CN112550754A

CN112550754A - Tail supporting and falling balancing device for assembling small airplane

Info

Publication number: CN112550754A
Application number: CN202011555158.7A
Authority: CN
Inventors: 盛明扬; 宋伟超; 王海路; 丁志勇; 李志军
Original assignee: Wuhu Zhongke Aircraft Manufacturing Co ltd
Current assignee: Wuhu Zhongke Aircraft Manufacturing Co ltd
Priority date: 2020-12-24
Filing date: 2020-12-24
Publication date: 2021-03-26
Anticipated expiration: 2040-12-24
Also published as: CN112550754B

Abstract

The invention relates to the technical field of small airplane assembly, in particular to a tail supporting and balancing device for small airplane assembly, which comprises a support frame, a tail pendant and a power-assisted buffer mechanism, wherein the support frame comprises a horizontal strip plate and two vertical frames, a soft rubber pad is arranged at the top of the horizontal strip plate, the tail pendant is hinged with the middle section of the bottom of the horizontal strip plate through a rotating rod, the power-assisted buffer mechanism comprises a horizontally arranged swinging rod and two telescopic rods, a sliding sleeve is slidably arranged on the rotating rod, the sliding sleeve is in linkage fit with the swinging rod through a connecting column head, the upper half section of each telescopic rod is in sliding fit with the upper half section of one of the vertical frames through a buffer assembly, when the tail pendant is lifted, the difficulty of lifting the tail pendant can be reduced, and when the tail pendant is put down, the speed of the tail pendant rotating around a horizontal central line along with the rotating rod is reduced, the potential safety hazard of workers is eliminated.

Description

Tail supporting and falling balancing device for assembling small airplane

Technical Field

The invention relates to the technical field of small airplane assembly, in particular to a tail supporting and balancing device for small airplane assembly.

Background

The small-size aircraft is at the in-process of assembly, and the aircraft head is heavier, and the aircraft head takes place easily and leans forward, accidentally injures staff or aircraft, and the expert length needs a heavy object of aircraft afterbody back-drop at dismouting engine in-process, can make the aircraft float at the certain limit, but when the aircraft nose lands soon, plays the aggravation effect, and the heavy object generally is the outward appearance grog container that is carved with the scale, is equipped with 500 KG's weight in the container, and four universal wheels are equipped with to the bottom.

The structure needs the manual work to lift up the heavy object like this, then ties the heavy object at the aircraft afterbody, because the heavy object is heavier, and it is very inconvenient to operate, also has the potential safety hazard to the staff moreover, and the heavy object plays balanced effect, because the heavy object can't accomplish absolute balance, current processing mode also probably causes the danger that the aircraft afterbody lands.

Disclosure of Invention

The invention aims to provide a tail supporting and balancing device for assembling a small airplane, which aims to solve the problems in the prior art.

The technical scheme of the invention is as follows:

a tail supporting and balancing device for assembling a small airplane, the supporting device comprises a supporting frame, a tail pendant and a power-assisted buffer mechanism, the supporting frame comprises a horizontal lath and two vertical frames which are respectively integrated with the two ends of the horizontal lath, the top of the horizontal slat is provided with a soft rubber mat, the tail pendant is hinged with the middle section of the bottom of the horizontal slat through a rotating rod, the power-assisted buffer mechanism comprises a swing rod horizontally arranged and two telescopic rods which are both vertical to the swing rod, two ends of the swing rod are respectively fixedly connected with one ends of the two telescopic rods, one ends of the two telescopic rods far away from the swing rod are respectively hinged with the bottoms of the two vertical frames, sliding mounting has the sliding sleeve on the dwang, the sliding sleeve cooperates with the swinging arms interlock through connecting the column cap, and the first half of every telescopic link passes through buffering subassembly and the first half sliding fit of one of them vertical frame.

Further, the lower half section of vertical frame is the triangle-shaped board of vertical setting, the vertical upwards extension in top of triangle-shaped board has vertical pole, and the length direction of all telescopic links is parallel to each other and perpendicular with the length direction of horizontal slat, the position of the skew mid point in connecting axle and triangle-shaped board bottom is passed through to the bottom of telescopic link is articulated, the axis of connecting axle is parallel with the length direction of horizontal slat.

Furthermore, one end of the connecting column head is rotatably connected with the swinging rod, the other end of the connecting column head is hinged with the outer side of the sliding sleeve through a connecting shaft, and the axis of the connecting shaft is parallel to the central line of the swinging rod.

