RU2507120C2 - Single-seat helicopter - Google Patents

Single-seat helicopter Download PDF

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Publication number
RU2507120C2
RU2507120C2 RU2012120529/11A RU2012120529A RU2507120C2 RU 2507120 C2 RU2507120 C2 RU 2507120C2 RU 2012120529/11 A RU2012120529/11 A RU 2012120529/11A RU 2012120529 A RU2012120529 A RU 2012120529A RU 2507120 C2 RU2507120 C2 RU 2507120C2
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RU
Russia
Prior art keywords
helicopter
rotors
pilot
control
single
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RU2012120529/11A
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Russian (ru)
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RU2012120529A (en
Inventor
Боян Фаисович Ахметшин
Original Assignee
Боян Фаисович Ахметшин
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Application filed by Боян Фаисович Ахметшин filed Critical Боян Фаисович Ахметшин
Priority to RU2012120529/11A priority Critical patent/RU2507120C2/en
Publication of RU2012120529A publication Critical patent/RU2012120529A/en
Application granted granted Critical
Publication of RU2507120C2 publication Critical patent/RU2507120C2/en

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Abstract

FIELD: transport.
SUBSTANCE: invention relates to production of helicopters. Single-seat helicopter comprises tubular airframe with power plant arranged at its bottom part and furnished with assembly units and mechanisms required for transmission and distribution of torque via shafts to coaxial opposite-rotation rotors mounted at helicopter top part. Pilot cab is arranged above said rotors, jointed with said airframe and equipped with necessary controls. Helicopter vertical sizes are one and a half time larger than rotors while helicopter center of gravity shifted downward does not exceed one third of said vertical size at full load of helicopter.
EFFECT: higher safety, better controllability.
5 dwg

Description

The invention relates to the field of aviation technology and can be used to create single-seat helicopters of vertical take-off and landing with increased flight safety for the pilot and others, high maneuverability, easy control, low cost and ease of manufacture, compactness and low operating costs.

Known single-seat helicopter containing coaxially located rotors, the engine and the pilot's seat located under the propellers (see US patent 6293421, B64C 27/52, 2001). The control is carried out by tilting the axis of the rotors through the control lever.

A disadvantage of the known helicopter is poor maneuverability, high danger of flight for the pilot and for others.

A compact aircraft is also known, containing coaxially located rotors, without swashplate, two engines and a pilot's seat located above the screws (see US patent 2011/0163199, B64C 27/10, 2011).

A disadvantage of the known aircraft is poor maneuverability, high flight danger and low performance.

The well-known Aerosikle Delekner helicopter comprising a frame with a landing gear, a cabin in the form of a trellis basket connected to a frame located above two coaxial screws, an engine mounted in a trellis basket connected to propellers, a horizontal stabilizer on a remote rod, control mechanisms. Engine - Kickheifer 43 hp two-stroke outboard engine (31.6 kW), design weight 99 kg, flight range 24 km, speed 121 km / h, fuel reserve 3.8 liters. Pitch and roll control - by tilting the body, and on the course - using the control knob / P. Bauer. Aircraft of unconventional schemes. M .: Mir, 1991, p. 110, Fig. 5.19 /.

The well-known helicopter "Aerosike" Delekner, as the closest in technical essence, achieved useful result and control method, is taken as a prototype.

The shortcomings of the famous Delekner Aerosike helicopter are determined by complex propellers, low maneuverability, high flight danger for the pilot and others, and the inability to fly in difficult weather conditions.

The aim of the present invention is to increase the safety of piloting, ensuring high maneuverability and ease of control, the ability to fly in difficult weather conditions, reducing the cost and complexity of manufacturing, as well as reducing the operating costs of a single helicopter.

