CN115634445A - Small aircraft transmitter - Google Patents

Abstract

The invention provides a small aircraft transmitter, which comprises a base rotation adjusting module, a feeding transmitting module and a height adjusting module, wherein the feeding transmitting module is positioned at the upper part of the height adjusting module; the feeding emission module comprises a feeding emission rack, an emission mechanism, a feeding mechanism and a direction stabilizing mechanism; the launching mechanism, the feeding mechanism and the direction stabilizing mechanism are all fixed on the launching rack, the feeding mechanism is movably connected to the rear end of the feeding launching rack, and the launching mechanism is fixed at the front end of the feeding launching mechanism; the direction stabilizing mechanism is positioned in the middle of the launcher frame. The invention has fast direction adjustment and high emission efficiency.

Description

Small aircraft transmitter

Technical Field

The invention belongs to the field of robots, and particularly relates to a small aircraft transmitter.

Background

The dart is a kind of small-sized typing device, which is more and more popular as a kind of entertainment mode of people, and with the development of automation equipment, a user can play entertainment by using a transmitter of a small aircraft instead of the user to manually launch the dart, and the small aircraft transmitter needs to launch the dart to hit only half of an armor plate with the size of A4 paper outside 16 meters and 20 meters, so as to realize the hitting capability of a building with long distance and high injury. The small aircraft launcher needs to throw objects such as badminton, tennis, table tennis and the like out.

The utility model relates to a dart launching robot, which comprises a frame, wherein a launching part is arranged on the frame, the launching part comprises a launching frame, a launching seat is arranged on the launching frame through a slide rail, and an elastic part is arranged between the launching seat and the launching frame; the launching frame is provided with a moving assembly, and the moving assembly can be used for driving the launching seat to move along the sliding rail; and a material supplementing part is arranged right above the launching rack, the material supplementing part comprises a material placing plate, a cylinder is arranged on the material placing plate, and the projections of the cylinder and the sliding rail on the same horizontal plane are overlapped.

But the utility model discloses a feed supplement process pushes the transmission seat with the dartlike weapon through the cylinder, the transmission seat with put the difference in height between the flitch, very easily take place the dartlike weapon at the feed supplement in-process and drop, and the alignment accuracy is lower between feed supplement process dartlike weapon and the transmission seat, every feed supplement all needs the third motor to be close to as early as possible with the adjustable shelf lifting and puts the flitch and push the transmission seat with the dartlike weapon again from putting the flitch, readjust transmission direction again, the direction adjustment is slower, the emission efficiency is low.

Disclosure of Invention

The invention aims to provide a small aircraft transmitter which is fast in direction adjustment and high in transmitting efficiency.

In order to achieve the purpose, the small aircraft transmitter comprises a base rotation adjusting module, a feeding transmitting module and a height adjusting module, wherein the feeding transmitting module is positioned at the upper part of the height adjusting module, the height adjusting module is fixed on the base rotation adjusting module, and a transmitting channel is arranged in the feeding transmitting module; the feeding emission module comprises a feeding emission rack, an emission mechanism, a feeding mechanism and a direction stabilizing mechanism; the launching mechanism, the feeding mechanism and the direction stabilizing mechanism are all fixed on the launching rack, the feeding mechanism is movably connected to the rear end of the feeding launching rack and used for storing aircrafts and enabling the aircrafts to be launched to be in contact with the launching mechanism so as to be launched, the launching mechanism is fixed at the front end of the feeding launching mechanism, and the direction stabilizing mechanism is located in the middle of the launching rack; as shown in the figures, the feeding mechanism comprises a feeding motor, a feeding lead screw coupler, a feeding head part fixing part, a feeding tail part fixing part, an upper hinge plate, a feeding lower hinge plate, a feeding push plate, a filling lead screw and a feeding lead screw nut, wherein the feeding head part fixing part is fixed at the upper end of a feeding emission stand, an output shaft of the feeding motor is fixedly connected with one end of the feeding lead screw coupler, the other end of the feeding lead screw coupler is fixedly connected with the filling lead screw, the other end of the filling lead screw penetrates through the feeding head part fixing part to be connected with the feeding tail part fixing part, bearings are arranged in the feeding head part fixing part and the feeding tail part fixing part, the filling lead screw is positioned in the bearings for rotation, the middle part of the filling lead screw penetrates through the feeding push plate, a feeding lead screw nut is arranged in the feeding push plate, and the filling lead screw is movably connected with the feeding lead screw nut; the feeding push plate is fixedly connected with an upper hinge plate, the other end of the upper hinge plate is movably connected with a lower hinge plate, a feeding lower plate is fixed on the front side of the lower hinge plate and is aligned to a transmitting channel, one end, close to the transmitting mechanism, of the transmitting channel is a transmitting opening, and the end, close to the feeding mechanism, of the transmitting channel is a feeding opening.

According to the arrangement, when the aircraft is ready to be launched, the aircraft is stored at the rear end of a launching channel in a feeding launching module, a feeding mechanism in the feeding launching module is used for storing the aircraft and enabling the aircraft to be launched to be in contact with the launching mechanism so as to launch the aircraft, and a direction stabilizing mechanism is arranged in the middle of the launching mechanism and used for adjusting the feeding direction and the launching direction of the aircraft, so that a plurality of aircraft can be stored in the feeding mechanism and launched by the launching mechanism, the whole material supplementing accuracy is high, the next aircraft can be immediately pushed to the launching mechanism to be launched after the last aircraft is launched, the material supplementing speed is high, the output end of a feeding motor with high launching efficiency rotates to drive a feeding screw rod coupler to rotate, a loading screw rod is driven to rotate by the feeding screw rod coupler, inertia for damping and eliminating radial force is provided, a screw rod nut transmission is formed by the loading screw rod and a feeding screw rod nut in a feeding push plate, the loading rotation drives the feeding screw rod nut to move along the loading axial direction, and further drives the feeding push plate to move along the loading screw rod axial direction; during the aircraft feed, the feed motor drives and loads the lead screw and rotate, loads the lead screw and rotates and drive the feed push pedal and remove toward the firing mechanism direction, and the feed push pedal drives the feed hypoplastron of lower extreme and promotes the aircraft and remove toward the firing mechanism direction along the firing channel, and the feed process butt joint accuracy is high.

