CN117699007A - Aircraft projectile body mounting and throwing device and aircraft - Google Patents

Abstract

The invention discloses an aircraft elastomer mounting and throwing device and an aircraft, and belongs to the technical field of aircraft equipment; solves the problems of poor mounting stability and low projectile throwing efficiency of the conventional projectile bodies randomly mounted on the aircraft. The device for mounting and throwing the projectile body of the aircraft comprises an aircraft mounting plate, a projectile body throwing telescopic assembly, a throwing pushing assembly and a projectile body mounting assembly; two ends of the throwing telescopic component are respectively and movably connected with one projectile body mounting component through a throwing pushing component; the pushing supporting unit for putting the pushing assembly comprises a pushing rocker arm, and the pushing movable unit for putting the pushing assembly comprises a pushing movable plate and a pushing spring; the elastomer mounting assembly comprises a claw, and a claw ratchet is arranged at the upper end of the claw. The device for mounting and releasing the projectile body of the aircraft realizes automatic locking in the projectile body mounting process, has simple releasing process, improves the projectile body mounting and releasing reliability and the projectile body mounting and releasing efficiency, and has wide applicability.

Description

Aircraft projectile body mounting and throwing device and aircraft

Technical Field

The invention relates to the technical field of aircraft equipment, in particular to an aircraft elastomer mounting and throwing device and an aircraft.

Background

The multi-rotor platform or the small unmanned helicopter platform is widely applied to rescue and relief work and other harsher environments due to the advantages of flexibility, rapid response, accurate positioning, strong environmental adaptability and the like.

Cargo such as a projectile is often needed to be hung when a multi-rotor platform or a small unmanned helicopter platform is used for rescue and other tasks are executed; the application scene generally requires that the aircraft mount and release the projectile body have the stability of the mount projectile body, the accuracy of releasing the projectile body, the high efficiency of releasing and the like.

At present, the elastomer mounting mode used on the aircraft mainly comprises two modes of transverse mounting and vertical mounting. The transverse missile-borne structure is suitable for the working condition that the bottom space is compact compared with the vertical missile-borne structure.

In any of the above-mentioned loading methods, at least the loading of the projectile is performed manually in the loading and delivering device of the prior art. Generally, an operator cooperates with the hanger hook by manipulating the lug structure on the exterior of the projectile body to achieve the loading function of the projectile body. .

The operation of manually directly interfering with the cooperation of the lifting lug structure outside the projectile body and the hanging rack lifting hook inevitably has serious influence on the stability of the projectile body mounting of the aircraft, and the reliability and the throwing efficiency of the projectile body are candled.

Therefore, how to improve the equipment for mounting and throwing the projectile body so as to realize automatic and efficient projectile loading and throwing of the aircraft with high repeatability has great significance.

Disclosure of Invention

In view of the analysis, the invention aims to provide an aircraft projectile body mounting and throwing device and an aircraft, so as to solve the technical problems of poor reliability of mounting projectile bodies on the aircraft and low projectile body throwing efficiency.

The invention adopts the following technical scheme to solve the technical problems:

the device comprises an aircraft mounting plate, a projectile throwing telescopic component, a throwing pushing component and a projectile mounting component; the throwing telescopic assembly and the projectile body mounting assembly are connected below the aircraft mounting plate; two ends of the throwing telescopic component are respectively and movably connected with one elastomer mounting component through one throwing pushing component; the two elastomer mounting assemblies are symmetrically arranged; the throwing telescopic assembly comprises a throwing power unit and a pull rod unit; the throwing pushing assembly comprises a pushing supporting unit and a pushing movable unit; the pushing supporting unit comprises a pushing rocker arm; the pushing movable unit comprises a pushing movable plate and a pushing spring; the elastomer mounting assembly comprises a shimmy damper unit and a claw unit; the swing reducer unit comprises a swing reducing clamping part; the claw unit comprises a claw, a claw ratchet is arranged at the upper end of the claw, and a claw clamping part is arranged at the lower part of the claw.

Further, the throwing power unit comprises a throwing power source and a throwing rotary disk; the pull rod unit comprises a pull rod and a pull rod bearing joint.

Further, the throwing pushing assembly comprises a pushing supporting unit and a pushing movable unit.

Further, the pushing supporting unit comprises a pushing supporting fixed plate, a pushing rocker arm and a pushing rotary pin shaft; the pushing rocker arm comprises a rocker arm input ear and a rocker arm output ear.

Further, the rocker arm input ear articulates the pull rod bearing knuckle of the distal end of the pull rod unit; the rocker arm output lug abuts against the lower end of the pushing movable plate and pushes up the pushing movable unit.

Further, the pushing movable unit comprises a pushing movable plate, a pushing guide body and a pushing spring; the pushing movable plate is provided with a pushing movable plate sliding limiting part.

Further, the elastomer mounting assembly further comprises an upper limit body, a lower limit body and a torsion spring; the jaw unit comprises two symmetrically arranged jaws.

Further, the swing reducer unit comprises a swing reducing main box body and a swing reducing cover plate; the swing-reducing main box body and the swing-reducing cover plate are respectively provided with a limiting groove and form a swing-reducing device limiting groove together; the swing-reducing main box body and the swing-reducing cover plate are respectively provided with a clamping part and form the swing-reducing clamping part together; the swing-reducing main box body is internally provided with a claw rotating shaft.

