CN112550754B - A tail support balancing device for small aircraft assembly - Google Patents

Abstract

The invention relates to the technical field of small aircraft assembly, in particular to a tail support balance device for small aircraft assembly. Two vertical frames, the top of the horizontal strip is provided with a soft rubber pad, the tail pendant is hinged with the bottom middle section of the horizontal strip through a rotating rod, and the power-assisted buffer mechanism includes a horizontally arranged swing rod and two telescopic rod, a sliding sleeve is slidably installed on the rotating rod, the sliding sleeve is connected with the swing rod through the connecting column head, and the upper half of each telescopic rod is slidably matched with the upper half of one of the vertical frames through the buffer assembly When the tail pendant is lifted, the present invention can reduce the difficulty of lifting the tail pendant, and when the tail pendant is lowered, the speed at which the tail pendant rotates around the center line of the horizontal strip along with the rotating rod is reduced, and the safety hazard of the staff is eliminated.

Description

A tail support balancing device for small aircraft assembly

technical field

The invention relates to the technical field of assembly of small aircraft, in particular to a tail support balance device for assembly of small aircraft.

Background technique

In the process of assembling a small aircraft, the head of the aircraft is heavy, and the head of the aircraft is prone to tilt forward, accidentally injuring the staff or the aircraft. In the process of disassembling and assembling the engine, it is necessary to drop a heavy object from the tail of the aircraft, which can make the aircraft in a certain position. It floats within the range, but when the nose of the machine touches the ground quickly, it will play an aggravating role. The heavy object is generally a clinker container with a scale engraved on the appearance. The container is equipped with a 500KG weight, and the bottom is equipped with four universal wheels.

Such a structure requires manual lifting of the heavy objects and then tethering the heavy objects to the tail of the aircraft. Because the heavy objects are heavy, it is very inconvenient to operate, and it also poses a safety hazard to the staff. The heavy objects play a balancing role. To achieve absolute balance, the existing handling methods may also cause the danger of the tail landing of the aircraft.

SUMMARY OF THE INVENTION

The purpose of the present invention is to provide a tail drop balancing device for assembling a small aircraft, so as to solve the above-mentioned problems in the background art.

The technical scheme of the present invention is:

A tail drop balancing device for small aircraft assembly, the support device includes a support frame, a tail pendant and a booster buffer mechanism, the support frame includes a horizontal strip and two integrally formed with both ends of the horizontal strip respectively. The vertical frame, the top of the horizontal strip is provided with a soft rubber pad, the tail pendant is hinged with the middle section of the bottom of the horizontal strip through a rotating rod, and the power-assisted buffer mechanism includes a horizontally arranged swing rod and two The swing rod is a vertical telescopic rod, the two ends of the swing rod are respectively fixedly connected with one end of the two telescopic rods, and the ends of the two telescopic rods away from the swing rod are hinged with the bottoms of the two vertical frames, respectively, and the rotating rod is on the bottom of the two vertical frames. A sliding sleeve is slidably installed, the sliding sleeve is linked and matched with the swing rod through the connecting column head, and the upper half of each telescopic rod is slidably matched with the upper half of one of the vertical frames through the buffer assembly.

Further, the lower half of the vertical frame is a vertically arranged triangular plate, the top of the triangular plate extends vertically upward with a vertical rod, and the length directions of all the telescopic rods are parallel to each other and the length of the horizontal strip. The direction is vertical, the bottom end of the telescopic rod is hinged with the position of the bottom of the triangular plate deviated from the midpoint through a connecting shaft, and the axis of the connecting shaft is parallel to the length direction of the horizontal strip.

Further, one end of the connecting column head is rotatably connected with the swing rod, and the other end of the connecting column head is hinged with the outside of the sliding sleeve through a connecting shaft, and the axis of the connecting shaft is parallel to the center line of the swing rod.

Further, the buffer assembly includes a guide rod and a buffer spring sleeved on the guide rod, one end of the guide rod is installed with a fixed head, the upper half of the telescopic rod is fixedly installed with a rotating shaft, and the fixed head is installed on the upper half of the telescopic rod. The head is rotatably matched with the rotating shaft, the axis of the rotating shaft is parallel to the axis of the connecting shaft, the upper half of the vertical frame is rotatably installed with a rotating head, and the rotating head is connected to the vertical through the central axis parallel to the rotating shaft. The upper half of the frame is rotatably connected, and the rotating head is vertically provided with a guide hole for the guide rod to pass through.

