CN103171764A - Perpendicular/short-distance lifting warplane with two retractable rotor wings - Google Patents

Abstract

A fighter capable of vertical or short take-off and landing, in addition to the components of a common fighter, it is also equipped with: rotor (1), vector tail nozzle (3), transmission mechanism (4), deceleration-clutch Mechanism (5), support truss (7), rotating shaft (6) arranged at the connection between the support truss (7) and the fuselage, rotor cabins (8) arranged on both sides of the fuselage, and cabins of the rotor cabin (8) The door (9) is fixedly connected to the slipstream rudder (10) on the support truss (7), so that the fighter can work in three different modes: vertical take-off and landing mode, short take-off and landing mode and cruise mode Works under one of the modals. In the vertical take-off and landing mode, the rotor expands outwards, and the vector tail nozzle is deflected downward by 90°, and the power is supplied to the rotor through the deceleration-clutch mechanism, and the power of the turbofan engine is reasonably distributed to the rotor and the vector tail nozzle. The nozzles jointly generate lift; in the short take-off and landing mode, the vector tail nozzles simultaneously generate forward thrust; in the cruise mode, the deceleration-clutch mechanism stops providing power to the rotor, and the support truss, slipstream rudder and rotor are received through the rotating shaft In the rotor compartment, close the hatch to maintain the original good aerodynamic shape of the fighter.

Description

V/STOL fighter with retractable twin rotors

technical field

The invention relates to a fighter jet capable of vertical or short-distance take-off and landing, and belongs to the technical field of fixed-wing aircraft design in aviation aircraft.

Background technique

Vertical take-off and landing and short take-off and landing technology, as one of the cutting-edge technologies in the development of fighter jets, have been developing continuously with the improvement of thrust vectoring system in recent decades. Compared with fighters that can only take off and land conventionally, fighters with V/STOL capabilities have the following advantages:

1. The reliance on airports is small, and it can take off and land at damaged airports and simple field airports. If necessary, it can even take off and land on roads, rooftops, and open spaces, greatly improving its survivability.

2. It is more suitable to be deployed on an aircraft carrier. It can take off and land on an aircraft carrier without a catapult, and at the same time can increase the number of aircraft on the aircraft carrier.

3. With the ability to hover, it is more suitable for special missions.

Since fighter jets mostly use turbojet or turbofan engines, such as the British "Harrier" type using F402-RR-406 turbofan engines, the efficiency of these two engines in the hovering phase is low, resulting in huge fuel consumption during the hovering phase, thus Seriously affect the voyage, and the ammunition load when using vertical take-off and landing is limited.

Contents of the invention

The present invention looks at the design of a fighter jet with vertical and short takeoff and landing (V/STOL) capabilities. In front of the fighter's center of gravity, two rotors are arranged on both sides of the fuselage, and the power of the engine is transmitted to the rotors, so that the rotors can directly generate lift. At the same time, the thrust direction of the turbofan engine can be changed by deflecting the vector tail nozzle, and all or part of the thrust can be transformed. For the lift, it works with the rotor to generate enough lift and balance the moment to realize the vertical or short take-off and landing under the direct force control in the vertical direction, so that the aircraft has the ability of vertical and short take-off and landing at the same time.

During the cruising phase of the fighter jet, the rotor can be stored in the rotor compartment on the side of the fuselage, so as not to affect the overall aerodynamic performance of the aircraft.

According to one aspect of the present invention, a fighter with vertical or short take-off and landing capability is provided, in addition to the components of the usual fighter, it is also equipped with: rotor, vector tail nozzle, transmission mechanism, deceleration-clutch mechanism , the support truss, the rotating shaft that is arranged on the support truss 7 and the fuselage connection, the rotor compartment that is arranged on both sides of the fuselage, the hatch of the rotor compartment, the slipstream rudder that is fixedly connected on the support truss, so that the fighter It can work in one of three different working modes: vertical take-off and landing mode, short take-off and landing mode and cruise mode.