Further, the clamping jaw is of an arc-shaped plate structure; the clamping jaw further comprises a clamping jaw rotating shaft hole and a clamping jaw contact piece; the lower part of the claw contact piece is provided with the claw clamping part; the jaw rotating shaft hole is mutually matched and connected with the jaw rotating shaft.

An aircraft comprises an aircraft body and an aircraft projectile body mounting and throwing device; the aircraft elastomer mounting and throwing device is arranged at the lower part of the aircraft body.

Compared with the prior art, the invention has at least one of the following beneficial effects:

1. the projectile body mounting component of the projectile body mounting and throwing device is provided with the fixed swing-reducing clamping part and the movable claw clamping part, so that the projectile body can be gradually clamped and finally locked between the two opposite claw clamping parts and the swing-reducing clamping part; the static and dynamic combined clamping structure can greatly improve the reliability of the device for mounting the elastic body.

2. According to the device for mounting and throwing the aircraft projectile body, only the mounting force of the projectile body is needed to be hoisted in the projectile body loading and mounting process; the elastic body can be automatically locked on the device, so that the operation steps are simplified, and the loading efficiency of the elastic body is improved.

3. According to the device for mounting and throwing the aircraft projectile body, disclosed by the invention, the projectile body can be thrown only by the gravity of the projectile body through automatic linkage of the throwing telescopic assembly and the two throwing pushing assemblies in the projectile body throwing process, the throwing process is simple, and the throwing reliability and the throwing efficiency are improved.

4. The device for mounting and throwing the aircraft projectile body has the advantages of simple structure, simple operation steps and wide applicability.

The above technical schemes of the invention can be mutually combined to realize more preferable combination schemes. Additional features and advantages of the invention will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. The objectives and other advantages of the invention may be realized and attained by the structure particularly pointed out in the written description and drawings.

Drawings

In order to further clearly understand the technical means of the present invention, the present invention will be described in detail with reference to the following drawings and detailed description.

The drawings are only for purposes of illustrating particular techniques and are not to be construed as limiting the invention, like reference numerals indicating like parts throughout the drawings.

FIG. 1 is a schematic view of the overall structure of the device of the present invention in a mounted elastomeric state;

FIG. 2 is a partial schematic view of the section taken along the axial direction (A-A) in FIG. 1;

FIG. 3 is a schematic view of the overall structure of the device of the present invention in the jaw closed condition;

FIG. 4 is a schematic view of the overall structure of the launch telescoping assembly of the present invention;

FIG. 5 is a schematic view showing the overall structure of the pushing unit of the present invention;

FIG. 6 is a schematic view of a portion of the pushing unit according to the present invention;

FIG. 7 is a schematic view of a pushing movable unit according to the present invention;

FIG. 8 is a schematic view of a portion of the structure of the elastomeric mounting assembly of the present invention;

FIG. 9 is a schematic view of a pendulum-reducing main box structure of the present invention;

FIG. 10 is a schematic view of the structure of the pawl of the present invention;

FIG. 11 is a schematic view of the overall structure of the device of the present invention in a condition during opening of the projectile body;

FIG. 12 is an axial elevational view of the overall structure of the device of the present invention in a condition of mounting a projectile body;

FIG. 13 is a schematic view of the device of the present invention in a stressed state when it is about to lock a projectile;

FIG. 14 is a schematic view of the device of the present invention in a stressed state when the projectile is launched.

Reference numerals:

1. an aircraft mounting plate;

2. throwing in a telescopic component; 21. throwing in a power unit; 211. throwing in a power source; 212. throwing in a rotating disc; 22. a pull rod unit; 221. a pull rod; 222. a pull rod bearing joint; 23. putting in a telescopic unit;

3. a projectile body mounting assembly; 31. a shimmy damper unit; 311. a swing-reducing main box body; 3111. a swing-reducing main box body limit groove; 3112. a main box body pushing avoidance part; 3113. an upper limit body mounting part; 31131. an upper limit body mounting table; 31132. an upper limit body mounting hole; 3114. a torsion spring mounting portion; 31141. a torsion spring upper limit cavity; 31142. a torsion spring lower limit cavity; 31143. a torsion spring mounting groove; 3115. a lower limit body mounting part; 31151. a lower limit body mounting table; 31152. a lower limit body mounting hole; 3116. a jaw rotation shaft; 3117. a main box clamping part; 312. a swing reducing cover plate; 3121. a swing reducing cover plate limit groove; 3122. a swing reducing cover clamping part; 32. a claw; 321. a claw contact piece; 322. the claw rotates the shaft hole; 323. jaw ratchet; 324. a claw clamping part; 325. a jaw elastic cushion; 33. an upper limit body; 34. a lower limit body; 35. a torsion spring;

4. a throwing pushing component; 41. pushing the supporting unit; 411. pushing the supporting and fixing plate; 4111. pushing the mounting plate part; 4112. a fixing plate abdication part; 4113. pushing the connecting arm part; 41131. pushing and installing a rotary shaft hole; 412. pushing the rocker arm; 4121. a rocker arm input ear; 41211. a rocker arm input connection; 4122. a rocker arm output ear; 41221. the rocker outputs a first pushing surface; 41222. the rocker outputs a second pushing surface; 4123. pushing the rocker arm to rotate the shaft hole; 413. pushing the rotary pin shaft; 42. pushing the movable unit; 421. pushing the movable plate; 4211. pushing the movable plate sliding limit part; 4212. pushing the movable plate guide body mounting hole; 422. pushing the guide body; 423. pushing the compression spring;

100. and (3) an elastomer.