Further, a horizontal limit plate is installed on the bottom of the two vertical frames, and a limit notch is provided on the side of the horizontal limit plate close to the power-assisted buffer mechanism.

Further, the top of the tail pendant is rotatably connected to the end of the rotating rod away from the soft rubber pad through a linkage shaft, and both ends of the linkage shaft are rotatably installed with rope joints.

Further, the middle section of the horizontal limit plate is rotatably installed with a hook, and the side of the tail pendant is provided with a handle that is engaged with the hook.

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

One: the tail pendant of the present invention, 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. The drop of the tail pendant generates resistance, which can reduce the speed of the tail pendant rotating around the center line of the horizontal strip with the rotating rod, avoid the tail pendant from falling too fast, and further reduce the risk of the tail pendant falling.

Second: the tail pendant of the present invention can only rotate around the center line of the horizontal strip along with the rotating rod. As long as the staff does not approach the rotating route, the safety hazard of the staff can be eliminated.

Description of drawings

Below in conjunction with accompanying drawing and embodiment, the present invention is further explained:

Fig. 1 is three-dimensional structure schematic diagram one of the present invention;

Fig. 2 is the three-dimensional structure schematic diagram two of the present invention;

Fig. 3 is three-dimensional schematic diagram of the present invention;

Fig. 4 is the three-dimensional structure schematic diagram four of the present invention;

Fig. 5 is three-dimensional structure schematic diagram five of the present invention;

Description of reference numbers:

Support frame 1, horizontal strip 11, vertical frame 12, soft rubber pad 13, triangular plate 14, vertical rod 15, connecting shaft 16, tail pendant 2, rotating rod 21, sliding sleeve 22, connecting column head 23, connecting shaft 24, rope connection part 25, handle 26, linkage shaft 27, booster buffer mechanism 3, swing rod 31, telescopic rod 32, buffer assembly 4, buffer spring 41, guide rod 42, fixed head 43, rotating shaft 44, rotating head 45 , the central axis 46, the horizontal limit plate 5, the limit notch 51, and the hook 52.

Detailed ways

The present invention will be described in detail below, and the technical solutions in the embodiments of the present invention will be described clearly and completely. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

The present invention provides a tail support balancing device for assembly of a small aircraft through improvement. As shown in Figures 1-5, the support device includes a support frame 1, a tail pendant 2 and a booster buffer mechanism 3. The The support frame 1 includes a horizontal strip 11 and two vertical frames 12 integrally formed with the two ends of the horizontal strip 11 respectively. The top of the horizontal strip 11 is provided with a soft rubber pad 13, and the tail pendant 2 is rotated by rotating The rod 21 is hinged to the middle section of the bottom of the horizontal strip 11. The booster buffer mechanism 3 includes a horizontally arranged swing rod 31 and two telescopic rods 32 that are both perpendicular to the swing rod 31. The two ends of the swing rod 31 are respectively connected to the two One end of the two telescopic rods 32 is fixedly connected, and one end of the two telescopic rods 32 away from the swing rod 31 is hinged with the bottoms of the two vertical frames 12 respectively. A sliding sleeve 22 is slidably installed on the rotating rod 21 , and the sliding sleeve 22 The upper half of each telescopic rod 32 is slidably matched with the upper half of one of the vertical frames 12 through the buffer assembly 4 through the linkage between the connecting column head 23 and the swing rod 31 .

The tail of the aircraft rests on the horizontal strip 11 of the support frame 1. When the tail pendant 2 needs to be tied to the tail of the aircraft, and the tail pendant 2 is lifted to drive the rotating rod 21 to rotate and rise around the horizontal strip 11, the swing rod 31 is turned back One side of the support frame 1 is pulled, and the telescopic rod 32 is extended at the same time, and the sliding sleeve 22 slides on the rotating rod 21 towards the tail pendant 2. The restoring force of the buffer assembly 4 assists the staff to lift the tail pendant 2 and lowers the lift of the staff. The difficulty of the tail pendant 2, and then tether the tail pendant 2 to the tail of the aircraft.

