CN116691997A

CN116691997A - Heavy-load light aircraft

Info

Publication number: CN116691997A
Application number: CN202310628932.XA
Authority: CN
Inventors: 祁腾飞; 季宝锋; 吴禹錡; 安梦雷; 王非; 张亮; 刘千
Original assignee: Tianjin Istar Space Technology Co ltd
Current assignee: Tianjin Istar Space Technology Co ltd
Priority date: 2023-05-31
Filing date: 2023-05-31
Publication date: 2023-09-05

Abstract

The invention provides a heavy-load light aircraft, which comprises a fuselage, wings and a plurality of tail wings at the tail part of the fuselage, wherein the fuselage comprises a front fuselage part and a rear fuselage part, and the front fuselage part and the rear fuselage part are fixed through a butt joint frame; the front fuselage part comprises a front fuselage inner frame and a front fuselage outer skin structure, the rear fuselage part comprises a rear fuselage inner frame and a rear fuselage skin structure, and two tail wing connectors are symmetrically arranged on the rear fuselage inner frame; the wing comprises a wing main body and an aileron, wherein the wing main body comprises a wing skeleton and a wing outer skin structure; the aileron comprises an aileron body and aileron rib boxes arranged at two ends of the aileron body; the tail fin comprises a stabilizer provided with a mounting groove at the rear side, a control surface is arranged in the stabilizer mounting groove, and the control surface is driven by a transmission shaft. The invention utilizes the composite material to the greatest extent for light weight design, adopts the metal material for reinforcement at the key stress part, and has the advantages of light weight, maneuvering performance and aerodynamic performance, good durability and ensured service life.

Description

Heavy-load light aircraft

Technical Field

The invention belongs to the technical field of aerospace, and particularly relates to a heavy-load lightweight airplane.

Background

With the development of aviation technology, whether it is civil aircraft or military aircraft, not only is the aircraft required to have a reliable service life, but also good stealth performance and good maneuvering performance are required for practical application requirements such as combat, investigation, survey and the like or considering the influence of fuselage resistance. Generally, the lift force generated by the fuselage is small, but the zero lift resistance is large, so that the maximum cross-sectional area of the fuselage which is as small as possible is beneficial to improving the performance of the aircraft. However, as the cross-sectional area of the fuselage decreases, the resultant structural strength and stability issues are more pronounced, and although lightweight designs have been considered in the prior art, such as those disclosed in CN 109484609A, CN 214002025U and CN 102167155B, these aircraft or aircrafts have been investigated for stealth performance and maneuver performance, which have not met the ever-increasing performance requirements of modern use. In particular, for a fixed wing aircraft manufactured by adopting or containing a composite structural member, the stealth performance and the maneuvering performance of the fixed wing aircraft are very dependent on the structural design of the fuselage and the wing, and in general, only one performance requirement can be met in a focused manner, so that the aspects of light weight, aerodynamic performance, stealth performance and maneuvering performance cannot be simultaneously considered. Accordingly, there is a need for rational improvement over existing aircraft products.

Disclosure of Invention

In view of the above, the invention aims to overcome the defects in the prior art, and provides a heavy-load light aircraft, which has the advantages that the reasonable structural member design is adopted, the composite material is utilized to replace metal parts to the maximum extent, the light weight and weight reduction design effect is obvious, and simultaneously, the aerodynamic performance, the stealth performance and the maneuvering performance are improved.

In order to achieve the above purpose, the technical scheme of the invention is realized as follows:

a heavy-load light aircraft comprises a fuselage, wings on two sides of the fuselage and a plurality of tail wings on the tail of the fuselage; the machine body comprises a front machine body part and a rear machine body part, the front machine body part and the rear machine body part are fixed through a butt joint frame, the butt joint frames can be arranged on the front machine body and the rear machine body, the butt joint frames are provided with connecting holes, and the butt joint frames of the front machine body part and the rear machine body part are fixed through connecting pieces penetrating through the connecting holes;

as shown in fig. 3, the front fuselage section includes a front fuselage inner frame and a front fuselage outer skin structure outside the front fuselage inner frame, the front fuselage inner frame includes a front fuselage frame and longitudinal elements at the periphery of the front fuselage frame, and two sets of wing connectors are symmetrically mounted on the front fuselage frame; the front fuselage frame comprises a front fuselage butt joint frame, a front fuselage front reinforcing frame, a wing front connecting frame, a wing rear connecting frame and a front fuselage middle reinforcing frame which are sequentially arranged forwards along the fuselage; the front fuselage butt joint frame is connected with the front fuselage front reinforcement frame, the front fuselage front reinforcement frame is connected with the wing front connection frame, the front fuselage butt joint frame is connected with the wing front connection frame, and the wing front connection frame is connected with the wing rear connection frame through short trusses; the longitudinal element comprises a plurality of front fuselage stringers arranged along the length direction of the fuselage, a front fuselage butt joint frame, a front fuselage front reinforcing frame and a front fuselage middle reinforcing frame, which are all fixed with the front fuselage stringers at the same time, and the outer edges of the front fuselage butt joint frame, the front fuselage front reinforcing frame and the front fuselage middle reinforcing frame are all provided with flanging structures attached to the front fuselage outer skin structure.

