RU2815129C1 - Krishtop hybrid aircraft (ha) and method of functioning of ha (versions) - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: invention relates to VTOL aircraft. Hybrid aircraft includes a storage battery, a control system with a target homing module, body made according to normal "aircraft" aerodynamic configuration, but without tail unit, with straight rectangular wing of flat-convex profile with tips on edges. On the front frontal edge of the wing on support bearings there is a rotary shaft with rigidly fixed on it two electric motors with one or two screws of invariable pitch and with opposite direction of rotation. Rotation of motors through angle of 90 degrees is carried out by a rotary shaft. Suspension devices for bomb weapons are installed on lower flat surface of the hull and straight rectangular wing. On top in the central part of the housing there is an electromagnetic latch for connecting a disposable ring, to which a group of rubber balls inflated with a gas lighter than air is tied for ascent to a given height in a balloon way.

EFFECT: creation of unmanned aerial vehicle of hybrid type, combining properties of balloon, quadcopter, convertiplane, aircraft.

6 cl, 3 dwg

Description

The group of inventions relates to the field of aircraft construction and aviation technology.

From the existing level of technology, unmanned aerial vehicles (UAVs) are known that combine the properties of a quadcopter, tiltrotor or airplane.

However, no hybrid unmanned aerial vehicle (UAV) is known from the existing level of technology, combining the hybrid properties of a balloon, quadcopter, tiltrotor or airplane, using at least two fixed electric motors with a propeller, like a quadrocopter, and at least two rotary ones. an electric motor with an impeller, like a tiltrotor, as well as a balloon balloon, in the form of a group, inflated with lighter-than-air gas, rubber balls, manually attached immediately before a vertical launch like a balloon and automatically detached by an electromagnetic latch, in flight at the operator’s command when switching to horizontal flight UAV in flight modes like a quadcopter, tiltrotor or airplane.

Thus, the task of creating a hybrid unmanned aerial vehicle (UAVV) remains relevant, combining the hybrid properties of a balloon, quadcopter, tiltrotor or aircraft using at least two fixed electric motors with a propeller, like a quadrocopter, and at least two rotary ones. an electric motor with an impeller, like a tiltrotor, as well as a balloon balloon, in the form of a group, inflated with lighter-than-air gas, rubber balls, manually attached immediately before a vertical launch like a balloon and automatically detached by an electromagnetic latch, in flight at the operator’s command when switching to horizontal flight UAV in flight modes like a quadcopter, tiltrotor or airplane.

The task of achieving the technical result to which the stated group of inventions is aimed is to create an unmanned aerial vehicle (UAV) of a hybrid type, combining the hybrid properties of a balloon, quadcopter, tiltrotor or aircraft using at least two fixed electric motors with a propeller, like a quadcopter and at least two rotary electric motors with an impeller, like a tiltrotor, as well as a balloon balloon, in the form of a group, inflated with lighter-than-air gas, rubber balls, attached manually immediately before a vertical launch in a balloon style and automatically detached with an electromagnetic latch in flight operator command when switching to horizontal flight of the UAV in flight modes such as a quadcopter, tiltrotor or airplane.

The specified task (achieving a technical result) is solved by the fact that the Krishtop Hybrid aircraft is proposed according to paragraph 1 of the claims.

The specified task (achieving a technical result) is solved by the fact that the Krishtop Hybrid aircraft is proposed according to paragraph 2 of the claims.

The specified task (achieving a technical result) is solved by the fact that the Krishtop Hybrid aircraft is proposed according to paragraph 3 of the claims.

The specified task (achieving a technical result) is solved by the fact that the Krishtop Hybrid aircraft is proposed according to paragraph 4 of the claims.

The specified task (achieving a technical result) is solved by the fact that the Krishtop Hybrid aircraft is proposed according to paragraph 5 of the claims.

The technical result is also achieved in the method of operation of the Krishtop Hybrid aircraft according to paragraphs 1-5 of the claims.

The essence of the group of inventions is illustrated by the drawings of Fig. 1, Fig. 2 and Fig. 3.

