RU152807U1 - AIRCRAFT - Google Patents

Abstract

1. An aircraft containing a fuselage, a tail boom with a tail, two tandem-mounted wings, each of which is made in the form of rotary wings at the base, on which propeller-mounted groups are mounted, and a payload compartment, characterized in that the wings are spaced apart in height relative to the center of mass of the aircraft, the wing spar of each wing is made of composite of half-wing spars and a rotary spar installed inside the fuselage, even Separate rotor-motor groups with electric drive with separate control, rotor-groups are fixed on the wing spars symmetrically with respect to the axis of the aircraft, the fuselage is equipped with a removable landing gear, the payload compartment is located in the front of the fuselage between the wings, and the fuselage connections with the wings and the tail boom are detachable. 2 . Aircraft according to claim 1, characterized in that the fuselage is made in the form of a monocoque. 3. Aircraft according to claim 1, characterized in that the wings are equipped with flaps. 4. Aircraft according to claim 1, characterized in that the landing gear is tricycle and contains a front and two rear struts. Aircraft according to claim 1, characterized in that the tail unit contains two keels installed at the ends of a stabilizer equipped with elevators. 6. Aircraft according to claim 1, characterized in that the rotation of the wings is carried out synchronously by transmitting rotation to the rotary side members at an angle from 0 ° to 90 °. 7. Aircraft according to claim 1, characterized in that in the hovering mode the aircraft is controlled by a change in thrust

Description

The utility model relates to the field of aviation technology, and can be used in the construction of aircraft (LA), combining the capabilities of shortened and vertical take-off and landing, flight at a given distance in horizontal mode by plane and hovering in the zone of interest in quadrocopter mode.

There are various technical solutions in this area.

In patent US 3035789 A, IPC B64C 29/00, publ. 05/22/1962 a tiltrotor containing a fuselage, two rotor screws mounted on the wing ends is described, which is configured to rotate the entire wing around an axis transverse to the fuselage, in accordance with the selected flight conditions in helicopter and aircraft modes. A disadvantage of the known design of a tiltrotor is the use of a single wing, which complicates its assembly and transportation.

Known tiltrotor according to patent US 6367736, IPC B64C 27/22, B64C 29/00, publ. 04/09/2002, in which two half-wings are rotary, at the respective ends of which rotor-screws are located. The use of half wings simplifies the assembly and transportation of the device. However, the well-known tiltrotor with one carrier wing have a common disadvantage, which is the difficulty of controlling the device in transition and helicopter modes.

Tiltrotor according to patent RU 128182, IPC B64C 37/00, publ. 05/20/2013, also known as the Era-100 unmanned aerial vehicle (http://www.aviaport.ru/news/2014/03/14/278543.html), has two fixed spaced wings, at the ends of the consoles of which are located four electric motors. The engines are rotary, which allows the tiltrotor to take off and land vertically and fly in a horizontal plane relative to the ground in an airplane.

The known design provides increased maneuverability of the aircraft at all stages of the flight, improved stability and aerodynamic quality, but does not provide take-off in a more economical mode by plane.

In terms of essential features, the closest to the claimed utility model is the Quad-Tilt-Wing (QTW) UAV (Autonomous Flying Robots: Unmanned Aerial Vehicles and Micro Aerial Vehicles (Video Link) Chapter 4: Modeling and Control of an Autonomous Quad-Tilt- Wing (QTW) UAV), http://mec2.tm.chiba-u.jp/monograph/contents.html), which contains a fuselage with a tail boom, tail unit, two tandem wings located, each of which is made in the form of rotary at the base of the half-wings on which propeller-mounted groups are mounted, and the payload compartment located in the fuselage. The main disadvantage of the prototype is the lack of a chassis, which does not provide take-off / landing in a more economical mode on an airplane.

The task to which the claimed technical solution is directed is to create an aircraft that combines the capabilities of shortened and vertical take-off and landing, flight at a given distance in horizontal mode by airplane and hovering in the zone of interest.

The technical result achieved by the implementation of the proposed utility model is to increase the duration and range of the flight, as well as to simplify the control of the aircraft in transition and helicopter modes.