As shown in fig. 4 to 7, the rear fuselage section includes a rear fuselage inner frame and a rear fuselage skin structure outside thereof, and two tail wing connection joints are symmetrically installed on the rear fuselage inner frame; the rear fuselage inner frame comprises a rear fuselage butt joint frame, a first reinforcing frame, a second reinforcing frame, a first bulkhead and a second bulkhead which are sequentially arranged backwards along the fuselage, wherein the butt joint frame, the first reinforcing frame, the second reinforcing frame, the first bulkhead and the second bulkhead are all provided with flanging structures; the butt joint frame is connected with the first reinforcing frame through a plurality of rear fuselage stringers; the tail wing connector comprises a connector body, wherein a vertical tail connecting part and a horizontal tail connecting part are arranged on the connector body;

as shown in fig. 8 to 12, the wing includes a wing main body and an aileron installed in a wing main body installation slot, and the wing main body includes a wing skeleton and a wing outer skin structure outside the wing skeleton; the wing framework comprises a longitudinal member unit and a transverse member unit, wherein the longitudinal member unit comprises a front beam, a middle beam and a rear beam, the front beam and the middle beam and the rear beam are arranged at an acute angle, and the transverse member unit comprises a plurality of ribs arranged between the front beam and the middle beam, between the middle beam and the rear beam and at one side of the front beam towards the front of the fuselage; spar connectors for connecting with the fuselage are arranged on the front beam, the middle beam and the rear beam, and the spar connectors extend out of the large open ends of the outer skin structure; a metal reinforcing rib is arranged between the front beam and the middle beam; the side surfaces of the front beam, the middle beam, the rear beam, the wing ribs and the metal reinforcing ribs are all attached to the inner surface of the wing outer skin structure;

As shown in fig. 12, the aileron includes an aileron body and aileron rib boxes mounted at two ends of the aileron body, and a trailing edge strip is arranged at the trailing edge position of the aileron body; the aileron body comprises a foam sandwich and an aileron outer skin structure outside the foam sandwich, a metal rotating shaft is penetrated in the foam sandwich, and metal joints are respectively arranged at two ends of the metal rotating shaft; the metal rotating shaft is connected with a transmission rotating shaft, and is connected with a steering engine short shaft through the transmission rotating shaft, so that the control power transmission is realized; the middle part of the metal rotating shaft is provided with a spherical bearing, and a bearing avoiding hole is formed in the aileron outer skin structure; the two metal joints are respectively fixed on the corresponding aileron rib boxes;

13-19, the tail fin comprises a stabilizer, wherein the rear side of the stabilizer is provided with a mounting groove, a control surface is arranged in the mounting groove, and the control surface is driven by a transmission shaft; the stabilizer comprises an inner framework and a skin structure outside the inner framework, wherein the inner framework comprises a front beam and a rear beam, and a plurality of reinforcing ribs are arranged between the front beam and the rear beam.

Further, at least one bulkhead is uniformly distributed on one side of the nose between the front fuselage front reinforcing frame and the wing front connecting frame, between the wing front connecting frame and the wing rear connecting frame, between the wing rear connecting frame and the front fuselage middle reinforcing frame and between the front fuselage middle reinforcing frame, and each bulkhead is fixed with a frame structure corresponding to at least one side through a short truss.

Further, be equipped with a plurality of connecting holes on the second reinforcing frame to be equipped with additional strengthening in the second reinforcing frame position that is close to the connecting hole, the fin connector is fixed with the second reinforcing frame through the fastener of wearing to locate the connecting hole.

Further, under the condition that the tail part of the machine body is provided with a vertical tail, two ends of the first reinforcing frame are respectively provided with a U-shaped section joint for fixing the vertical tail, and the U-shaped section joint is usually fixed with a machine body connecting structure on the vertical tail.

Further, the reinforcing rib comprises a rib plate, and U-shaped reinforcing members are respectively arranged at two sides of the rib plate; one end of the front beam is provided with a T-shaped front beam butt joint section, and the other end of the front beam is provided with a machine body connecting structure; the machine body connecting structure is U-shaped and comprises a main body and side plates at two sides of the main body, and a plurality of connecting holes are respectively arranged on the main body and the side plates at two sides of the main body;

the front Liang Hengjie is U-shaped and comprises front beam side plates at two sides of a front Liang Tiji front beam body; one end of the back beam is provided with a T-shaped back beam butt joint section, and the other end of the back beam is provided with an outer suspension section; the rear Liang Hengjie is U-shaped and comprises rear beam side plates at two sides of a rear Liang Tiji rear beam body; the rear beam butt joint section and the front beam butt joint section are positioned on the same side of the inner framework and are simultaneously fixed on the wingtip box;

The rear beam butt joint section is of a U-shaped structure, and comprises rear beam butt joint plates which are arranged at the tail ends of two rear beam side plates respectively, the outer surfaces of the rear beam side plates are protruded out of the outer surfaces of the corresponding rear beam butt joint plates, and after the wingtip box is assembled on the framework, the two side surfaces of the wingtip box are respectively flush with the corresponding front beam side plate surfaces.

Further, a vertical plate is arranged between the two back beam butt joint plates, a butt joint tail plate is arranged on one side of the back beam butt joint plate, facing the back beam side plate, of the back beam butt joint plate, the outer surface of the butt joint tail plate is lower than that of the back beam butt joint plate, a positioning step is formed between the two, when the back beam butt joint section is inserted into the tail end of the back beam, the tail end of the back beam side plate abuts against the positioning step, the butt joint tail plate is attached to the back beam side plate, and then a reinforcing structure is formed at the joint of the butt joint tail plate and the back beam side plate.

Further, the front beam butt joint section comprises front beam butt joint plates respectively arranged at the tail ends of the two front beam side plates, and the outer surfaces of the front beam side plates are protruded out of the outer surfaces of the corresponding front beam butt joint plates.

Further, the spar connecting head is provided with a joint end lug, the lug is provided with a plurality of connecting holes, and the axial direction of the connecting holes is perpendicular to the plane of the longitudinal member unit.

Further, the spar connectors comprise connection parts in a shape of a Chinese character kou, and the front beam, the middle beam and the rear beam are spliced with the corresponding spar connectors and fixed through gluing.

Further, the cross sections of the front beam, the middle beam and the rear beam are all in a shape of a Chinese character kou.

Compared with the prior art, the invention has the following advantages:

the invention has simple and reliable structure, clear force transmission paths of main structural members such as a fuselage, a wing and the like, greatly improves the maneuverability of the whole aircraft, utilizes the composite material to carry out light weight design to the greatest extent, adopts the metal material to strengthen the stress key part, has good durability and ensured service life, ensures the technical requirements of appearance, strength and weight, and simultaneously can improve the production efficiency and reduce the production cost.

