阅读说明：本技术 一种用于飞行器的梭形结构 (Shuttle-shaped structure for aircraft ) 是由 吴珊 李军峰 廖桂香 刘磊 刘俊杰 于 2020-12-22 设计创作，主要内容包括：本发明公开了一种用于飞行器的梭形结构,所述内置异形框架内部开设有内置空腔,所述内置空腔内侧通过平衡束缚拉绳悬置连接有梭形稳定器,所述梭形稳定器两侧边部中端对称连接有平衡连接杆,本发明通过将梭形稳定器稳定的束缚于内置异形框架的内部,且通过该方式方便将梭形稳定器以悬置的方式置于内置异形框架内,再结合梭形稳定器边端的平衡连接杆将梭形稳定器与飞行器壳体进行固定,进而使得飞行器壳体在产生晃动时不会带动内置异形框架进行大幅度的晃动,进而使得内置异形框架和其内部的元件也不会因为晃动而产生损坏的现象,保证了飞行器的稳定飞行,同时提高了飞行器内部元件的使用寿命。(The invention discloses a shuttle-shaped structure for an aircraft, wherein a built-in cavity is arranged in a built-in special-shaped frame, the inner side of the built-in cavity is connected with a shuttle-shaped stabilizer in a suspension manner through a balance constraint pull rope, the middle ends of the two side edge parts of the shuttle-shaped stabilizer are symmetrically connected with balance connecting rods, the shuttle-shaped stabilizer is stably constrained in the built-in special-shaped frame, the shuttle-shaped stabilizer is conveniently arranged in the built-in special-shaped frame in a suspension manner in the manner, the shuttle-shaped stabilizer is fixed with an aircraft shell by combining the balance connecting rods at the edge ends of the shuttle-shaped stabilizer, so that the aircraft shell cannot drive the built-in special-shaped frame to largely shake when shaking occurs, further the built-in special-shaped frame and the elements in the built-in special-shaped frame cannot be damaged due to shaking, and the stable flight of, at the same time, the service life of the aircraft interior components is increased.)

1. Shuttle structure for aircraft, comprising a built-in profiled frame (1), characterized in that: the middle end of each edge part of the outer side of the built-in special-shaped frame (1) is provided with a through hole (2) in a penetrating manner, the edge ends of the through holes (2) positioned at each side position of the built-in special-shaped frame (1) are connected with installation binding rings (3), the edge ends of the through holes (2) positioned at the top and the bottom position of the built-in special-shaped frame (1) are connected with binding edge plates (4), and a built-in cavity (5) is formed in the built-in special-shaped frame (1);

the top corners of each edge on the outer side of the built-in special-shaped frame (1) are fixedly connected with positioning end plates (6), the middle ends of the inner sides of the positioning end plates (6) are provided with through holes (7) in a penetrating mode, threaded connecting rods (8) are embedded into the inner sides of the through holes (7) and connected in a matching mode, one ends of the threaded connecting rods (8) are fixedly connected with movable knobs (9), balance binding pull ropes (10) are connected in a penetrating mode in the middle portions of the inner sides of the positioning end plates (6) and the threaded connecting rods (8), and limiting rope heads (11) are connected to the positions, located at the end portions of;

built-in cavity (5) inboard is connected with fusiformis stabilizer (12) through balanced constraint stay cord (10) suspension, fusiformis stabilizer (12) both sides limit portion middle-end symmetric connection has balanced connecting rod (13), fusiformis stabilizer (12) limit portion and balanced constraint stay cord (10) are located same center axis and all correspond and have seted up connection perforation (14), each apex angle of built-in cavity (5) inboard corresponds equal splice with balanced constraint stay cord (10) position department and has had spacing gluey seat (15), balanced constraint stay cord (10) run through in spacing gluey seat (15), and balanced constraint stay cord (10) pass inside connection perforation (14) of fusiformis stabilizer (12).

2. A shuttle structure for an aircraft according to claim 1, wherein: the outer side of the installation binding ring (3) and the edge of the binding side plate (4) are both convenient to be bonded with protective rings through adhesive tapes.

3. A shuttle structure for an aircraft according to claim 1, wherein: an inner thread groove is formed in the inner side edge of the through hole (7), and the through hole (7) is connected with the threaded connecting rod (8) in an embedded fit mode through the inner thread groove in the through hole.

4. A shuttle structure for an aircraft according to claim 1, wherein: the limiting rubber seat (15) and the positioning end plate (6) are located on the same axis, a rope hole is formed in the limiting rubber seat (15), and the circle center of the rope hole and the circle center of the through hole (7) are located on the same axis.