Detailed Description

Preferred embodiments of the present invention will be described in detail below with reference to the attached drawings; wherein; the accompanying drawings form a part of this invention; and together with the description serve to explain the principles of the invention; and are not intended to limit the scope of the invention.

It should be noted that; unless otherwise indicated; technical or scientific terms used herein should be given the ordinary meaning as understood by one of ordinary skill in the art to which this invention belongs.

Definition:

(1) One end close to the center is a near end, and one end far away from the center is a far end;

(2) The axial direction of the projectile 100 is the axial direction of the projectile mounting and throwing device of the aircraft;

(3) The normal direction of the outer end surface of the outer interface board 11 is upward;

(4) The inward direction from the outer peripheral surface of the projectile body 4 is a centripetal direction including not only the direction pointing toward the axis.

The technical solution of the present invention will be described in more detail with reference to fig. 1 to 14.

Example 1

An aircraft projectile body mounting and throwing device.

Embodiment 1 shows an aircraft projectile loading and delivery device for gripping and delivering projectile 100.

As shown in fig. 1, the device for mounting and releasing the elastomer of the aircraft in this embodiment 1 includes an aircraft mounting plate 1, a releasing telescopic assembly 2, a releasing pushing assembly 4 and an elastomer mounting assembly 3. The throwing telescopic assembly 2 and the elastomer mounting assembly 3 are connected to the lower portion of the aircraft mounting plate 1, and two ends of the throwing telescopic assembly 2 are movably connected with the elastomer mounting assembly 3 through the throwing pushing assembly 4 respectively.

Specifically, the putting telescopic assembly 2 is of a symmetrical structure, and two ends of the putting telescopic assembly 2 are respectively connected with the elastomer mounting assembly 3.

Specifically, the two elastomer mount assemblies 3 are arranged under the aircraft mounting plate 1 in a mirror symmetry manner.

As shown in fig. 3 and 4, the launch telescoping assembly 2 includes a launch power unit 21 and a pull rod unit 22. The throwing power unit 21 is connected to the middle part of the aircraft mounting plate 1. The two pull rod units 22 are symmetrically arranged, are connected with the lower end of the throwing power unit 21 at the proximal end, and are respectively connected with one throwing pushing component 4 at the distal end.

As shown in fig. 4, the throwing power unit 21 includes a throwing power source 211 and a throwing rotary disk 212. The pull rod unit 22 comprises a pull rod 221 and a pull rod bearing joint 222; the two ends of the pull rod 221 are respectively connected with one pull rod bearing joint 222.

The throwing power source 211 in this embodiment 1 is a steering engine. The throwing power source 211 is connected to the upper part of the middle part of the aircraft mounting plate 1; the output end of the throwing power source 211 extends downwards out of the aircraft mounting plate 1 and is connected with the throwing rotary disk 212; the proximal ends of the two pull rod units 22 are respectively hinged to the two ends of the diameter of the throwing rotary disk 212 through the pull rod bearing joints 222 at the proximal ends of the pull rod units 22 by ball bearings. The launch power source 211 is capable of rotating the launch rotary 212 in the range of 0 ° -90 ° (0 ° when coincident with the axial position).

The steering engine of the throwing power source 211 is electrically started, and the throwing rotary disk 212 can drive the proximal end of the pull rod unit 22 to rotate within the range of 0-90 degrees, so that the pull rod unit 22 presents an axial expansion and contraction state.

The distal ends of the two pull rod units 22 are respectively movably connected with the throwing pushing component 4 through the pull rod bearing joints 222 positioned at the distal ends.

As shown in fig. 5, the delivery pushing assembly 4 includes a pushing support unit 41 and a pushing movable unit 42.

As shown in fig. 5 and 6, the pushing supporting unit 41 includes a pushing supporting fixing plate 411, a pushing rocker 412 and a pushing rotating pin 413; the pushing support fixing plate 411 and the pushing rocker arm 412 are hinged through the pushing rotary pin shaft 413, and the pushing support fixing plate 411 is a mounting base of the pushing rocker arm 412.

Specifically, the pushing support fixing plate 411 includes a pushing mounting plate portion 4111 and a pushing connecting arm portion 4113. The distal end face of the pushing mounting plate 4111 abuts against the elastomer mount assembly 3 and is fixedly connected to the elastomer mount assembly 3.

The pushing connection arm 4113 has a plate structure, and extends obliquely downward from the pushing mounting plate 4111. The two pushing connection arm portions 4113 are arranged in pairs on two sides of the proximal end face of the pushing mounting plate portion 4111; the pushing connection arm portion 4113 is integrally formed with/fixedly connected to the pushing mounting plate portion 4111.

The integrally formed body of the push mounting plate portion 4111 and the push connecting arm portion 4113 is provided with a fixing plate relief portion 4112 at a distal end lower portion.