In the drawing FIG. 1 shows explanatory sketches: (-1/1-) side view of the Krishtop Hybrid Aircraft (hereinafter - GLAC) in horizontal flight, where: 1 - body, 2 - rotary shaft mounted on support bearings (not shown in the sketch), 3 - a straight rectangular wing of a flat-convex profile, located on the body 1 so that the rotary shaft 2 is at the center of gravity of a fully equipped GLAC, 4 - an impeller, with an electric motor, with one or two screws, a constant pitch (not shown in the sketch), operating in pulling mode, 5 - electric motor with a propeller, 12 - plug-in device for controlled disconnection of the electrical cable, with power supply from an external power source, switched off at the operator’s command. The sketch (-1/2-) shows a side view of the GLAC during vertical takeoff or landing, as well as hovering in flight, where: 4 - impeller, with an electric motor, with one or two propellers, constant pitch (not shown in the sketch), operating in lifting mode. The sketch (-1/3-) shows a top view of the GLAC during vertical takeoff or landing. Suspension devices for missile and bomb weapons and means of destroying enemy drones, installed on the lower flat surface of a straight rectangular wing, as well as wing tips and acoustic microphones, a rotating laser altimeter - range finder are not shown in all sketches.

In the drawing FIG. 2 presents explanatory sketches (-2/1-) and (-2/2-) of the Vertical Launch Device (hereinafter referred to as UVZ) for unmanned or manned aircraft for vertical take-off and landing, which allows, without using the charge of the aircraft’s own battery, to carry out vertical take-off and remain for a long time at a certain altitude, limited by the length of the electrical cable, with power supplied from an external stationary or mobile source of electricity, switched off at the operator’s command when the aircraft’s own battery is fully charged. The sketch (-2/1-) shows a side view of the GLAC for the version when a plug-in device 12 for controlled disconnection of the electrical cable is installed in the bow of the body 1, with power supply from an external source of electricity, switched off at the operator’s command, where: 12 - plug-in device for controlled disconnecting the electric cable, with power supply from an external source of electricity, turned off at the operator's command, 13 - an electric two-core or single-core electric cable with a metal cable cord inside, 14 - a rotary drum with a manual or electric drive (not shown in the sketch), on which an electric two-wire is wound or a single-core electrical cable with a metal cable cord inside, 15 - the base on which a rotary drum with a manual or electric drive is installed. In the sketch (-2/2-) UVZ, which includes a control system (not shown in the sketch), contacts minus 26 and plus 27 of a two-core or single-core electrical cable 13 with a metal cable cord inside, which on one side can be connected via switching device (not shown in the sketch), to an external stationary or mobile source of electricity (not shown in the sketch), and on the other hand is connected directly to the electrical plug 21, which is manually connected to the plug device for controlled disconnection of the electrical cable 12, installed directly on the aircraft device and connected to the battery, which has the ability to automatically turn off at the command of the aircraft operator, where: 18 - insulating housing of the plug-in device for controlled disconnection of the electrical cable 12, 17 spring, 19 - electrical plus contact connected directly to the battery, 20 - electrical plus contact of the electrical plug 21, 22 - electrical minus contact connected directly to the battery, 23 - electrical minus contact of the electrical plug 21, 24 - mechanical latch controlled by the electromagnet core 25. The sketch (-2/3-) shows a worm gearbox with electric drive 16, located in housing 1, controlling the position of the rotary shaft 2 mounted on support bearings (not shown in the sketch), to rotate the impellers 4 at an angle of 90 degrees to a horizontal or vertical position.

In the drawing FIG. 3 shows an explanatory sketch of a variant of the GLAC with a connected group, inflated with gas lighter than air, rubber balls for lifting the GLAC like an aerostat and an additional, for example, jettisonable solid rocket booster installed under the body 1 in the tail section of the GLAC, where: 1 - body, 4 - impeller, with an electric motor, with one or two screws, constant pitch (not shown in the sketch), in the operating position in lifting mode, 5 - electric motor with a propeller, 6 - group of lighter-than-air gas-inflated rubber balls, 7 - slings group, inflated with gas lighter than air, rubber balls, 8 - electromagnetic latch, controlled remotely by the operator, 9 - metal ring, which has the ability to connect and disconnect to the electromagnetic latch 8, on which the slings of group 7, inflated with gas lighter than air, rubber balls 6 are attached, 10 - mount for dropping a solid propellant rocket accelerator controlled by the operator's command, 11 - resettable solid propellant rocket booster with a remote launch system upon the operator's command.

Operation of the most preferred version of the GLAC, for example, with two impellers and two electric motors with a propeller, described in the drawings of Fig. 1, Fig. 2 and Fig. 3 is carried out as follows.

