CN103770937B - The aircraft of vertical and STOL - Google Patents

Abstract

The aircraft of a kind of vertical and STOL, fuselage plane is flat, rectangular, and fuselage vertical section is wing profile shape, so fuselage also can produce lift during flight, and jointly praises aircraft with wing, and flight efficiency significantly improves。Flat, rectangular fuselage front and back respectively sets the lift wind wheel of an equal diameters, and reversion makes balance each other；Lift rotor diameter is big, and lift is also big, adopts large power long tubular ordnance engine in addition, it is possible to do the vertical of relatively large supersonic flight and short field aircraft；But without thousand degree of high temperature above air-flows that similar aircraft erupts downwards, therefore to the steel floor of airfield runway and aircraft carrier without damage。In a word, the relatively existing aeroplane performance of this aircraft is better, both can vertical lift, it is also possible to short distance is sliding runs landing。Can be used for the place not having airport or airfield runway very short, both can do military fighter aircraft and transporter, it is also possible to making aircarrier aircraft, range of application is wide, and domestic and abroad market prospect is considerable。

Description

VTOL and STOL aircraft

technical field

The invention relates to a "vertical and short take-off and landing aircraft". The fuselage plane of this aircraft is flat and rectangular, and the longitudinal section of the fuselage is in the shape of a wing section. The two fans have a large diameter and rotate in opposite directions, and the torque is self-balanced; because the diameter is large, the lift is also relatively large, so it can be used as a "vertical and short take-off and landing aircraft" that bears a large load ", this kind of aircraft can not only take off vertically, but also save fuel by short roll takeoff and landing. The aircraft of the invention can be used in places without airports or airports with very short runways, can be used for both military and civil purposes, and belongs to the technical field of aviation industry.

Background technique

So far, there are many types of vertical and short take-off and landing aircraft in the world.

The so-called vertical/short take-off and landing aircraft refers to aircraft that can take off and land vertically or within a short distance. The development of vertical/short take-off and landing aircraft is mainly due to military needs. The improvement of aircraft speed and performance has brought a big disadvantage, that is, the take-off and landing distances are also continuously lengthened, which is very unfavorable for the tactical and strategic use of military aircraft. Although the helicopter has the ability to take off and land vertically, its speed is too small and its ceiling is not high, so it is completely unsuitable for tasks such as air combat and large-scale bombing. Therefore, people realize that if the advantages of ordinary combat aircraft and helicopters can be combined to form an aircraft that can take off and land vertically or short distances, and can fly at high speed, then its military value will be greatly enhanced.

The mode that existing jet aircraft realizes vertical/short take-off and landing mainly is to make engine nozzle can turn, be used for lift when taking off, be used for propulsion when level flight. Several practical jet vertical/short take-off and landing aircrafts that have occurred have adopted the lift plus thrust engine scheme and the thrust steering engine scheme respectively. Today, only two truly successful vertical take-off and landing aircraft have reached the practical stage and are put into service. They are the Yak-38 "Blacksmith" of the former Soviet Union and the "Harrier" aircraft of the United Kingdom. The American F35 fighter jet belongs to the most advanced vertical and short take-off and landing aircraft. Although the research and development has basically passed, there are still many technical problems, and the high cost has caused the price to continue to rise, so it has not yet been mass-produced.

Contents of the invention

Aiming at some shortcomings of the existing vertical and short take-off and landing aircraft, the present invention provides an improved vertical and short take-off and landing aircraft. The characteristics of this vertical and short take-off and landing aircraft (hereinafter referred to as the aircraft) are: according to According to the principle of aerodynamics, the plane of the fuselage of this aircraft is a flat rectangle, and the longitudinal section of the fuselage is the shape of the wing section. A lift fan with equal diameter and the same speed is respectively set up at the front and rear of the fuselage. It rotates in the opposite direction, and the torque is self-balanced during flight; because the diameter is larger, the lift force is correspondingly larger, so it can be used as a "vertical and short take-off and landing aircraft" that bears a large load, which can not only lift vertically, but also short It can be used for both military and civilian purposes.

The technical scheme that the present invention solves its technical problem is as follows:

A vertical and short take-off and landing aircraft", which includes an orderly combination of components such as a cockpit, a fuselage, a lift wind wheel, a jet engine, a wing, a vertical tail, and a landing gear, and is characterized by: the longitudinal section of the fuselage Make the plane section shape, and fuselage can produce lift when flying in the air; The fuselage tail that is positioned at the fuselage back can rotate up and down and do horizontal empennage concurrently; It is beneficial to make a supersonic fighter and a supersonic military transport aircraft, and it is also beneficial to make a supersonic passenger transport aircraft, which may become an innovative alternative to the previously eliminated supersonic Concorde passenger transport aircraft.

