UA146401U - VERTICAL TAKE-OFF AND LANDING AIRCRAFT - Google Patents

Abstract

Aircraft with vertical takeoff and landing, including the fuselage, bearing planes-wings, engine, flight control device, in which the lifting and driving forces at all stages of flight arise due to the interaction of the bearing planes with the oncoming air flow, according to the utility model , to simplify the design of the aircraft with vertical takeoff and landing, increase safety during flight or landing in confined spaces, the bearing planes are made in the form of a fixed wing, and the incoming air flow is generated in the aircraft and directed to the front of the wing;

Description

The useful model belongs to aviation, specifically to aircraft capable of flying at zero horizontal speed and can be used in special purpose aviation, where helicopters are usually used, for example, as sanitary and patrol transport, for rescue operations, etc.

Known aircraft with vertical take-off and landing (LVZP) (English MTOY, Mepisai

TaKe-OY apa Iapaipd). They can take off and land at zero horizontal speed, using engine-driven lift devices that create vertical thrust using propellers of various designs, or direct vertical thrust from a jet engine, and in horizontal flight mode, lift is created by a fixed wing in interaction with the incoming air (11, (21.

Piloting this type of machine is very difficult. This is especially noticeable in flight in hover and transition modes - at the moments of transition from hover to horizontal flight and back.

In these regimes, LVZP are generally unstable, prone to lateral sliding. They are characterized by a complex and expensive design, the destruction of runway coatings by the hot gas exhaust of engines |11, (21.

Helicopters are also known. In them, lifting and propulsive forces at all stages of flight are created by the blades of the main rotor - movable wings that rotate in the horizontal plane, interacting with the oncoming air flow. They are stable in flight at low and zero horizontal speeds, which led to their use for performing specific tasks, for example, in the case of urgent evacuation of people from dangerous places, for the delivery of people and goods to hard-to-reach places, for effective patrolling of places with a complex landscape and urban areas with dense buildings, etc.

The main advantage of helicopters is the ability to take off and land vertically, in any place where there is a flat area one and a half times the diameter of the propeller, as well as their maneuverability - helicopters are capable of hovering in the air and flying back. They can transport cargo on an external suspension, which allows you to transport bulky cargo, as well as perform installation work. They are the closest analogue both in terms of functional purpose and constructive execution.

Helicopters have their own special, dangerous flight modes characteristic only for them,

Emergency modes and aerodynamic features: for example, a vortex ring, ground resonance, etc. PI, IZ (p. 612-613)), 14 (p. 19-24)). The supporting screw creates a vibration that threatens to destroy the structure (1), IZ (p. 635-639; 792-796)|, (4 (p. 18; 22-24)). As the helicopter flies forward, one half of the propeller creates more lift than the other, and an additional pitching moment occurs.

At the same time, on the retreating blades, under certain circumstances, a flow disruption may be observed, and the end sections of the advancing blades may experience a wave crisis when passing the sound barrier.

These and other specific features of the main rotor impose certain restrictions on the speed, load capacity and other characteristics of the helicopter |5 (items 1, 2, 3, 4)). To compensate for the reactive moment of the main propeller, with its large mass, up to 20-25 95 of the engine's power |4 (p. 45)) is spent on the steering propeller.

In addition, the main rotor, rotating, poses a danger to everything nearby and threatens the disaster of the helicopter itself when it collides with tall vegetation, power lines, masts and other random objects.

The useful model is based on the task of increasing the safety of aircraft with vertical take-off and landing, simplifying their design and control systems by replacing the movable support planes - movable wings, with fixed ones, with the possibility of blowing them with the air flow generated in the aircraft itself.

This problem is solved by using a fixed wing instead of a main propeller, for example, in the form of a ring, in the center of which is a centrifugal turbofan with nozzles facing the tip of the wing.

Horizontal flight can be set, for example, by shifting the center of gravity and tilting the aircraft. Or with the help of additional devices that create horizontal traction.

In Fig. 1 is a side view, and Fig. 2 - a top view, showing a diagram of an aircraft with vertical take-off and landing, made in accordance with this technical solution.

The aircraft has a fuselage 1, a fixed wing 2, a centrifugal turbofan 3, with guide baffles 4, a turbofan drive 5, which can be used, for example, by a gas turbine. In Fig. From fig. 4, respectively, a side view and a top view, the propulsive complex is shown separately, consisting of two main devices - the wings 2 and the turbofan 3, which are connected into a single structure with the help of guide partitions

4. These partitions, together with the upper cover b of the turbofan and the lower cover 7 of the turbofan, form the outlet nozzles of the turbofan. They are also the central binding element of the propulsive complex. The following are rigidly attached to them: the upper cover b of the turbofan, the lower cover 7 of the turbofan and wing 2. Thus, the entire propulsive complex is assembled into a single rigid structure. The impeller 8 of the turbofan is driven by the shaft 9 from the engine located in the upper part of the fuselage. Details 2, 6, 7 are shown in section.

Fig. 5 shows the propulsive complex in an axonometric view, with a section of the upper cover 6 of the centrifugal turbofan and a section of the wing 2.

The lifting force arises in the process of the airflow from the centrifugal turbofan flowing around the wing surfaces. The direction of horizontal flight is set by devices similar to those used on helicopters, for example, a tail rotor. Just like a helicopter, the proposed aircraft can move in any direction and hover in place with the mechanization of the wing. For this, the entire propulsive complex, consisting of a wing and a turbofan, is made with the ability to move relative to the fuselage in the horizontal plane, in two perpendicular directions. At the same time, the center of gravity of the aircraft shifts from the axis of the propulsive complex, the aircraft tilts and, in the lifting force acting on the wing, a horizontal component appears, which ensures flight in the given direction. Also, as an option, flaps on opposite sides of the wing can be used for this purpose, simultaneously deflecting them in opposite directions.

Due to the fact that the propulsive complex, consisting of a fixed wing together with a turbofan, is a less complex and more reliable device, compared to a helicopter main rotor, this aircraft is simpler and cheaper to manufacture. It is easier to manage and more reliable in operation. It can fly safely in mountain gorges and among tall buildings. He can sit in unprepared places - accidentally touching foreign objects will not lead to an accident.

Sources of information: 1. Wikipedia: Vertical take-off and landing aircraft; Helicopter. 2. Ruzhitsky E.I. Modern aviation. European plane! vertical take-off and landing. Moscow: Astrel, 2000. 3. U. Johnson. "Helicopter Theory". M., Mir, 1983. 4. V. V. Dudnyk. "Helicopter design". Rostov-on-Don, Izdatelsky dom IUY AP, 2005. 5. V.A. Pavlov "On the problems of vertical take-off and landing of aircraft".

Kazan State Technical University (Aviation Institute), 1998.

Claims (3)

USEFUL MODEL FORMULA 1. An aircraft with vertical take-off and landing, which includes a fuselage, supporting planes - wings, an engine, a flight control device, in which the lifting and driving forces at all stages of flight arise due to the interaction of the supporting planes with the oncoming air flow, which is different the fact that to simplify the design of an aircraft with vertical take-off and landing, increase safety during flight or landing in conditions of limited space, the bearing planes are made in the form of a fixed wing, and the oncoming air flow is generated in the aircraft itself and directed to the wing from the front . 2. The aircraft according to claim 1, which is characterized by the fact that the incoming air flow is generated using a centrifugal turbofan. 3. The aircraft according to claim 1 and 2, which differs in that the nozzle guides are located along the perimeter of the turbofan, and the wing has the shape of a ring around the turbofan, and the tip is turned to the nozzles.