The launch of a GLAC into flight can be carried out in several well-known ways, for example, like a balloon, silently and without consuming electricity, like a balloon balloon in the form of a group of rubber balloons inflated with lighter-than-air gas 6 Fig. 3 in sufficient quantities to rise to a given height like a balloon. For example, for the GLAC version weighing 5 kg, a balloon balloon can be used in the form of a group of 6-7, inflated, for example, with hydrogen, rubber balls with a volume of 1 cubic meter, the lifting force of each of which will be equal to 1.2 kg and, accordingly, the total lifting force for GLAC weighing 5 kg will be 7.2-8.4 kg. This method is advisable to use at night in calm weather or with a tailwind in the intended direction of the GLAC flight. After reaching the desired flight altitude, a group of rubber balloons inflated with lighter-than-air gas can be turned off at the operator's command by an electromagnetic latch 8 metal ring 9 Fig. 3, to release a group of lighter-than-air gas-inflated rubber balloons 6 into free flight, when switching to horizontal flight of the GLAC in multicopter, tiltrotor or airplane mode only.

An interesting option for launching GLAC is also possible, as a hybrid balloon-multicopter option, for example, when loading the maximum payload, when the lifting force is summed up by a group of lighter-than-air gas-inflated rubber balls 6 and the vertical thrust of all electric motors with a propeller 5 and impellers with an electric motor 4 Fig. 3.

Also, if preliminary long-term aerial reconnaissance is necessary at altitudes from 10 to 100 meters, when line of sight increases by tens of kilometers, a GLAC launch can be used using an additional plug-in device for controlled disconnection of the electrical cable, with power supplied from an external stationary or mobile power source, switched off by operator command carried out using a Vertical Launch Device (hereinafter referred to as UVZ) FIG. 2 (-2/1-), when both impellers 4, with an electric motor, with one or two screws, of constant pitch must be installed vertically and operate as lifting ones, and the electrical plug 21 is manually connected to the plug device for controlled disconnection of the electrical cable 12, installed directly on the GLAC and connected to its battery FIG. 2 and thus, GLAC rises like a multicopter, with additional lift from the straight rectangular wing 3 in the presence of wind, “like a well-known kite” to a height determined by the length of the electric cable 13 with a metal cable cord inside. At the same time, the GLAC battery does not consume its reserve of electricity, since the power supply of all GLAC electric motors is carried out from an external stationary or mobile source of electricity and, accordingly, the GLAC is capable of conducting long-term exploration without consuming its own reserve of electricity. When installing an UVZ with a connected GLAC on a moving tank, armored personnel carrier or infantry fighting vehicle, such a reconnaissance system is capable of reconnaissance of the area for a very long time, for example, within a radius of 26 km with a length of 50 meters of electric cable 13 with a metal cable cord inside. When a target is detected, at the operator’s command, by the action of a mechanical latch 24, controlled by the electromagnet core 25, the electrical plug 21 is disconnected from the plug device 12 of the controlled disconnection of the electrical cable and the GLAC is transferred to an independent flight in a multicopter or aircraft manner, like a controlled tiltrotor at the operator’s commands for conducting reconnaissance, conducting targeted missile and bomb strikes and countering enemy UAVs. When flying like an airplane, the flight direction can be adjusted by changing the thrust of the impellers 4, with electric motors installed at the edges of the plane of a straight rectangular wing with a flat-convex profile, and the flight altitude can be adjusted by the pitch by changing the thrust of the bow and stern electric motors with the propeller 5, then there is, with a positive pitch, the GLAC climbs, and with a negative pitch, the GLACK lowers the altitude up to a possible dive onto a target with a subsequent climb or a “loop” type maneuver to gain altitude and then dive onto the next target.

It is also possible to launch the GLAC in a multicopter mode with a transition to the flight mode as a tiltrotor and an airplane, without a group, inflated with lighter-than-air gas, rubber balls 6, when all the impellers 4, with an electric motor, are installed vertically and work as lifting ones together with electric motors with a propeller 5, and then the impellers 4 are switched to operating mode as pulling for horizontal flight like an airplane and the change in the position of all impellers 4, with an electric motor, with one or two screws, a constant pitch is carried out at the operator’s command when turning an angle within 90 degrees using a worm gear with electric drive 16 Fig. 2 (-2/3-), located in housing 1, controlling the position of the rotary shaft 2 mounted on support bearings (not shown in the sketch).

And also the launch can be carried out, for example, like an airplane using a catapult or an additional resettable or non-resettable solid rocket booster, when all impellers 4, with an electric motor, with one or two screws, of constant pitch, are installed and operate in the pulling position.

The GLAC landing is carried out in a multicopter manner (all impellers are 4, with electric motors in the lifting position) by reducing the thrust of the electric motors or with preliminary planning like an airplane and landing like a tiltrotor at the operator’s commands.

The operating algorithm for other versions of the GLAC, for example, with an upper wing or with a different number of electric motors, is similar to that described above.

