WO1997007020A1 - A multi-winged aircraft - Google Patents

Abstract

The invention provides a multi-winged aircraft, the multi-winged aircraft according to the invention has two pairs of wings. A pair or rearwardly swept wings (2) is arranged in a front part of fuselage. A pair of forwardly swept wings (6) is arranged in a rear part of fuselage. The two pairs of wings are respectively arranged in upper and lower parts of fuselage, but not arranged in the same horizontal level. At their tips the forward wings join the tips of the pair of rearward wings by vertical fins having several functions or engines.

Description

 Compound wing aircraft

Technical field

 The present invention relates to an aircraft, and more particularly to a composite wing aircraft, that is, an aircraft provided with a swept-back wing and a forward-swept wing at the same time.

Background technique

 Currently, the aircraft adopts single straight wing, double straight wing, swept wing, variable wing, and some countries are currently studying forward swept wing technology. Among these wings, the single-straight wing and double-straight wing have good low-speed performance but poor high-speed performance. The swept wing has good high-speed performance, but low-speed performance is poor, and there is induced drag. In order to make the aircraft take into account both high-speed and low-speed performance, people have invented a variable-wing aircraft, but the wing structure of this aircraft is complicated and the weight is increased. Large, reduced strength performance. The forward-swept wing has better aerodynamic characteristics than the backward-swept wing, but its adoption is affected by the problem of aeroelastic divergence. Due to the current development of new materials and technologies, people have a preliminary approach to solve this problem to a certain extent, but it is impossible to adopt this technology on large aircrafts at present.

 In the next century, huge passenger aircraft will be in great demand. American and European manufacturers are developing this model. At present, there are mainly two technical solutions in the development of this project: one is to develop a wing-body complex aircraft; the other is to increase the size and wingspan of a traditional aircraft. The former scheme has not yet entered the implementation stage, while the latter scheme is restricted by the current airport facilities and cannot be arbitrarily enlarged.

 In flight, the entire weight of the fuselage affects the intersection of the wing and the fuselage, which has little effect on small aircraft, while large and medium-sized aircraft need to increase the fuselage and wing to meet the strength requirements. The use of strong materials, thereby greatly increasing the weight of the aircraft.

 Due to the limitation of carrier space, carrier-based aircraft often use foldable wings to increase the amount of aircraft. Compared with non-foldable wings of the same shape, this type of wing has a complicated structure, increased weight, and reduced insurance factor.

Due to the limitation of the current technical level, seaplanes have low wave resistance and slow flight speed. Because the bottom of the fuselage is designed to take into account the characteristics of the fluid on the water, it is designed into a boat shape, thereby reducing the aerodynamic characteristics therein. Summary of the invention

 The object of the present invention is to solve the above-mentioned shortcomings of existing aircraft, and provide a new type of aircraft that can satisfy both high and low speed performance, but has a relatively simple structure, a reasonable structure distribution, and a light weight. In order to achieve the above-mentioned object of the present invention, according to the present invention, The invention provides a composite wing aircraft including a fuselage, at least one engine, a vertical tail, a pair of horizontal tails, and a wing device, characterized in that the wing device includes two pairs of wings, a pair They are swept wings at the front of the fuselage. One pair is swept wings at the rear of the fuselage. The two pairs of wings are located above or below the fuselage, not at the same horizontal line. Corresponding wing tips are connected, the wing set under the fuselage of the two pairs of wings is set with an up-tilt, and the wing set above the fuselage is set with a down-tilt.

 Preferably, the respective wingtips of the two pairs of wings are connected by an engine, and the engines are located rearward of the wingtips of the swept wing in order to draw the spanwise flow that flows along the wingspan of the swept wings into the engine. This can not only increase the intake pressure of the engine, but also eliminate the induced resistance, thereby better improving the aerodynamic characteristics of the aircraft.

 Alternatively, the respective wing tips of the two pairs of wings are connected by a multifunctional vertical wing, and the front part of the multifunctional vertical wing is provided with the function of a winglet.

 When necessary, the rear part of the multifunctional vertical wing is also used as a vertical tail.

 The engine may be one of a piston propeller engine, a turboprop engine, a turbofan engine, and a turbojet engine.