Further, buffering subassembly establishes the buffer spring on the guide bar including guide bar and cover, the fixed head is installed to the one end of guide bar, first section fixed mounting of telescopic link has the rotation axis, fixed head and rotation axis normal running fit, the axis of rotation axis and the parallel that links up the axle axis, first section rotation of vertical frame installs the rotating head, the rotating head rotates with first section of vertical frame through the axis parallel with the rotation axis and is connected, and the vertical guiding hole that supplies the guide bar to pass that has of rotating head.

Furthermore, horizontal limiting plates are installed at the bottoms of the two vertical frames, and limiting notches are formed in the side edges, close to the power-assisted buffering mechanism, of the horizontal limiting plates.

Further, the top of afterbody pendant is passed through the universal driving shaft and is rotated with the one end that the soft cushion was kept away from to the dwang and be connected, the both ends of universal driving shaft are rotated and are installed rope connection portion.

Furthermore, the middle section of horizontal limiting plate rotates installs the pothook, the lateral part of afterbody pendant is provided with the handle with pothook joint complex.

The invention provides a tail supporting and balancing device for assembling a small airplane through improvement, and compared with the prior art, the tail supporting and balancing device has the following improvements and advantages:

one is as follows: according to the tail pendant, under the cooperation of the buffer assembly, when the tail pendant is lifted, the restoring force of the buffer spring can reduce the difficulty of lifting the tail pendant, when the tail pendant is put down, the buffer spring is compressed to generate resistance to the falling of the tail pendant, the speed of the tail pendant rotating around the central line of the horizontal batten along with the rotating rod can be reduced, the tail pendant is prevented from falling too fast, and the risk of falling of the tail pendant is further reduced.

The second step is as follows: the tail pendant can only rotate around the central line of the horizontal batten along with the rotating rod, and potential safety hazards of workers can be eliminated as long as the workers do not approach the rotating line.

Drawings

The invention is further explained below with reference to the figures and examples:

FIG. 1 is a first perspective view of the present invention;

FIG. 2 is a schematic perspective view of the present invention;

FIG. 3 is a third schematic perspective view of the present invention;

FIG. 4 is a fourth schematic perspective view of the present invention;

FIG. 5 is a schematic perspective view of the present invention;

description of reference numerals:

the support frame 1, horizontal slat 11, vertical frame 12, soft rubber pad 13, triangle-shaped board 14, vertical pole 15, connecting axle 16, afterbody pendant 2, dwang 21, sliding sleeve 22, connect column cap 23, link up axle 24, rope connection portion 25, handle 26, universal driving shaft 27, helping hand buffer gear 3, swinging arms 31, telescopic link 32, buffer module 4, buffer spring 41, guide bar 42, fixed head 43, rotation axis 44, rotating head 45, axis 46, horizontal limiting plate 5, spacing breach 51, pothook 52.

Detailed Description

The present invention is described in detail below, and technical solutions in the embodiments of the present invention are clearly and completely described, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

The invention provides a tail supporting and balancing device for assembling a small airplane by improvement, as shown in fig. 1-5, the supporting device comprises a supporting frame 1, a tail pendant 2 and a power-assisted buffering mechanism 3, the supporting frame 1 comprises a horizontal strip plate 11 and two vertical frames 12 which are respectively and integrally formed with two ends of the horizontal strip plate 11, a soft rubber cushion 13 is arranged at the top of the horizontal strip plate 11, the tail pendant 2 is hinged with the middle section of the bottom of the horizontal strip plate 11 through a rotating rod 21, the power-assisted buffering mechanism 3 comprises a horizontally arranged swinging rod 31 and two telescopic rods 32 which are respectively vertical to the swinging rod 31, two ends of the swinging rod 31 are respectively and fixedly connected with one ends of the two telescopic rods 32, one ends of the two telescopic rods 32 far away from the swinging rod 31 are respectively hinged with the bottoms of the two vertical frames 12, a sliding sleeve 22 is slidably mounted on the rotating rod 21, the sliding sleeve 22 is in linkage fit with the swinging rod 31 through the connecting column head 23, and the upper half section of each telescopic rod 32 is in sliding fit with the upper half section of one of the vertical frames 12 through the buffer assembly 4.

