UA121496U - VERTICAL FLOWER PLANE AND LANDING - Google Patents

Abstract

The vertical take-off and landing aircraft contains a lifting device, a fuselage, a parachute rescue system, portable consoles with rear chassis supports installed in them, portable beams with elevation controls and a rudder connecting the fuselage to the lifting device. The structure of the lifting device includes a gondola, located above the fuselage, with it installed in series along the longitudinal axis of the trellis-wing, air screw, power unit, main and auxiliary generators. The power plant is kinematically coupled to an air propeller and an additional generator. Remote consoles located at the front of the fuselage with front end supports of the chassis placed at the ends of each console are additionally introduced to the aircraft design. The fuselage is made in the form of a streamlined body, which accommodates the payload and necessary systems of the aircraft, parachute rescue system. The gondola is configured to rotate its position by rotating about a transverse axis fixed at the junction of each outrigger console and outrigger beam. The trellis wing-polyplan is made with the negative removal of profile elements, made, in turn, with the possibility of changing the angle of attack relative to the transverse axis and rotation about the longitudinal axis. The aforementioned air screw is made in the form of a fan. All the chassis wheels are equipped with fairings, the chassis wheels mounted on the rear supports are equipped with brakes, the chassis wheels mounted on the portable consoles located in the front of the fuselage are made rotary. Mentioned wheels, placed on the portable consoles, equipped with built-in electric motors, portable consoles are made in the form of aerodynamic surfaces with the possibility of equipping additional lift and balancing the aircraft in horizontal flight. The power plant is made with the possibility of breaking the kinematic connection with the air screw and with the possibility of connecting and disconnecting an additional generator.

Description

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The useful model belongs to aviation, in particular to aircraft, namely to devices designed to ensure vertical take-off and landing, movement in the air in a horizontal plane and with a change in the nature of the flight.

A well-known vertical take-off and landing aircraft, in which the jet engines are carried over the leading edge of the wing and have a rotary nozzle nozzle of the slot type, while the engines are also equipped with a nozzle guide device aimed at blowing the wing (11.

The disadvantage of the known aircraft is the low value of the generated lifting force, since most of the jet is dispersed in the space around a single wing, considering the remoteness of the source of the high-speed jet from the plane of blowing (at the same time, only a small part of it is blown). The engines are located horizontally and the traction force from the engines does not participate in creating a vertical force.

A known aircraft that has a slotted air collector on a jet engine, in the cavity of which the inner wing |21 is located.

This feature of a known aircraft at the possible speeds of air flow relative to a single wing cannot implement vertical take-off and landing, but can only serve as a means of creating additional lifting force of the device. Engines are involved only in creating horizontal thrust. The engine inlet device is basically intended only for the direction and equalization of the flow at the engine entrance. Any additional disturbances and unevenness of the flow lead to unstable operation of the gas turbine engine.

A well-known aircraft in which aerodynamic surfaces are forcibly blown, placed in air intake channels located along the perimeter of the body and radially converging into a trough-like cavity open downward |ZI.

The disadvantage of the known aircraft is the large relative mass of the structure when creating the proposed disc-shaped body. Traction forces from the propellers do not participate in the creation of vertical lifting force and compensate each other.

A known aircraft with a lattice wing, designed according to an aerodynamic scheme, while the wing is two keel racks, mounted with the possibility of turning in the vertical plane and between which there are rotating profile elements with a negative offset |І4І. When the wing is raised, the polyplane turns into an aircraft, and when

From descent - to a ground vehicle.

The disadvantages of the known aircraft include the fact that the flight of the aircraft is possible only at a certain translational speed, vertical take-off from a place is impossible.

A well-known aircraft of vertical take-off and landing, containing an air flow generator in the form of counter-rotating fans, aerodynamic surfaces, a cabin, a power plant, control and stabilization systems, while the aerodynamic surfaces are lattices of a multi-plane wing, installed at a positive angle of attack relative to the forcibly created air flow, the rectangular parts of the air duct are connected by bells to the ring in which the fans are located, at least two lattices of the multi-plane wing are installed in the rectangular part of the air ducts (51.

The disadvantages of the well-known vertical take-off and landing aircraft are the large relative mass of the structure, and the mode of hanging in place is impossible. Changing the direction of the air flow behind the multi-plane wings and the effect of the flow on the duct leads to the appearance of centrifugal forces directed against the lifting force of the wings, which can make take-off impossible. The disadvantages include the fact that the fans do not participate in the creation of vertical lifting force, which requires a significant increase in the power of the propulsion system.