The first example of the present invention is a military fighter plane, and the plane of the fuselage is arranged successively as a cockpit, a lift wind wheel, a cabin, a lift wind wheel, a fuel tank and a body tail from front to back. Bombs are placed in the cabin, the wings are installed above the cabin and stretched to both sides, and a jet engine is installed on each side of the fuselage. The wheel jets downward to lift the weight of the fuselage. The two lift wind wheels have larger diameters, the same diameter and rotate in opposite directions, so the torque is self-balanced during flight; because the diameter is larger, it can be achieved. Larger vertical and STOL fighter.

Second example of the present invention is military transport plane, and the plane layout of above-mentioned fighter plane is similar, just engine room does not place bomb, and changes cargo compartment. Because it is transporting goods and equipment, the overall dimensions of the transport aircraft are much larger than those of the fighter jets. In addition, in order to facilitate the stacking of goods and equipment on the floor in the cargo compartment, the cross-shaped bevel gear transmission rod system does not pass through the cargo compartment, and instead drives the front and rear two lift wind rotors to rotate from under the fuselage floor.

The third example of the present invention is a passenger transport aircraft, which is similar to the plane layout of the above-mentioned military transport aircraft, except that the cabin is not a cargo compartment and is changed to a passenger cabin. In addition to placing passenger seats in the cabin, it is also necessary to arrange food cabinets, luggage compartments and toilets for passengers.

Description of drawings

The present invention will be further described below in conjunction with the accompanying drawings and implementation examples.

Fig. 1 is the plane view of the fuselage of the vertical and STOL fighter of the present invention.

Fig. 2 is the longitudinal sectional view of the fuselage of the vertical and STOL fighter of the present invention.

Fig. 3 is the longitudinal section view of the landing gear compartment of the vertical and short take-off and landing fighter of the present invention.

Fig. 4 is the bottom view of the fuselage of the vertical and STOL fighter of the present invention.

Fig. 5 is a top view of the fuselage of the vertical and STOL fighter of the present invention.

Fig. 6 is the front view of the fuselage of the vertical and STOL fighter of the present invention

(Both the upper wind wheel cover and the lower wind wheel cover have been opened).

Fig. 7 is a fuselage side view of the vertical and STOL fighter of the present invention.

Figure 8 is a front view of the fuselage of the vertical and STOL fighter of the present invention.

(Neither the upper wind rotor cover nor the lower wind rotor cover is opened).

Fig. 9 is a plane view of the fuselage of the vertical and short take-off and landing cargo aircraft of the present invention.

Fig. 10 is a plane view of the fuselage of the vertical and STOL passenger transport aircraft of the present invention.

Fig. 11 is a longitudinal sectional view of the fuselage of the vertical and STOL passenger transport aircraft of the present invention.

Fig. 12 is a side view of the fuselage of the vertical and short take-off and landing passenger transport aircraft of the present invention.

In the figure 1. Radar cabin, 2. Cockpit, 3. Instrument cabin, 4. Front landing gear, 5. Engine room, 6. Fuselage, 7. Vertical tail, 8. Shaft, 9. Fuselage tail, 10. Fuel tank , 11. main landing gear, 12. fuselage tail handle, 13. hatch, 14. lift wind wheel, 15. wing installation center body, 16. jet engine, 17. cross bevel gear transmission rod system, 18. Downwind wheel cover, 19. Wing, 20. High-pressure air nozzle, 21. High-pressure air supply pipe, 22. Column, 23. Upwind wheel cover, 24. Passenger cabin, 25. Deflector, 26. Cargo compartment, 27. Bathroom , 28. Crew lounge.

detailed description

In the plane view of the fuselage of the present invention shown in Fig. 1, the plane of the fuselage 6 is rectangular, and the radar cabin 1, the cockpit 2, the lift wind wheel 14, the nacelle 5, and the cross bevel gear transmission rod system are arranged successively from front to back. 17, lift wind wheel 14, fuel tank 10 and fuselage tail 9. A jet engine 16 is respectively installed close to the fuselage 6 both sides, and the front landing gear 4 is arranged at the front two corners of the fuselage 6, and the main landing gear 11 is arranged at both sides of the lift wind wheel 14 near the back,

In the longitudinal section of the fuselage 6 shown in Figure 2, it can be seen that the radar cabin 1, the cockpit 2, the lift wind wheel 14, the nacelle 5, the cross bevel gear transmission rod system 17, the lift wind wheel Wheel 14, fuel tank 10 and fuselage tail 9. The fuel tank 10 and the fuselage tail 9 are connected by a rotating shaft 8, and the fuselage tail 9 can turn up and down around the rotating shaft 8. Wing 19 is to spread out to both sides from the wing installation central body 15 on the top surface of fuselage 9 . Vertical tail 7 is installed on the both sides top of fuselage 6 rear portion.