Aircraft afterbody is taken on the horizontal slat 11 of support frame 1, tie afterbody pendant 2 at aircraft afterbody when needs, lift afterbody pendant 2 and drive dwang 21 when horizontal slat 11 is rotatory to be risen, swinging arms 31 is by the one side pulling of support frame 1 dorsad, telescopic link 32 extends simultaneously, tail pendant 2 slides towards on dwang 21 to sliding sleeve 22, buffer unit 4's the supplementary staff of restoring force lifts afterbody pendant 2, reduce the staff and lift up the degree of difficulty of afterbody pendant 2, then tie afterbody pendant 2 at aircraft afterbody.

Hang the afterbody when needs and take off from aircraft afterbody, untie the rope on the afterbody pendant 2, the staff slowly transfers afterbody pendant 2 and drives dwang 21 when the rotatory decline of horizontal slat 11, swinging arms 31 is by the one side pulling towards support frame 1, telescopic link 32 returns simultaneously and contracts, sliding sleeve 22 slides afterbody pendant 2 dorsad on dwang 21, buffer unit 4 by the compression, 2 whereabouts produce the resistance to afterbody pendant, supplementary staff puts down afterbody pendant 2, reduce the staff and transfer the degree of difficulty of afterbody pendant 2.

The vertical frame 12 is the triangle-shaped board 14 of vertical setting in the second half section, the vertical upwards extension in top of triangle-shaped board 14 has vertical pole 15, and the length direction of all telescopic links 32 is parallel to each other and perpendicular with the length direction of horizontal slat 11, the position of connecting axle 16 and the skew mid point in triangle-shaped board 14 bottom is passed through to the bottom of telescopic link 32 is articulated, the axis of connecting axle 16 is parallel with the length direction of horizontal slat 11, and triangle-shaped board 14 structure can make when the afterbody aircraft is taken on support frame 1, and afterbody pendant 2 can not make support frame 1 unbalance.

The one end of connecting column cap 23 rotates with rocking rod 31 to be connected, and the other end of connecting column cap 23 is articulated through linking axle 24 and sliding sleeve 22's the outside, and the axis that links up axle 24 is parallel with the central line of rocking rod 31, guarantees that rocking rod 31 can stimulate sliding sleeve 22 through connecting column cap 23 and slide on dwang 21 when being promoted, produces the interference when avoiding dwang 21 rotatory, guarantees that dwang 21 can the steady rotation.

Buffer unit 4 establishes buffer spring 41 on guide bar 42 including guide bar 42 and cover, fixed head 43 is installed to the one end of guide bar 42, first section fixed mounting of telescopic link 32 has rotation axis 44, fixed head 43 and rotation axis 44 normal running fit, the axis of rotation axis 44 and the parallel of linking 24 axes, first section rotation of vertical frame 12 installs rotating head 45, rotating head 45 is connected through first section rotation with the parallel axis 46 of rotation axis 44 and vertical frame 12, and rotating head 45 vertically has the guiding hole that supplies guide bar 42 to pass.

Aircraft afterbody takes on the horizontal slat 11 of support frame 1, tie afterbody pendant 2 at aircraft afterbody as needs, lift afterbody pendant 2 and drive dwang 21 when horizontal slat 11 is rotatory to be risen, swinging arms 31 is by the one side pulling of support frame 1 toward back, telescopic link 32 extends simultaneously, tail pendant 2 slides on dwang 21 is gone to sliding sleeve 22, buffer spring 41 that buffer assembly 4 compressed resumes gradually, this recovery force assists the staff to lift afterbody pendant 2, reduce the staff and lift up the degree of difficulty of pendant afterbody 2, then tie afterbody pendant 2 at aircraft afterbody.

Hang the afterbody when needs and take off from aircraft afterbody, untie the rope on the afterbody pendant 2, the staff slowly transfers afterbody pendant 2 and drives dwang 21 when descending around the rotation of horizontal slat 11, swinging arms 31 is by the one side pulling towards support frame 1, simultaneously telescopic link 32 returns and contracts, sliding sleeve 22 slides to afterbody pendant 2 on dwang 21 dorsad, 4 buffer spring 41 of buffer unit are compressed, produce the resistance to 2 whereabouts of afterbody pendants, supplementary staff puts down afterbody pendant 2, reduce the staff and transfer the degree of difficulty of afterbody pendant 2.

Horizontal limiting plates 5 are installed at the bottoms of the two vertical frames 12, limiting notches 51 are formed in the side edges, close to the power-assisted buffering mechanisms 3, of the horizontal limiting plates 5, the horizontal limiting plates 5 can avoid the tail pendant 2 from falling to swing back and forth around the central line of the horizontal batten 11, and the tail pendant 2 can be stopped quickly.