The fixing plate abdication portion 4112 is an inclined surface with a fixed angle with the pushing mounting plate portion 4111, and is used for forming an abdication space for swinging of the pushing rocker arm 412.

The distal end of the pushing connection arm portion 4113 is provided with a pushing installation rotation shaft hole 41131; the pushing rotary pin shaft 413 is movably connected in the pushing installation rotary shaft hole 41131, and is used for hinging the pushing support fixing plate 411 and the pushing rocker arm 412.

Specifically, the pushing rocker 412 is formed by two perpendicular ears, the opposite perpendicular structure is a rocker input ear 4121, and the opposite horizontal structure is a rocker output ear 4122; in the portions perpendicular to each other, a pushing rocker arm rotation shaft hole 4123 is provided. The pushing rotating pin shaft 413 is movably connected in the pushing rocker arm rotating shaft hole 4123 while being connected to the pushing installation rotating shaft hole 41131.

As shown in fig. 6, the upper part of both ears of the rocker arm input ear 4121 is provided with a rocker arm input connection portion 41211. Specifically, the rocker arm input connection portion 41211 is a via penetrating through two ears of the rocker arm input ear 4121, and is used for hinging the pull rod to the delivery telescopic assembly 2.

As shown in fig. 2, the throwing pushing component 4 is movably connected with the throwing telescopic component 2 through a rocker arm input pin shaft penetrating through the rocker arm input connecting portion 41211. The rocker arm input pin penetrates through the central hole of the pull rod bearing knuckle 222 at the distal end of the pull rod unit 22 and the rocker arm input connection portion 41211 at the same time.

As shown in fig. 6, both ears of the rocker arm output ear 4122 are used to lift the ejector unit 42. The upper portion of the rocker arm output ear 4122 includes a horizontal rocker arm output first push surface 41221 and a distally downwardly sloping rocker arm output second push surface 41222.

When the device for mounting and releasing the projectile body of the aircraft in this embodiment 1 is in the closed state of the projectile, the output first pushing surface 41221 is in a horizontal position to abut against the pushing movable unit 42.

When the device for mounting and throwing the projectile body of the aircraft in this embodiment 1 is in the open state for throwing the projectile body, the pushing rocker 412 rotates around the pushing rotating pin 413 until the second pushing surface 41222 of the rocker is in a horizontal position; at this time, the second pushing surface 41222 of the rocker arm pushes up against the pushing movable unit 42.

The proximal ends of the two pull rod units 22 can be synchronously rotated from 0 deg. to 90 deg. with a maximum rotation angle not exceeding 90 deg., so as to drive the pushing movable unit 42 to displace upward to release the projectile body 100, and then return to 0 deg.. Corresponding to the pushing rocker 412 rotating around the pushing rotating pin 413 from the horizontal state of the first pushing surface 41221 of the rocker output to the horizontal state of the second pushing surface 41222 of the rocker output, and returning after the projectile 100 is released.

As shown in fig. 5 and 7, the pushing movable unit 42 includes a pushing movable plate 421, a pushing guide 422, and a pushing spring 423.

As shown in fig. 7, the pushing movable plate 421 is provided with a plurality of pushing guide body mounting portions, specifically a pushing movable plate guide body mounting hole 4212 of a via hole, for the pushing guide body 422 to pass through; correspondingly, the installation position for fixedly installing the pushing guide body 422 is arranged on the elastomer mounting assembly 3.

Two pairs of pushing movable plate sliding limiting parts 4211 are symmetrically arranged on the side vertical surfaces of the proximal end and the distal end of the pushing movable plate 421.

Preferably, in this embodiment 1, the pushing guide body 422 includes two pushing guide bodies 422, and correspondingly, the pushing movable plate 421 has at least two mounting holes 4212 for the pushing movable plate guide bodies, and the elastomer mounting assembly 3 has two mounting positions for fixedly mounting the pushing guide bodies 422.

The pushing guide 422 of this embodiment 1 is a threaded bolt with threads on the end of the bolt. The two pushing guide bodies 422 are symmetrically arranged, pass through the pushing movable plate guide body mounting holes 4212 from the lower end of the pushing movable plate 421 and are screwed up to the elastomer mounting assembly 3. The two pushing springs 423 are disposed at the upper part of the pushing movable plate 421, and the pushing movable plate guide body mounting holes 4212 are respectively sleeved on the peripheries of the light cylindrical surfaces of the two pushing guide bodies 422.

Preferably, the pushing spring 423 is a compression spring.

The pushing rocker 412 of this embodiment 1 overcomes the reaction force of the compression spring of the pushing spring 423, and pushes the pushing movable plate 421 to move upwards along the guiding of the optical column surface of the pushing guiding body 422 and the guiding of the elastomer mounting assembly 3 to the sliding limiting portion 4211 of the pushing movable plate; when the pushing rocker arm 412 returns to the original position, the pushing movable plate 421 is displaced downward under the action of the compression spring of the pushing spring 423, and returns to the original position.

As shown in fig. 3 and 8, the elastomer mount assembly 3 includes a shimmy damper unit 31 and a claw unit, and further includes an upper stopper 33, a lower stopper 34, and a torsion spring 35. The clamping and rotating unit comprises two clamping claws 32 which are symmetrically arranged.