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 invention and do not constitute an undue limitation on the invention. In the drawings:

FIG. 1 is a schematic diagram of the structure of the present invention;

FIG. 2 is a schematic diagram of the invention in a disassembled state with the main components;

FIG. 3 is an exploded view of the front fuselage section of the present invention;

FIG. 4 is a schematic view of a connector in a rear fuselage section in accordance with the present invention;

FIG. 5 is an exploded view of the inventive aft fuselage section;

FIG. 6 is a schematic view of a first stiffener frame in an aft fuselage section according to the present disclosure;

FIG. 7 is a schematic illustration of a second reinforcing frame in an aft fuselage section created in accordance with the present invention;

FIG. 8 is a schematic view of an inventive airfoil;

FIG. 9 is a schematic view of a side of a large open end of a wing in accordance with the present invention;

FIG. 10 is a schematic illustration of the invention in an exploded configuration of a wing;

FIG. 11 is a schematic illustration of the invention creating a wing skeleton portion with an aileron mounted thereto;

FIG. 12 is an exploded view of the inventive aileron portion;

FIG. 13 is a schematic view of the tail of the present invention;

FIG. 14 is a schematic view of the invention in an exploded configuration;

FIG. 15 is a schematic view of the invention creating an inner backbone portion of the tail;

FIG. 16 is a schematic view of the tail back beam portion of the present invention;

FIG. 17 is a schematic view of the present invention creating a butt section portion of the tail boom;

FIG. 18 is a schematic view of the present invention creating a tail reinforcement rib section;

fig. 19 is a schematic view of a front beam portion of an inventive embodiment of the present invention.

Detailed Description

It should be noted that, without conflict, the embodiments of the present invention and features of the embodiments may be combined with each other.

In the description of the invention, it should be understood that the terms "center," "longitudinal," "transverse," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate orientations or positional relationships that are based on the orientation or positional relationships shown in the drawings, merely to facilitate describing the invention and simplify the description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be configured and operate in a particular orientation, and therefore should not be construed as limiting the invention. Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first", "a second", etc. may explicitly or implicitly include one or more such feature. In the invention, the metal parts are adopted except for few parts which are easy to generate stress concentration, such as the wing joint, the tail joint, the rib box and the like, and the rest parts can be made of composite materials, so that the invention has the advantages of simple molding, simplified process, high manufacturing efficiency, effective control of cost and obvious light weight design advantage.

In the description of the invention, it should be noted that, unless explicitly specified and limited otherwise, 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; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. By way of example, the parts of the front and rear fuselage frame structures of the invention where the specific connection between the structural members is not explicitly specified may be connected by connectors, or may be bonded, or may be connected by other means, so long as the structural members can be fixed or installed at the corresponding positions. The specific meaning of the above terms in the creation of the present invention can be understood by those of ordinary skill in the art in a specific case.

The invention will be described in detail below with reference to the drawings in connection with embodiments.

A heavy-load light-weight aircraft, as shown in fig. 1 to 19, comprises a fuselage, wings 3 on both sides of the fuselage, and a plurality of tail wings 4 on the tail of the fuselage; the machine body comprises a front machine body part 1 and a rear machine body part 2, the front machine body part and the rear machine body part are fixed through butt joint frames, the butt joint frames can be arranged on the front machine body and the rear machine body, the butt joint frames are provided with connecting holes, the butt joint frames of the front machine body part and the rear machine body part are fixed through connecting pieces (such as bolts) penetrating through the connecting holes, and the front machine body and the rear machine body are further fixed;

The front fuselage section comprises a front fuselage inner frame and its outer front fuselage outer skin structure comprising a front fuselage upper skin 112, a front fuselage lower skin 113. The front fuselage inner frame comprises a frame 11 and a longitudinal element on the periphery of the frame, the frame comprises a front fuselage butt joint frame 12, a front fuselage front reinforcing frame 13, a wing front connecting frame 14, a wing rear connecting frame 15 and a front fuselage middle reinforcing frame 16 which are sequentially arranged from the tail to the nose direction, at least one bulkhead 17 is uniformly distributed between the front fuselage front reinforcing frame and the wing front connecting frame, between the wing front connecting frame and the wing rear connecting frame, between the wing rear connecting frame and the front fuselage middle reinforcing frame and between the front fuselage middle reinforcing frame to one side of the nose. It should be noted that each spacer is fixed by the stringers to at least one side of the corresponding frame structure (e.g., stiffener, connector, interface).

The front fuselage butt joint frame is connected with the front fuselage front reinforcement frame, the front fuselage front reinforcement frame is connected with the wing front connection frame, the front fuselage butt joint frame is connected with the wing front connection frame, the wing front connection frame is connected with the wing rear connection frame through the short trusses 18, and the short trusses are prevented from being overlapped with the front fuselage long trusses, so that the frame integrity is better and the strength is higher.

The longitudinal element includes the long purlin 19 of several preceding fuselage that arranges along fuselage length direction, and preceding fuselage butt joint frame, preceding strengthening frame and preceding fuselage middle part strengthening frame all are fixed with long purlin of each preceding fuselage, and preceding fuselage butt joint frame, preceding strengthening frame and preceding fuselage middle part strengthening frame outer fringe all are equipped with the turn-ups structure of laminating with the outer skin structure of preceding fuselage. Through the connection and supporting function of the stringers and the stringers, the structural strength of the fuselage is increased, the working stress level is reduced, and the rigidity change tends to be gentle. The front fuselage outer skin structure bears the aerodynamic force of the fuselage, bears the shearing force and bending moment in the bending deformation of the fuselage, and bears the axial force caused by the bending moment together with the reinforcing frames, the connecting frames, the front fuselage stringers and the short stringers. Typically, the longitudinal members include four front fuselage stringers disposed about the upper left, lower left, upper right and lower right of the frame.

