CN108583859A - A kind of VTOL binary aircraft - Google Patents

Abstract

The invention relates to the technical field of aviation aircraft, in particular to a vertical take-off and landing catamaran aircraft. It is characterized in that it includes a right fuselage and a left fuselage in a symmetrical layout, the front ends of the right fuselage and the left fuselage are connected by a front canard, the rear ends of the right fuselage and the left fuselage are connected by a horizontal tail, the lower part of the right fuselage is provided with a landing gear, and the right fuselage The rear part is provided with a vertical tail, the upper part of the right fuselage is provided with an engine compartment, the front end of the engine compartment is set as an air inlet, the front and rear ends of the engine compartment are set as engine nozzles, and the engine compartment is equipped with an aircraft power system, and the aircraft power system passes through the power transmission mechanism. Connected to the paddle. It solves the balance problem of the main propeller torque through the symmetrical layout of the double body and the fixed-wing/rotor design that can rotate in opposite directions; the turbine engine that can perform mode conversion between the turboshaft mode and the turbofan mode realizes different The optimal thermal cycle in the flight state increases the maximum speed of the aircraft in level flight.

Description

A vertical take-off and landing dual-hull aircraft

technical field

The invention relates to the technical field of aviation aircraft, in particular to a vertical take-off and landing catamaran aircraft.

Background technique

More than a hundred years ago, the Wright Brothers' manned powered aircraft successfully flew. Until today, aviation technology has developed rapidly, and various new aircraft concepts continue to emerge, which have played a huge air superiority in wars. It has played a huge role in promoting the development of the national economy and has greatly changed people's way of life. Fixed-wing aircraft must rely on the runway to take off and land, while helicopters are not subject to this restriction, but the disadvantage is that its maximum cruising speed is usually 300km/h due to the limitation of rotor speed. If there is an aircraft that can take off and land helicopters and high-speed fixed-wing cruise advantages, it will have important uses in military and civilian fields.

Currently, there are three main types of vertical take-off and landing high-speed cruise aircraft, one is the British "Harrier" type, and the American F-35 fighter jet, which uses a turbofan engine with a rotating nozzle, which has low efficiency in the vertical take-off and landing state. , high fuel consumption; one is the U.S. tilt-rotor V-22 "Osprey". To a certain extent, the horizontal flight speed is reduced, and at the same time, the tilt rotor has high requirements on the reliability of the control system and control method; there is also a plan for Boeing's rotary wing X-50 "Dragonfly", whose wings can The rotation generates lift, and it can be locked and used as a fixed wing. The blade tip jet is used to drive the wing, and the rotor drive efficiency of this method is low.

The invention patent of publication number CN 106585976 A proposes a tilt rotor/lift fan aircraft layout, by installing a coaxial anti-propeller ducted lift fan at the front of the aircraft fuselage, and at the same time, a left-right symmetrical flat tail end at the rear of the fuselage The tilting rotor is installed to realize the vertical take-off and landing of the aircraft and realize the flight of the aircraft in the fixed-wing mode by the rotation of the tilting rotor in a plane perpendicular to the horizontal tail. The problem is the control complexity and lower safety that the tilt rotor brings. When the aircraft is converted from the vertical take-off and landing mode to the fixed-wing mode, it is necessary to coordinate the lift of the lift fan and the tilting rotor in the vertical direction to keep the center of gravity of the aircraft within a controllable range; the tilting rotor will also limit the aircraft in the fixed-wing mode level flight speed.

The invention patent of publication number CN 106882373 A proposes a compound tilting rotor helicopter, which uses a coaxial anti-propeller dual rotor (marker 1 in the figure) system as the main lift rotor, and adopts a tilting rotor and a tilting airfoil To realize the attitude control of the aircraft, to achieve the purpose of transitioning from vertical takeoff to level flight state. The problem is that the coaxial anti-propeller dual-rotor system still provides the main lift of the aircraft during straight flight, which greatly limits its flight speed in level flight; and the coaxial anti-propeller dual-rotor system has a complex structure, low reliability, and maintenance. and higher manufacturing costs.

The invention patent of Publication No. WO 2005/066020 A1 proposes a tilt-rotor aircraft, which can be tilted through a single tiltable axis to achieve the interchange between vertical take-off and landing and horizontal flight status of the aircraft. The position of the tilting axis and tilt directions can be changed and new scenarios generated from this. The problem is that the coaxial anti-propeller dual-rotor system has a complex structure, low safety, and limits its maximum level flight speed.