The closest technical solution, both in essence and in terms of the problem to be solved, which was chosen as the closest analogue (prototype), is an aircraft of vertical take-off and landing, containing a lifting device, a fuselage, a parachute-rescue system, remote consoles with installed in them with the rear supports of the chassis, the outriggers with the height rudder and the rudder located on them, which connect the fuselage with the lifting device, while the lifting device includes a gondola located above the fuselage with a lattice wing installed in it sequentially along the longitudinal axis - polyplane, propeller, power plant, main and additional generators, and the power plant is kinematically connected to the propeller and additional generator |b|.

The disadvantages of the well-known vertical take-off and landing aircraft, which was chosen as the closest analogue (prototype), include the fact that the flight of the aircraft is possible only at a certain forward speed, vertical take-off from a place is impossible.

The basis of a useful model is the task by additional introduction of structural elements, the execution of a nacelle with the possibility of changing its position around the transverse axis, because it is fixed at the junction of each outrigger console and outrigger beam, the execution of a lattice wing-polyplane, with a negative offset of profile elements, and the execution of them with the possibility of changing the angle of attack relative to the transverse axis and turning around the longitudinal axis, to ensure the ability of the aircraft with a payload to move in the air environment forward, backward, sideways, up, down without changing and with a change in the longitudinal axis of the apparatus, to move on the solid surface of the earth, take off and sit on unprepared surfaces.

The essence of a useful model in an aircraft of vertical take-off and landing, containing a lifting device, a fuselage, a parachute-rescue system, remote consoles with the rear supports of the landing gear installed in them, remote beams with an altitude rudder and a rudder located on them, connecting the fuselage with a lifting device, while the lifting device includes a gondola located above the fuselage, with a lattice polyplane wing installed in it sequentially along the longitudinal axis, a propeller, a power plant, the main and additional generators, and the power plant is kinematically connected to the air propeller and an additional generator, consists in the fact that the design of the aircraft additionally includes remote consoles located in the front part of the fuselage, with front landing gear supports located at the ends of each of the consoles, the fuselage is made in the form of a streamlined body, where the payload and necessary aircraft systems are located , a parachute rescue system designed for rescue of the aircraft and the payload in the event of engine failure, located in the upper part of the nacelle, the nacelle is made with the possibility of changing its position by rotating around the transverse axis, fixed at the junction of each outrigger console and outrigger beam, lattice wing-polyplane, made with a negative outrigger of profile elements made, in turn, with the possibility of changing the angle of attack with respect to the transverse axis and turning around the longitudinal axis, the mentioned lattice wing-polyplane, made with the possibility of creating a lifting force greater than or comparable to the thrust force of the propeller, the said propeller is made in the form of a propeller fan, all wheels of the landing gear are equipped with fairings, wheels of the landing gear installed on the rear supports are equipped with brakes, wheels of the landing gear installed on the remote consoles located in the front part of the fuselage are made of swivel, the mentioned wheels, located on the remote consoles, are provided built-in electric motors, remote consoles nor in the form of aerodynamic surfaces with the possibility of providing additional lift

Due to the strength and balancing of the aircraft in horizontal flight, the power plant is made with the possibility of breaking the kinematic connection with the propeller and with the possibility of connecting and disconnecting the additional generator.

The essence of the useful model is that the lifting device is made with the possibility of movement relative to the fuselage in the longitudinal and transverse directions. The essence of the useful model also lies in the fact that the lattice wing-polyplane is installed in the nacelle either in front of the propeller or behind it on the output edge of the said nacelle.

A comparative analysis of the technical solution with the prototype allows us to conclude that the proposed vertical takeoff and landing aircraft differs in that the aircraft design is additionally equipped with remote consoles located in the front part of the fuselage, with front landing gear supports located at the ends of each of the consoles, the fuselage made in the form of a streamlined body, where the payload and necessary aircraft systems are located, the parachute rescue system, designed to save the aircraft and payload in case of engine failure, is located in the upper part of the nacelle, the nacelle is designed with the ability to change its position by rotating around the transverse of the axis, fixed at the junction of each outrigger console and outrigger beam, a lattice polyplane wing, made with a negative offset of profile elements, made, in turn, with the possibility of changing the angle of attack relative to the transverse axis and rotation around the longitudinal axis, the said lattice polyplane wing , made with the possibility of creating p idiomatic force in magnitude greater than or proportional to the thrust force of the propeller, the mentioned propeller is made in the form of a propeller fan, all wheels of the chassis

BO equipped with fairings, wheels of the chassis installed on the rear supports, equipped with brakes, wheels of the chassis installed on the remote consoles located in the front part of the fuselage, made rotary, the mentioned wheels, located on the remote consoles, equipped with built-in electric motors, the remote consoles made in the form of aerodynamic surfaces with the possibility of providing additional lifting force and balancing the aircraft in horizontal flight, the power plant is made with the possibility of breaking the kinematic connection with the propeller and with the possibility of connecting and disconnecting the additional generator, the lifting device is made with the possibility of moving relative to the fuselage in the longitudinal and in the transverse directions, and the lattice wing-polyplane is installed in the nacelle either in front of the propeller or behind it on the exit edge of the said nacelle.