Further, it loads the optical axis still to be equipped with on lead screw one side and loads the optical axis, load optical axis one end and run through feed prelude mounting, the other end runs through feed afterbody mounting, and the middle part runs through the feed push pedal, loads the optical axis and all is connected through solid fixed ring with feed prelude mounting and feed afterbody mounting, loads the optical axis and passes through the bearing with the feed push pedal and be connected.

The above setting, the removal that is located the filling optical axis that loads lead screw one side and is the feed push pedal increases stability, the optical axis one end that loads that is located filling lead screw one side runs through feed prelude mounting, the other end runs through feed afterbody mounting, the feed push pedal is run through at the middle part, it all passes through solid fixed ring swing joint with feed prelude mounting and feed afterbody mounting to load the optical axis, it passes through the bearing with the feed push pedal to be connected to load the optical axis, improve feed stability.

Further, launching mechanism includes two pairs of friction pulleys and corresponds and sets up the accelerating motor, the transmission passageway both sides are located to the friction pulley, the accelerating motor is fixed in the launching frame through the accelerating motor mount, the output shaft fixed connection of friction pulley and accelerating motor, the accelerating motor mount includes upper fixed plate, bottom plate and side fixed plate, side fixed plate perpendicular to launching frame length direction sets up, both sides are equipped with the joint mouth on the side fixed plate, upper fixed plate and bottom plate are equipped with along launching frame length direction both ends and match the joint lug that sets up with the joint mouth, upper fixed plate and side fixed plate pass through the joint lug and can dismantle with the joint mouth and be connected, bottom plate and side fixed plate pass through the lug joint and can dismantle with the joint mouth and be connected, the side fixed plate middle part is equipped with the support recess.

According to the arrangement, the friction wheels are respectively driven by independent accelerating motors, the accelerating motors are fixed on two sides of a launching channel in the launching rack, the friction wheels are fixedly connected with output shafts of the accelerating motors, after the friction wheels are accelerated to a specified rotating speed by the accelerating motors, the aircraft to be launched is pushed into the launching mechanism by the feeding push plate, two sides of the aircraft rub against the friction wheels, the aircraft is accelerated and launched out under the action of the friction wheels, and the two oppositely arranged friction wheels accelerate the aircraft; upper fixed plate and bottom plate are respectively through joint lug and joint mouth and side fixing plate fixed connection, and the convenience will increase and reduce required accelerating motor and friction pulley to the transmission speed that the adjustment aircraft goes out from the transmission mouth.

Further, the base rotation regulation module includes base, round platform carousel, rotation regulation motor, motor fixing plate, driving gear and rack plate, the round platform carousel rotates to be connected on the base, rotation regulation motor and round platform carousel pass through motor fixing plate fixed connection, motor fixing plate lower extreme and round platform carousel upper end fixed connection, rotation regulation motor is fixed in motor fixing plate up end, the output shaft of rotation regulation motor runs through motor fixing plate fixedly connected with driving gear, the rack plate is fixed in the base lower extreme, the driving gear is connected with rack plate meshing, and rotation regulation motor drives the driving gear and rotates and with rack plate meshing, because rack plate fixes on the base, rotation regulation motor fixes on the motor fixing plate to the driving gear drives and rotates on the base with the round platform carousel with rack plate meshing.

The rotary adjusting motor is arranged on the base, the output end of the rotary adjusting motor rotates to drive the driving gear to rotate, the driving gear is meshed with the rack plate and is moved along the arc direction of the rack plate, meanwhile, the driving gear moves to drive the rotary adjusting motor to move, meanwhile, the rotary adjusting motor drives the motor fixing plate fixedly connected with the rotary adjusting motor to rotate, meanwhile, the rotary adjusting motor and the motor fixing plate fixedly connected with the rotary adjusting motor rotate on the base along the circumferential direction of the circular table turntable, and the rotary structure is simple and reliable.

Furthermore, the height adjusting module comprises a height adjusting motor, a height adjusting screw rod coupler, a screw rod seat, an adjusting screw rod nut, a screw rod nut seat, a linear rail sliding block, a linkage fixing plate, a supporting rod and a supporting frame, wherein the lower end of the supporting frame is fixedly connected with the upper end of the circular truncated cone turntable, the linkage fixing plate is arranged at the front end of the supporting frame in a sliding manner, the supporting rods are arranged on two sides of the upper end of the linkage fixing plate, the lower ends of the supporting rods are rotatably connected with the linkage fixing plate, the upper ends of the supporting rods are rotatably connected with the lower end of the front part of the launcher frame, and the rear part of the supporting frame is rotatably connected with the lower end of the rear part of the launcher frame; the height adjusting motor is arranged in the middle of the support frame and fixedly connected with the middle of the upper end of the height motor fixing plate, two sides of the upper end of the height motor fixing plate are fixedly connected with the lower ends of two sides of the support frame, the output end of the height adjusting motor is connected with one end of a height adjusting lead screw coupler, the other end of the height adjusting lead screw coupler is connected with a height adjusting lead screw, the other end of the height adjusting lead screw is movably connected with a bearing in a lead screw seat, the lead screw seat is fixed on the support frame, the middle of the height adjusting lead screw penetrates through a lead screw nut seat at the lower end of the linkage fixing plate, an adjusting lead screw nut is arranged in the lead screw nut seat, and the height adjusting lead screw is movably connected with the adjusting lead screw nut; the two sides of the support frame are provided with linear rails, the two sides of the lower end of the linkage fixing plate are provided with linear rail sliders, and the lower ends of the linear rail sliders are provided with sliding chutes which are arranged corresponding to the linear rails; the direction of the output end of the height adjusting motor is the same as the length direction of the linear rail; the support frame is characterized in that pulley fixing plates are further arranged at the front end and the rear end of the support frame, pulleys are arranged on the pulley fixing plates, arc guide rails corresponding to the pulleys are arranged on the base, and damping plates are arranged between the arc guide rails and the pulley fixing plates and used as supports.