There are many technical solutions for vertical take-off and landing high-speed cruise aircraft in the prior art, but most of them have: (1) the low efficiency of the rotatable nozzle during vertical take-off and landing or the maximum speed limit caused by the rotor in level flight; (2) There are many adjustment and control mechanisms, and the control is complicated; (3) when balancing the torque of the main propeller, coaxial anti-rotor dual rotors are often used or symmetrical layouts are used but tilt rotors are used, which makes the structure complex and reduces safety.

Contents of the invention

The object of the present invention is to avoid the defects of the prior art and provide a vertical take-off and landing catamaran, which effectively solves the problems of the prior art.

In order to achieve the above object, the technical solution adopted by the present invention is: the described vertical take-off and landing dual-body aircraft, which is characterized in that it comprises a symmetrically arranged right body and a left body, and the front ends of the right body and the left body are connected by front canards, The rear ends of the right fuselage and the left fuselage are connected by a horizontal empennage. The lower part of the right fuselage is provided with a landing gear, the rear part of the right fuselage is provided with a vertical tail fin, the upper part of the right fuselage is provided with an engine compartment, and the front end of the engine compartment is arranged as an air inlet. The front and rear ends of the cabin are set as engine nozzles, and an aircraft power system is arranged in the engine compartment. The aircraft power system is connected with the blades through a power transmission mechanism. The aircraft power system includes an engine, and the power output shaft of the engine is connected with a clutch. The reducer is connected, the power output of the reducer is connected to the transmission shaft through the rotating shaft locking mechanism, and the transmission shaft is connected to the propeller hub.

The structure of the left body and the right body is arranged symmetrically, and the locking mechanism of the rotating shaft includes a positioning sleeve sleeved on the transmission shaft. The positioning sleeve is provided with a spiral groove, and a spiral rib is correspondingly provided in the spiral groove. The helical ribs are provided with a positioning bayonet, and an adjustment spring is provided under the positioning sleeve. The rotating shaft locking mechanism locks the propeller hub in the horizontal flight mode of the aircraft, so that the propeller blades are kept in a direction perpendicular to the aircraft body.

When the clutch disconnects the connection between the transmission shaft and the power output shaft, the shaft locking mechanism stops braking after the transmission shaft is reduced to a low rotational speed by braking, and the adjustment spring rises to push the positioning sleeve upward, and the transmission shaft The fixed spiral rib rotates into the spiral groove on the positioning sleeve, and after the spiral fin rotates to the bottom of the rotating groove, the positioning bayonet positions and locks the transmission shaft, so that the blade is fixed at a position parallel to the front canard; Before the clutch connects the transmission shaft and the power output shaft, the adjustment spring in the shaft locking mechanism moves downward and drives the positioning sleeve to rotate in reverse, and the spiral groove on the positioning sleeve is disengaged from the spiral rib on the transmission shaft , so that the rotating shaft locking mechanism does not affect the operation of the transmission shaft; the transmission shaft is connected to the reducer; the reducer is connected to the power output shaft through a clutch; the power output shaft is firmly connected to the low-pressure rotor of the engine.

The blades are fixed wings or rotors, and the blades provide lift for the aircraft during vertical take-off and landing and horizontal flight; the power transmission mechanism includes a hub and a transmission shaft, and the blades are arranged on the hub, and the hub installed on the drive shaft.

The front canard, the horizontal empennage and the vertical empennage are provided with rudder surfaces for attitude adjustment of the aircraft in level flight.

The beneficial effect of the present invention is: described a kind of vertical take-off and landing catamaran aircraft, it adopts the twin body of symmetrical layout, the fixed wing/rotor that can be interchanged between two states of fixed wing and rotor, and can be positioned at the vortex axis The turbine engine with mode conversion between modal and turbofan mode not only avoids the problem of adopting a complex structure for balancing the torque of the main propeller, but also avoids the problem that the rotor affects the maximum level flight speed when the aircraft is flying horizontally; through symmetry The layout of the dual body and the fixed-wing/rotor design that can rotate in opposite directions solves the balance problem of the main propeller torque; through the rotation and locking of the fixed-wing/rotor, the interchangeability of the aircraft in the vertical take-off and landing state and the horizontal flight state is realized, and It solves the problem that the main rotor affects the maximum level flight speed when it is in level flight; it adopts a turbine engine that can perform mode conversion between the turboshaft mode and the turbofan mode to realize the optimal thermal cycle under different flight states and improve The maximum level flight speed of the aircraft.