When the tail pendant needs to be removed from the tail of the aircraft, the rope on the tail pendant 2 is unfastened, and the staff slowly lowers the tail pendant 2 to drive the rotating rod 21 to rotate and descend around the horizontal strip 11 , the swing rod 31 is moved toward the support frame 1 . One side is pulled, and the telescopic rod 32 is retracted at the same time, the sliding sleeve 22 slides on the rotating rod 21 away from the tail pendant 2, the buffer assembly 4 is compressed, and resistance is generated to the falling of the tail pendant 2, and the auxiliary staff puts down the tail pendant 2 , to reduce the difficulty for the staff to lower the tail pendant 2.

The lower half of the vertical frame 12 is a vertically arranged triangular plate 14, the top of the triangular plate 14 extends vertically upward with a vertical rod 15, and the length directions of all the telescopic rods 32 are parallel to each other and to the horizontal strips The length direction of 11 is vertical, the bottom end of the telescopic rod 32 is hinged with the position of the bottom of the triangular plate 14 deviating from the midpoint through the connecting shaft 16, the axis of the connecting shaft 16 is parallel to the length direction of the horizontal strip 11, and the triangular plate 14 The structure can make the tail pendant 2 not unbalance the support frame 1 when the tail of the aircraft is placed on the support frame 1 .

One end of the connecting column head 23 is rotatably connected with the swing rod 31 , and the other end of the connecting column head 23 is hinged with the outer side of the sliding sleeve 22 through the connecting shaft 24 , and the axis of the connecting shaft 24 is parallel to the center line of the swing rod 31 to ensure the swing rod 31 While being pulled, the sliding sleeve 22 can be pulled to slide on the rotating rod 21 through the connecting column head 23 , so as to avoid interference while the rotating rod 21 rotates, and ensure that the rotating rod 21 can rotate smoothly.

The buffer assembly 4 includes a guide rod 42 and a buffer spring 41 sleeved on the guide rod 42. One end of the guide rod 42 is installed with a fixed head 43, and the upper half of the telescopic rod 32 is fixedly installed with a rotating shaft. 44. The fixed head 43 is rotatably matched with the rotating shaft 44, the axis of the rotating shaft 44 is parallel to the axis of the connecting shaft 24, the upper half of the vertical frame 12 is rotatably installed with a rotating head 45, and the rotating head 45 is rotatably connected to the upper half of the vertical frame 12 through a central axis 46 parallel to the rotating shaft 44, and the rotating head 45 is vertically provided with a guide hole for the guide rod 42 to pass through.

The tail of the aircraft rests on the horizontal strip 11 of the support frame 1. When the tail pendant 2 needs to be tied to the tail of the aircraft, and the tail pendant 2 is lifted to drive the rotating rod 21 to rotate and rise around the horizontal strip 11, the swing rod 31 is turned back One side of the support frame 1 is pulled, while the telescopic rod 32 is extended, the sliding sleeve 22 slides on the rotating rod 21 towards the tail pendant 2, the buffer spring 41 compressed by the buffer assembly 4 is gradually restored, and the restoring force assists the staff to remove the tail pendant 2 Lift it up to reduce the difficulty for the staff to lift the tail pendant 2, and then tie the tail pendant 2 to the tail of the aircraft.

When the tail pendant needs to be removed from the tail of the aircraft, the rope on the tail pendant 2 is unfastened, and the staff slowly lowers the tail pendant 2 to drive the rotating rod 21 to rotate and descend around the horizontal strip 11 , the swing rod 31 is moved toward the support frame 1 . One side is pulled, while the telescopic rod 32 is retracted, the sliding sleeve 22 slides on the rotating rod 21 away from the tail pendant 2, the buffer spring 41 of the buffer assembly 4 is compressed, which produces resistance to the falling of the tail pendant 2, and assists the staff to remove the tail pendant 2 Lower it to reduce the difficulty for staff to lower the tail pendant 2.

The bottoms of the two vertical frames 12 are installed with a horizontal limit plate 5 , and a limit notch 51 is provided on the side of the horizontal limit plate 5 close to the booster buffer mechanism 3 , and the horizontal limit plate 5 prevents the tail pendant 2 from falling. During the process, swinging back and forth around the center line of the horizontal strip 11 can quickly stop the tail pendant 2 .

The top of the tail pendant 2 is rotatably connected to the end of the rotating rod 21 away from the soft rubber pad 13 through the linkage shaft 27. The two ends of the linkage shaft 27 are rotatably installed with a rope joint 25. The rope joint 25 is convenient for threading the rope. The tail pendant 2 is tethered to the tail of the aircraft.