5. A shuttle structure for an aircraft according to claim 1, wherein: the length and the size of the balance connecting rods (13) positioned at the middle ends of the side parts of the two sides of the shuttle-shaped stabilizer (12) are the same, and the end parts of the two balance connecting rods (13) are fixedly connected with threaded rods.

6. A shuttle structure for an aircraft according to claim 1, wherein: the shuttle-shaped stabilizer (12) is provided with two petals, the middle ends of the edge parts of the two petals of the shuttle-shaped stabilizer (12) are fixedly connected through a connecting and installing ring (16), installing through holes (17) are formed in the edge parts of the connecting and installing ring (16) at equal intervals, and fixing bolts (18) are embedded and connected into the inner sides of the installing through holes (17).

7. A shuttle structure for an aircraft according to claim 6, wherein: the fixing bolts (18) are positioned in the mounting through holes (17), and the fixing bolts (18) penetrate through the connecting mounting ring (16).

Technical Field

The invention relates to the technical field of aircrafts, in particular to a shuttle-shaped structure for an aircraft.

Background

With the current fact that aircraft are instrumental flyers manufactured by mankind, capable of flying off the ground, flying in space and controlled by man, flying in the atmosphere or in space outside the atmosphere, so-called aircrafts flying in the atmosphere, and so-called spacecraft flying in space, in addition, the types of aircraft are divided into: the system comprises a butterfly aircraft, a superconducting aircraft and a four-axis aircraft, wherein a balance mechanism is required to be installed inside the aircraft in the actual flying process of the aircraft;

because the interior of the existing aircraft lacks a shuttle-shaped stable balance structure, the elements installed in the aircraft shell easily generate large-amplitude shaking along with the flight of the aircraft, so that the stability of the aircraft in the flight process is reduced, and meanwhile, the elements in the aircraft are easily damaged.

Disclosure of Invention

The invention provides a shuttle-shaped structure for an aircraft, which can effectively solve the problem that the prior aircraft lacks a shuttle-shaped stable balance structure in the prior art, so that elements arranged in an aircraft shell easily generate large-amplitude shaking along with the flight of the aircraft, the stability of the aircraft in the flight process is reduced, and the elements in the aircraft are easily damaged.

In order to achieve the purpose, the invention provides the following technical scheme: a shuttle-shaped structure for an aircraft comprises a built-in special-shaped frame, wherein the middle end of each edge part of the outer side of the built-in special-shaped frame is provided with a through hole in a penetrating way, the edge ends of the through holes at each side position of the built-in special-shaped frame are connected with an installation binding ring, the edge ends of the through holes at the top and the bottom positions of the built-in special-shaped frame are connected with binding edge plates, and a built-in cavity is formed in the built-in special-shaped frame;

the positioning end plates are fixedly connected to top corners of all the edge parts on the outer side of the built-in special-shaped frame, through holes are formed in the middle ends of the inner sides of the positioning end plates in a penetrating mode, threaded connecting rods are connected to the inner sides of the through holes in an embedded and matched mode, movable knobs are fixedly connected to one ends of the threaded connecting rods, balance constraint pull ropes are connected to the middle portions of the inner sides of the positioning end plates and the threaded connecting rods in a penetrating mode, and limiting rope heads are connected to the positions, located;

the built-in cavity is inboard to be connected with the fusiform stabilizer through balanced constraint stay cord suspension, fusiform stabilizer both sides limit portion middle-end symmetric connection has balanced connecting rod, fusiform stabilizer limit portion and balanced constraint stay cord all correspond on being located same center axis and have seted up and connect the perforation, each apex angle of built-in cavity inboard all splices with balanced constraint stay cord corresponding position department and has limited gluey seat, balanced constraint stay cord runs through in limited gluey seat, and balanced constraint stay cord passes the inside connection perforation of fusiform stabilizer.

Preferably, the outer side of the installation binding ring and the edge part of the binding side plate are both conveniently bonded with protective rings through adhesive tapes.

Preferably, an inner thread groove is formed in the inner side edge of the through hole, and the through hole is in embedded fit connection with the threaded connecting rod through the inner thread groove.

Preferably, the limiting rubber seat and the positioning end plate are positioned on the same axis, a rope hole is formed in the limiting rubber seat, and the circle center of the rope hole and the circle center of the through hole are positioned on the same axis.

Preferably, the length and the size of the balance connecting rods positioned at the middle ends of the two side edges of the shuttle-shaped stabilizer are the same, and threaded rods are fixedly connected to the end parts of the two balance connecting rods.

Preferably, the fusiform stabilizer is provided with two petals, the middle ends of the two petals of the fusiform stabilizer are fixedly connected through the connecting and installing ring, the edges of the connecting and installing ring are equidistantly provided with installing through holes, and the inner sides of the installing through holes are connected with fixing bolts in an embedded mode.