Description of drawings

Fig. 1 is the front view structure schematic diagram of the present invention;

Fig. 2 is the top view structure schematic diagram of the present invention;

Fig. 3 is a schematic structural diagram of the principle of the power transmission system of the present invention;

Fig. 4 is a front structural schematic diagram of the rotating shaft locking mechanism of the present invention;

Fig. 5 is a schematic diagram of the axonometric structure of the rotating shaft locking mechanism of the present invention;

Fig. 6 is a schematic diagram of the exploded structure of the rotating shaft locking mechanism of the present invention.

As shown in the figure: 1. Front canard; 2. Landing gear; 3. Horizontal tail; 4. Vertical tail; 5. Engine nozzle; 6. Engine compartment; 7. Blade; 8. Power transmission mechanism; 9. 10, right body; 11, left body; 12, engine; 13, clutch; 14, reducer; 15, rotating shaft locking mechanism; 16, propeller hub; 17, transmission shaft; 18, power output shaft; 19. Positioning bayonet; 20. Positioning sleeve; 21. Spiral groove; 22. Adjusting spring; 23. Spiral rib.

Detailed ways

The principles and features of the present invention are described below in conjunction with the accompanying drawings, and the examples given are only used to explain the present invention, and are not intended to limit the scope of the present invention.

As shown in Figures 1 to 6, a kind of vertical take-off and landing catamaran is characterized in that it comprises a right fuselage 10 and a left fuselage 11 of a symmetrical layout, and the front ends of the right fuselage 10 and the left fuselage 11 are connected by the front canard 1, Right fuselage 10 and left fuselage 11 rear ends are connected by horizontal empennage 3, and described right fuselage 10 bottom is provided with landing gear 2, and right fuselage 10 rear portion is provided with vertical empennage 4, and right fuselage 10 top is provided with nacelle 6, engine The front end of the cabin 6 is set as an air inlet 9, the front and rear ends of the engine compartment 6 are set as engine nozzles 5, and the engine compartment 6 is provided with an aircraft power system, which is connected to the blades 7 through a power transmission mechanism 8. The aircraft The power system includes an engine 12, the power output shaft 18 of the engine 12 is connected to the clutch 13, the clutch 13 is connected to the speed reducer 14, the power output of the speed reducer 14 is connected to the transmission shaft 17 through the rotating shaft locking mechanism 15, and the transmission shaft 17 is connected to the propeller hub 16 .

The left body 11 and the right body 10 are arranged symmetrically. The shaft locking mechanism 15 includes a positioning sleeve 20 sleeved on the transmission shaft 17. The positioning sleeve 20 is provided with a spiral groove 21, and the spiral groove 21 Correspondingly, a spiral fin 23 is arranged inside, and a positioning bayonet 19 is disposed on the spiral fin 23, an adjustment spring 22 is disposed below the positioning sleeve 20, and the rotating shaft locking mechanism 15 locks the propeller hub 16 in the horizontal flight mode of the aircraft. Make the paddle 17 remain on the direction perpendicular to the body.

When the clutch 13 disconnects the connection of the transmission shaft 17 and the power output shaft 18, the shaft locking mechanism 15 stops braking after the transmission shaft 17 is reduced to a low speed by braking, and the adjustment spring 22 rises to position the positioning sleeve 20 is pushed upwards, the spiral fin 23 fixed on the transmission shaft 17 rotates into the spiral groove 21 on the positioning sleeve 20, the spiral fin 23 rotates to the bottom of the rotation groove 21, and the positioning bayonet 19 positions and locks the transmission shaft 17 , so that the paddle 7 is fixed at a position parallel to the front canard 1; before the clutch 13 connects the transmission shaft 17 and the power output shaft 18, the adjustment spring 22 in the shaft locking mechanism 15 moves downward and drives the positioning sleeve The cylinder 20 rotates in reverse, and the spiral groove 21 on the positioning sleeve 20 is disengaged from the spiral fin 23 on the transmission shaft 17, so that the rotating shaft locking mechanism 15 does not affect the operation of the transmission shaft 17; the transmission shaft 17 and the reducer 14 is connected; the speed reducer 14 is connected with the power output shaft 18 through the clutch 13;

The blade 7 is a fixed wing or a rotor, and the blade 7 provides lift for the aircraft in vertical take-off and landing and horizontal flight; the power transmission mechanism 8 includes a hub 16 and a transmission shaft 17, and the blade 7 is arranged on On the propeller hub 16, the propeller hub 16 is installed on the transmission shaft 17.