The technical result is achieved by the fact that in an aircraft containing a fuselage, a tail boom with a tail, two tandem-mounted wings, each of which is made in the form of rotary at the base of the half-wings on which propeller groups are mounted, and a compartment with a payload, according to the utility model , the wings are spaced apart in height relative to the center of mass of the aircraft, the spar of each wing is made up of half-wing spars and a rotary spar mounted inside the fuser cradle, four propeller-driven groups with an electric drive with separate control are used as propulsion systems, rotor-mounted groups are mounted on the wing spars symmetrically with respect to the axis of the aircraft, the fuselage is equipped with a removable landing gear, the payload compartment is located in front of the fuselage between the wings, and the fuselage has half-wings and tail boom are detachable.

The technical result is also achieved by the fact that:

the fuselage is made in the form of a monocoque;

wings are equipped with flaps;

the chassis is tri-bearing and contains a front and two rear racks;

the tail contains two keels mounted on the ends of the stabilizer, equipped with elevators.

the rotation of the wings is carried out synchronously using the nodes of rotation at an angle from 0 ° to 90 °;

in hovering mode, the aircraft is controlled by a change in the thrust of the propeller groups;

control is automatic.

The technical result is provided by the possibility of takeoff and landing in an airplane in the presence of a runway (runway), vertical takeoff and landing in quadrocopter mode in the absence of a runway, and horizontal flight in an airplane.

The essence of the utility model is illustrated by drawings, on which are presented:

FIG. 1 - general view of the aircraft in vertical take-off mode;

FIG. 2 - general view of the aircraft in flight mode;

FIG. 3 - top view of the aircraft in flight mode;

FIG. 4 - side view of the aircraft in flight mode;

FIG. 5 is a front view of the aircraft in flight mode;

FIG. 6 - side view of the aircraft in vertical take-off mode;

FIG. 7 is a section A-A of the fuselage in the form shown in FIG. 6.

In FIG. 1-7 introduced the notation:

1 - propeller group;

2 - lower wing;

3 - upper wing;

4 - flap;

5 - aileron wing;

6 - fuselage;

7 - payload compartment;

8 - tail boom with tail;

9 - elevator;

10 - keel;

11 - a forward rack of the chassis;

12 - rear landing gear;

13 - the center of mass of the aircraft;

14 - axis of symmetry of the aircraft;

15 - side member half wing;

16 - node rotation of the lower wing;

17 - node rotation of the upper wing;

18 - rotary spar;

19 - stabilizer.

The aircraft, which is controlled automatically, comprises a fuselage 6, a tail boom 8 with a tail unit comprising two keels 10 mounted at the ends of a stabilizer 19 equipped with elevators 9. The fuselage is made in the form of a monocoque. The lower 2 and upper 3 wings are made in the form of half-wings rotatable at the base, on which rotor groups are mounted 1. The lower 2 and upper 3 wings are equipped with flaps 4 and ailerons 5 and are located with a height spacing relative to the center of mass 13 of the aircraft, which provides, in addition to aerodynamic control of the position of the aircraft in airplane mode, control due to the multi-thrust propeller groups 1. The spar of each wing is made of composite spars of the wings 15 and the swivel Rhone 18, mounted inside the fuselage 6. As a power plant, four rotor-motor groups 1 with an electric drive with separate control are used. The rotor-motor groups 1 are mounted on the side members of the half-wings 15 symmetrically with respect to the axis of symmetry 14 of the aircraft and are located at a minimum distance from the base of the half-wings, which ensures the safe operation of the rotor-motor groups 1. This arrangement reduces the strength requirements of the wings and reduces the weight of the device. The fuselage 6 is equipped with a removable chassis, which is preferably tri-bearing and includes a front 11 and two rear 12 racks. The removable chassis provides the ability to launch the aircraft from the launcher. To ensure the stability of the alignment of the aircraft, the payload compartment 7 is located in front of the fuselage 6 between the wings 2 and 3 near the center of mass. The connection of the fuselage 6 with half wings and a tail boom 8 is made detachable, which simplifies the storage and transportation of aircraft. The rotation of the wings 2 and 3 is carried out by transmitting rotation to the rotary side members 18 from the rotation nodes 16 and 17. The rotation is carried out synchronously at an angle from 0 ° to 90 °, depending on the flight mode. In hovering mode, the aircraft is controlled by a change in the thrust of the propeller groups 1.