The longitudinal members are used for bearing axial force generated when the fuselage is bent, in addition, the stringers and the short stringers of each front fuselage have supporting effect on the skin, so that the critical stress of the stressed and sheared instability of the skin is improved, and the aerodynamic force born by the longitudinal members and acting on the skin is transferred to the reinforcing frame, the butt joint frame, the connecting frame and each bulkhead. Each bulkhead is used for maintaining the cross-sectional shape of the fuselage, and is also subjected to distributed pressure caused by bending deformation of the fuselage, and meanwhile, the bulkhead also plays a supporting role on the skin and the stringers.

The wing front connecting frame, the wing rear connecting frame and the spacer frame between the wing front connecting frame and the wing rear connecting frame are respectively provided with a wing connector 110, and the front fuselage front reinforcing frame and the front fuselage rear reinforcing frame are used as frames for connecting the recovery umbrella and bear instantaneous concentrated loads caused by interaction of air resistance of the recovery umbrella and aircraft flying speed when the recovery umbrella is opened. The butt-joint frame is used as a frame for mounting the engine and mainly bears the axial load of the engine and also bears the normal load brought by partial weight of the engine. In order to make the butt joint of the front and rear fuselage better connect, reduce the stress level of the joint, the butt joint bulkhead can be widened and thickened, and double rows of rivets are arranged during assembly.

The front fuselage middle reinforcing frame or the wing rear connecting frame is provided with the slots, the front fuselage stringers are provided with plugs 111 matched with the slots, and the combination degree among the components is high and the structural stability is good. As an example, the front fuselage outer skin structure is glue-riveted with the flange structures of the frames. The front fuselage outer skin structure is adhesively riveted to each stringer. The front fuselage outer skin structure is integrally formed by prepreg. Each stringer is integrally formed from a prepreg. During assembly, the skin structure, the spacer frames, the connecting frames and the flanging of the reinforcing frames are glued and riveted into a whole, and the flanging is connected with the skin to play a role in crack arrest, so that longitudinal crack expansion under the action of hoop stress is prevented. In addition, the outer surfaces of the front fuselage stringers and the short stringers are all flush with the corresponding frames, the skin structure is firmly attached to the frames, and cracks are effectively prevented from being generated at the joints of the fuselage when the fuselage is subjected to external pressure.

The rear fuselage section comprises an inner frame 21 and a skin structure outside the inner frame, and two tail connectors 22 are symmetrically arranged on the inner frame; the skin structure comprises an upper skin 23 on the upper side of the inner frame and a lower skin 24 on the lower side of the inner frame; the inner frame comprises a butt joint frame 25, a first reinforcing frame 26, a second reinforcing frame 27, a first bulkhead 28 and a second bulkhead 29 which are sequentially arranged backwards along the course, and the butt joint frame, the first reinforcing frame, the second reinforcing frame, the first bulkhead and the second bulkhead are provided with flanging structures 210; the butt joint frame is connected with the first reinforcing frame through a plurality of rear fuselage stringers 211, a plurality of connecting holes 212 are formed in the second reinforcing frame, and reinforcing structures 213 are arranged at positions, close to the connecting holes, of the second reinforcing frame. The fin connector is fixed with the second reinforcing frame through a fastener penetrating through the connecting hole. In the practical application process, the reinforcing frame or the bulkhead serving as the key bearing part can be made of a metal material, the reinforcing frames and the bulkhead at other parts can be made of a composite material, and the composite material is used for replacing the metal material, so that the structural member is formed and manufactured, and meanwhile, the lightweight design is realized.

The tail connector comprises a connector body 215 which is fixed to the second reinforcing frame through fasteners. The joint body is provided with a vertical tail connection 216 and a horizontal tail connection 217. The machine body connecting structure of the horizontal tail is directly fixed with the connecting part of the horizontal tail. The butt joint frame, the first reinforcing frame, the second reinforcing frame, the first bulkhead and the flanging structure of the second bulkhead are all in glue riveting connection with the skin structure into a whole.

The top of the first reinforcing frame is connected with a joint of the engine and mainly bears normal load brought by the weight of the engine and also bears part of the axial load of the engine. Meanwhile, when the tail of the machine body is further provided with a vertical tail, two ends of the first reinforcing frame are respectively provided with a U-shaped section joint 214 for connection with the vertical tail. The machine body connecting structure of the vertical tail is directly fixed with the U-shaped section joint and is fixed with the outer suspension section through the horizontal tail connecting part, so that the bearing capacity of the tail wing structure is effectively improved. The first and second formers serve to maintain the cross-sectional shape of the fuselage, also subject to distributed stresses caused by bending deformation of the fuselage, and also to support the skin and the aft fuselage stringers. The first and second reinforcing frames spread the load of the load mass and other components, and the concentrated forces transferred to the fuselage structure through the joints are transferred to the skin in shear.

The skin structure is used as the aerodynamic shape of the fuselage, bears local aerodynamic force, and bears shearing force and bending moment in bending deformation of the fuselage, and (together with the stringer of the rear fuselage) bears axial force caused by the bending moment. The long purlin of back fuselage and butt joint frame, first reinforcing frame are integrated into one piece, or are glued fixedly, and the long purlin of back fuselage and butt joint frame, first reinforcing frame surface parallel and level, when effectively avoiding the organism to receive the external pressure, because of the long purlin turn-ups eccentric and produce the crackle of back fuselage.

The reinforcing structure comprises L-shaped reinforcing members, wherein the L-shaped reinforcing members are arranged on one side of the second reinforcing frame, which is different from the side with the flanging structure, so that the second reinforcing frame forms a T-shaped reinforcing structure at a position close to the connector. The connector is made of aluminum alloy materials, is used for being connected with a rear beam joint of the vertical tail wing and a front beam joint of the horizontal tail wing, can effectively ensure concentrated load brought by the horizontal tail wing and the vertical tail wing, and is not easy to damage, high in reliability and long in service life.

The butt joint frame, the first reinforcing frame, the second reinforcing frame, the first spacing frame and the second spacing frame are manufactured by prepreg through integral molding. Wherein, the butt joint frame, the first reinforcing frame and the second reinforcing frame are all thickened, thereby ensuring better structural strength. The rear fuselage stringers are arranged 16 on the periphery of the butt-joint frame. The structural strength of the rear fuselage is increased, the working stress level is reduced, and the rigidity change is smoothed.