Preferably, the fixing bolts are located in the mounting through holes and penetrate through the connecting mounting ring.

Compared with the prior art, the invention has the beneficial effects that: the invention has scientific and reasonable structure and safe and convenient use:

1. the shuttle-shaped stabilizer is conveniently and stably bound inside the built-in special-shaped frame through the through hole, the threaded connecting rod, the movable knob, the balance binding pull rope and the limiting rope head, the shuttle-shaped stabilizer is conveniently placed in the built-in special-shaped frame in a suspension mode through the mode, the shuttle-shaped stabilizer is fixed with the aircraft shell through the balance connecting rod at the edge end of the shuttle-shaped stabilizer, the aircraft shell cannot drive the built-in special-shaped frame to shake greatly when shaking occurs, the built-in special-shaped frame and elements inside the built-in special-shaped frame cannot be damaged due to shaking, stable flight of the aircraft is guaranteed, and the service life of internal elements of the aircraft is prolonged;

in addition, the stretching position and the stretching length of the balance constraint stay cord can be conveniently adjusted through the through hole, the threaded connecting rod and the movable knob, so that the balance constraint stay cord is guaranteed to have a better tensioning effect in the practical application process, and the stability of the balance constraint stay cord and the shuttle-shaped stabilizer in use is further guaranteed.

2. The installation bind ring and the constraint sideboard outside through built-in special-shaped frame conveniently tie up the guard ring fast fixed in the outside of built-in special-shaped frame to this guarantees the stability after the guard ring installation, and then conveniently protects the outside of built-in special-shaped frame through the guard ring, prevents to produce the rigidity collision between built-in special-shaped frame and the aircraft casing.

3. Conveniently carry out quick butt joint with two lamella fusiformis stabilizers through connecting collar, installation through-hole and fixing bolt, conveniently carry out quick fixed with two lamella fusiformis stabilizers simultaneously, and then reduced the installation degree of difficulty of fusiformis stabilizer, make follow-up people become more convenient when dismantling the maintenance to fusiformis stabilizer simultaneously.

Drawings

The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention and not to limit the invention.

In the drawings:

FIG. 1 is a schematic structural view of the present invention;

FIG. 2 is a schematic view of the connection structure of the threaded connection rod of the present invention;

FIG. 3 is a schematic view of the mounting structure of the shuttle stabilizer of the present invention;

FIG. 4 is a half-sectional view of the present invention built-in profile frame;

reference numbers in the figures: 1. a special-shaped frame is arranged inside; 2. a through hole is penetrated; 3. installing a binding ring; 4. binding the side plate; 5. a cavity is arranged inside; 6. positioning the end plate; 7. a through hole; 8. a threaded connecting rod; 9. a movable knob; 10. a balance binding pull rope; 11. limiting rope ends; 12. a shuttle stabilizer; 13. a balance connecting rod; 14. connecting through holes; 15. a limiting rubber seat; 16. connecting the mounting ring; 17. mounting a through hole; 18. and (5) fixing the bolt.

Detailed Description

The preferred embodiments of the present invention will be described in conjunction with the accompanying drawings, and it will be understood that they are described herein for the purpose of illustration and explanation and not limitation.

Example (b): as shown in fig. 1-4, the invention provides a technical scheme, a shuttle-shaped structure for an aircraft comprises a built-in special-shaped frame 1, wherein the middle end of each edge part of the outer side of the built-in special-shaped frame 1 is provided with a through hole 2 in a penetrating manner, the edge ends of the through holes 2 positioned at each side position of the built-in special-shaped frame 1 are connected with mounting binding rings 3, the edge ends of the through holes 2 positioned at the top and bottom positions of the built-in special-shaped frame 1 are connected with binding edge plates 4, protective rings are conveniently bonded on the outer side of the mounting binding rings 3 and the edge parts of the binding edge plates 4 through adhesive tapes, each edge part of the outer side of the built-in special-shaped frame 1 is conveniently protected, meanwhile, the protective rings are conveniently and rapidly bound on the outer side of the built;

the top corners of all the edges of the outer side of the built-in special-shaped frame 1 are fixedly connected with positioning end plates 6, the middle ends of the inner sides of the positioning end plates 6 are provided with through holes 7 in a penetrating mode, threaded connecting rods 8 are embedded and connected in a fit mode in the through holes 7, inner threaded grooves are formed in the inner sides of the through holes 7, the through holes 7 are connected with the threaded connecting rods 8 in a fit mode in a penetrating mode through the inner threaded grooves in the through holes 7 in a penetrating mode, connection between the threaded connecting rods 8 and the through holes 7 is facilitated, meanwhile, stepless adjustment of the positions of the threaded connecting rods 8 in the through holes 7 is facilitated, movable knobs 9 are fixedly connected to one ends of the threaded connecting rods 8, balance constraint pull ropes 10 penetrate through the middle portions of the inner sides;