According to one aspect of the present invention, a fighter with vertical or short-distance take-off and landing capability is provided. In addition to the components of the usual fighter, it is also equipped with: rotor, vector tail nozzle, transmission mechanism, deceleration-clutch Mechanism, supporting trusses, rotating shafts arranged at the connection between the supporting trusses and the fuselage, rotor cabins arranged on both sides of the fuselage, hatches of the rotor cabins, and slipstream rudders fixedly connected to the supporting trusses, so that the The fighter can work under one of three different working modes: vertical take-off and landing mode, short take-off and landing mode and cruise mode.

Description of drawings

Fig. 1 is a schematic top view of a fighter according to an embodiment of the present invention.

FIG. 2 is a schematic front view of the embodiment of the fighter jet shown in FIG. 1 .

FIG. 3 is a schematic side view of the embodiment of the fighter jet shown in FIG. 1 .

Reference signs:

[1]Rotor [2]Turbofan engine [3]Vector tail nozzle

[4] transmission mechanism [5] deceleration, clutch mechanism [6] rotating shaft

[7]Support truss [8]Rotor compartment [9]Hatch door

[10] slipstream rudder

Detailed ways

This scheme is modified on the basis of the currently commonly used fighter layout, so that it has the capability of vertical or short-range takeoff and landing. According to an embodiment of the present invention, the fighter is additionally equipped with a rotor 1, a vector tail nozzle 3, a transmission mechanism 4, a deceleration-clutch mechanism 5, a support truss 7, a rotor cabin 8 and a slipstream rudder 10. The specific layout according to an embodiment of the present invention is shown in Figs. 1-3.

The fighter layout according to an embodiment of the present invention supports three different operating modes of vertical take-off and landing, short take-off and landing and cruise, wherein:

- Vertical take-off and landing mode: rotor 1 spreads out, vector tail nozzle 3 deflects downward by 90° (Fig. 3), turbofan engine 2 provides power to rotor 1 through deceleration-clutch mechanism 5, and the power of turbofan engine 2 is reasonable Distributed to the rotor 1 and the vector tail nozzle 3, the rotor 1 and the vector tail nozzle 3 jointly generate lift to overcome gravity, and do not generate forward thrust.

During the VTOL phase:

1) Roll stability is maintained by controlling the pull difference between the two rotors 1.

2) Pitch stability is maintained by controlling the pull of rotor 1 and the thrust of turbofan 2.

3) Maintain heading stability by controlling the transverse deflection of the vector tail nozzle 3 and the slipstream rudder 10 fixedly connected to the support truss 7 .

-Short take-off and landing mode: During the take-off and landing stages, the rotor 1 spreads out and rotates under the drive of the turbofan engine 2, so that the rotor 1 directly generates lift, and the vector tail nozzle 3 is lowered at an appropriate angle to push the fighter jet to slide A certain lift is generated while running, and the lift directly generated by the rotor 1 and the turbofan engine 2 can replace part of the aerodynamic lift required for conventional take-off and landing, and reduce the minimum flight speed, thereby realizing short-distance take-off and landing. Usually, in order to overcome the nose-down moment during conventional takeoff and landing of fighter jets, the elevator deflects upwards, so the elevator produces negative lift. However, in this scheme, because the rotor 1 generates a large nose-up moment, it can balance the nose-down moment generated during take-off and landing with a high lift coefficient. , at the same time, the elevator can be deflected downward to generate positive lift, which further reduces the minimum flight speed of the aircraft.

During the STOL phase:

1) Roll stability is maintained by controlling the pull difference between the two rotors 1.

2) Pitch stability is maintained by controlling the pull of the rotor 1, the thrust of the turbofan engine 2 and the deflection of the elevator.

3) Maintain heading stability by controlling the slipstream rudder 10 and rudder fixedly connected to the support truss 7 .

4) The lift is jointly provided by the pulling force of the rotor 1, part of the thrust of the turbofan engine 2 and the aerodynamic force.

5) The forward thrust is provided by the turbofan engine 2.

- Cruise mode: when the aircraft enters the cruising phase, the power supply to the rotor 1 is stopped through the deceleration-clutch mechanism 5, and the support truss 7, the slipstream rudder 10 and the rotor 1 are received through the rotating shaft 6 at the connection between the support truss 7 and the fuselage In the rotor compartment 8 on both sides of the fuselage, and close the hatch 9 to keep the original good aerodynamic profile of the fighter. There is no difference between the fighter of this stage and the general fighter in this embodiment.

