions. The limiting protrusions are engaged and fixed with the limiting grooves on the side limiting plates 341. The side limiting plates 341 are inclined outward on the side near the feed inlet. The side limiting brackets 342 are fixed on both sides of the launch channel 5 and the side limiting plates 341. The limiting plate 341 is connected to and extends to one end of the launching mechanism. The upper guide rail 343 is fixed to the upper side of the launching channel 5. One side of the upper guide rail 343 is fixed to the lower end of the feeding tail fixing component, and the other side of the upper guide rail 343 is fixed to one end of the launching port. There is one upper guide rail 343 and two lower guide rails 344. One side of the upper guide rail 343 is located between the two lower guide rails 344. The lower guide rail 344 is fixed to the lower side of the launching channel 5. One end of the lower guide rail 344 is fixed to one end of the feeding port, and the other end of the lower guide rail 344 is fixed to one end of the launching port. The side limiting plate 341, the side limiting bracket 342, the upper guide rail 343 and the lower guide rail 344 are in contact with the fuselage of the aircraft 1.

[0051] The above configuration, with the side limiting plate 341, side limiting bracket 342, upper guide rail 343, and lower guide rail 344 fitting snugly against the fuselage of the aircraft 1, can stabilize the launch direction; the smooth surfaces of the side limiting plate 341, side limiting bracket 342, upper guide rail 343, and lower guide rail 344 reduce friction; the side limiting plate 341 is tilted outwards near the feed port, which makes the feed port opening larger, thus facilitating feeding; and after feeding, it is guided by the lower guide rail. The upper guide rail is set at the end near the launch port, and the upper guide rail 343 and lower guide rail 344 limit the aircraft 1 from the vertical direction of the launch channel 5 to enter the launch port, so that the aircraft can enter the launch port better and more reliably.

[0052] like Figure 2 As shown, the feeding launcher frame 31 has two or more microswitches 311 spaced apart on one side, and the feeding pusher plate 337 has a microswitch trigger 312 on the side near the microswitch 311. The spacing length of the microswitches 311 is the same as the length of the aircraft 1. Each time the feeding pusher plate 337 pushes an aircraft 1 forward, the microswitch trigger 312 touches a microswitch 311.

[0053] With the above configuration, when the feeding pusher plate 337 pushes the aircraft 1 to feed the launch mechanism 32, each time an aircraft 1 is pushed into the launch mechanism 32, the micro switch 312 on the side of the feeding pusher plate 337 near the micro switch 311 contacts the micro switch 311. The micro switch 311 is connected to send a start signal to the acceleration motor 322 of the launch mechanism 32. The acceleration motor 322 starts to accelerate the friction wheel 321, thereby launching the aircraft 1 to be launched. The trigger switch realizes automatic feeding and automatic launch.

[0054] like Figure 2 As shown, the feeding transmitter frame 31 is also equipped with an infrared aiming device 310. The infrared aiming device 310 is located at the upper end of the emission port and is used to emit infrared laser to illuminate the emission port direction.

[0055] The above settings allow for adjustment of the firing direction of the firing port. The infrared laser emitted by the infrared sight 310 can be used to determine the firing direction, making it easy to observe whether the firing point is aligned with the firing location and achieve long-range target hit.

[0056] In the above structure, when the aircraft 1 is ready to launch, it is stored at the rear end of the launch channel 5 within the feeding and launching module 3. Side limiting plates 341 and side limiting brackets are installed on both sides of the feeding mechanism 33 in the launch channel 5 to conform to the aircraft 1 and limit the feeding direction. Upper guide rails 343 and lower guide rails 344 are installed on the upper and lower sides of the launch mechanism in the launch channel 5 to conform to the aircraft 1 and limit the launch direction. The output of the rotation adjustment motor 23 in the base rotation adjustment module 2 rotates, driving the drive gear 25 to rotate. The drive gear 25 meshes with the rack plate 25, and moves along the arc of the rack plate 25. The movement of the drive gear 25 drives the rotation adjustment motor... When the machine 23 moves, it simultaneously drives the motor fixing plate 28 and the frustum turntable 22, which are fixedly connected to the rotary adjustment motor 23, to rotate on the base 21 along the circumference of the frustum turntable 22. In the height adjustment module 4, the height adjustment motor 41 drives the output end to rotate, which in turn drives the height adjustment screw coupling 43 to rotate. The height adjustment screw coupling 43 drives the height adjustment screw 42 to rotate. The height adjustment screw 42 and the adjustment screw nut 45 form a screw-nut transmission. The adjustment screw nut 45 moves along the axial direction of the height adjustment screw 42 nut, which drives the linkage fixing plate 49 on the screw nut seat 46 to move along the length direction of the linear guide 47. When the linkage fixing plate 49 moves, it will drive the support on the linkage fixing plate 49. When the support rod 40 moves, it causes the front part of the launcher frame 31 to move. Since the rear part of the launcher frame 31 is connected to the rear part of the support frame 27 via a movable connection, the height of the front part of the launcher frame 31 changes even when the rear pin of the launcher frame 31 is fixed, thus adjusting the launch height and direction quickly. The output end of the feeding motor 331 in the feeding launch module 3 rotates, driving the feeding screw coupling 332 to rotate. This, in turn, drives the loading screw 338 to rotate. The rotation of the loading screw 338 causes the feeding screw nut 339 to move axially along the loading screw 338, which in turn moves the feeding push plate towards the launch mechanism 32. Meanwhile, the loading optical shaft 351 located on one side of the loading screw 338 increases the stability of the movement of the feeding push plate. The feeding push plate 337 drives the lower feeding plate 330 to push the aircraft 1 along the launch channel 5 towards the launch mechanism 32. After the friction wheel 321 in the launch mechanism 32 is accelerated to the specified speed by the acceleration motor 322, the feeding push plate 337 pushes the aircraft 1 to be launched into the launch mechanism 32. The two sides of the aircraft 1 rub against the friction wheel 321. The aircraft 1 is accelerated and launched under the action of the friction wheel 321. The overall feeding speed is fast. After the previous aircraft 1 is launched, the next aircraft 1 can be pushed to the launch mechanism 32 for launch immediately. The launch efficiency is high.