The pushing rocker 412 rotates around the pushing rotary pin 413, and can toggle the pushing movable unit 42 to move upwards, so that the pushing movable plate 421 of the pushing movable unit 42 is separated from the jaw unit.

As shown in fig. 3, the shimmy damper unit 31 includes a shimmy damper main case 311 and a shimmy damper cover 312; the appearance boundaries of the swing-reducing main box body 311 and the swing-reducing cover plate 312 are the same, and the swing-reducing main box body 311 and the swing-reducing cover plate 312 are both structures with two symmetrical supporting legs under the cross beam. Wherein, the swing-reducing main box body 311 is in a special-shaped box body structure, and an opening is at the far end; the swing-reducing cover plate 312 is a plate structure. The swing-reducing cover plate 312 is fastened and fixedly connected to the opening side of the swing-reducing main box body 311 from the distal end to the proximal end.

As shown in fig. 9, two main box body guiding and mounting positions, specifically two screw holes, are symmetrically arranged on the upper end surface of the beam of the swing-reducing main box body 311 in the embodiment 1; the pushing guide body 422 is fixedly connected to the guide installation position of the main box body through a threaded portion at the upper end.

Two swing-reducing main box body limiting grooves 3111 are symmetrically formed in the beam of the swing-reducing main box body 311 of the embodiment 1, swing-reducing main box body reinforcing ring grooves are symmetrically formed in two ends of the beam, and torsion spring mounting portions are arranged on the inner sides of the supporting legs of each swing-reducing main box body 311.

As shown in fig. 3 and 9, the swing reducing main box 311 is further provided with an upper stopper mounting portion 3113, a torsion spring mounting portion 3114, a lower stopper mounting portion 3115, a jaw rotation shaft 3116, and a main box clamping portion 3117.

Specifically, the upper limit body mounting portion 3113 is disposed on an inner side wall of the swing-reducing main box body reinforcing ring groove; the lower limit body mounting part 3115 is arranged outside the lower list of the supporting leg of the swing reducing main box body 311; torsion spring mounting portions 3114 are provided on inner side portions of the legs of the sway brace main case 311; the jaw rotation shaft 3116 is provided in the torsion spring mounting 3114; the two main box body clamping parts 3117 are symmetrically arranged at the upper parts of the inner sides of the two supporting legs of the swing reducing main box body 311; the main box body clamping part 3117 is a symmetrical plane centripetally arranged in the normal direction.

Specifically, the upper limiter mounting portion 3113 includes an upper limiter mounting platform 31131, and an upper limiter mounting hole 31132 is provided on the upper limiter mounting platform 31131; the upper limit body 33 is connected to the upper limit body mounting hole 31132. The upper stopper mounting hole 31132 in embodiment 1 is a screw hole, and the upper stopper 33 is a bolt/screw.

Specifically, the lower limiter mounting portion 3115 includes a lower limiter mounting table 31151, and the lower limiter mounting table 31151 is provided with a lower limiter mounting hole 31152; the lower stopper 34 is connected to the lower stopper mounting hole 31152. The lower stopper mounting hole 31152 of the present embodiment 1 is a screw hole, and the lower stopper 34 is a bolt/screw.

In this embodiment 1, the bolts/screws of the upper limit body 33 and the lower limit body 34 are screwed or unscrewed, so that the rotation angle range of the claw 32 can be adjusted, and the claw 32 is prevented from over-stroke rotation to occupy unnecessary working space and damage to the device for mounting and releasing the aircraft elastomer.

As shown in fig. 8 and 9, the torsion spring mounting portion 3114 includes a torsion spring upper limit chamber 31141, a torsion spring lower limit chamber 31142, and a torsion spring mounting slot 31143. The jaw rotation shaft 3116 is concentrically disposed within the torsion spring mounting slot 31143; the torsion spring 35 is sleeved on the jaw rotating shaft 3116, one end of the torsion spring 35 is located in the torsion spring lower limiting cavity 31142, and the other end of the torsion spring 35 is placed in the torsion spring upper limiting cavity 31141 in a limiting mode and is limited on the jaw 32.

In the absence of external forces, the torsion spring 35, which is retained in the torsion spring mounting portion 3114, applies a torsion force to the jaws 32, so that the two jaws 32 of the elastomer mount assembly 3 are always in an open state.

As shown in fig. 3, the swing reducing cover plate 312 is provided with a swing reducing cover plate limiting groove 3121 and a swing reducing cover clamping portion 3122.

Specifically, the two swing reducing cover plate limiting grooves 3121 are symmetrically disposed at the beam of the swing reducing cover plate 312, and correspond to the two swing reducing main box body limiting grooves 3111 in position in the installed state.

The two swing reducing cover clamping parts 3122 are symmetrical inclined planes symmetrically arranged at the upper parts of the inner sides of the two supporting legs of the swing reducing cover plate 312; in the mounted state, the swing reducing cover clamping portion 3122 and the main box clamping portion 3117 are both centripetally disposed in the normal direction.