These goals are ensured by the fact that in a single-seat helicopter containing a tubular frame, in the lower part of which there is a power plant with the nodes and mechanisms necessary for transmitting and distributing torque through the shafts to a pair of coaxial rotor rotors located in the upper part of the helicopter over which, connected to the frame, there is a cockpit with controls and controls, according to the invention, the vertical dimensions of the helicopter exceed the diameter n more than one and a half times, and its center of gravity, shifted down, is at full load the apparatus is not higher than a third of its vertical size. The hull is designed in such a way as to ensure maximum flight safety in all weather conditions, except extreme for aircraft of this type, convenience and low cost of manufacture and operation, as well as take-offs and landings on small-sized platforms, in particular in the city.

Main rotors that do not have automatic swash plates fixed in rings create an additional gyroscopic effect during operation, which is necessary for confident and easy control of the device, they have few vibrations during operation, creating a danger for piloting and rapid wear of parts. The absence of a swashplate allows the rotors to be made in the form of a solid or composite rigid structure, which simplifies and reduces the cost of their manufacture from composite materials, such as fiberglass. There is no danger of overlapping screws.

The blades and their fixing ring in the rotor can have internal cavities to lighten their weight and give extra strength.

The invention is illustrated by drawings, where figure 1 shows a General view of the helicopter, figure 2 - view of the helicopter without several details of its structure for a more clear explanation of its essence, figure 3 - view of the upper part of the helicopter, figure 4 - view of one of the rotors helicopter, figure 5 is a view of the pilot in a position ready for flight, where the dash-dot line shows an example of helicopter roll control.

The proposed helicopter (general view, see Fig. 1, p. 1) comprises a housing having a pilot platform 2, a control mast 53, a central vertical hollow tube 29, with a power unit compartment 30 attached thereto, a cone-shaped compartment 31 having ventilation holes 70, and a compartment for accommodating ballast and payload 32. The housing also has tubular vertical elements 45-48, horizontal tubular rods 11-26 and 49-52, by means of connecting rings 27 and 28 attached to the pipe 29. The housing also includes landing supports 41 -44 with built-in amort congestion, and the ring-shaped tubular elements 33-39, giving the structure the necessary rigidity and ensure the safety and ease of access to the site of the pilot. The housing also contains a safety grill 3 and a removable casing 4, which, when mounted, will provide increased flight comfort with reduced efficiency due to the impossibility of air intake from the side for a pine pair of screws.

Figure 2 presents a section in the pipe 29, showing the location of the shaft of the lower screw 5 and the shaft of the upper screw 6, which stretch from those placed in the compartments 30 and 31 of the power plant and transmission to the lower screw 8 and the upper screw 7. The lower and upper rotors 5 and 6 are attached to the shaft of the lower and upper screws by bushes 10 and 9, respectively.

The control mast 53 is located on the pilot platform 2 so that the total center of gravity of the pilot’s body and mast in the horizontal plane is as close as possible to the vertical axis of the device, coinciding with the axis of rotation of the rotors and the general vertical axis of the device. In the place of attachment to the pilot’s platform, the control mast contains an elastic element 55 which, at rest, holds the mast parallel to the general axis of the apparatus, and with efforts from the pilot's side, allows the mast to be deflected in any direction by an angle that is safe for flight. The control mast also contains horizontal elements 58 and 59, on which a control handle 61 with a control ring 62 is mounted and an indication and control unit 57 mounted with hinges 56 and 69 is installed. The control mast also includes a fixation device for the back of the pilot 63, with pilot seat belts 64 -67 with a lock for their fixation 68. A cable 54 (Fig. 3) is inserted into the base of the control mast made of pipes, which is connected to the control and monitoring elements located on the mast and the power unit and other nodes and devices of the pilot Foot machine placed outside the mast. The upper part of the control mast has a latch 60 for attaching to it a parachute rescue system from a number of existing ones.

The control of the aircraft is carried out in a simple, intuitive way. The pilot stands up to the back control mast and secures himself with seat belts. After the pilot installs the required power of the power plant (control ring 62, FIG. 3), it transmits torque to the rotors through the transmission. The device takes off vertically, reaching a height corresponding to the achieved speed. With a decrease in the power of the power plant, the apparatus accordingly decreases.