Claims

1. A small aircraft transmitter, characterized in that: It includes a base rotation adjustment module, a feeding and launching module, and a height adjustment module. The feeding and launching module is located above the height adjustment module and is fixed on the base rotation adjustment module. The feeding and launching module has a launching channel inside. The feeding and launching module includes a feeding and launching frame, a launching mechanism, a feeding mechanism, and a directional stabilizing mechanism. The launching mechanism, feeding mechanism, and directional stabilizing mechanism are all fixed to the launching frame. The feeding mechanism is movably connected to the rear end of the feeding and launching frame, the launching mechanism is fixed to the front end of the feeding and launching mechanism, and the directional stabilizing mechanism is located in the middle of the launching frame. The feeding mechanism includes a feeding motor, a feeding screw coupling, a feeding head fixing component, a feeding tail fixing component, an upper hinge plate, a lower hinge plate, a feeding push plate, a loading screw, and a feeding screw nut. The feeding head fixing component is fixed to the upper end of the feeding and launching frame. The output shaft of the feeding motor is fixedly connected to one end of the feeding screw coupling, and the other end of the feeding screw coupling... One end of the feeding screw is fixedly connected to the feeding screw, and the other end of the feeding screw passes through the feeding head fixing part and is connected to the feeding tail fixing part. Both the feeding head fixing part and the feeding tail fixing part are equipped with bearings, and the feeding screw rotates within the bearings. The middle part of the feeding screw also passes through the feeding push plate, and the feeding push plate is equipped with a feeding screw nut. The feeding screw and the feeding screw nut are movably connected. The feeding push plate is fixedly connected to an upper hinge plate, and the other end of the upper hinge plate is movably connected to a lower hinge plate. A lower feeding plate is fixed to the front side of the lower hinge plate. The lower feeding plate is aligned with the feeding alignment and launching channel. The end of the launching channel near the launching mechanism is the launching port, and the end of the launching channel near the feeding mechanism is the feeding port.

2. The small aircraft transmitter according to claim 1, characterized in that: A loading optical shaft is also provided on one side of the loading screw. One end of the loading optical shaft passes through the feeding head fixing component, the other end passes through the feeding tail fixing component, and the middle part passes through the feeding push plate. The loading optical shaft is connected to both the feeding head fixing component and the feeding tail fixing component through a fixing ring. The loading optical shaft is connected to the feeding push plate through a bearing.

3. A small aircraft transmitter according to claim 1, characterized in that: The launching mechanism includes a friction wheel and an acceleration motor. The friction wheel is located on both sides of the launching channel. The acceleration motor is fixed inside the launch frame by an acceleration motor mounting bracket. The friction wheel is fixedly connected to the output shaft of the acceleration motor. The acceleration motor mounting bracket includes an upper mounting plate, a lower mounting plate, and a side mounting plate. The side mounting plate is arranged perpendicular to the length direction of the launch frame. The side mounting plate has locking interfaces on both sides. The upper and lower mounting plates have locking protrusions at both ends along the length direction of the launch frame that match the locking interfaces. The upper mounting plate and the side mounting plate are detachably connected to the locking interfaces through the locking protrusions. The lower mounting plate and the side mounting plate are detachably connected to each other through the locking protrusions. The side mounting plate has a support groove in the middle.

