CN215884054U

CN215884054U - High-load-ratio short-distance take-off and landing aircraft

Info

Publication number: CN215884054U
Application number: CN202120343841.8U
Authority: CN
Inventors: 李宸灏
Original assignee: Individual
Current assignee: Individual
Priority date: 2021-02-05
Filing date: 2021-02-05
Publication date: 2022-02-22
Anticipated expiration: 2031-02-05

Abstract

The utility model discloses a high-load-ratio short-distance take-off and landing aircraft, which comprises an aircraft body, a main wing and an empennage, wherein the main wing and the empennage are installed on the aircraft body, the main wing is composed of a framework and skins coated on the surface of the framework, the framework is composed of a main beam, an auxiliary beam and wing ribs, the main beam and the auxiliary beam are correspondingly connected and fixed through the wing ribs, the main beam is composed of an upper edge strip, a lower edge strip and foam filling, and the foam filling is filled between the upper edge strip and the lower edge strip. According to the utility model, the main beam and the auxiliary beam are arranged in the main wing of the aircraft, the main beam is designed into the upper edge carbon plate and the lower edge carbon plate, and the middle of the main beam is filled with the solid beam structure combined by high-strength PMI foam, so that the aircraft has the characteristics of light weight and high strength, compared with a structural frame beam, the aircraft tail wing can effectively prevent local instability of the wing, the reliability of the overall flight of the aircraft is improved, the aircraft tail wing is a full-motion horizontal tail and a vertical tail, the aircraft tail wing has the function of stabilizing course, the weight is as light as possible, and the practicability is higher.

Description

High-load-ratio short-distance take-off and landing aircraft

Technical Field

The utility model relates to the field of model airplanes, in particular to a high-load-ratio short-distance take-off and landing aircraft.

Background

Model airplanes are generally classified into two types, dynamic and static: the model is static for collection, display and the like, can not fly, and is a model which takes an airplane as an image and is reduced according to a certain proportion; the dynamic state can fly and can realize the control of the airplane by remote control and the like. Some existing dynamic model airplanes are also used for heavy-load flight.

The existing model plane has the key of flight capability, namely the main wing structure and the tail wing structure of the model plane, and the existing model plane has the defects of single main wing structure, large flight resistance, long sliding distance and poor carrying flight capability, so that the aircraft capable of realizing high-load-ratio short-distance take-off and landing is designed.

SUMMERY OF THE UTILITY MODEL

The utility model aims to solve the defects in the prior art and provides a high-load-ratio short-distance take-off and landing aircraft.

In order to achieve the purpose, the utility model adopts the following technical scheme: high load ratio short-distance take-off and landing aircraft, including the fuselage to and install main wing and the fin on the fuselage, the main wing comprises skeleton and the covering of cladding on the skeleton surface jointly, the skeleton comprises girder, auxiliary girder and rib board jointly, it is fixed to correspond through rib board connection between girder and the auxiliary girder, the girder comprises upper flange strip, lower flange strip and foam packing jointly, and the foam packing is filled between upper flange strip and lower flange strip, the fin sets up to move flat tail and vertical fin entirely.

As a further description of the above technical solution:

the fuselage sets up to 3K hollow carbon pipe, the shaft of fuselage divide into two sections front and back, anterior segment the shaft internal diameter of fuselage is the same with the shaft external diameter of back end fuselage, and passes through the bolt connection between the shaft of two sections fuselages front and back.

As a further description of the above technical solution:

the fuselage is connected in the lower surface middle part position of main wing relatively, the surface of whole skeleton of covering cladding.

As a further description of the above technical solution:

the wing ribbed slab is provided with the polylith in the frame body inside of skeleton, the polylith the front end of wing ribbed slab connects fixedly through the leading edge strip, the polylith the rear end of wing ribbed slab connects fixedly through the trailing edge strip.

As a further description of the above technical solution:

the width of the upper edge strip is twice that of the lower edge strip, and the foam filling is set to be PMI foam.

As a further description of the above technical solution:

the auxiliary beam is mainly a truss structure which is constructed by long tung beams and light wood webs.

The utility model has the following beneficial effects:

1. in the high-load-ratio short-distance take-off and landing aircraft, the main beam and the auxiliary beam are arranged in the main wing of the aircraft, the main beam is designed into the upper edge strip carbon plate and the lower edge strip carbon plate, and the middle of the main beam is filled with the solid beam structure combined by the high-strength PMI foam.

2. In the high-load-ratio short-distance take-off and landing aircraft, the tail wings of the aircraft are full-moving horizontal tails and vertical tails, so that the high-load-ratio short-distance take-off and landing aircraft has the advantages of course stabilizing function and high steering efficiency, and is light in weight as much as possible and high in practicability.

3. In the high-load-ratio short-distance take-off and landing aircraft, the main wing of the aircraft is internally of a rack type hollow structure, the self weight of the aircraft is lighter than that of the existing aircraft, and the requirement of high-load-ratio flight can be met.

Drawings

FIG. 1 is a top view of a high-duty-ratio short-range takeoff and landing flight platform design;

FIG. 2 is a semi-sectional view of a main wing of the high-load-ratio short-range takeoff and landing aircraft;

FIG. 3 is a skeleton diagram of a high-duty-ratio short-range take-off and landing aircraft;

FIG. 4 is a structural diagram of a main beam of the high-load-ratio short-range take-off and landing aircraft.

Illustration of the drawings:

1. a body; 2. a main wing; 3. a tail wing; 4. covering a skin; 5. a main beam; 6. a secondary beam; 7. a leading edge strip; 8. a trailing edge strip; 9. a rib plate; 10. an upper edge strip; 11. a lower edge strip; 12. a framework; 13. and (4) filling foam.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, 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.