the inner side of the built-in cavity 5 is connected with a shuttle-shaped stabilizer 12 in a suspension way through a balance constraint stay cord 10, the middle ends of the two side edge parts of the shuttle-shaped stabilizer 12 are symmetrically connected with balance connecting rods 13, the length and the size of the balance connecting rods 13 positioned at the middle ends of the two side edge parts of the shuttle-shaped stabilizer 12 are the same, the end parts of the two balance connecting rods 13 are fixedly connected with threaded rods, the two sides of the shuttle-shaped stabilizer 12 and an aircraft shell are conveniently and fixedly connected through the threaded rods at the end parts of the two balance connecting rods 13, the edge parts of the shuttle-shaped stabilizer 12 and the balance constraint stay cord 10 are positioned on the same central axis and are correspondingly provided with connecting through holes 14, each vertex angle inside the built-in cavity 5 is connected with a limit rubber seat 15 through the limit rubber seat 15, the limit rubber seat 15 and the positioning end plate 6 are positioned on the same axis, and a cord hole is, the centre of a circle of rope hole and the centre of a circle of through hole 7 are located the same axis, conveniently will pass the inside balanced constraint stay cord 10 of location end plate 6 more accurate penetrate to spacing gluey seat 15 in, come the convenience through spacing gluey seat 15 to restrict the position of balanced constraint stay cord 10 simultaneously, and balanced constraint stay cord 10 passes the inside connection perforation 14 of shuttle-shaped stabilizer 12.

Shuttle stabilizer 12 is provided with two lamellas, and two lamella shuttle stabilizer 12 limit portion middle-ends all are through connecting collar 16 fixed connection, connect 16 limit portion equidistance of collar and seted up installation through-hole 17, and the inboard embedding of installation through-hole 17 is connected with fixing bolt 18, fixing bolt 18 is located installation through-hole 17, and fixing bolt 18 all passes and connects collar 16, conveniently carry out fixed connection with two lamella shuttle stabilizer 12 through connecting collar 16 and fixing bolt 18, the convenience is dismantled two lamella shuttle stabilizer 12 simultaneously.

The working principle and the using process of the invention are as follows: in practical use, the shuttle structure for the aircraft is characterized in that the two half shuttle-shaped stabilizers 12 are connected in an alignment way through the connecting and mounting rings 16 at the ends of the shuttle-shaped stabilizers 12, then the fixing bolts 18 are inserted into the mounting through holes 17, the fixing bolts 18 penetrate into the two shuttle-shaped stabilizers 12, and the two half shuttle-shaped stabilizers 12 are fixed through the fixing bolts 18;

then, one end of a balance binding pull rope 10 penetrates through the threaded connecting rod 8 and the movable knob 9, the balance binding pull rope 10 penetrates into the limiting rubber seat 15 through the through hole 7, then the balance binding pull rope 10 penetrates through the limiting rubber seat 15 and penetrates into the connecting through hole 14 in the shuttle-shaped stabilizer 12, one end of the balance binding pull rope 10 penetrates out of the connecting through hole 14, meanwhile, the end part of the balance binding pull rope 10 penetrates into the threaded connecting rod 8 and the movable knob 9 at the corresponding position, and finally, the two ends of the balance binding pull rope 10 are limited at the end part of the movable knob 9 through the limiting rope head 11, and in this way, the balance binding pull ropes 10 at the positioning end plates 6 are sequentially penetrated and bound;

after the shuttle-shaped stabilizer 12 is bound in the built-in special-shaped frame 1 in a suspension mode, the protective ring is bound and installed through the installation binding ring 3 and the binding side plate 4 on the edge of the built-in special-shaped frame 1, so that the protective ring is convenient to install, and elements on the outer side of the built-in special-shaped frame 1 and in the built-in special-shaped frame are convenient to protect through the protective ring;

finally, fix the both ends of shuttle stabilizer 12 respectively with between the aircraft casing through the balanced connecting rod 13 of the both sides limit end of shuttle stabilizer 12, and make built-in special-shaped frame 1 and the guard ring of its limit portion all arrange the aircraft casing in, make the aircraft casing can not rock it and transmit to built-in special-shaped frame 1 at the flight in-process, make rock after transmitting to shuttle stabilizer 12, the power that rocks is subdued through the balanced constraint stay cord 10 in the shuttle stabilizer 12 outside, and then guarantee that built-in special-shaped frame 1 possesses higher stability in the actual work in-process.

Finally, it should be noted that: although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that changes may be made in the embodiments and/or equivalents thereof without departing from the spirit and scope of the invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.