 Preferably, the forward swept wing and the backward swept wing are used in combination with a duck wing and a side wing. The horizontal tail wing and the forward swept wing may be integrated into a whole.

 In one embodiment, the aircraft is a seaplane including a plurality of floating tanks, the swept-back wings are disposed below the front of the fuselage, and the swept-wings are disposed on the Above the rear of the fuselage, the engines are two engines mounted on the upper part of the tail, and the vertical tails are provided on both sides of the engine in a V shape.

 Preferably, the floating tank is provided at one or more of a fuselage, a wing root outside the fuselage, or a wing tip, and a lowermost part of the multifunctional vertical wing.

Due to the use of this composite wing, this aircraft has good aerodynamic characteristics. Two problems, and compared with single-wing aircraft, the structure distribution of this aircraft is more reasonable. Under the condition of ensuring the strength, it can greatly reduce the weight of the aircraft. Under the condition of ensuring lift or even increasing lift, Wingspan can be reduced. When used in seaplanes, it can increase the wave resistance of seaplanes.

Overview of the drawings

 The present invention is described in detail below with reference to the drawings and embodiments. In the drawings:

 1 to 3 show a first embodiment of the composite wing aircraft of the present invention, wherein FIG. 1 is a front view, FIG. 2 is a top view, and FIG. 3 is a side view, which shows a pair of forward swept wings and a pair of The wingtips of the swept wings are connected by an engine, respectively;

 4 to 6 show a modification of the first embodiment of the composite wing aircraft of the present invention, wherein FIG. 3 is a front view, FIG. 4 is a top view, and FIG. 5 is a side view, which shows a pair of front The wing tips of a swept wing and a pair of swept wing are connected by a multifunctional vertical wing respectively;

 7 to 9 show a second embodiment of the composite wing aircraft of the present invention, which is used for a seaplane, wherein FIG. 7 is a front view, FIG. 8 is a top view, and FIG. 9 is a side view. Best Mode of the Invention

 1 to 3 show a first embodiment of a composite wing aircraft of the present invention. This is a general military or civilian aircraft, which includes a fuselage 1, at least one engine 3, a pair of swept wings 2, A pair of swept wing flaps 5, a pair of forward swept wings 6,-a forward swept wing flap 7, a pair of horizontal tail fins 8, 8, (which can be connected to the forward swept wing as shown by the solid line in Fig. 1 The integrated horizontal tail wing 8 ′ or the separated horizontal tail wing 8), a vertical tail wing 9, a plurality of front wheels 10, and a plurality of rear wheels 11, are shown as dashed lines.

 The invention is characterized in that a forward swept wing and a backward swept wing 2 are simultaneously provided on one aircraft. In the embodiment shown in FIG. 1, the swept-back wings are disposed below the front of the fuselage, and the swept-wings 6 are disposed above the rear of the fuselage. Of course, the swept-back wing 2 can also be set above the fuselage, and the forward-swept wing 6 can be set below the fuselage. In short, the two pairs of wings are above and above the fuselage, and not on a horizontal line. The corresponding wing tips of the two pairs of wings are connected by an engine 3. The corresponding wing tips of the two pairs of wings can also be connected by a multifunctional vertical wing 4 respectively.

The engine 3 may be arranged at the rear of the wing tip of the swept wing, so as to draw the spanwise flow that flows along the wing span of the swept wing into the engine. In order to eliminate the induced resistance, the aerodynamic characteristics of the aircraft can be improved. Alternatively, the engine is installed at the wing root of the forward-swept wing of the aircraft, and the spanwise flow along the forward-swept wing spanwise direction can be drawn into the engine, thereby increasing the engine intake pressure. The wing or engine makes the aeroelastic divergence phenomenon of the forward swept wing and the aeroelastic convergence phenomenon of the back swept wing eliminated.

 In order to increase the strength of the wing, especially the strength of the wing of a seaplane, the wing at the upper part of the fuselage can be designed with a certain downward tilt, and the wing at the lower part of the fuselage can be designed with a certain upward tilt. .