The stringer is used as a longitudinal member of the fuselage structure and is mainly used for bearing axial force generated when the fuselage is bent, in addition, the stringer has supporting effect on the skin, the critical stress of the skin for compression and shear instability is improved, and the aerodynamic force born by the stringer and acting on the skin is transferred to the bulkhead. The longitudinal member in the fuselage structure effectively bears the axial force generated when the fuselage is bent, has supporting effect on the skin, improves the critical stress of the stressed and sheared instability of the skin, transmits the aerodynamic force born by the skin to the reinforcing frame, the butt joint frame, the connecting frame and each bulkhead, and has clear force transmission path of the fuselage structure, simple and reliable structure, light weight, low cost, convenient use and maintenance, good corrosion resistance and fatigue resistance, low crack expansion rate and adaptability to the working conditions of high strength and complex load condition.

The wing comprises a wing main body 31 and an aileron 32 arranged in a wing main body mounting groove, wherein the wing main body comprises a wing skeleton 33 and a wing outer skin structure 34 arranged outside the wing skeleton; the wing skeleton comprises a longitudinal member unit 35 comprising three spars, in particular a front spar 37, a centre spar 38 and a rear spar 39, each arranged at an acute angle between the front and centre spars and between the centre spar and the rear spar, and a transverse member unit 36 comprising a number of ribs 310 arranged between the front and centre spar, between the centre spar and the rear spar and on the side of the front spar facing forward of the fuselage. The wing skeleton is equipped with wing trailing edge strips 333 respectively in the position of being in wing main part mounting groove both sides, improves wing structure rear side intensity, guarantees aileron during operation stable in structure.

Spar connectors 311 for connecting with the fuselage are arranged on the front beam, the middle beam and the rear beam, and the spar connectors extend outwards from the large open ends of the outer skin structure; a metal reinforcing rib 312 is arranged between the front beam and the middle beam; the side surfaces of the front beam, the middle beam, the rear beam, the wing ribs and the metal reinforcing ribs are attached to the inner surface of the wing outer skin structure, so that the whole structure is stable, and the load conduction route is clear. Typically, the spar joint is made of an aluminum alloy material.

The aileron comprises an aileron body 313 and aileron rib boxes 314 arranged at two ends of the aileron body, and an aileron trailing edge strip 315 is arranged at the trailing edge position of the aileron body; the aileron body comprises a foam sandwich 316 and an aileron outer skin structure outside the foam sandwich, wherein a metal rotating shaft 319 is arranged in the foam sandwich in a penetrating way, and metal connectors 320 are respectively arranged at two ends of the metal rotating shaft. The metal joint is provided with a support plate 321 for supporting the foam sandwich. In an alternative embodiment, in order to ensure that the metal connector is stably matched with the foam sandwich, a clamping groove 322 is formed in the end part of the foam sandwich, the metal connector is matched with the clamping groove, and two ends of a connecting rod in the foam sandwich are matched with the metal connector, so that the aileron body structure is more compact, high in stability and higher in bearing capacity.

A transmission rotating shaft 323 is connected to the metal rotating shaft and is connected with a steering engine short shaft 324; a spherical bearing 325 is arranged in the middle of the metal rotating shaft, and a bearing avoidance hole 326 is arranged on the aileron outer skin structure; the two metal joints are respectively fixed on the corresponding aileron rib boxes.

The bearing seat 327 of the spherical bearing is fixed on the wing, and the short shaft is driven by the rotation of the steering engine, so that the short shaft drives the transmission shaft, and the aileron structure rotates around the axis of the metal rotating shaft, thereby realizing the rolling control of the airplane. The transmission rotating shaft is connected with the steering engine end shaft short shaft through a coupler. The metal rotating shaft, the transmission shaft and the steering engine end shaft are coaxially arranged.

The outside of the back beam is provided with the back beam reinforcing ribs 328, the transmission rotating shaft and the steering engine rotating shaft are respectively arranged on the corresponding back beam reinforcing ribs, the reliability of connection between the aileron and the wing main body is improved, and each back beam reinforcing rib is mainly used for bearing the concentrated force and moment on the aileron (fixed on the back beam) and transmitting and converting the concentrated force and moment into dispersion force to be transmitted to the back beam, so that the overall structure is more stable after loading. When the attitude control of the aircraft is carried out, the aileron can generate a large bending moment on the wing back beam under the action of pneumatic force, the back beam is integrally formed by a beam body with a mouth-shaped section, the structural strength and the rigidity are guaranteed, and when the bending moment is additionally applied by the aileron, the bending moment can be effectively transmitted to each rib box, so that the three-beam structure is effectively loaded, and the stability is good.

The aileron adopts the thin wall structure, and both ends are metal rib box, and the centre is the foam sandwich, has a metal pivot between two metal rib boxes, installs ball-type bearing in the middle of the metal pivot. The metal rotating shaft effectively improves the rigidity of the aileron body, and the metal connector is provided with the supporting plate for supporting the foam sandwich, so that the weight of main structural members is effectively reduced, the number of connecting pieces is reduced, and the weight of the whole aileron structure is further reduced.

The aileron outer skin structure includes an aileron upper skin 317 and an aileron lower skin 318, and the aileron upper skin, the aileron lower skin and the trailing edge strip are all made of prepreg. In an alternative embodiment, the metal joint, metal shaft, foam sandwich, spherical bearing, upper aileron skin, lower aileron skin, and trailing edge strip are overmoulded using co-cementitious moulding. Typically, the aileron rib box is secured to the metal fitting by a connector.

The wing spar connecting heads are respectively provided with a joint end lug 329 connected with a wing front connecting frame, a wing rear connecting frame and a spacer frame (upper wing connecting joint) between the wing front connecting frame and the wing rear connecting frame, the lug is provided with a plurality of connecting holes, the connecting holes are axially perpendicular to the plane of the longitudinal member unit, and connecting pieces 330 are arranged in the connecting holes in a penetrating mode. The metal reinforcing ribs may be provided in a plurality, at least one of which is arranged adjacent the spar joint. The connecting piece is perpendicular to the longitudinal component unit, when the skin is subjected to aerodynamic force, the skin flexes, and each spar and each rib provide a supporting reaction force for the skin, so that the skin is in a balanced state.