The top of the tail pendant 2 is rotatably connected with one end, far away from the soft rubber pad 13, of the rotating rod 21 through the universal driving shaft 27, the two ends of the universal driving shaft 27 are rotatably provided with the rope connecting portion 25, the rope connecting portion 25 conveniently penetrates through a rope, and the tail pendant 2 is fastened at the tail of the airplane.

Horizontal limiting plate 5's middle section is rotated and is installed pothook 52, afterbody pendant 2's lateral part is provided with pothook 52 joint complex handle 26, and the bottom of support frame 1 is provided with a plurality of universal wheel, and when promoting support frame 1, pothook 52 catches on handle 26, guarantees that support frame 1 when removing, and afterbody pendant 2 can not swing.

The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. The utility model provides a afterbody holds in palm weighs down balancing unit that small-size aircraft assembly used which characterized in that: the supporting device comprises a supporting frame (1), a tail pendant (2) and a power-assisted buffering mechanism (3), wherein the supporting frame (1) comprises a horizontal batten (11) and two vertical frames (12) which are integrally formed with the two ends of the horizontal batten (11) respectively, a soft rubber mat (13) is arranged at the top of the horizontal batten (11), the tail pendant (2) is hinged with the middle section of the bottom of the horizontal batten (11) through a rotating rod (21), the power-assisted buffering mechanism (3) comprises a horizontally arranged swinging rod (31) and two telescopic rods (32) which are both perpendicular to the swinging rod (31), the two ends of the swinging rod (31) are respectively fixedly connected with one ends of the two telescopic rods (32), one ends of the two telescopic rods (32) far away from the swinging rod (31) are hinged with the bottoms of the two vertical frames (12) respectively, a sliding sleeve (22) is arranged on the rotating rod (21), the sliding sleeve (22) is in linkage fit with the swinging rod (31) through the connecting column head (23), and the upper half section of each telescopic rod (32) is in sliding fit with the upper half section of one vertical frame (12) through the buffer assembly (4).

2. The tail plummet balancing apparatus for small aircraft assembly of claim 1, wherein: the lower half section of vertical frame (12) is triangle-shaped plate (14) of vertical setting, the vertical upwards extension in top of triangle-shaped plate (14) has vertical pole (15), and the length direction of all telescopic links (32) is parallel to each other and perpendicular with the length direction of horizontal slat (11), the position of the bottom of telescopic link (32) through connecting axle (16) and triangle-shaped plate (14) bottom skew midpoint is articulated, the axis of connecting axle (16) is parallel with the length direction of horizontal slat (11).

3. The tail plummet balancing apparatus for small aircraft assembly of claim 1, wherein: one end of the connecting column head (23) is rotatably connected with the swinging rod (31), the other end of the connecting column head (23) is hinged with the outer side of the sliding sleeve (22) through a connecting shaft (24), and the axis of the connecting shaft (24) is parallel to the central line of the swinging rod (31).

4. The tail plummet balancing apparatus for small aircraft assembly as claimed in claim 3, wherein: buffer unit (4) establish buffer spring (41) on guide bar (42) including guide bar (42) and cover, fixed head (43) are installed to the one end of guide bar (42), first section fixed mounting of telescopic link (32) has rotation axis (44), fixed head (43) and rotation axis (44) normal running fit, the axis of rotation axis (44) and the parallel of linking up axle (24) axis, first section rotation of vertical frame (12) installs rotating head (45), rotating head (45) are connected through first section rotation with axis (46) parallel of rotation axis (44) and vertical frame (12), and rotating head (45) vertical have the guiding hole that supplies guide bar (42) to pass.

5. The tail plummet balancing apparatus for small aircraft assembly of claim 1, wherein: horizontal limiting plates (5) are installed at the bottoms of the two vertical frames (12), and limiting notches (52) (51) are formed in the side edges, close to the power-assisted buffering mechanism (3), of the horizontal limiting plates (5).

6. The tail plummet balancing apparatus for small aircraft assembly of claim 1, wherein: the top of afterbody pendant (2) is passed through universal driving shaft (27) and is rotated with the one end that soft cushion (13) was kept away from in dwang (21) and be connected, the both ends of universal driving shaft (27) are rotated and are installed rope connection portion (25).

7. The tail plummet balancing apparatus for small aircraft assembly as claimed in claim 5, wherein: the middle section of the horizontal limiting plate (5) is rotatably provided with a clamping hook, and the side part of the tail pendant (2) is provided with a handle (26) which is clamped and matched with the clamping hook.