 When the composite wing aircraft of the present invention is provided with a multifunctional vertical wing, the front part of the multifunctional vertical wing is designed according to the winglet winglet function, and the rear part of the multifunctional vertical wing can be placed here when necessary, so that the multifunctional vertical wing has a wingtip at the same time Winglets; vertical tails; strengthened forward and swept wing structure; balance the comprehensive functions of aeroelastic divergence and aeroelastic convergence of the forward and swept wings respectively.

 The engine of the aircraft of the present invention may be a piston propeller engine, or a turboprop engine, a turbofan engine, or a jet engine. The engine can be installed at the root of the wing (when using a jet engine) or at the tip of the wing. It can be installed on the forward or backward swept wings, or on both sides of the tail or on the upper part of the tail.

 The forward and backward swept wings can also be combined with duck wings and side wings to improve the aerodynamic characteristics of the aircraft.

 Figures 7-9 show a second embodiment of the composite wing aircraft of the present invention, which is a water-based composite wing aircraft. A pair of swept wings 2 is provided below the front of the fuselage, and a pair of swept wings 6 is provided above the rear of the fuselage. The two engines 3 are mounted on the upper part of the tail, and there is an engine air inlet 14 in front of the engine, and V-shaped tail fins 13 are arranged on both sides of the engine. The two engines share an air inlet, so that after entering the air inlet, the air will be biased to both sides. This structure has a great advantage in preventing bird collisions. The pontoon 12 may be provided at the wing root or at an appropriate position at the wing tip.

 The present invention has been described by way of illustrated embodiments, but these embodiments are not a limitation on the present invention. Various changes can be made within the scope of the present invention defined by the claims appended below, and the modifications should belong to The scope of the invention.

Claims

Rights request 1. A composite wing aircraft, comprising a fuselage (1), at least one engine (3), a vertical tail (9), a pair of horizontal tails (8, 8,), and a wing device (2, 5) It is characterized in that the wing device (2, 5) includes two pairs of wings, one is a swept wing (2) provided at the front of the fuselage, and one is a forward swept at the rear of the fuselage Wing (6), two pairs of wings (2, 6) are respectively arranged above or below the fuselage, not at the same horizontal line, the corresponding wing tips of the two pairs of wings are connected, and the wing provided under the fuselage of the two pairs of wings is set with a tilt angle The wings set above the fuselage are set with a downtilt.  2. The composite wing aircraft according to claim 1, characterized in that the corresponding wing tips of the two pairs of wings (2, 6) are each connected by an engine (3), and the engines are located at the wingtips of the swept wings. The rear position is used to draw the spanwise flow that flows along the spanwise direction of the swept-wing wing into the engine. This can not only increase the intake pressure of the engine, but also eliminate the induced resistance, thereby better improving the aerodynamic characteristics of the aircraft.  3. The composite wing aircraft according to claim 1, characterized in that the corresponding wing tips of the two pairs of wings (2, 6) are each connected by a multifunctional vertical wing (4), and the multiple The front of the functional vertical wing (4) is set to function as a winglet.  4. The composite wing aircraft according to claim 3, characterized in that the rear part of the multifunctional vertical wing (4) is used simultaneously as a vertical flying wing.  5. The composite wing aircraft according to claim 1, characterized in that said engine (3) is one of a piston propeller engine, a turboprop engine, a turbofan engine, and a jet engine.  6. The composite wing aircraft according to claim 1, characterized in that said forward swept wings (6), backward swept wings (2) are used in combination with duck wings and edge wings.  7. The composite wing aircraft according to claim 1, characterized in that said horizontal tail (8) and said forward swept wing (6) are integrated into a whole. 8. The composite wing aircraft according to claim 1, characterized in that said aircraft is a seaplane, comprising a plurality of floating tanks (12), and said swept-back wings (2) are provided on said aircraft In the lower part of the front part, the forward swept wing (6) is provided above the rear part of the fuselage, and the engine (3) is two engines, which are installed at the upper part of the tail. Said vertical tail (9) is provided on both sides of said engine (3) into a V shape. 9. The composite wing aircraft according to claim, characterized in that said floating tank (12) is provided at the fuselage (1), at the wing root outside the fuselage, or at the wing tip, and the multifunctional vertical wing (4 ) At one or more of the bottom.