A part of the distributed load acting on the spar is balanced by the rib providing a counter-force and a part of the distributed load is balanced by the connection joint providing a counter-force. The connecting joint adopts lug design, lugs are vertically (horizontally) arranged, vertical shearing force and vertical bending moment are transmitted by shearing through bolts, horizontal shearing force is transmitted by lug extrusion, and horizontal bending moment is also transmitted by shearing through bolts. The aerodynamic force born by the wing needs to be transmitted to the fuselage by the connecting joints, so that the wall thickness of the spar connecting joints is larger than that of each spar, and the bearing capacity of the joint of the wing and the fuselage can be effectively improved by adopting the reinforced design, so that the damage caused by stress concentration is avoided.

In an alternative embodiment, the cross sections of the front beam, the middle beam and the rear beam are all in a shape of a Chinese character kou. The spar connectors comprise a connecting part 331 in a shape of a Chinese character kou, and the front beam, the middle beam and the rear beam are spliced with the corresponding spar connectors and fixed by gluing. Of course, in another alternative embodiment, the front beam, the middle beam and the rear beam may be fixed to the corresponding spar connectors by fixing members (such as screws), and the fixing manner may be flexibly selected according to actual needs.

Generally, the front beam, the center sill, the rear beam and the ribs are all made of prepreg. In an alternative embodiment, the front, center and rear beams are secured to a wing interface rib 332 at an end remote from the fuselage. The front beam, the middle beam, the rear beam and the wing ribs are adhered with the wing outer skin structure by using glue and fixed by using blind rivets. The wing spar connectors arranged at one ends of the three wing spars are connected with the fuselage, and the other ends of the three wing spars are fixed on the wing butt joint ribs, so that the tail ends of the three wing spars have better rigidity, and the wing is kept to have better overall performance. The wing provided by the invention adopts a three-beam structure, and each wing spar is shaped into a mouth section, so that each wing spar forms a multi-wall form, and the structure has the advantages of providing a higher centroid position and higher torsional rigidity and bearing bending moment and torque brought by a larger wing effective load.

In addition, because the wing spar is of a mouth-shaped section, the skin is connected with the upper surface and the lower surface of the wing spar, compared with the wing spar of other section shapes, the number of fasteners is reduced, the openings on the skin and the wing spar are reduced, the stress weakening and damage of the skin caused by the openings are reduced, the surface quality of the wing surface is improved, and the wing performance is better. The wing has high strength and good integrity, the joint of the wing and the fuselage adopts the spar connector made of metal materials, and the spar connector adopts a reinforced design, so that the bearing capacity of the wing is effectively improved, and the defect that the joint of the wing and the fuselage is easily damaged due to stress concentration when loaded is overcome. The aircraft attitude control can be effectively and reliably carried out through the aileron, and when the situation that the stress of the skin is discontinuous due to the large opening at the root of the wing is solved, aerodynamic force on the wing can still be transferred to the fuselage to balance the load of the fuselage.

The tail fin comprises a stabilizer 41, a mounting groove 42 is formed in the rear side of the stabilizer, a control surface 43 is arranged in the mounting groove, the control surface is driven by a transmission shaft 44, the outer edge of the control surface is flush with the rear edge of the stabilizer in a normal state, and the control surface is in streamline consistency with the outer surface of the stabilizer. The stabilizer includes an inner frame 45 and a skin structure 46 outboard of the inner frame structure. It should be noted that, in order to improve stability of the stabilizer after loading, the front side of the inner skeleton is provided with a front edge strip 427, the positions of the inner skeleton at two sides of the mounting groove are respectively fixed with a rear edge strip 428, and the inner wall of the skin structure is attached to the rear edge strip, the skeleton and the front edge strip, so that the force transmission route is clear.

The tail wing structure provided by the invention is 100% made of the composite material, fully utilizes the characteristics of high specific strength, high specific rigidity, good fatigue resistance and strong material designability of the composite material, integrally forms complex parts, greatly reduces the number of parts and the number of fasteners, and further reduces the weight of the structure. Therefore, the anti-flutter steel has the advantages of low manufacturing cost, high torsional rigidity, good anti-flutter effect, light structure weight and good economy.

The inner skeleton comprises a front beam 47 and a rear beam 48, a plurality of reinforcing ribs 49 are arranged between the front beam and the rear beam, one end of the front beam is provided with a T-shaped front beam butt joint section 410, the other end is provided with a machine body connecting structure 411, and the machine body connecting structure is fixed with a U-shaped section joint. The front beam butt joint section is positioned at one end close to the wing tip, and the machine body connecting structure faces one end of the machine body; one end of the back beam is provided with a T-shaped back beam butt joint section 412, and the other end is provided with an outer suspension section 413, and the outer suspension section is consistent with the main structure of the back beam in shape. The rear beam butt joint section and the front beam butt joint section are positioned on the same side of the inner framework and are simultaneously fixed to the wingtip box 414, and T-shaped butt joint sections are adopted among the front beam, the rear beam and the wingtip box, so that the connecting area is increased, the connection is firm, and the stress is stable.

In an alternative embodiment, the stiffening rib comprises ribs 429 on each side of which are arranged stiffening members of the U type, in particular, as shown in FIG. 18, comprising a member body 430 secured to the ribs, on each side 431 of which are intended to support the upper and lower skins of the skin structure, respectively. In a further improved scheme, the outer edge of the rib plate is concave between the two reinforcing members, namely the outer edge surface of the rib plate is lower than the outer edge surface of the side edge, so that the structural design ensures that the stiffening rib has good structural strength, and meanwhile, a buffer gap is formed between the two reinforcing members, namely, when the skin is loaded, a certain deformation is allowed between the two reinforcing members, and the reinforcing members limit the deformation of the skin to be diffused to other positions of the skin structure, so that the tail fin performance is better. The deformation gap between every two reinforcing ribs is larger than the buffer gap between the two reinforcing members, so that the local small deformation of the skin is allowed to be generated between the two reinforcing ribs, and the deformation quantity of the skin in the area is limited to be diffused by the two reinforcing ribs. A buffer gap and a deformation gap between two reinforcing members and between two reinforcing ribs form a two-stage limiting structure for limiting the deformation of the skin, so that the tail wing has excellent stability and high performance.