The middle section of the horizontal limit plate 5 is rotatably installed with a hook 52, the side of the tail pendant 2 is provided with a handle 26 that is snap-fitted with the hook 52, and the bottom of the support frame 1 is provided with a number of universal wheels. When the support frame 1 is pushed, the hook 52 hooks the handle 26 to ensure that the tail pendant 2 will not swing while the support frame 1 is moving.

The above description of the disclosed embodiments enables 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 implemented in 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 (7)

1. A tail support balancing device for small aircraft assembly, characterized in that: the support device includes a support frame (1), a tail pendant (2) and a power-assisted buffer mechanism (3), and the support frame (1) includes There are horizontal strips (11) and two vertical frames (12) integrally formed with the two ends of the horizontal strips (11) respectively. The top of the horizontal strips (11) is provided with a soft rubber pad (13), so The tail pendant (2) is hinged with the bottom middle section of the horizontal strip (11) through a rotating rod (21), and the booster buffer mechanism (3) includes a horizontally arranged swing rod (31) and two swing rods (31) both connected to the swing rod (31). ) vertical telescopic rod (32), two ends of the swing rod (31) are respectively fixedly connected with one end of two telescopic rods (32), and one end of the two telescopic rods (32) away from the swing rod (31) is respectively connected with one end of the two telescopic rods (32). The bottoms of the two vertical frames (12) are hinged, a sliding sleeve (22) is slidably installed on the rotating rod (21), and the sliding sleeve (22) is linked with the swing rod (31) through the connecting column head (23) In cooperation, the upper half of each telescopic rod (32) is slidably matched with the upper half of one of the vertical frames (12) through the buffer assembly (4). 2. The tail drop balancing device for assembling a small aircraft according to claim 1, wherein the lower half of the vertical frame (12) is a vertically arranged triangular plate (14), so A vertical rod (15) extends vertically upward from the top of the triangular plate (14), and the length directions of all the telescopic rods (32) are parallel to each other and perpendicular to the length direction of the horizontal strip (11). The bottom end of ) is hinged with the position of the bottom of the triangular plate (14) deviated from the midpoint through a connecting shaft (16), the axis of the connecting shaft (16) being parallel to the length direction of the horizontal strip (11). 3. The tail drop balancing device for assembling a small aircraft according to claim 1, characterized in that: one end of the connecting stud (23) is rotatably connected with the swing rod (31), and the connecting stud (23) is rotatably connected. The other end is hinged with the outside of the sliding sleeve (22) through a connecting shaft (24), and the axis of the connecting shaft (24) is parallel to the center line of the swing rod (31). 4 . The tail drop balancing device for small aircraft assembly according to claim 3 , wherein the buffer assembly ( 4 ) comprises a guide rod ( 42 ) and is sleeved on the guide rod ( 42 ). 5 . A buffer spring (41) is provided, one end of the guide rod (42) is installed with a fixed head (43), the upper half of the telescopic rod (32) is fixedly installed with a rotating shaft (44), and the fixed head (43) ) is rotatably matched with the rotating shaft (44), the axis of the rotating shaft (44) is parallel to the axis of the connecting shaft (24), and the upper half of the vertical frame (12) is rotatably installed with a rotating head (45), The rotating head (45) is rotatably connected to the upper half of the vertical frame (12) through a central axis (46) parallel to the rotating shaft (44), and the rotating head (45) is vertically provided for the guide rod (42) to pass through. through the pilot hole. 5 . The tail drop balancing device for assembling a small aircraft according to claim 1 , wherein a horizontal limit plate ( 5 ) is installed at the bottom of the two vertical frames ( 12 ). 6 . A limit notch (51) is provided on the side of the horizontal limit plate (5) close to the power-assisted buffer mechanism (3). 6. The tail support pendant balancing device for assembling a small aircraft according to claim 1, characterized in that: the top of the tail pendant (2) is away from the soft glue through the linkage shaft (27) and the rotating rod (21) One end of the pad (13) is rotatably connected, and the two ends of the linkage shaft (27) are rotatably installed with rope connection parts (25). 7 . The tail drop balancing device for assembling a small aircraft according to claim 5 , wherein the middle section of the horizontal limit plate ( 5 ) is rotatably installed with a hook, and the tail pendant ( 2 ) is rotatably installed with a hook. A handle (26) which is snap-fitted with the snap hook is arranged on the side of the snap hook.

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