Thus, the proposed vertical take-off and landing aircraft meets the utility model criterion of "novelty".

The essence of a useful model in an airplane of vertical take-off and landing is explained by schematic drawings, where in fig. 1 shows a general view of a vertical take-off and landing aircraft in a 3/4 front view from above, in fig. 2 shows the layout diagram of the proposed vertical take-off and landing aircraft in a longitudinal section (in the case of placement in the nacelle in front of the propeller behind the leading edge of the nacelle), in fig. C shows the layout diagram of the proposed vertical take-off and landing aircraft in a longitudinal section (in the case of placement in the nacelle behind the propeller on the output edge of the said nacelle), in fig. 4 shows the diagram of forces in horizontal flight, in fig. 5 shows the diagram of the action of forces in the modes of vertical take-off, hovering and landing, in fig. b shows the scheme of creating additional lifting force by cantilever beams.

The claimed aircraft 1 of vertical take-off and landing contains (as a design variant) a lifting device 2, a fuselage 3, a parachute-rescue system 4, remote consoles 5 with the rear supports of the landing gear b installed in them, remote beams 7 with a rudder located on them height 8 and rudder 9, connecting the fuselage 3 with the lifting device 2, the remote consoles 10 located in the front part of the fuselage 3, with the front supports of the chassis 11 located at the ends of each of the consoles 10, while all the wheels (positions b and 11) the chassis is equipped with fairings 12, the wheels of the chassis b, which are mounted on the rear supports, are equipped with brakes 13, the mentioned wheels (6 and 11), located, respectively, on the remote consoles 5 and 10, are equipped with built-in electric motors 14 (see diagrams on fig. 1-3).

Structurally, the lifting device 2 includes a gondola 15, located above the fuselage 3, with a lattice polyplane wing 17, a propeller 18 located to the lattice polyplane wing 17, a power plant 19, a main 20 and an additional 21 generators, and the power unit 19 is made kinematically connected to the propeller 18 and the additional generator 21 (see diagrams in Fig. 2-3).

Structurally and technologically: the fuselage 3 is made in the form of a streamlined body, where the payload 22 and

From the necessary systems 23 of the aircraft, the parachute rescue system 4, which is designed to save the aircraft and the payload 22 in case of engine failure (power plant 19), is located in the upper part of the nacelle 15, the nacelle 15 is made with the possibility of changing its position by rotating around the transverse axis 24, fixed at the junction of each outrigger console 5 and outrigger beam 7, lattice wing-polyplane 17, made with a negative offset of profile elements 25, made, in turn, with the possibility of changing the angle of attack relative to its transverse axis and turning around its longitudinal axis axes, the mentioned lattice wing-polyplane 17 is made with the possibility of creating a lifting force Ru of a magnitude greater than or comparable to the thrust force K of the propeller 18 (see diagrams in Fig. 4-5), the mentioned propeller 18 is made in the form of a propeller, wheels chassis 11, mounted on remote consoles 10, located in the front part of the fuselage 3, are made rotary, remote consoles 5 and 10 are made in in the form of aerodynamic surfaces with the possibility of providing additional lifting force U1 and balancing the aircraft 1 in horizontal flight, the power plant 19 is made with the possibility of breaking the kinematic connection with the propeller 18 and with the possibility of connecting and disconnecting the additional generator 21, the lifting device 2 is made with the possibility of moving relative to the fuselage Z in the longitudinal and transverse directions.

The design of the lifting device 2 provides for two options for placing the lattice wing 17 in the nacelle 15: the lattice wing-polyplane 17, installed in the nacelle 15 in front of the propeller 18 behind the leading edge 26 (see diagrams in Fig. 1, 3); lattice wing-polyplane 17, installed in the nacelle 15 behind the propeller 18 on the output edge 27 of the specified nacelle 15 (see diagrams in fig. 2, 4-5).

Aircraft 1 vertical take-off and landing is operated as follows.