According to the arrangement, when the launching height is adjusted, the output end of the height adjusting motor is driven to rotate to drive the height adjusting screw rod coupler to rotate, the height adjusting screw rod coupler drives the height adjusting screw rod to rotate, the height adjusting screw rod and the adjusting screw rod nut form screw rod nut transmission, the adjusting screw rod nut axially moves along the height adjusting screw rod nut, so that the linkage fixing plate on the screw rod nut seat is driven to move along the length direction of the linear rail, the supporting rod on the linkage fixing plate is driven to move when the linkage fixing plate moves, the front part of the launching rack is driven to move when the supporting rod moves, and the rear part of the launching rack is movably connected with the rear part of the supporting frame, so that the height of the front part of the launching rack is changed under the condition that the rear part of the launching rack is movably connected, the launching height is adjusted, and the height adjusting mode is simple and reliable; the bull's eye wheel that lies in both ends around the support frame during rotation slides along the circular arc guide rail on the base, and the bull's eye wheel at both ends can provide sufficient holding power for the support frame around the support frame, and the shock attenuation board can produce deformation when the pulley rotates and when the aircraft launches and can provide a pretightning force for offsetting recoil when launching and pressure when rotating.

Further, the direction stabilizing mechanism comprises side limiting plates, side limiting supports, an upper guide rail and a lower guide rail, wherein the side limiting plates are vertically arranged at intervals and fixed on two sides of the launching channel and extend to the middle of the launching channel from a feeding port of the launching channel, the side limiting plates are fixed through limiting fixing plates, the limiting fixing plates are L-shaped plates, more than four limiting lugs are arranged at one end of each limiting fixing plate and are clamped and fixed with limiting grooves in the side limiting plates, one side, close to the feeding port, of each side limiting plate is obliquely arranged at the end part, the side limiting supports are fixed on two sides of the launching channel, connected with the side limiting plates and extend to one end of the launching mechanism, the upper guide rail is fixed on the upper side of the launching channel, one side of the upper guide rail is fixed at the lower end of the tail fixing part of the feeding device, the other side of the upper guide rail is fixed at one end of the launching port, the lower guide rail is fixed at the lower side of the launching channel, one end of the lower guide rail is fixed at one end of the feeding port, and the other end of the lower guide rail is fixed at one end of the launching port; the side limiting plate, the side limiting support, the upper guide rail and the lower guide rail are attached to the body of the aircraft.

According to the arrangement, the side limiting plate, the side limiting bracket, the upper guide rail and the lower guide rail are attached to the body of the aircraft, so that the launching direction can be stabilized; side limiting plate, side limiting bracket, the smooth friction that reduces in surface of upper guideway and lower rail, side limiting plate is close to feed inlet one side and leans out the setting for the tip through making feed inlet direction opening great, thereby make things convenient for the feeding, and lead through the lower rail after the feeding is accomplished, one end near the transmission mouth sets up the upper guideway, it is spacing to get into the transmission mouth to the aircraft from the upper and lower direction of transmission passageway to go up guide rail and lower rail, can make the aircraft can enter into the transmission mouth better more reliably.

Furthermore, be equipped with the micro-gap switch that two above intervals set up on feed launcher frame one side, be equipped with micro-gap switch trigger piece on one side that the feed push pedal is close to micro-gap switch, micro-gap switch interval length is the same with aircraft length, and every aircraft that promotes of feed push pedal is forward, micro-gap trigger piece touching micro-gap switch.

Above setting, when the feed push pedal promoted the aircraft and carries out the feed to launching mechanism, every aircraft of propelling movement gets into launching mechanism, the feed push pedal is close to micro-gap switch spare and micro-gap switch contact on one side of micro-gap switch, during micro-gap switch connects the accelerating motor who sends start signal to launching mechanism, accelerating motor starts to accelerate the friction pulley to treat the aircraft of transmission and carry out the transmission operation, trigger formula switch realizes automatic feeding and automatic transmission.

Further, still be equipped with infrared sight on the feed emission frame, infrared sight locates the transmission mouth upper end, and the transmission infrared laser is used for shining the transmission mouth direction of transmission mouth.

By the arrangement, the emission direction of the emission port can be adjusted to be judged together with the infrared laser emitted by the infrared sighting device, so that whether the emission is aligned with the emission site or not can be conveniently observed, and the target can be hit remotely.

The structure is characterized in that when the aircraft is ready to be launched, the aircraft is stored at the rear end of a launching channel in a feeding launching module, side limiting plates and side limiting supports are arranged on two sides of a feeding mechanism of the launching channel and are used for being attached to the aircraft to limit the feeding direction, upper guide rails and lower guide rails are arranged on the upper side and the lower side of a launching channel transmitter mechanism and are used for being attached to the aircraft and limiting the launching direction, an output end of a rotary adjusting motor in a base rotary adjusting module rotates to drive a driving gear to rotate, the driving gear is meshed with a rack plate and moves along the arc direction of the rack plate, the driving gear moves to drive the rotary adjusting motor to move, a motor fixing plate fixedly connected with the rotary adjusting motor and a round table rotary table rotate on a base along the circumferential direction of the round table rotary table, a height adjusting motor in the height adjusting module drives an output end to rotate to drive a height adjusting screw rod coupler to rotate, the height adjusting screw rod coupler drives a height adjusting screw rod to rotate, the height adjusting screw rod coupler to form screw nut transmission, the screw nut moves axially along the height adjusting screw rod nut, the height adjusting nut, the fixed plate on the rear end of a launching channel is driven by a feeding rod coupler, and the feeding motor, and the rear end of a movable feeding adjusting screw rod coupler, and the rear end of a feeding mechanism is connected with the feeding mechanism, and is driven by the feeding mechanism, load the lead screw and rotate and drive feed screw-nut along loading lead screw axial displacement, load the lead screw and rotate and drive the feed push pedal and remove toward the launching mechanism direction, the removal that is located the loading optical axis that loads lead screw one side for the feed push pedal simultaneously increases stability, the feed hypoplastron that the feed push pedal drove the lower extreme promotes the aircraft and removes toward the launching mechanism direction along launching channel, the friction pulley is after appointed rotational speed is accelerated to the accelerating motor among the launching mechanism, the aircraft that the feed push pedal will wait to launch is pushed to the launching mechanism in, the aircraft both sides and friction pulley friction, the aircraft is accelerated and launched under the effect of friction pulley, whole feed supplement is fast, last aircraft is launched and can be launched next aircraft propelling movement to the launching mechanism at once, the emission efficiency is high.