Shown in Fig. 3 is the retractable mode of front landing gear 4 and main landing gear 11.

Fig. 4 is the fuselage bottom view of this aircraft, can find out among the figure that each lift wind wheel 14 is blocked by two lower wind wheel covers 18, represents in the figure closed, so can't see the lift wind wheel 14, also in the figure It can be seen that the fuselage tail handle 12 is installed on the rear of the fuselage 6 through the rotating shaft 8 .

Fig. 5 is the top view of the fuselage of this aircraft, and among the figure, the wind wheel cover 23 of the lift wind wheel 14 has been opened, so the lift wind wheel 14 can be seen.

Fig. 6 is the front view of the fuselage of the aircraft of the present invention, shows that the upper wind wheel cover 23 of the lift wind wheel 14 has been opened, and its lower wind wheel cover 18 has also been opened, and the lower wind wheel cover 18 is horizontally slid and opened. At this time, the aircraft can take off vertically.

Shown in Fig. 7 is the side view of the fuselage of the aircraft of the present invention, in which the upper wind wheel cover 23 of the lift wind wheel 14 has been opened. The jet engine 16 is mounted against the lower surface of the wing 19 .

Be the front view of the fuselage of the aircraft of the present invention among Fig. 8, this moment, upper wind wheel cover 23 and lower wind wheel cover 18 have all been closed.

Fig. 9 is a plane view of the fuselage of the vertical and short take-off and landing cargo aircraft of the present invention. Its plane layout is similar to that of a fighter plane, except that the cabin 5 is not equipped with bombs, but the cargo compartment 26 has been changed. In addition, a hatch is added on each side for loading and unloading cargo.

Fig. 10 is a plane view of the fuselage of the vertical and STOL passenger transport aircraft of the present invention. It can be seen that the nacelle 5 is positioned in the middle of two lift wind wheels 14, and the nacelle 5 is designed by the cabin, and outside some seats are installed in it, two hatches 13 are also opened for personnel to enter and exit. There is wicket to lead to cockpit 2 from the lift wind wheel 14 limits of front. A toilet 27 and a cargo compartment 26 for stacking passenger luggage are arranged at the rear of the cabin.

Fig. 11 is the longitudinal section view of the fuselage of the vertical and short take-off and landing passenger transport aircraft of the present invention, the layout in the figure arranges the radar cabin 1, the cockpit 2, the lift wind wheel 14, the passenger cabin 24, the cross-shaped bevel gear successively from front to back The orderly arrangement of transmission rod system 17, lift wind wheel 14, fuel tank 10 and fuselage tail 9.

Fig. 12 is a side view of the fuselage of the vertical and short take-off and landing passenger transport aircraft of the present invention. It can be seen from the figure that people entering and exiting the cabin are all under the wing 19, and the wing 19 is very high, so it is very convenient for people to enter and exit the aircraft.

Claims (2)

1. A vertical and short take-off and landing aircraft, which mainly includes a cockpit, a lift wind wheel, a wing, a cabin, a cross-shaped bevel gear transmission rod system, a fuselage tail and an orderly combination of landing gear, and the cockpit protrudes The front of the flat fuselage, the plane of the fuselage is rectangular, the combined longitudinal section of the fuselage and the tail of the fuselage is the shape of the wing section, and the tail of the fuselage can be turned up and down around the rotating shaft on both sides of the fuel tank in the cabin and used as a flat tail; its characteristics are : The front and rear of the flat rectangular fuselage are equipped with a lift wind wheel with the same diameter, and the nacelle is located in the middle of the two lift wind wheels; the jet engines on both sides of the fuselage simultaneously drive the two lift wind wheels at the same speed through the cross-shaped bevel gear transmission rod system Rotate in the opposite direction; the wings extend from the wing installation center above the fuselage to both sides; the cross-shaped bevel gear transmission rod system can not only connect the front and rear two lift wind rotors in the cabin, but also pass through the cabin floor to The outside of the bottom plate of the nacelle is connected with the main shafts of the front and rear two lift wind wheels to make the floor in the nacelle flat; a pair of upper wind wheel covers that can be turned up and down are respectively installed on the upper fuselage surface of the two lift wind wheels. The lower surface of the fuselage is respectively equipped with a pair of lower wind wheel covers that can be horizontally retracted left and right. 2. A kind of vertical and short take-off and landing aircraft according to claim 1, characterized in that: two front landing gears are placed on the front two corners of the rectangular fuselage, and two main landing gears are on the back side of the cabin. The lift wind wheel, the tail of the fuselage is connected with the nacelle with a rotating shaft through the lifting lug of the tail of the fuselage.