The pilot 28 sits in the cabin 29 located in the front part of the fuselage Z and with the help of the appropriate systems 23 of the aircraft starts the engine 19 and the main 20 and additional 21 generators.

The engine 19 through the kinematic connection spins the air propeller 18, which creates a thrust force K bo (see diagrams in Fig. 4-5).

In the variant, when the lattice wing-polyplane 17 is installed in the nacelle 15 in front of the propeller 18 behind the inlet edge 26 (see diagrams in Fig. 1, 3), the high-speed flow is drawn by the propeller 18 through the front edge (inlet edge 26) of the nacelle 15 and passes through the profile elements 25 of the lattice wing-polyplane 17, which is made with a negative offset of the specified profile elements 25 (made, in turn, with the possibility of changing the angle of attack relative to its transverse axis and turning around its longitudinal axis). As a result of the interaction of the profile elements 25 of the lattice wing-polyplane 17 with the air flow, the lifting force Ru on the lattice wing 17 is obtained.

In the variant, when the lattice wing-polyplane 17 is installed in the nacelle 15 behind the propeller 18 on the outlet edge 27 of the said nacelle 15 (see the diagrams in Fig. 2, 4-5), the entire high-speed flow from the propeller 18 is directed to the lattice wing - polyplane 17. As a result of the interaction with the flow, we get the lifting force Ru on the lattice wing 17.

Lattice wing-polyplane 17 has the ability to change its position (angle of attack) in relation to the oncoming air flow from the propeller 18 in the vertical plane, the ability to rotate with respect to the longitudinal axis of the nacelle 15. Changing the position of the lattice wing-polyplane 17 allows you to change the amount of lifting force Ru, to obtain transverse force to change the direction of movement of the aircraft 1 without changing the position of the longitudinal axis of the aircraft 1. This feature of the design allows for wide maneuverability both during the take-off and landing stages of the aircraft 1 and during the horizontal flight.

The peculiarity of the operation of the lifting device 2 in the aircraft 1 of vertical take-off and landing (which is claimed) is the joint operation of the propeller 18 and the lattice wing-polyplane 17, to create total forces (creating the resultant force P on the lattice wing 17, overcoming the resistance Рх of the lattice wing 17 and frontal resistance X of aircraft 1 in relation to the point (position "C.T." - see the diagram in Fig. 4) of the center of gravity C) - see diagram of the decomposition of forces in fig. 4.

The rotation of the lifting device 2 in the vertical plane (see the diagram in Fig. 5) allows you to set the required mode of movement of the aircraft (aircraft 1) from horizontal flight forward with the creation of horizontal thrust from the propeller 18 and the total lifting force "Ru sum" from the lattice wing -polyplane 17, to vertical movement or backward or sideways movement with the joint creation of vertical and horizontal force from the propeller 18 and the lattice wing-polyplane 17. Point "OO" of application of the net force P from the lifting device 2 (created by the lattice wing 17 - polyplane) does not change its position.

The center of gravity C of the plane 1 is below the point "OO" of application of the net force P from the lifting device 2 and has the resulting:

Ah - the projection of force K on the X axis,

Рх - the projection of force P on the axis X (see the diagram of force distribution in Fig. 5).

In this way, an aerodynamically stable scheme is created, regardless of the vibrations of the aircraft.

Such a scheme greatly simplifies the piloting of aircraft 1.

The line of action of the resulting aerodynamic force P on the lattice wing 17, the line of action of the thrust force K from the propeller 18, the transverse axis 24 of the rotation of the nacelle 2 intersect at one point - point "O" - see diagrams in fig. 4-5.

The lift coefficient Ru of the lattice wing 17 at the angle of attack of the wing (polyplane) is equal to 2.0 and higher.

Before take-off, the pilot 28 rotates the lifting device 2 to the required angle (take-off position). By increasing the revolutions of the engine 19, the pilot 28 performs a run-up (using wheels 6 and 11) of the chassis and separation of the aircraft 1 from the surface.

By changing the position of the lifting device 2 and the position of the lattice wing-polyplane 17, the pilot 28 parries the impact of wind gusts on the aircraft 1. When the angle of installation of the lifting device 2 is reduced, the acceleration of the aircraft 1 occurs. When the lifting device is installed at an angle greater than the take-off angle, the aircraft brakes 1 (additional braking of the aircraft 1 is carried out with the help of brakes 13, which are installed in the wheels 6 of the chassis, located on the remote console 5.

Takeoff and landing of the aircraft 1 are carried out when the entire lifting device 2 is deflected in the vertical plane by an angle determined by the aerodynamic perfection of the lattice wing 17.

