RU2564942C1 - Hybrid craft - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: claimed craft comprises car-shape body, steering system, gyrostabilizer and lift-and-pull device, two lengthwise symmetric air duct composed between body cowling and walls, straightener blades and two parachute compartments. It includes two engines to run two rotors located longitudinally. For body stabilization, jet engines are used with gimballed nozzles arranged in craft body.

EFFECT: higher reliability, lower costs.

1 dwg

Description

The invention relates to multifunctional transport equipment and is a car suitable for use as an aircraft with vertical take-off and landing.

A well-known aircraft (US Pat. RU 2344946, IPC B60F 5/02), comprising a car-shaped body, a power plant, hoisting devices made using the Magnus effect in the form of planetary mechanisms.

The disadvantage of this aircraft is the design complexity of the lifting and traction devices and, accordingly, low reliability and high cost.

A well-known airplane (US Pat. RU 2484980 C2, IPC B60F 5/02), comprising a car-shaped housing, a steering system, a gyro stabilizer, a drive chassis, a power unit, an air channel located inside the body, a lifting and traction device made in the form of several longitudinally located screws rotating in pairs in opposite directions and located inside the air channel.

A disadvantage of the known aircraft is its high cost, due to the presence of a large number of screws necessary to create a large carrying capacity.

All of the above disadvantages are deprived of the proposed aircraft.

The essence of the invention lies in the fact that in an aircraft containing a car-shaped body, a steering system, a gyro stabilizer, a driving chassis, a power unit, an air channel placed inside the body, a lifting and traction device made in the form of several longitudinally arranged screws rotating in pairs in opposite directions and located inside the air channel, the power plant is closed by a fairing, forming with the body two longitudinal, symmetrically located air channels, with those placed in them straightens devices, wherein within the housing on each side thrusters arranged with diverging nozzles.

The technical result of the invention is the real possibility of implementing a device with a high degree of reliability and low cost.

Analysis of known similar solutions allows us to conclude that they lack features similar to the distinctive features in the claimed device, that is, on the compliance of the claimed technical solution with the criteria of “novelty” and “inventive step”.

In FIG. 1 is a two-seat aircraft, a) a side view without side walls, b) a rear view without rear walls.

The aircraft contains a housing consisting of a cabin 1, a body 2, in the upper part of the cabin 1 there is a parachute compartment 3, a power unit consisting of two engines 4 and 5 with clutches 6 and 7, respectively, a gearbox 8, a universal joint 9 transmitting rotation to a wheel gearbox 10 and then to a lightweight chassis 11, a clutch 12, which transmits torque to the rear screw 13, a gearbox 14, which transmits torque to the front screw 15, to provide lateral stability of the body in the rear and front (not shown) body parts 2 placed on two react engine 16 with deflecting nozzles 17, closing the power plant, fairing 18, forming with the walls of the body 2 two longitudinal, symmetrically located air channels 19,20 with straightening devices (not shown), parachute compartment 21.

The aircraft in the "car" configuration is operated in the usual way, while the torque from the engine 5 is transmitted to the chassis 11 through the clutch 7, the gearbox 8, the cardan 9 and the wheel gear 10. The gearbox 8 provides the necessary mode of movement on the ground. To take off from a place or in motion, it is necessary to start additionally the engine 4, turn on the clutch 12. In this case, the screws 13 and 15 will rotate in opposite directions, the revolutions of which will correspond to the revolutions of the engines 5 and 4, respectively. Before takeoff, the gearbox 8 is put in a neutral position. The entire air flow generated by the propellers is directed down along the body 2 through the air channels 19, 20 and creates a lifting force. Due to the presence of the walls of the body 2, the thrust of the screws increases by 20%. Part of the air flow enters under the hull of the aircraft, creating a dynamic air cushion, so that the aircraft can take off from the ground and rise several meters with less power than is needed to “hang” at a height of 10-15 meters. Due to air preload, the thrust of the rotors in this case, at the same power consumption, increases by 30-40%. With distance from the earth, this effect quickly decreases, at a certain flight altitude it decreases to 15-20%. Roughly, the propeller thrust can be calculated by the Zhukovsky formula (1):

where T is the propeller thrust, kg;

h - propeller efficiency, 0.8;

D is the diameter of the propeller, m;

N - engine power, hp .;

For example: at N = 150 hp, D = 1.75 m.

We get:

Taking into account the effect of the shell, two screws will create a traction equal to 877.0 kg. Thus, the lifting force of 877.0 kg, with a power plant power of 300 hp, is able to provide the flight of an aircraft with a payload of at least 250 kg.

During take-off, the longitudinal and transverse stabilization of the aircraft body is carried out by jet engines 16, at the command of a gyrostabilizer. The transition to horizontal flight is carried out by increasing the thrust of the jet engines 16, while the body of the aircraft is tilted at a certain angle relative to the horizon. Horizontal flight is achieved due to the horizontal component of the full aerodynamic force vector of the propellers. The speed of horizontal movement depends on the angle of inclination of the housing relative to the horizon. The body is turned in the air with the help of the reactive force created by the jet engines 16 and the position of the nozzles 17. The jet thrust can also be generated by the exhaust gases of the 4.5 engines. The landing of the aircraft is carried out by moving the hull to a horizontal position and reducing the engine speed of 4.5. To go into the “car” configuration, all control systems are reset.

The aircraft can be operated as a vehicle for traveling on land or above the ground at a low altitude.

Claims (1)

An aircraft comprising a car-shaped body, a steering system, a gyro stabilizer, a drive chassis, a power unit, an air channel located inside the body, a lifting and traction device made in the form of several longitudinally arranged screws rotating in pairs in opposite directions and located inside the air channel, characterized in that the power plant is closed by a fairing, forming with the body two longitudinal, symmetrically located, air channels, with rectifying devices placed in them, Rich within the housing on each side thrusters arranged with diverging nozzles.