The inner skeleton of the invention adopts a double-beam structure, and in an alternative embodiment, the front beam butt joint section, the machine body connecting structure and the main body structure of the front beam are integrally processed and formed by prepregs. The main body structures of the rear beam butt joint section, the outer suspension section and the rear beam are integrally formed by prepreg. By way of example, the front beam is arranged at the chord length of 1/3, the rear beam is arranged at the chord length of 1/2, the reinforcing ribs, the front beam and the rear beam are assembled by gluing, and then are connected with the upper skin, the lower skin and the wing tip box by gluing rivets. Because the front beam and the rear beam have complex structures and high bearing requirements, the composite material forming process is utilized for production, the technical requirements of appearance, strength and weight can be ensured, the production efficiency can be improved, and the production cost can be reduced.

In an optional embodiment, the front beam is acute with the contained angle between the back beam, and the fuselage connection structure of front beam and the overhang section parallel arrangement of back beam also are equipped with a plurality of reinforcing ribs in front beam towards aircraft nose one side, and each reinforcing rib all perpendicular to the roof beam section of Liang Dangqian position in front, in addition front beam, back beam, reinforcing rib, leading edge strip and trailing edge strip effectively support the covering structure, and when the covering receives aerodynamic force, the fin atress direction is more clear and definite, and fin and fuselage force transmission are more balanced, and stability is better.

The control surface of the high-performance tail wing is assembled on the back beam of the stabilizer through the hinge seat, and the transmission shaft is connected with the steering engine rotated by the machine body, so that the control surface is driven to rotate around the shaft, and further the control is completed. The control surface is required to have high rigidity because the control surface is influenced by pneumatic load and has a possibility of occurrence of control reaction, but the control surface is required to have light weight because the center of gravity of the control surface is far away from the center of gravity of the airplane so as to better balance the center of gravity of the airplane, therefore, a reinforcing rod can be arranged in the inner cavity of the control surface along the length direction of the tail wing and is fixed with the two ends of the control surface, and the control surface can be driven to rotate when the reinforcing rod is driven to rotate by the transmission shaft through connecting the transmission shaft with the reinforcing rod. Therefore, the control surface formed by the prepreg can ensure rigidity and reduce self weight.

Generally, the body connecting structure is U-shaped and comprises a main body 417 and side plates 418 at both sides of the main body, and a plurality of connecting holes 419 are respectively formed in the side plates at both sides of the main body. Adopt fuselage connection structure for the local size of front beam grow to main part and curb plate all thicken and handle, fin and fuselage junction bearing capacity are better. In an alternative embodiment, the transmission shaft is installed in the stabilizer inner cavity, one end penetrating into the installation groove is connected with the operation surface, an operation opening 415 is arranged on the upper skin of the skin structure corresponding to the transmission shaft, an operation opening cover 416 is installed on the operation opening, the operation opening cover is connected with the upper skin through a fastener, and the operation opening cover can be conveniently detached when the tail wing is installed or maintenance is needed.

In an alternative embodiment, the front Liang Hengjie is U-shaped and includes a front beam 420 and front beam side plates 421 on opposite sides of the front beam. The front beam butt joint section comprises front beam butt joint plates 422 respectively arranged at the tail ends of the two front beam side plates, and the outer surfaces of the front beam side plates are protruded out of the outer surfaces of the corresponding front beam butt joint plates. The rear Liang Hengjie is U-shaped and comprises a rear beam body 423 and rear beam side plates 424 on two sides of the rear beam body. The back beam butt joint section comprises back beam butt joint plates 425 which are respectively arranged at the tail ends of the two back beam side plates, and the outer surfaces of the back beam side plates are protruded out of the outer surfaces of the corresponding back beam butt joint plates, so that after the wingtip box is assembled on the framework, the two side surfaces of the wingtip box are respectively flush with the corresponding front beam side plate surfaces, namely the framework and the wingtip box are in streamline design, and are stably attached to the outer skin structure, and better stress is transferred.

Preferably, the back beam butt joint board is fixed directly through the riser for back beam butt joint section forms U type structure, bears the effect better, and be equipped with butt joint tailboard 426 towards one side of back beam curb plate at back beam butt joint board, butt joint tailboard surface is less than back beam butt joint board surface, form the location step between the two, when back beam butt joint section cartridge is terminal at the back beam, butt joint tailboard and back beam curb plate laminating, fixed back through gluing or connecting piece, butt joint tailboard and back beam curb plate junction obtains strengthening the framework, and back beam curb plate surface and back beam butt joint board surface parallel and level, effectively avoid stress concentration to cause the damage, and can effectively transfer the load, improve performance.

The outer surfaces of the two rear beam side plates and the two front beam side plates are made into molded surfaces so as to ensure stable fit with the inner surfaces of the upper skin and the lower skin, effectively ensure the pneumatic appearance requirement of the tail wing, and the skin structure is used as a main bearing aerodynamic member and is connected with the spar and the reinforcing rib through an adhesive and rivets. The skin structure flexes when subjected to aerodynamic forces, and the adhesive and rivet are pulled to provide a counter force to the skin, causing the skin to be in a balanced state. The inner framework formed by the front beam, the rear beam and each reinforcing rib has strong integrity, so the local stress of the skin structure is small, the skin is made of very thin composite materials, the performance requirement can be met, the weight of the whole structure of the tail wing is reduced, and the production cost is reduced. The empennage has reasonable design, clear force transmission path, good anti-corrosion performance, good fatigue resistance, low crack propagation rate and capability of bearing the working conditions of high strength and complex load conditions, and is also suitable for the product requirements of large-size empennages on the premise of convenient use and maintenance.