The remote consoles 5 and 10, made in the form of aerodynamic surfaces (see the diagram in Fig. 6), provide additional lifting force Mi and balancing of the aircraft 1 in horizontal flight.

To move on the ground, the pilot 28 disconnects the propeller 18 (by breaking the kinematic connection between the power plant 19 and the propeller 18) and connects the additional generator 21. The electric motors 14 located in the wheels 6 and 11 change the power to the specified wheels. Controlling an airplane 1 while moving on the ground is no different from driving a car.

The increase in the efficiency of the application of the proposed vertical take-off and landing aircraft, compared to the prototype, is achieved by the additional introduction of new structural elements to the aircraft design, the execution of a nacelle with the possibility of changing its position around the transverse axis fixed at the junction of each outrigger console and outrigger beam, execution of a lattice wing-polyplane 17, with a negative offset of profile elements, and their execution with the possibility of changing the angle of attack relative to the transverse axis and turning around the longitudinal axis, which provides the aircraft with a payload the ability to move in the air environment forward, backward, sideways, up, down without a change and with a change in the longitudinal axis of the aircraft, move on the solid surface of the earth, take off and land on unprepared surfaces.

Sources of information: 1. Patent of the Russian Federation (KO) No. 2406652 "Vertical take-off and landing aircraft" dated September 10, 2009, IPC 8 B64C 29/00 - analogue. 2. Patent of the Russian Federation (KY) No. 2389653 "Aircraft" dated 20.05.2010,

MPK 8 V64C 29/00 - analogue.

Z. Patent of the Russian Federation (KO) No. 2172705 "Aircraft" dated August 27, 2001,

Bul. Mo 24, MPK 8 Vb64S2 9/00 - analogue. 4. Patent of the Russian Federation (KY) No. 2025295 "Aircraft with lattice wing" dated December 30, 1994, IPC 7 VbOE 5/02 - analog. 5. Patent of the Russian Federation (KO) Mo 2459746 "Vertical take-off and landing aircraft" dated 21.08.2012, IPC (2012.01) В64С 29/00 - analogue. 6. Tsyhosh Z. "Vertical take-off and landing aircraft", M.: 1983 - prototype.

Claims (2)

USEFUL MODEL FORMULA 1. An aircraft of vertical take-off and landing, containing a lifting device, a fuselage, a parachute-Z rescue system, remote consoles with the rear supports of the landing gear installed in them, remote beams with an altitude rudder and a rudder located on them, connecting the fuselage with the lifting device, while the lifting device includes a nacelle located above the fuselage, with a lattice polyplane wing installed in it sequentially along the longitudinal axis, a propeller, a power plant, the main (and Z5 additional generators, and the power plant is made kinematically connected with propeller and an additional generator, which is distinguished by the fact that the aircraft design is additionally equipped with remote consoles located in the front part of the fuselage, with front landing gear supports located at the ends of each of the consoles, the fuselage is made in the form of a streamlined body, where the payload and necessary systems are located aircraft, 40 parachute-rescue system designed for rescues of the aircraft and the payload in the event of engine failure, located in the upper part of the nacelle, the nacelle is made with the possibility of changing its position by rotating around the transverse axis fixed at the junction of each outrigger console and outrigger beam, the lattice polyplane wing is made with a negative outrigger of profile elements , made, in turn, with the possibility of changing the angle of attack relative to the 45 transverse axis and turning around the longitudinal axis, the mentioned lattice wing-polyplane is made with the possibility of creating a lifting force greater than or equal to the thrust force of the propeller, the said propeller is made in in the form of a propeller fan, all wheels of the landing gear are equipped with fairings, the wheels of the landing gear mounted on the rear supports are equipped with brakes, the wheels of the landing gear mounted on the remote consoles located in the front part 50 of the fuselage are rotatable, the mentioned wheels located on the remote consoles are equipped built-in electric motors, remote consoles are made by you in terms of aerodynamic surfaces with the possibility of equipping additional lifting force and balancing the aircraft in horizontal flight, the power plant is made with the possibility of breaking the kinematic connection with the propeller and with the possibility of connecting and disconnecting the additional generator. 55 2. The aircraft according to claim 1, which is characterized by the fact that the lifting device is made with the possibility of movement relative to the fuselage in the longitudinal and transverse directions. C. An aircraft according to claim 1, which is characterized by the fact that the lattice polyplane wing is installed in the nacelle either in front of the propeller or behind it on the leading edge of said nacelle.