Drawings

Fig. 1 is a schematic structural diagram of a small aircraft transmitter according to the present invention.

Fig. 2 is an exploded view of a feed launch module with an aircraft in accordance with the present invention.

Fig. 3 is an exploded view of the feeding mechanism of the present invention.

Fig. 4 is a schematic structural view of a base rotation adjusting module according to the present invention.

Fig. 5 is an exploded view of the base rotation adjustment module of the present invention.

Fig. 6 is a schematic structural view of the height adjustment module of the present invention.

Fig. 7 is an exploded view of the height adjustment module of the present invention.

FIG. 8 is a schematic view of the base of the present invention after rotation.

Fig. 9 is a schematic structural diagram of the present invention after height adjustment.

Fig. 10 is a schematic structural view of the connection of a side limiting plate, a side limiting bracket, a side fixing plate, an upper guide rail, a lower guide rail, a friction wheel, an accelerating motor and a motor fixing frame in the invention.

Fig. 11 is a schematic structural view of a friction wheel, an acceleration motor and a motor fixing frame in the present invention.

Fig. 12 is an exploded view of the friction wheel, the acceleration motor and the motor holder according to the present invention.

Fig. 13 is a front view of the side fixing plate of the present invention.

Fig. 14 is a front view of the position limiting fixing plate of the present invention.

Detailed Description

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

As shown in fig. 1-14, a small aircraft transmitter is used for transmitting a small aircraft 1, and comprises a base rotation adjusting module 2, a feeding transmitting module 3 and a height adjusting module 4, wherein the feeding transmitting module 3 is positioned at the upper part of the height adjusting module 4, the height adjusting module 4 is fixed on the base rotation adjusting module 2, and a transmitting channel 5 is arranged in the feeding transmitting module 3; the feeding emission module 3 comprises a feeding emission rack 31, an emission mechanism 32, a feeding mechanism 33 and a direction stabilizing mechanism 34; launching mechanism 32, feeding mechanism 33 and direction stabilizing mean 34 are all fixed on launcher 31, feeding mechanism 33 swing joint is in feeding launcher 31 rear end for deposit aircraft 1 and make aircraft 1 and launching mechanism 32 contact and launch waiting to launch, launching mechanism 32 is fixed in feeding launching mechanism 31 front end, direction stabilizing mean 34 is located launcher 32 middle part.

As shown in fig. 2 and fig. 3, the feeding mechanism 33 includes a feeding motor 331, a feeding screw coupler 332, a feeding head fixing part 333, a feeding tail fixing part 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 part 333 is fixed at the upper end of the feeding launcher 31, an output shaft of the feeding motor 331 is fixedly connected with one end of the feeding screw coupler 332, the other end of the feeding screw coupler 332 is fixedly connected with the loading screw 338, the other end of the loading screw 338 passes through the feeding head fixing part 333 and is connected with the feeding tail fixing part 334, bearings are arranged in the feeding head fixing part 333 and the feeding tail fixing part 334, the loading screw 338 is positioned in the bearings for rotation, the middle part of the loading screw 338 further passes through the feeding push plate 337, a feeding screw 339 is arranged in the feeding push plate 337, and the loading screw 338 is movably connected with the feeding screw nut 339; the feeding push plate 337 is fixedly connected with an upper hinge plate 335, the other end of the upper hinge plate 335 is movably connected with a lower hinge plate 336, a feeding lower plate 330 is fixed on the front side of the lower hinge plate 336, and the feeding lower plate 330 extends into the launching channel 5.

In the above arrangement, when ready to launch, a plurality of aircrafts 1 are stored at the rear end of the launching channel 5 in the feed launching module 3 at intervals, the feed mechanism 33 in the feed launching module 3 is used for storing the aircrafts 1 and enabling the aircrafts 1 to be launched to contact with the launching mechanism 32 so as to launch the aircrafts 1, the direction stabilizing mechanism 34 is arranged in the middle of the launching mechanism 32 and is used for adjusting the feed direction and the launching direction of the aircrafts 1, therefore, a plurality of aircrafts 1 can be stored in the feed mechanism 33 and wait for the launching mechanism 32 to launch the aircrafts, the overall material supplementing accuracy is high, the next aircraft 1 can be pushed to the launching mechanism 32 immediately after the last aircraft 1 is launched, the output end of the feed motor 331 with high material supplementing speed and launching efficiency rotates to drive the feed screw coupler 332 to rotate, the loading screw 338 is driven by the feed screw coupler 332 to rotate, inertia for damping and eliminating radial force is provided, the loading screw and forms screw nut transmission with the feed screw nut 339 in the feed pushing plate 337, the loading screw 338 rotates to drive the feed screw nut 339 to move axially along the feed screw 338, thereby driving the pushing plate 337 to move axially along the loading screw 338; during the aircraft 1 feed, feed motor 331 drives and loads lead screw 338 and rotates, loads lead screw 338 and rotates and drive feed push plate 337 and remove toward launching mechanism 32 direction, and feed push plate 337 drives the feed hypoplastron 330 of lower extreme and promotes aircraft 1 and remove toward launching mechanism 32 direction along firing channel 5, and the feeding process butt joint accuracy is high.