An acoustic locator with acoustic microphones and a rotating laser altimeter - range finder can be used to search and destroy enemy drones with an additional “duck shotgun” type device. The rotary laser altimeter - range finder can also be used to determine the ascending air flows for soaring the GLAC at an eagle-like altitude, which increases the flight duration.

Thanks to the above, the group of inventions achieves a technical result consisting in the creation of GLAC, an unmanned aerial vehicle (UAV) of a hybrid type, combining the hybrid properties of an aerostat, quadcopter, tiltrotor or aircraft using at least two fixed electric motors with a propeller, like a quadcopter and at least two rotary electric motors with an impeller, like a tiltrotor, as well as a balloon balloon, in the form of a group, inflated with lighter-than-air gas, rubber balls, attached manually immediately before a vertical launch in a balloon style and automatically detached with an electromagnetic latch in flight operator command when switching to horizontal flight of the UAV in flight modes such as a quadcopter, tiltrotor or airplane.

Claims (6)

1. A hybrid aircraft, characterized by the fact that it includes a battery and a control system with a target homing module, a body made according to a normal “aircraft” aerodynamic design, but without a tail, with a low or high rectangular flat wing. a convex profile with endings or without endings at the edges, on the front front edge of which a rotary shaft is mounted on support bearings with at least two electric motors with an impeller rigidly mounted on it, with one or two screws of constant pitch and with a counter direction of rotation, the rotation of which is at an angle 90 degrees is carried out by a rotary shaft through a worm gear drive with an additional control electric motor, and at the same time, inside, along the longitudinal axis of the housing, perpendicular to the rotary shaft, a bracket is rigidly fixed, at the output ends of which at least two electric motors with a propeller, with one or two screws of a constant pitch and with a counter-direction of rotation, having a constant vector of thrust vertically upward, like a quadcopter, and on the lower flat surface of the body and the straight rectangular wing, suspension devices for bomb weapons are installed, and on top in the central part of the body there is an electromagnetic latch for connecting the outside of a disposable a ring to which a group of gas-inflated lighter-than-air rubber balloons is attached in sufficient quantity to rise to a given height like a balloon, and at the same time, after gaining altitude at the command of the operator, the electromagnetic latch can be turned off to release the group of gas-inflated lighter-than-air rubber balloons into free flight when switching to horizontal flight of a hybrid aircraft in quadcopter, tiltrotor or airplane mode. 2. A hybrid aircraft according to claim 1, characterized in that it includes a rotary laser altimeter-rangefinder. 3. Hybrid aircraft according to any one of paragraphs. 1, 2, characterized in that it includes an acoustic locator containing two acoustic microphones directed in the direction of horizontal flight, installed at the edges of a straight rectangular wing of a flat-convex profile, and an electronic unit for determining the direction and intensity of noise from the propellers of an enemy aircraft. 4. Hybrid aircraft according to any one of paragraphs. 1-3, characterized in that it has an additional resettable or non-resettable solid rocket booster installed in the tail section under the body of the hybrid aircraft. 5. Hybrid aircraft according to any one of paragraphs. 1-4, characterized in that it has an additional plug-in device for controlled disconnection of the electrical cable with power supply from an external stationary or mobile power source, switched off at the operator’s command. 6. Method of operation of a hybrid aircraft (hereinafter - HAV) according to any one of paragraphs. 1-5, which consists in the fact that the GLA can carry out vertical take-off either silently and without power consumption, like a balloon, or noisily, with power consumption, like a multicopter, or as a hybrid of a balloon and a multicopter when loading the maximum payload and can also carry out long-term reconnaissance from a take-off altitude using an additional plug-in device for controlled disconnection of the electrical cable with power supply from an external stationary or mobile power source, switched off at the operator’s command, and if necessary, can quickly, at the command of the operator, disconnect the plug of the additional plug-in device for controlled disconnection of the electrical cable and an electromagnetic latch for automatic detachment of a disposable ring for the free separate flight of a group of gas-inflated, lighter-than-air rubber balloons when switching to horizontal flight of the GLA, like a hybrid of a quadcopter, tiltrotor or airplane, with the transfer of the operating mode as lifting to the operating mode as pulling for all electric motors by operator commands with a GLA impeller with adjustment of the GLA flight in direction by the magnitude of the thrust of the electric motors with the impeller and in height when changing pitch by the magnitude of the thrust of the electric motors with the propeller, and if it is necessary to hover over a target or land, the GLA can also quickly, at the operator’s command, switch to quadcopter mode when switching the operating mode as pulling on the operating mode as a lift for all electric motors with a GLA impeller.

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