In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention; the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance, and furthermore, unless otherwise explicitly stated or limited, the terms "mounted," "connected," and "connected" are to be construed broadly and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.

Referring to fig. 1-4, one embodiment of the present invention is provided: the high-load-ratio short-distance take-off and landing aircraft comprises an aircraft body 1, a main wing 2 and an empennage 3 which are installed on the aircraft body 1, an integral composition structure of the aircraft is provided, the main wing 2 is jointly composed of a framework 12 and a skin 4 coated on the surface of the framework 12, a basic structure of the main wing 2 is provided, the framework 12 is jointly composed of a main beam 5, an auxiliary beam 6 and a wing rib plate 9, the basic composition structure of the framework 12 is provided, the main beam 5 and the auxiliary beam 6 are correspondingly connected and fixed through a wing rib plate 9 to realize integral connection and fixation, the main beam 5 is jointly composed of an upper edge strip 10, a lower edge strip 11 and foam filling 13 to form a solid filling beam, the solid filling beam not only has lower quality, but also has stronger bending and shearing resistance and can improve the strength of the wings, and the foam filling 13 is filled between the upper edge strip 10 and the lower edge strip 11, and the tail fin 3 is arranged as a horizontal vertical tail and has the function of stabilizing the course.

The fuselage 1 is set as a 3K hollow carbon tube, the strength and the rigidity are high, the tube body of the fuselage 1 is divided into a front section and a rear section, the front loading and the rear connecting operation are respectively provided, the inner diameter of the tube body of the front section fuselage 1 is the same as the outer diameter of the tube body of the rear section fuselage 1, a premise is provided for butt joint, the tube bodies of the front section fuselage 1 and the rear section fuselage 1 are connected through a bolt, the simple, convenient and rapid connecting operation is realized, the fuselage 1 is relatively connected at the middle position of the lower surface of the main wing 2, the stability of the integral structure is ensured, the skin 4 coats the outer surface of the whole framework 12, a plurality of wing rib plates 9 are arranged inside the framework of the framework 12, the relative fixation of the main beam 5 and the auxiliary beam 6 is ensured, the front ends of the plurality of wing rib plates 9 are fixedly connected through the front edge strips 7, the rear ends of the plurality of the wing rib plates 9 are fixedly connected through the rear edge strips 8, the relative fixation among the plurality of the wing rib plates 9 is realized, the width of the upper edge strips 10 is twice that of the lower edge strips 11, the foam filling 13 is PMI foam, realizes the constitution of solid beam, and auxiliary beam 6 mainly adopts long purlin of tung wood, the mutual framed structure that founds of balsa web, and self quality is light, and the practicality is high.

The working principle is as follows: in the short distance take-off and landing aircraft with high load ratio, the main beam 5 and the auxiliary beam 6 are arranged inside the main wing 2 of the aircraft body 1, the main beam 5 is designed into an upper edge strip 10 carbon plate and a lower edge strip 11 carbon plate, a solid beam structure combined by high-strength PMI foam is filled in the middle, the aircraft has the characteristics of light weight and high strength, local instability of wings can be effectively prevented, the reliability of the overall flight of the aircraft is improved, the aircraft tail fin 3 is a full-moving horizontal tail and a vertical tail, the aircraft has the advantages of being high in course stabilizing function and rudder efficiency, light in weight and handy as much as possible, and high in practicability.

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 modifications may be made to the embodiments or portions thereof without departing from the spirit and scope of the utility model.

Claims

1. High load ratio short-distance take-off and landing aircraft, its characterized in that: including fuselage (1) to and install main wing (2) and fin (3) on fuselage (1), main wing (2) comprises skeleton (12) and cladding skin (4) on skeleton (12) surface jointly, skeleton (12) comprises girder (5), auxiliary girder (6) and rib board (9) jointly, it is fixed to correspond through rib board (9) connection between girder (5) and auxiliary girder (6), girder (5) are filled by last border strip (10), lower edge strip (11) and foam and are constituteed jointly (13), and foam is filled (13) and is filled between last border strip (10) and lower edge strip (11), fin (3) set up to move flat tail and vertical tail entirely.

2. The high duty ratio short take-off and landing aircraft of claim 1, wherein: fuselage (1) sets up to the hollow carbon pipe of 3K, the shaft of fuselage (1) is divided into two sections around, the anterior segment the shaft internal diameter of fuselage (1) is the same with the shaft external diameter of back end fuselage (1), and passes through the bolt connection between the shaft of two sections fuselage (1) around and.

3. The high duty ratio short take-off and landing aircraft of claim 1, wherein: the fuselage (1) is connected in the lower surface middle part position of main wing (2) relatively, the surface of whole skeleton (12) of covering (4) cladding.

4. The high duty ratio short take-off and landing aircraft of claim 1, wherein: the wing rib plate (9) is provided with the polylith inside the frame body of skeleton (12), the polylith the front end of wing rib plate (9) is connected fixedly through leading edge strip (7), the polylith the rear end of wing rib plate (9) is connected fixedly through trailing edge strip (8).

5. The high duty ratio short take-off and landing aircraft of claim 1, wherein: the width of the upper edge strip (10) is twice that of the lower edge strip (11), and the foam filling (13) is set to be PMI foam.

6. The high duty ratio short take-off and landing aircraft of claim 1, wherein: the auxiliary beam (6) is mainly a framework structure which is constructed by long tung wood beams and light wood webs.