To describe the operation of the aircraft, it is advisable to distinguish the following operating modes: “Vertical take-off”, “Hanging 1”, “Transition mode 1”, “Horizontal flight”, “Transition mode 2”, “Hanging 2”, “Vertical landing”, “Take-off” "," Landing. "

In the “Vertical take-off” mode, the aircraft is on the ground, wings with propeller groups 1 are moved to a vertical position. After starting all the engines and exceeding the propeller thrust of the aircraft weight, it takes off at zero translational speed. The control and stabilization of the aircraft is due to the different thrust of the propeller groups 1, as in quadrocopters.

In the “Hanging 1” mode, the aircraft hangs in the air at a given height with zero vertical and a given translational speed. The necessary movement at a set height is carried out by tilting the aircraft in the appropriate direction due to the different thrust of the propeller groups 1.

In the "Transition mode 1" mode, the aircraft switches from the "Hanging 1" mode to the "Horizontal flight" mode and gains the speed necessary for horizontal flight. Wings with propeller groups 1 are transferred from vertical to horizontal position. Management - mixed: due to the different thrust of the propeller groups 1 and aerodynamic due to the ailerons of 5 wings and elevators 9.

In the “Horizontal flight” mode, the lifting force is created by the wings due to the oncoming high-speed air flow. The control of the aircraft is aerodynamic due to the ailerons of 5 wings and rudders of height 9.

In the "Transition mode 2" mode, the aircraft switches from the "Horizontal flight" mode to the "Hanging 2" mode and reduces the translational speed to zero. Wings with propeller groups 1 are transferred from horizontal to vertical position. Management - mixed: due to the different thrust of the propeller groups 1 and aerodynamic due to the ailerons of 5 wings and elevators 9.

In the “Hanging 2” mode, the aircraft hangs in the air at a given height with zero vertical and given translational speeds. The necessary movement at a set height is carried out by tilting the aircraft in the appropriate direction due to the different thrust of the propeller groups 1.

In the “Vertical Landing” mode, the aircraft lands at zero translational speed.

In the "Take-off" wings with propeller groups 1 are located horizontally. LA takes off in an airplane due to the lifting force of the wings. The control of the aircraft is aerodynamic.

In the "Landing" mode, the wings with rotor groups 1 are located horizontally. The aircraft lands in an airplane, control - aerodynamic.

Thus, the rotary wings with installed propeller groups allow you to create an aircraft that combines a long duration of flight in an airplane and the possibility of vertical take-off and landing, as in quadrocopters.

Claims (8)

1. An aircraft containing a fuselage, a tail boom with a tail, two tandem-mounted wings, each of which is made in the form of rotary wings at the base, on which propeller-mounted groups are mounted, and a payload compartment, characterized in that the wings are spaced apart in height relative to the center of mass of the aircraft, the wing spar of each wing is made of composite of half-wing spars and a rotary spar installed inside the fuselage, even Separate rotor-motor groups with an electric drive with separate control, rotor-groups are fixed on the wing spars symmetrically relative to the axis of the aircraft, the fuselage is equipped with a removable landing gear, the payload compartment is located in the front of the fuselage between the wings, and the fuselage connections with half-wings and the tail boom are detachable. 2. Aircraft according to claim 1, characterized in that the fuselage is made in the form of a monocoque. 3. Aircraft according to claim 1, characterized in that the wings are equipped with flaps. 4. The aircraft according to claim 1, characterized in that the landing gear is tricycle and contains a front and two rear racks. 5. Aircraft according to claim 1, characterized in that the tail unit contains two keels installed at the ends of a stabilizer equipped with elevators. 6. Aircraft according to claim 1, characterized in that the rotation of the wings is carried out synchronously by transmitting rotation to the rotary side members at an angle from 0 ° to 90 °. 7. The aircraft according to claim 1, characterized in that in the hovering mode the aircraft is controlled by a change in the thrust of the propeller groups. 8. Aircraft according to claim 1, characterized in that the control is automatic.

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