Turn right-left relative to the central axis is carried out using the signals supplied by the pilot to the transmission (tilt the control knob 61, figure 3) to slow down the rotation of one of the screws.

Movement in any direction is carried out by tilting the pilot in the right direction. In this case, due to the displacement of the center of gravity, the apparatus tilts, the horizontal projection of the lifting force increases, and movement in space in the selected direction is carried out. The center of mass of the apparatus, which is strongly shifted downward, allows safe piloting, which excludes diving and dangerous pitch or roll angles. An additional role in flight safety is played by the limitation of the amplitude of the deflection of the control mast, the elastic element of which tends to return the mast to its original position.

Due to the small diameter of the rotors, up to 3 m, in the event of a power plant failure, it is not necessary to rely on autorotation during an emergency landing. Therefore, to ensure flight safety, one of the standard parachute rescue systems will be mounted to the top of the control mast, which will save the pilot’s life and maintain the integrity of the aircraft.

The proposed single-seat helicopter can be used in any area where it is required to conduct surveillance from the air, transport small loads, for entertainment and as a complete alternative to motor vehicles, as a means of transportation.

The implementation of the invention can not be very difficult, since all components and design details can be manufactured at existing enterprises with well-known materials processing technologies, and the simplicity of construction and control, flight safety for the pilot and others, relative independence from the vagaries of weather, low cost of manufacture and operation make the proposed helicopter an attractive product.

Claims (1)

  1. Single helicopter containing a tubular frame, in the lower part of which there is a power plant with the components and mechanisms necessary for transmitting and distributing torque through the shafts to a pair of coaxial rotor rotors of the opposite direction of rotation, located in the upper part of the helicopter, over which, connected to the frame, there is a cabin pilot with controls and controls, characterized in that its vertical dimensions exceed the diameter of the rotors by more than one and a half times, and its center of gravity, shifted to bottom, is at full load the device is not higher than a third of its vertical size.
RU2012120529/11A 2012-05-17 2012-05-17 Single-seat helicopter RU2507120C2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2012120529/11A RU2507120C2 (en) 2012-05-17 2012-05-17 Single-seat helicopter

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2012120529/11A RU2507120C2 (en) 2012-05-17 2012-05-17 Single-seat helicopter

Publications (2)

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RU2012120529A RU2012120529A (en) 2013-11-27
RU2507120C2 true RU2507120C2 (en) 2014-02-20

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RU2012120529/11A RU2507120C2 (en) 2012-05-17 2012-05-17 Single-seat helicopter

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RU (1) RU2507120C2 (en)

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060049304A1 (en) * 2002-01-07 2006-03-09 Sanders John K Jr Quiet vertical takeoff and landing aircraft using ducted, magnetic induction air-impeller rotors
RU2314972C2 (en) * 2005-05-03 2008-01-20 Алексей Александрович Анищенко Helicopter
US7631834B1 (en) * 2006-02-24 2009-12-15 Stealth Robotics, Llc Aerial robot with dispensable conductive filament
US20110163199A1 (en) * 2008-05-30 2011-07-07 Giles Cardozo A flying machine comprising twin contra-rotating vertical axis propellers

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060049304A1 (en) * 2002-01-07 2006-03-09 Sanders John K Jr Quiet vertical takeoff and landing aircraft using ducted, magnetic induction air-impeller rotors
RU2314972C2 (en) * 2005-05-03 2008-01-20 Алексей Александрович Анищенко Helicopter
US7631834B1 (en) * 2006-02-24 2009-12-15 Stealth Robotics, Llc Aerial robot with dispensable conductive filament
US20110163199A1 (en) * 2008-05-30 2011-07-07 Giles Cardozo A flying machine comprising twin contra-rotating vertical axis propellers

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MM4A The patent is invalid due to non-payment of fees

Effective date: 20150518

BF4A Cancelling a publication of earlier date [patents]

Free format text: PUBLICATION IN JOURNAL SHOULD BE CANCELLED

MM4A The patent is invalid due to non-payment of fees

Effective date: 20180518