The front canard 1, the horizontal empennage 3 and the vertical empennage 4 are provided with rudder surfaces for attitude adjustment of the aircraft in level flight.

Described a kind of vertical take-off and landing catamaran, when it works, in the vertical take-off and landing state, the outlet area of the engine nozzle 5 is increased to become an expansion nozzle, the engine 12 is in the turboshaft mode, and the power output shaft 18 Output power, the clutch 13 connects the power output shaft 18 with the reducer 14, the output power is output to the decelerated transmission shaft 17, the rotating shaft locking mechanism 15 is released, the transmission shaft 17 drives the propeller hub 16 and the propeller blade 7 to rotate, The propeller hub adjusts the two blades 7 to be in the helicopter rotor state, thereby generating upward lift for the aircraft when rotating; in the horizontal flight state, the engine nozzle 5 reduces the outlet area and becomes a convergent nozzle, and the engine 12 is in the turbofan mode , through the exhaust gas of the engine nozzle 5 to generate forward thrust, the clutch 13 disconnects the power output shaft 18 from the reducer 14, and the rotating shaft locking mechanism 15 decelerates the transmission shaft 17 to stop, positions and locks, so that the blade 7 Being in a position parallel to the front canard 1, the propeller hub 16 adjusts the blade 7 to be in a fixed-wing state, so as to generate upward lift as a fixed wing when the aircraft is in level flight.

To limit the present invention, any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims (5)

1. A vertical take-off and landing dual-body aircraft is characterized in that it comprises a right body and a left body of symmetrical layout, the right body and the left body front end are connected by a front canard, and the right body and the left body rear end are connected by a horizontal empennage, said The lower part of the right fuselage is provided with a landing gear, the rear of the right fuselage is provided with a vertical tail, the upper part of the right fuselage is provided with an engine compartment, the front end of the engine compartment is provided with an air inlet, the front and rear ends of the engine compartment are provided with engine nozzles, and the engine compartment is provided with Aircraft power system, the aircraft power system is connected with the propeller through the power transmission mechanism, the aircraft power system includes the engine, the power output shaft of the engine is connected with the clutch, the clutch is connected with the speed reducer, and the power output of the speed reducer is passed through the shaft locking mechanism Connect the transmission shaft, and the transmission shaft connects to the propeller hub. 2. A vertical take-off and landing catamaran as claimed in claim 1, characterized in that: the left body and the right body structure are arranged symmetrically, and the locking mechanism of the rotating shaft includes a positioning mechanism sleeved on the transmission shaft. The sleeve, the positioning sleeve is provided with a spiral groove, and the spiral rib is correspondingly provided with a spiral fin, and the spiral fin is provided with a positioning bayonet, and an adjustment spring is provided under the positioning sleeve. The rotating shaft locking mechanism is in the horizontal flight mode of the aircraft Lock the propeller hub down to keep the propeller in the direction perpendicular to the machine body. 3. A vertical take-off and landing catamaran as claimed in claim 1 or 2, characterized in that: when the clutch disconnects the connection between the transmission shaft and the power output shaft, the rotating shaft lock mechanism waits for the brake to lock the transmission shaft. After reducing to a low speed, stop the brake, adjust the spring to rise, push the positioning sleeve upwards, the spiral fins fixed on the transmission shaft rotate into the spiral grooves on the positioning sleeve, and the spiral fins rotate to the bottom of the rotation groove to position The bayonet pin positions and locks the transmission shaft, so that the blades are fixed at a position parallel to the front canard; before the clutch connects the connection between the transmission shaft and the power output shaft, the adjustment spring in the shaft locking mechanism moves downward and drives The positioning sleeve rotates in reverse, and the spiral groove on the positioning sleeve is disengaged from the spiral fin on the transmission shaft, so that the shaft locking mechanism does not affect the operation of the transmission shaft; the transmission shaft is connected to the reducer; the reducer is connected to the power The output shaft is connected through a clutch; the power output shaft is firmly connected with the low-pressure rotor of the engine. 4. a kind of vertical take-off and landing catamaran aircraft as claimed in claim 3, is characterized in that: described blade is fixed wing or rotor, and blade provides the lift of aircraft when vertical take-off and landing and horizontal flight; The specific power transmission mechanism includes a propeller hub and a transmission shaft, the blades are arranged on the propeller hub, and the propeller hub is installed on the propeller shaft. 5. A kind of vertical take-off and landing catamaran aircraft as claimed in claim 1, characterized in that: said front canard, horizontal empennage and vertical empennage are provided with rudder surfaces for attitude adjustment when the aircraft is in level flight.