As shown in fig. 2 and 3, a loading optical axis 351 is further disposed on one side of the loading screw 338, one end of the loading optical axis 351 penetrates through the feeding head fixing member 333, the other end of the loading optical axis 351 penetrates through the feeding tail fixing member 334, the middle part of the loading optical axis passes through the feeding push plate 337, the loading optical axis 351 is movably connected with the feeding head fixing member 333 and the feeding tail fixing member 334 through a fixing ring 352, and the loading optical axis 351 is connected with the feeding push plate 337 through a bearing.

Above setting, be located the removal that loads optical axis 351 on one side of loading lead screw 338 increases stability for the feed push pedal, be located the optical axis 351 one end that loads lead screw 338 one side and run through feed leader mounting 333, the other end runs through feed tail mounting 334, the middle part runs through feed push pedal 337, load optical axis 351 and feed leader mounting 333 and feed tail mounting 334 all through solid fixed ring 352 swing joint, it passes through the bearing with feed push pedal 337 to be connected to load optical axis 351, thereby it leads to make and load lead screw 337 and drive feed push pedal 337 and move through setting up the one side that loads lead screw 337, improve feed stability.

As shown in fig. 2, 11 and 12, in this embodiment, the launching mechanism 32 includes two pairs of friction wheels 321 and an acceleration motor 322 correspondingly disposed, the friction wheels 321 are disposed on two sides of the launching channel 5, the acceleration motor 322 is fixed in the launching frame 31 through an acceleration motor fixing frame 323, the friction wheels 321 are fixedly connected to an output shaft of the acceleration motor 322, the acceleration motor fixing frame 323 includes an upper fixing plate 324, a lower fixing plate 325 and side fixing plates 326, the upper fixing plate 324 and the lower fixing plate 325 are respectively connected to upper and lower ends of the side fixing plate 326, in this embodiment, two side fixing plates 326 are disposed on two sides of the upper fixing plate 324 and the lower fixing plate 325 and connected to the upper fixing plate 324 and the lower fixing plate 325 to form a fixing frame, fixedly connected with accelerating motor 322 on upper fixed plate 324, side fixing plate 326 perpendicular to transmitter frame 31 length direction sets up, both sides are equipped with joint interface 3261 on the side fixing plate 326, upper fixed plate 324 and bottom plate 325 are equipped with along transmitter frame 31 length direction both ends and match the joint lug 3262 that sets up with joint interface 3261, upper fixed plate 324 and side fixing plate 3262 pass through joint lug 3262 and joint interface 3261 fixed connection, bottom plate 325 and side fixing plate 326 can dismantle with joint interface 3261 through joint lug 3262 and be connected, side fixing plate 326 middle part is equipped with support recess 3263.

According to the arrangement, the friction wheels 321 are respectively driven by the independent accelerating motors 322, the accelerating motors 322 are fixed on two sides of the launching channel 5 in the launcher 31, the friction wheels 321 are fixedly connected with output shafts of the accelerating motors 322, after the friction wheels 321 are accelerated to a specified rotating speed by the accelerating motors 322, the feeding push plate 337 pushes the aircraft 1 to be launched into the launching mechanism 32, two sides of the aircraft 1 rub against the friction wheels 321, the aircraft 1 is accelerated and launched out under the action of the friction wheels 321, and the two oppositely arranged friction wheels 321 realize acceleration of the aircraft 1; the upper fixing plate 324 and the lower fixing plate 325 are detachably connected with the side fixing plate 3262 through the clamping convex block 3262 and the clamping interface 3261 respectively, so that the number of the required accelerating motors 322 and friction wheels 321 can be increased and reduced conveniently, and the launching speed of the aircraft 1 from the launching port can be adjusted.

As shown in fig. 4 and 5, the base rotation adjusting module 2 includes a base 21, a circular table turntable 22, a rotation adjusting motor 23, a motor fixing plate 28, a driving gear 25 and a rack plate 26, the circular table turntable 22 is rotatably connected to the base 21, the rotation adjusting motor 23 and the circular table turntable 22 are fixedly connected to 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 circular table turntable 22, the rotation adjusting motor 23 is fixed to the upper end face of the motor fixing plate 28, the output shaft of the rotation adjusting motor 23 penetrates through the motor fixing plate 28 and is fixedly connected to the driving gear 25, the rack plate 26 is fixed to the lower end of the base 21, the driving gear 25 is meshed with the rack plate 26, the rotation adjusting motor 23 drives the driving gear 25 to rotate with the rack plate 26, and the rotation adjusting motor 23 is fixed to the base 21 due to the rack plate 26, and the rotation adjusting motor 23 is fixed to the driving gear 25 and the circular table turntable 22 to rotate on the base 21.

Above setting, the output of rotation regulation motor 23 rotates and drives the driving gear 25 and rotate, the driving gear 25 is connected with rack plate 25 meshing, consequently, the driving gear 25 moves along rack plate 25 circular arc direction meshing, and simultaneously, the driving gear 25 moves and drives rotation regulation motor 23 and move, and rotation regulation motor 23 drives the motor fixed plate 28 rotation with rotation regulation motor 23 fixed connection simultaneously, rotate along circular platform carousel 22 circumferencial direction with motor fixed plate 28 fixed connection circular platform carousel 22 on base 21 simultaneously, and revolution mechanic is simple and reliable.

As shown in fig. 13, two parallel convex columns 32631 are further convexly disposed in the middle of the supporting groove 3263, the two convex columns 32631 form a first groove 32632, and second grooves 32633 are formed on two sides of the first groove 32632, so that when the aircraft 1 enters the launch opening, the bottom of the aircraft 1 contacts with the two convex columns 32631 to support the aircraft, and the flying fins on two sides of the aircraft are accommodated by the second groove 32622 to achieve a guiding effect, so that the aircraft smoothly enters the launch opening.