In order to make the fighter have a larger bomb load and fuel load, short take-off and vertical landing (STO/VL) can be used.

Advantages and effects of the present invention include

Compared with the existing fighter vertical take-off and landing technology, the present invention has the following advantages:

1 Additional light weight and small size. It has little impact on the cruise performance, stealth performance, maneuverability and other aspects of fighter jets.

2 has little influence on the position of the center of gravity of the aircraft.

3 The impact on the overall structure of the aircraft is small.

4 In low-speed situations such as vertical or short take-off and landing, the larger paddle area ensures that the lift efficiency of the rotor is theoretically higher than that of existing pure jet vertical take-off and landing fighters (such as: AV-8B Harrier fighter ) and ducted fan-assisted vertical take-off and landing fighters (such as F-35B), so part of the power of the jet engine is transmitted to the large rotor to generate lift more efficiently, thereby reducing fuel consumption and increasing lift, making the fighter more powerful. bomb load and range.

5 The structure is relatively simple, and the maintenance time per unit flight hour is greatly reduced.

In summary, the vertical and STOL technology of the present invention is a solution with excellent comprehensive performance.

Claims (5)

1. fighter plane that possesses the ability of V/STOL, it also adds except each assembly of common fighter plane:

Rotor (1),

Vector tail nozzle (3),

Transmission device (4),

Deceleration-engaging and disengaging gear (5),

Sub-truss (7),

Be arranged on the turning cylinder (6) of sub-truss (7) and fuselage junction,

Be arranged on the rotor cabin (8) of fuselage both sides,

The hatch door (9) in rotor cabin (8),

Be connected in the slip-stream rudder (10) on sub-truss (7),

Thereby make described fight function in vertical takeoff and landing mode, short take-off and landing (STOL) mode and the work under one of three kinds of different operation modes of mode of cruising.

2. according to claim 1 fighter plane is characterized in that:

Under vertical takeoff and landing mode, rotor (1) outwards launches, lower inclined to one side 90 ° of vector tail nozzle (3), provide power by deceleration-engaging and disengaging gear (5) to rotor (1), the power of fanjet (2) is reasonably allocated to rotor (1) and vector tail nozzle (3), jointly produce lift by rotor (1) and vector tail nozzle (3) and overcome gravity, do not produce thrust forward.

3. according to claim 1 and 2 fighter plane, is characterized in that

Described fighter plane also can be operated under the short take-off and landing (STOL) mode in take-off and landing stage, under short take-off and landing (STOL) mode, rotor (1) outwards launches, rotate under the driving of fanjet (2), make rotor (1) directly produce lift, owing to producing simultaneously larger nose-up pitching moment, but the balance high coefficient of lift combined is taken off, the nose-down pitching moment that produces when landing, make aircraft can adopt larger lift coefficient to take off, land, reduce minimum flying speed.

4. according to claim 1 and 2 fighter plane, is characterized in that

Under the mode of cruising, stop providing power to rotor (1) by deceleration-engaging and disengaging gear (5), by turning cylinder (6), sub-truss (7), slip-stream rudder (10) and rotor (1) are taken in rotor cabin (8), and shut hatch door (9) to keep the original good aerodynamic configuration of fighter plane.

5. according to claim 2 fighter plane is characterized in that:

Under vertical takeoff and landing mode:

-by controlling the poor roll stability of keeping of pulling force of two rotors (1),

-keep pitching stability by the pulling force of control rotor (1) and the thrust of fanjet (2),

-keep course stability by the horizontal lateral deflection of controlling vector tail nozzle (3) and the slip-stream rudder (10) that is connected on sub-truss (7), 6, fighter plane according to claim 3, it is characterized in that:

-by the poor roll stability of keeping of the pulling force of controlling two rotors 1,

-keep pitching stability by the pulling force of controlling rotor 1, thrust and the elevating rudder deflection of fanjet 2,

-slip-stream the rudder 10 and the yaw rudder that are connected on sub-truss 7 by control kept course stability,

-jointly provide lift by the pulling force of rotor 1, part thrust and the aerodynamic force of fanjet 2,

-provide forward thrust by fanjet 2.

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