The above embodiments are merely preferred embodiments of the present invention and are not intended to limit the present invention, and any modifications, equivalent substitutions, improvements, etc. within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A heavy-load lightweight aircraft, characterized by: the wing-mounted aircraft comprises an aircraft body, wings on two sides of the aircraft body and a plurality of tail wings at the tail part of the aircraft body, wherein the aircraft body comprises a front aircraft body part and a rear aircraft body part which are fixed through a butt joint frame;

the front fuselage part comprises a front fuselage inner frame and a front fuselage outer skin structure, the front fuselage inner frame comprises a front fuselage frame and longitudinal elements at the periphery of the front fuselage frame, and two groups of wing connectors are symmetrically arranged on the front fuselage frame; the front fuselage frame comprises a front fuselage butt joint frame, a front fuselage front reinforcing frame, a wing front connecting frame, a wing rear connecting frame and a front fuselage middle reinforcing frame which are sequentially arranged forwards along the fuselage; the longitudinal element comprises a plurality of front fuselage stringers arranged along the length direction of the fuselage, and a front fuselage butt joint frame, a front fuselage front reinforcing frame and a front fuselage middle reinforcing frame which are all fixed with the front fuselage stringers;

the rear fuselage part comprises a rear fuselage inner frame and a rear fuselage skin structure, and two tail wing connectors are symmetrically arranged on the rear fuselage inner frame; the rear fuselage inner frame comprises a rear fuselage butt joint frame, a first reinforcing frame, a second reinforcing frame, a first bulkhead and a second bulkhead which are sequentially arranged backwards along the fuselage, wherein the butt joint frame, the first reinforcing frame, the second reinforcing frame, the first bulkhead and the second bulkhead are all provided with flanging structures; the butt joint frame is connected with the first reinforcing frame through a plurality of rear fuselage stringers; the tail wing connector comprises a connector body, wherein the connector body is provided with a vertical tail connecting part and a horizontal tail connecting part;

The wing comprises a wing main body and an aileron, wherein the wing main body comprises a wing skeleton and a wing outer skin structure; the wing framework comprises a longitudinal member unit and a transverse member unit, the longitudinal member unit comprises a front beam, a middle beam and a rear beam, and the front beam and the middle beam and the rear beam are arranged at acute angles; spar connectors for connecting with the fuselage are arranged on the front beam, the middle beam and the rear beam, and the spar connectors extend out of the large open ends of the outer skin structure;

the aileron comprises an aileron body and aileron rib boxes arranged at two ends of the aileron body; the aileron body comprises a foam sandwich and an aileron outer skin structure at the outer side of the aileron body, and a metal rotating shaft with metal joints installed at two ends is arranged in the foam sandwich in a penetrating manner; the two metal joints are respectively fixed on the corresponding aileron rib boxes;

the tail wing comprises a stabilizer provided with a mounting groove at the rear side, a control surface is arranged in the stabilizer mounting groove, and the control surface is driven by a transmission shaft; the stabilizer comprises an inner framework and a skin structure at the outer side of the inner framework, wherein the inner framework comprises a front beam and a rear beam, and a plurality of reinforcing ribs are arranged between the front beam and the rear beam.

2. A heavy-duty lightweight aircraft as claimed in claim 1, wherein: at least one bulkhead is distributed on one side of the nose towards the front frame, between the front frame and the rear frame, between the rear frame and the middle frame, and between the middle frame.

3. A heavy-duty lightweight aircraft as claimed in claim 1, wherein: be equipped with a plurality of connecting holes on the second reinforcing frame, the second reinforcing frame is close to the connecting hole position and is equipped with additional strengthening, and the fin connector is fixed with the second reinforcing frame through the fastener of wearing to locate the connecting hole.

4. A heavy-duty lightweight aircraft as claimed in claim 1, wherein: two ends of the first reinforcing frame are respectively provided with a U-shaped section joint.

5. A heavy-duty lightweight aircraft as claimed in claim 1, wherein: the reinforcing rib comprises a rib plate, and U-shaped reinforcing members are respectively arranged on two sides of the rib plate; one end of the front beam is provided with a T-shaped front beam butt joint section, and the other end of the front beam is provided with a machine body connecting structure; the machine body connecting structure is U-shaped and comprises a main body and side plates at two sides of the main body, and a plurality of connecting holes are respectively arranged on the main body and the side plates at two sides of the main body;

6. The heavy-duty lightweight aircraft of claim 5, wherein: a vertical plate is arranged between the two back beam butt joint plates, a butt joint tail plate is arranged on one side, facing the back beam side plates, of the back beam butt joint plates, the outer surface of the butt joint tail plate is lower than that of the back beam butt joint plates, a positioning step is formed between the two butt joint tail plates, when the back beam butt joint section is inserted into the tail end of the back beam, the tail end of the back beam side plates abuts against the positioning step, the butt joint tail plates are attached to the back beam side plates, and then a reinforcing structure is formed at the joint of the butt joint tail plates and the back beam side plates.

7. The heavy-duty lightweight aircraft of claim 5, wherein: the front beam butt joint section comprises front beam butt joint plates which are respectively arranged at the tail ends of the two front beam side plates, and the outer surfaces of the front beam side plates are protruded out of the outer surfaces of the corresponding front beam butt joint plates.

8. A heavy-duty lightweight aircraft as claimed in claim 1, wherein: the spar connecting head is provided with a joint end lug, the lug is provided with a plurality of connecting holes, and the axial direction of the connecting holes is perpendicular to the plane of the longitudinal member unit.

9. A heavy-duty lightweight aircraft as claimed in claim 1, wherein: the spar connectors comprise connection parts in a shape of a Chinese character kou, and the front beam, the middle beam and the rear beam are spliced with the corresponding spar connectors and fixed through gluing.

10. A heavy-duty lightweight aircraft as claimed in claim 1, wherein: the cross sections of the front beam, the middle beam and the rear beam are all in a shape of a Chinese character kou.