As shown in fig. 6 and 7, the height adjusting module 4 includes a height adjusting motor 41, a height adjusting screw 42, a height adjusting screw coupler 43, a screw seat 44, an adjusting screw nut 45, a screw nut seat 46, a linear rail 47, a linear rail slider 48, a linkage fixing plate 49, a supporting rod 40 and a supporting frame 27, the lower end of the supporting frame 27 is fixedly connected with the upper end of the circular table turntable 22, the linkage fixing plate 49 is slidably disposed at the front end of the supporting frame 27, the supporting rods 40 are disposed on two sides of the upper end of the linkage fixing plate 49, the lower end of the supporting rod 40 is rotatably connected with the linkage fixing plate 49, the upper end of the supporting rod 40 is rotatably connected with the lower end of the front portion of the launcher 31, and the rear portion of the supporting frame 27 is rotatably connected with the lower end of the rear portion of the launcher 31; the height adjusting motor 41 is arranged in the middle of the support frame 27, the height adjusting motor 41 is fixedly connected with the middle of the upper end of the height motor fixing plate 410, two sides of the upper end of the height motor fixing plate 410 are fixedly connected with the lower ends of two sides of the support frame 40, the output end of the height adjusting motor 41 is connected with one end of the height adjusting screw rod coupler 43, the other end of the height adjusting screw rod coupler 43 is connected with the height adjusting screw rod 42, the other end of the height adjusting screw rod 42 is movably connected with a bearing in the screw rod seat 44, the screw rod seat 44 is fixed on the support frame 27, the middle of the height adjusting screw rod 42 penetrates through the screw rod nut seat 46 at the lower end of the linkage fixing plate 49, the adjusting screw rod nut 45 is arranged in the screw rod nut seat 46, and the height adjusting screw rod 42 is movably connected with the adjusting screw rod nut 45; two sides of the supporting frame 27 are provided with linear rails 47, two sides of the lower end of the linkage fixing plate 49 are provided with linear rail sliders 48, and the lower ends of the linear rail sliders 48 are provided with sliding grooves 480 corresponding to the linear rails 47; the direction of the output end of the height adjusting motor 41 is the same as the length direction of the linear rail 47; pulley fixing plates 240 are further arranged at the front end and the rear end of the supporting frame 27, pulleys 24 are arranged on the pulley fixing plates 240, arc guide rails 29 corresponding to the pulleys 24 are arranged on the base 21, and a damping plate 290 is arranged between the arc guide rails 29 and the pulley fixing plates 240 to serve as a support.

In the above arrangement, when the launching height is adjusted, the height adjusting motor 41 drives the output end to rotate to drive the height adjusting screw rod coupling 43 to rotate, the height adjusting screw rod coupling 43 drives the height adjusting screw rod 42 to rotate, the height adjusting screw rod 42 and the adjusting screw rod nut 45 form screw rod nut transmission, and the adjusting screw rod nut 45 axially moves along the height adjusting screw rod 42 nut, so that the linkage fixing plate 49 on the screw rod nut seat 46 is driven to move along the length direction of the linear rail 47, the linkage fixing plate 49 moves to drive the supporting rod 40 on the linkage fixing plate 49 to move, the supporting rod 40 moves to drive the front part of the launcher 31 to move, and the rear part of the launcher 31 is movably connected with the rear part of the supporting frame 27, so that the height of the front part of the launcher 31 is changed under the condition that the rear part of the launcher 31 is movably connected, thereby the launching height is adjusted, and the height adjusting mode is simple and reliable; during rotation, the bull-eye wheels 24 located at the front end and the rear end of the supporting frame 27 slide along the arc guide rails on the base 21, the bull-eye wheels 24 at the front end and the rear end of the supporting frame 27 can provide enough supporting force for the supporting frame 27, and the damping plate 290 can generate deformation during rotation of the pulleys 24 and launching of the aircraft 1 to provide a pretightening force for offsetting recoil during launching and pressure during rotation.

As shown in fig. 10 and 14, the direction stabilizing mechanism 34 includes side position-limiting plates 341, side position-limiting brackets 342, an upper guide rail 343 and a lower guide rail 344, the side position-limiting plates 341 are vertically arranged at intervals and fixed on both sides of the launching channel 5 and extend from the feeding port of the launching channel 5 to the middle of the launching channel 5, the side position-limiting plates 341 are fixed by position-limiting fixing plates 327, the position-limiting fixing plates 327 are L-shaped plates, one end of each position-limiting fixing plate 327 is provided with four or more position-limiting protrusions which are fastened and fixed to position-limiting grooves on the side position-limiting plates 341, one side of each position-limiting plate 341 close to the feeding port is inclined outwards, the side position-limiting brackets 342 are fixed on both sides of the launching channel 5 and connected to the side position-limiting plates 341 and extend to one end of the launching mechanism, the upper guide rail 343 is fixed on the upper side of the launching channel 5, one side of the upper guide rail 343 is fixed on the lower end of the feeding tail fixing member, the other side of the launching port is fixed to one end of the upper guide rail 343, the number of one lower guide rail 344 is two lower guide rails 343, one side of the upper guide rail 343 is fixed between two lower guide rails 343, one side of the launching channel 344, and one end of the lower guide rail 344 is fixed to one end of the lower guide rail 344, and one end of the lower guide rail 344 is fixed to the feeding port 344; the side limitation plates 341, the side limitation brackets 342, the upper guide rail 343 and the lower guide rail 344 are fitted to the fuselage of the aircraft 1.

With the above arrangement, the side limiting plate 341, the side limiting bracket 342, the upper guide rail 343, and the lower guide rail 344 are attached to the body of the aircraft 1, so that the launching direction can be stabilized; side limiting plate 341, side limiting bracket 342, the smooth friction that reduces in surface of upper guideway 343 and lower rail 344, side limiting plate 341 is close to feed inlet one side and leans out the setting for the tip through making feed inlet direction opening great, thereby make things convenient for the feeding, and lead through the lower rail after the feeding is accomplished, set up the upper guideway in the one end that is close to the emission mouth, upper guideway 343 and lower rail 344 get into the emission mouth from the upper and lower direction of launching channel 5 to aircraft 1 and carry on spacingly, can make the aircraft can better enter into the emission mouth more reliably.

As shown in fig. 2, two or more micro switches 311 are disposed on one side of the feed launcher 31 at intervals, a micro switch trigger 312 is disposed on one side of the feed push plate 337 close to the micro switches 311, the interval length of the micro switches 311 is the same as the length of the aircraft 1, and when the feed push plate 337 pushes one aircraft 1 forward, the micro switch trigger 312 touches one micro switch 311.