As shown in fig. 2, 3 and 7, the swing-reducing main box 311 and the swing-reducing cover plate 312 may be combined to form a swing-reducing device supporting box; the swing reducing main box body limit groove 3111 and the swing reducing cover plate limit groove 3121 at corresponding positions together form a swing reducer limit groove of the swing reducer unit 31, and are used for limiting the pushing movable plate sliding limit portion 4211 and guiding the pushing movable plate 421. The swing reducing cover clamping portions 3122, which are centripetally arranged in the normal direction, correspond to the main box clamping portions 3117, and together form a swing reducing clamping portion of the swing reducer unit 31, for clamping the monomers 100 with different diameter specifications.

Because the swing-reducing clamping portion is relatively fixed at the position on the device for mounting and throwing the aircraft elastomer in this embodiment 1, when the fixed swing-reducing clamping portion is matched with the movable claw 32 to clamp and mount the elastomer 100, the static and dynamic combined clamping structure can effectively enhance the reliability of mounting the elastomer 100.

The pushing movable plate 421 is connected to the lower part of the middle cross beam of the swing reducer supporting box body in a limiting manner, and is specifically located at the pushing avoiding part 3112 of the main box body. At this time, two pairs of the pushing movable plate sliding limiting portions 4211 of the pushing movable plate 421 are limited in the shimmy damper limiting groove. The distance from the inner wall surface of the swing reducing cover plate 312 to the inner wall surface of the bottom of the main swing reducing box 311 is greater than B1 (B1 is the width of the pushing movable plate 421), and the distance from the outer wall surface of the swing reducing cover plate 312 to the outer wall surface of the bottom of the main swing reducing box 311 is less than B2 (B2 is the distance between the outer end surfaces of the two opposite pushing movable plate sliding limiting portions 4211).

When the pull rod unit 22 is contracted, the pushing rocker arm 412 does not push the pushing movable plate 421 any more, and the pushing movable plate 421 is pushed by the pushing spring 423 to move downward along the axial direction of the pushing guide body 422; at this time, the two pairs of sliding limiting portions 4211 of the pushing movable plate 421 are also limited in the limit groove of the shimmy damper to move downward, so that the claw 32 is opened under the action of the gravity G of the projectile body 100, and the projectile body 100 is released.

Further, the pushing spring 423 is disposed between the upper end surface of the pushing movable plate 421 and the lower end surface of the middle part of the inner cavity of the shimmy damper supporting box body, and the pretightening force of the device for mounting and throwing the aircraft elastomer in the process of filling the elastomer 100 can be adjusted by replacing the pushing spring 423.

Further, in the installation position, the upper end portion of the pushing guide body 422 is connected to the swing-reducing main box body 311, which not only can provide a guiding and limiting function for the pushing spring 423, but also is convenient for installing the pushing spring 423.

Preferably, the pushing spring 423 is a compression spring.

As shown in fig. 8 and 9, the body of the claw 32 is an arc-shaped plate structure. The jaw 32 includes a jaw rotation shaft hole 322 at the middle portion, jaw ratchets 323 at the upper end portion, and jaw contact pieces 321 at the inner side wall.

The jaw rotation shaft 3116 is coupled to the torsion spring 35 while being hinged to the jaw 32 at the jaw rotation shaft hole 322. The two symmetrical claws 32 simultaneously make opening and closing movements around the respective corresponding claw rotation shafts 3116, so that the projectile body mounting assembly 3 locks and mounts the projectile body 100 or opens and releases the projectile body 100.

The inner side wall surface of the claw contact piece 321 is arc-shaped; when the projectile 100 is locked by mounting, the projectile 100 is accommodated between the inner side wall surfaces of the two claw contact pieces 321.

As shown in fig. 10, the jaw portion contact piece 321 of the present embodiment 1 is provided on the inner arc surface of the jaw 32 body, which is in contact with the projectile body 100; the width of the contact piece 321 of the claw portion is larger than the width of the body of the claw 32, so as to increase the contact area when the claw 32 clamps and mounts the projectile body 100, which is beneficial to increasing the clamping and mounting reliability.

The jaws 32 can clamp the projectile 100 of the minimum diameter through the inner arc of the jaw contact piece 321.

As shown in fig. 10, the claw portion contact piece 321 of the present embodiment 1 is provided on an intrados surface of the claw 32 body which contacts the projectile body 100; the width of the jaw portion contact piece 321 is larger than the width of the jaw 32 body.

As shown in fig. 10 and 12, preferably, the jaw elastic pad layer 325 is provided on the intrados surface of the jaw contact piece 321 of the present embodiment 1. The jaw elastic pad layer 325 of the present embodiment 1 is an elastomer coated on the inner arc surface of the jaw contact piece 321, specifically, foam. The foam with a certain thickness is adhered to the inner arc surface of the jaw contact piece 321. When the clamping jaw contact pieces 321 clamp the elastomer 100 with the minimum diameter and the clamping jaw clamping portions 324 and the swing reducing clamping portions together clamp the elastomer 100 with a mounting diameter larger than that of the elastomer 100, the two clamping jaws 32 can clamp the elastomer 100 through the elastic clamping jaw elastic cushion 325 and the whole wall surface, so that the reliability of clamping and mounting the elastomer 100 can be further enhanced, and the impact force of the external loading force F on the aircraft elastomer mounting and throwing device of the embodiment 1 through the elastomer 100 can be buffered.