4. A small aircraft transmitter according to claim 1, characterized in that: The base rotation adjustment module includes a base, a frustum turntable, a rotation adjustment motor, a motor mounting plate, a drive gear, and a rack plate. The frustum turntable is rotatably connected to the base. The rotation adjustment motor and the frustum turntable are fixedly connected via the motor mounting plate. The lower end of one side of the motor mounting plate is fixedly connected to the upper end of the frustum turntable. The rotation adjustment motor is fixed to the upper surface of the motor mounting plate. The output shaft of the rotation adjustment motor passes through the motor mounting plate and is fixedly connected to the drive gear. The rack plate is fixed to the lower end of the base. The drive gear meshes with the rack. The rotation adjustment motor drives the drive gear to rotate and meshes with the rack plate. Since the rack plate is fixed to the base and the rotation adjustment motor is fixed to the motor mounting plate, the meshing of the drive gear and the rack plate drives the frustum turntable to rotate on the base.

5. A small aircraft transmitter according to claim 1, characterized in that: The height adjustment module includes a height adjustment motor, a height adjustment lead screw, a height adjustment lead screw coupling, a lead screw seat, an adjustment lead screw nut, a lead screw nut seat, a linear guide, a linear guide slider, a linkage fixing plate, support rods, and a support frame. The lower end of the support frame is fixedly connected to the upper end of the frustum turntable. The linkage fixing plate is slidably mounted on the front end of the support frame. Support rods are provided on both sides of the upper end of the linkage fixing plate. The lower ends of the support rods are movably connected to the linkage fixing plate, and the upper ends of the support rods are movably connected to the lower front end of the transmitter frame. The rear end of the support frame is movably connected to the lower rear end of the transmitter frame. The height adjustment motor is located in the middle of the support frame and is fixedly connected to the middle of the upper end of the height motor fixing plate. The two sides of the upper end of the height motor fixing plate are fixedly connected to the lower ends of both sides of the support frame. The output end of the height adjustment motor is connected to one end of the height adjustment lead screw coupling. The system comprises a height-adjusting screw coupling, with one end connected to a height-adjusting screw. The other end of the height-adjusting screw is movably connected to a bearing within a screw seat. The screw seat is fixed to a support frame. The middle of the height-adjusting screw passes through a screw nut seat at the lower end of a linkage fixing plate. An adjusting screw nut is located within the screw nut seat, and the height-adjusting screw is movably connected to the adjusting screw nut. Linear rails are provided on both sides of the support frame. Linear rail sliders are provided on both sides of the lower end of the linkage fixing plate. The lower end of the linear rail sliders has a groove corresponding to the linear rail. The output direction of the height-adjusting motor is the same as the length direction of the linear rail. Pulley fixing plates are also provided at both the front and rear ends of the support frame. Pulley fixing plates have pulleys on them. Arc guide rails corresponding to the pulleys are provided on the base. A shock-absorbing plate is provided between the arc guide rails and the pulley fixing plates for support.

6. A small aircraft transmitter according to claim 1, characterized in that: The directional stabilization mechanism includes side limiting plates, side limiting brackets, an upper guide rail, and a lower guide rail. The side limiting plates are vertically spaced and fixed on both sides of the launch channel, extending from the feed inlet of launch channel 5 to the middle of the launch channel. The side limiting plates are fixed together by limiting fixing plates. The limiting fixing plates are L-shaped plates, with two or more limiting protrusions at one end. The limiting protrusions engage with the limiting grooves on the side limiting plates. The side limiting plates near the feed inlet are inclined outwards. The side limiting bracket is fixed to both sides of the launch channel, connected to the side limiting plate, and extends to one end of the launch mechanism. The upper guide rail is fixed to the upper side of the launch channel, one side of the upper guide rail is fixed to the lower end of the feeding tail fixing component, and the other side of the upper guide rail is fixed to one end of the launch port. The lower guide rail is fixed to the lower side of the launch channel, one end of the lower guide rail is fixed to one end of the feeding port, and the other end of the lower guide rail is fixed to one end of the launch port. The side limiting plate, side limiting bracket, upper guide rail, and lower guide rail are in close contact with the fuselage of the aircraft.

7. A small aircraft transmitter according to claim 1, characterized in that: The feeding launcher frame has two or more microswitches spaced apart on one side. The feeding pusher plate has a microswitch trigger on the side near the microswitch. The interval length of the microswitches is the same as the length of the aircraft. Each time the feeding pusher plate pushes an aircraft forward, the microswitch trigger touches a microswitch.

8. A small aircraft transmitter according to claim 1, characterized in that: The feeding transmitter frame is also equipped with an infrared aiming device, which is located at the upper end of the emission port and is used to emit infrared laser light to illuminate the direction of the emission port.

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