Above setting, when feed push plate 337 promoted aircraft 1 and supplies launching mechanism 32, every 1 entering launching mechanism 32 of aircraft of propelling movement, feed push plate 337 is close to micro-gap switch 311 on one side of micro-gap switch part 312 and the contact of micro-gap switch 311, micro-gap switch 311 connects during the acceleration motor 322 of sending start signal to launching mechanism 32, acceleration motor starts 322 and accelerates friction pulley 321, thereby treat the aircraft 1 of launching and carry out the transmission operation, trigger formula switch realizes automatic feeding and automatic transmission.

As shown in fig. 2, the feed emission rack 31 is further provided with an infrared sight 310, and the infrared sight 310 is arranged at the upper end of the emission opening and used for emitting infrared laser to irradiate the direction of the emission opening.

With the arrangement, the emission direction of the emission port can be adjusted to be judged with the infrared laser emitted by the infrared sighting device 310, so that whether the emission site is aligned or not can be conveniently observed, and the target can be hit remotely.

With the above structure, when the aircraft 1 is ready to be launched, the aircraft 1 is stored at the rear end of the launching channel 5 in the feeding launching module 3, the two sides of the feeding mechanism 33 of the launching channel 5 are provided with the side limiting plate 341 and the side limiting bracket for being attached to the aircraft 1 to limit the feeding direction, the upper side and the lower side of the launching channel 5 are provided with the upper guide rail 343 and the lower guide rail 344 for being attached to the aircraft 1 and limiting the launching direction, the output end of the rotary adjusting motor 23 in the base rotary adjusting module 2 rotates to drive the driving gear 25 to rotate, the driving gear 25 is engaged with the rack plate 25, the driving gear 25 moves along the arc direction of the rack plate 25, the driving gear 25 moves to drive the rotary adjusting motor 23 to move, and simultaneously drives the motor fixing plate 28 fixedly connected with the rotary adjusting motor 23 and the circular table rotary table 22 to rotate along the circumferential direction of the circular table 22 on the base 21, the height adjusting motor 41 in the height adjusting module 4 drives the output end to rotate to drive the height adjusting screw rod coupling 43 to rotate, the height adjusting screw rod coupling 43 drives the height adjusting screw rod 42 to rotate, the height adjusting screw rod 42 and the adjusting screw rod nut 45 form screw rod nut transmission, the adjusting screw rod nut 45 axially moves along the height adjusting screw rod 42 nut to drive the linkage fixing plate 49 on the screw rod nut seat 46 to move along the length direction of the linear rail 47, the linkage fixing plate 49 can drive the supporting rod 40 on the linkage fixing plate 49 to move when moving, the supporting rod 40 can drive the front part of the launcher 31 to move when moving, and because the rear part of the launcher 31 is movably connected with the rear part of the supporting frame 27, under the condition that the rear pin of the launcher 31 is fixed, the height of the front part of the launcher 31 is changed, thereby the launching height is adjusted, and the direction is quickly adjusted, the output end of a feed motor 331 in the feed emission module 3 rotates to drive a feed screw coupling 332 to rotate, a loading screw 338 is driven to rotate by the feed screw coupling 332, the loading screw 338 rotates to drive a feed screw nut 339 to axially move along the loading screw 338, the loading screw 338 rotates to drive a feed push plate to move towards the direction of the emission mechanism 32, meanwhile, the loading optical axis 351 positioned on one side of the loading screw 338 increases the stability for the movement of the feed push plate, the feed push plate 337 drives a feed lower plate 330 at the lower end to push an aircraft 1 to move towards the direction of the emission mechanism 32 along an emission channel 5, a friction wheel 321 in the emission mechanism 32 is accelerated to a specified rotating speed by an accelerating motor 322, the feed push plate 337 pushes the aircraft 1 to be emitted to the emission mechanism 32, two sides of the aircraft 1 are rubbed with the friction wheel 321, the aircraft 1 is accelerated and emitted under the effect of the friction wheel 321, the overall material supplementing speed is high, the next aircraft 1 can be immediately pushed to the emission mechanism 32 to be emitted after being emitted, and the emission efficiency is high.

Claims (8)

1. A small aircraft transmitter, comprising: the feeding and transmitting device comprises a base rotation adjusting module, a feeding and transmitting module and a height adjusting module, wherein the feeding and transmitting module is positioned at the upper part of the height adjusting module, the height adjusting module is fixed on the base rotation adjusting module, and a transmitting channel is arranged in the feeding and transmitting module;

the feeding emission module comprises a feeding emission rack, an emission mechanism, a feeding mechanism and a direction stabilizing mechanism; the launching mechanism, the feeding mechanism and the direction stabilizing mechanism are all fixed on the launching stand, the feeding mechanism is movably connected to the rear end of the feeding launching stand, the launching mechanism is fixed at the front end of the feeding launching mechanism, and the direction stabilizing mechanism is located in the middle of the launching stand; the feeding mechanism comprises a feeding motor, a feeding lead screw coupler, a feeding head part fixing part, a feeding tail part fixing part, an upper hinge plate, a lower hinge plate, a feeding push plate, a filling lead screw and a feeding lead screw nut, wherein the feeding head part fixing part is fixed at the upper end of a feeding emission stand; the feeding push plate is fixedly connected with an upper hinge plate, the other end of the upper hinge plate is movably connected with a lower hinge plate, a feeding lower plate is fixed on the front side of the lower hinge plate, the feeding lower plate is aligned to a feeding and emission channel, one end, close to the emission mechanism, of the emission channel is an emission opening, and the emission channel extends into a feeding hole of the feeding mechanism.

2. A small aircraft transmitter as claimed in claim 1, wherein: load still to be equipped with on lead screw one side and load the optical axis, load optical axis one end and run through feed prelude mounting, the other end runs through feed afterbody mounting, and the middle part runs through the feed push pedal, loads the optical axis and all is connected through solid fixed ring with feed prelude mounting and feed afterbody mounting, loads the optical axis and passes through the bearing with the feed push pedal and be connected.