Further preferably, an elastic cushion reinforcing part is arranged on an arc section of the centripetal side of the jaw elastic cushion 325; the elastic cushion reinforcement part may be a structure gradually thicker in the centripetal arc section of the jaw elastic cushion 325, or may be a discrete protrusion structure provided on the centripetal arc section of the jaw elastic cushion 325. The elastic cushion reinforcement portion can further assist in enhancing the stability of the elastomer 100 being held and mounted.

Any technical solution for mounting the same aircraft projectile body mounting and releasing device on the projectile bodies 100 with different diameters through the structure and the material change of the claw portion contact piece 321 is included in the scope of the novel protection of the present embodiment.

As shown in fig. 10, a plurality of the jaw ratchet teeth 323 are provided at the upper end of the jaw 32. The jaw ratchets 323 on the two symmetrically arranged jaws 32 are in one-to-one correspondence and are used in pairs.

The jaw portion contact piece 321, the jaws 32 provided with a plurality of the jaw ratchet teeth 323 can be locked closed at each pair of different jaw ratchet teeth 323 to mount the projectile 100 of different diameters.

Specifically, the pawl ratchet 323 can cooperate with different gears to limit the pushing movable plate 421 to be positioned at different heights, so as to cooperate with the pawl 32 and the swing reducing clamping portion of the swing reducer unit 31 to clamp and mount the projectile bodies 100 with different diameters.

The jaw ratchet 323 can be used for realizing that the elastomer mounting assembly 3 mounts the elastomers 100 with different diameters by the same device, so that the equipment cost under the specification of using multiple elastomers is saved.

FIG. 11 shows the overall configuration of the device of the present invention for mounting and releasing an aircraft projectile in an open condition for releasing the projectile.

The process of mounting and locking the projectile 100 by the projectile mounting and releasing device of the aircraft in this embodiment 1 is as follows:

FIG. 13 illustrates the loading of the aircraft projectile loading and delivery apparatus during loading and locking of projectile 100.

In the state in which the overall structure of the apparatus for mounting and releasing an aircraft elastomer is opened as shown in fig. 11, the upward loading force F overcomes the urging force of the torsion spring 35, and the elastomer 100 is loaded upward from the lower portion of the apparatus for mounting and releasing an aircraft elastomer.

Specifically, the elastic body 100 is first contacted with the protruding parts of the lower parts of the upper ends of the two jaws 32, so that the two jaws 32 are respectively acted by the force components F1 and F2 obliquely upwards to rotate around the jaw rotation shaft 3116, the two jaws 32 relatively rotate, the lower ends gradually approach, the elastic body 100 is kept locked between the two opposite jaw contact pieces 321/between the two jaw clamping parts 324 and the swing reducing clamping parts, and the jaw elastic cushion 325 can assist in increasing the stability of clamping and mounting the elastic body 100.

During initial locking, the outermost pawl ratchet 323 at the upper end of the pawl 32 contacts with the pushing movable plate 421, and under the action of the loading force F, the pawl 32 continues to rotate around the rotation pin of the shimmy damper, so as to push the pushing movable plate 421 to move upwards continuously against the action force of the torsion spring 35 and the gravity G of the monomer 100 until the projectile body 100 is locked by the position.

In the locking state, the upper parts of the two clamping claws 32 bear the component force of the pushing movable plate 421 horizontally inwards; similarly, the pushing movable plate 421 is simultaneously subjected to two opposite inward reaction forces of the jaws 32, and the two reaction forces are mutually offset, so that the stress environment in the process of locking the projectile body 100 is simplified, the reliability of locking the projectile body 100 by the aircraft projectile body mounting and throwing device is improved, and the projectile body 100 can be always stably kept in a mounting state.

In addition, besides the loading force F for loading the projectile body 100, the projectile body 100 in the whole loading and locking process is automatically and mechanically locked, no manual locking operation is needed, and the projectile body mounting efficiency is improved.

The process of throwing the projectile 100 by the projectile mounting and throwing device of the aircraft in this embodiment 1 is as follows:

FIG. 14 illustrates the loading of the aircraft projectile loading and delivery device during delivery of projectile 100.

In fig. 14, f1x and f2x are the supporting forces of the pushing plate 421 on the claws 32 in the state where the projectile 100 is not put in.

As shown in fig. 2, the throwing power source 211 is started to drive the throwing rotary disk 212 to rotate, and the throwing rotary disk 212 drives the proximal end of the pull rod unit 22 to rotate from 0 ° to 90 ° in the axial direction around the center of the throwing rotary disk 212.

The pull rod unit 22 drives the pushing rocker arm to rotate around the pushing rotary pin shaft 413, and the distal end of the rocker arm output lug 4122 pushes the pushing movable plate 421 upwards to overcome the acting force of the pushing pressure spring 423; at this time, the projectile body 100 applies force components f1 and f2 in radial normal directions to the lower ends of the two jaws 32 under its own weight G, so as to push the two jaws 32 to rotate around the jaw rotation shaft 3116, the two jaws 32 rotate in opposite directions, and the lower section is gradually separated until the jaws 32 are completely opened, and the projectile body 100 is thrown under its own weight G. At this time, the clamping and rotating part 32 is limited at the lower limiting body 34; in a state where no other external force acts, the torsion spring 35 acts so that the jaws 32 are kept in a relatively open state, facilitating the next loading and mounting of the projectile 100.

According to the aircraft elastomer mounting and throwing device, only the loading force F of the elastomer 100 is needed to be hoisted in the process of loading and mounting the elastomer 100; the projectile 100 is capable of automatic locking on the apparatus, simplifying handling steps and improving projectile loading efficiency.

According to the device for mounting and throwing the aircraft projectile body, the projectile body is automatically linked with the throwing pushing assemblies 4 through the throwing telescopic assemblies 2 in the projectile body 100 throwing process, the throwing is completed as soon as possible only by the gravity of the projectile body 100, the throwing process is simple, and the throwing reliability and throwing efficiency are improved.

Example 2

An aircraft.

The aircraft of embodiment 2 includes an aircraft body and the device for mounting and releasing the projectile body of the vehicle of embodiment 1.

Specifically, the device for mounting and releasing the elastomer 100 of the vehicle is connected to the lower part of the vehicle body.

The above is only a preferred embodiment of the present invention; the scope of the invention is not limited in this respect; any changes or substitutions that would be readily apparent to one skilled in the art within the scope of the present disclosure are intended to be encompassed within the scope of the present invention. Simultaneously; the equipment with the device is mounted; to expand the application field and produce compound technical effects; all falling within the scope of the invention of the present device.

Claims (10)

1. The device for mounting and throwing the projectile body of the aircraft is characterized by comprising an aircraft mounting plate (1), a projectile body throwing telescopic assembly (2), a throwing pushing assembly (4) and a projectile body mounting assembly (3);

the throwing telescopic assembly (2) and the projectile body mounting assembly (3) are connected below the aircraft mounting plate (1); two ends of the throwing telescopic component (2) are respectively and movably connected with the projectile body mounting component (3) through one throwing pushing component (4); the two elastomer mounting assemblies (3) are symmetrically arranged;

the throwing telescopic assembly (2) comprises a throwing power unit (21) and a pull rod unit (22);

the throwing pushing assembly (4) comprises a pushing supporting unit (41) and a pushing movable unit (42); the pushing supporting unit (41) comprises a pushing rocker arm (412); the pushing movable unit (42) comprises a pushing movable plate (421) and a pushing spring (423);

the elastomer mounting assembly (3) comprises a shimmy damper unit (31) and a claw unit; the shimmy damper unit (31) comprises a shimmy damper clamping part; the jaw unit comprises a jaw (32);

the upper end of the claw (32) is provided with a claw ratchet (323), and the lower part of the claw (32) is provided with a claw clamping part (324).

2. The aircraft elastomer mounting and launch device according to claim 1, characterized in that said launch power unit (21) comprises a launch power source (211) and a launch rotating disc (212); the tie rod unit (22) includes a tie rod (221) and a tie rod bearing knuckle (222).

3. The device for mounting and releasing the projectile bodies of the aircraft according to claim 1, wherein the releasing pushing assembly (4) comprises a pushing supporting unit (41) and a pushing movable unit (42).

4. The device for mounting and releasing the elastomer of the aircraft according to claim 3, wherein the pushing support unit (41) comprises a pushing support fixing plate (411), a pushing rocker arm (412) and a pushing rotary pin shaft (413); the pushing rocker arm (412) comprises a rocker arm input ear (4121) and a rocker arm output ear (4122).

5. The aircraft elastomer mounting and delivery device according to claim 4, characterized in that the rocker arm input ear (4121) articulates the pull rod bearing knuckle (222) of the distal end of the pull rod unit (22); the rocker arm output lug (4122) abuts against the lower end of the pushing movable plate (421) and pushes up the pushing movable unit (42).

6. The device for mounting and releasing the elastomer of the aircraft according to claim 3, wherein the pushing movable unit (42) comprises a pushing movable plate (421), a pushing guide body (422) and a pushing spring (423); the pushing movable plate (421) is provided with a pushing movable plate sliding limiting part (4211).

7. The device for mounting and releasing an aircraft elastomer according to claim 1, wherein the elastomer mounting assembly (3) further comprises an upper limit body (33), a lower limit body (34) and a torsion spring (35); the jaw unit comprises two symmetrically arranged jaws (32).

8. The aircraft elastomer mounting and delivery device according to claim 7, characterized in that the shimmy damper unit (31) comprises a shimmy damper main box (311) and a shimmy damper cover plate (312);

the swing-reducing main box body (311) and the swing-reducing cover plate (312) are respectively provided with a limiting groove and form a swing-reducing device limiting groove together; the swing-reducing main box body (311) and the swing-reducing cover plate (312) are respectively provided with a clamping part and form the swing-reducing clamping part together; a claw rotating shaft (3116) is arranged in the swing-reducing main box body (311).

9. The device for mounting and releasing an aircraft elastomer according to claim 1, characterized in that said jaws (32) are of arcuate plate construction; the claw (32) further comprises a claw rotating shaft hole (322) and a claw contact piece (321); the lower part of the claw contact piece (321) is provided with the claw clamping part (324);

the jaw rotation shaft hole (322) is mutually matched and connected with the jaw rotation shaft (3116).

10. An aircraft comprising an aircraft body and an aircraft projectile body mounting and delivery device according to any one of claims 1 to 9; the aircraft elastomer mounting and throwing device is arranged at the lower part of the aircraft body.