3. A small aircraft transmitter as claimed in claim 1, wherein: the launching mechanism comprises a friction wheel and an accelerating motor, the friction wheel is arranged on two sides of a launching channel, the accelerating motor is fixed in a launching frame through an accelerating motor fixing frame, the friction wheel is fixedly connected with an output shaft of the accelerating motor, the accelerating motor fixing frame comprises an upper fixing plate, a lower fixing plate and a side fixing plate, the side fixing plate is perpendicular to the launching frame in length direction, a clamping port is arranged on two sides of the side fixing plate, clamping convex blocks matched with the clamping port are arranged on the upper fixing plate and the lower fixing plate along two ends of the launching frame in length direction, the upper fixing plate and the side fixing plate are detachably connected through the clamping convex blocks and the clamping port, the lower fixing plate and the side fixing plate are detachably connected through the clamping convex blocks and the clamping port, and a supporting groove is arranged in the middle of the side fixing plate.

4. A small aircraft transmitter as defined in claim 1, wherein: the base rotation regulation module comprises a base, a round platform rotary table, a rotation regulation motor, a motor fixing plate, a driving gear and a rack plate, wherein the round platform rotary table is rotatably connected to the base, the rotation regulation motor and the round platform rotary table are fixedly connected with the motor fixing plate, the lower end of one side of the motor fixing plate is fixedly connected with the upper end of the round platform rotary table, the rotation regulation motor is fixed on the upper end face of the motor fixing plate, an output shaft of the rotation regulation motor penetrates through the driving gear fixedly connected with the motor fixing plate, the rack plate is fixed at the lower end of the base, the driving gear is meshed with the rack wheel, the rotation regulation motor drives the driving gear to rotate and is meshed with the rack plate, and the rack plate is fixed on the base, so that the driving gear and the rack plate are meshed to drive and rotate on the base together with the round platform rotary table.

5. A small aircraft transmitter as claimed in claim 1, wherein: the height adjusting module comprises a height adjusting motor, a height adjusting screw rod coupler, a screw rod seat, an adjusting screw rod nut, a screw rod nut seat, a linear rail sliding block, a linkage fixing plate, a supporting rod and a supporting frame, wherein the lower end of the supporting frame is fixedly connected with the upper end of the circular table turntable, the linkage fixing plate is arranged at the front end of the supporting frame in a sliding mode, the supporting rods are arranged on two sides of the upper end of the linkage fixing plate, the lower end of the supporting rod is movably connected with the linkage fixing plate, the upper end of the supporting rod is movably connected with the lower end of the front part of the launching frame, and the rear part of the supporting frame is movably connected with the lower end of the rear part of the launching frame; the height adjusting motor is arranged in the middle of the support frame, the height adjusting motor is fixedly connected with the middle of the upper end of a height motor fixing plate, two sides of the upper end of the height motor fixing plate are fixedly connected with the lower ends of two sides of the support frame, the output end of the height adjusting motor is connected with one end of a height adjusting lead screw coupler, the other end of the height adjusting lead screw coupler is connected with a height adjusting lead screw, the other end of the height adjusting lead screw is movably connected with a bearing in a lead screw seat, the lead screw seat is fixed on the support frame, the middle of the height adjusting lead screw penetrates through a lead screw nut seat at the lower end of a linkage fixing plate, an adjusting lead screw nut is arranged in the lead screw nut seat, and the height adjusting lead screw is movably connected with the adjusting lead screw nut; two sides of the support frame are provided with linear rails, two sides of the lower end of the linkage fixing plate are provided with linear rail sliding blocks, and the lower ends of the linear rail sliding blocks are provided with sliding chutes which are arranged corresponding to the linear rails; the direction of the output end of the height adjusting motor is the same as the length direction of the linear rail; the support frame is characterized in that pulley fixing plates are further arranged at the front end and the rear end of the support frame, pulleys are arranged on the pulley fixing plates, arc guide rails corresponding to the pulleys are arranged on the base, and damping plates are arranged between the arc guide rails and the pulley fixing plates and used as supports.

6. A small aircraft transmitter as claimed in claim 1, wherein: the direction stabilizing mechanism comprises side limiting plates, side limiting supports, an upper guide rail and a lower guide rail, wherein the side limiting plates are vertically arranged at intervals and fixed on two sides of the launching channel and extend to the middle of the launching channel from a feeding port of the launching channel 5, the side limiting plates are fixed by limiting fixing plates, the limiting fixing plates are L-shaped plates, more than two limiting lugs are arranged at one end of each limiting fixing plate and clamped and fixed with limiting grooves in the side limiting plates, one side of each side limiting plate, which is close to the feeding port, is obliquely arranged at the end part, the side limiting supports are fixed on two sides of the launching channel, are connected with the side limiting plates and extend to one end of the launching mechanism, the upper guide rail is fixed on the upper side of the launching channel, one side of the upper guide rail is fixed at the lower end of the feeding tail fixing piece, the other side of the upper guide rail is fixed at one end of the launching port, the lower guide rail is fixed at the lower side of the launching channel, one end of the lower guide rail is fixed at one end of the feeding port, and the other end of the lower guide rail is fixed at one end of the launching port; the side limiting plate, the side limiting support, the upper guide rail and the lower guide rail are attached to the body of the aircraft.

7. A small aircraft transmitter as claimed in claim 1, wherein: the feed launcher is characterized in that two or more microswitches arranged at intervals are arranged on one side of the feed launcher frame, a microswitch trigger is arranged on one side, close to the microswitches, of the feed push plate, the interval length of the microswitches is the same as the length of an aircraft, and the microswitch trigger touches one microswitch when the feed push plate pushes one aircraft forwards.

8. A small aircraft transmitter as claimed in claim 1, wherein: the feeding launcher is characterized in that an infrared sighting device is further arranged on the feeding launcher frame, and the infrared sighting device is arranged at the upper end of the launching port and used for emitting infrared laser to irradiate the direction of the launching port.

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