WO2005037644A1

WO2005037644A1 - Vtol aircraft

Info

Publication number: WO2005037644A1
Application number: PCT/LV2004/000008
Authority: WO
Inventors: Peteris Dzerins
Original assignee: Peteris Dzerins
Priority date: 2003-10-22
Filing date: 2004-10-22
Publication date: 2005-04-28
Also published as: LV13116B

Abstract

The invention relates to aircrafts, more specifically - to the development of the design of aircraft that can conduct vertical take-off and landing, horizontal flying and changing of the flying direction. Its aim is to make the design of the aircraft simpler, to ensure the maneuvering capacity while being in horizontal motion, as well as to ensure security in case of emergency landing. The aim is achieved providing the aircraft, which comprises the hull (1), the cabin with the control system (2), the engines (4), by flat discoid hull with at least five engines located in the seats of the hull. Four engines are connected in pairs with the horizontal axles (6, 7), which are mutually firmly connected by the hawser (8). Said horizontal axles (6, 7) are fixed in the hull in such a way that they can be turned around its axis, and they are mutually interacting with the control system by help of hydraulic system (5). The fifth engine ensuring the maneuvering capacity of aircraft is connected with the control system.

Description

VTOL AIRCRAFT

The invention relates to the sphere of aviation engineering and may be used at constructing combined aircrafts of horizontal movement with vertical talcing off and landing. It is known a combined vertical taking off and landing aircraft of propeller- wing scheme, which contains all basic elements of an aircraft such as fuselage, wing with ailerons, engine, etc. and helicopter made according to a single-propeller scheme with a rudder, pulling and retractable two-blade propellers [1]. Conversion of an aircraft of vertical taking off and landing from the propeller-wing configuration in to the aircraft one is carried out while flying by way of jointing blades of the carrying propeller with the wing. The aircraft construction is complicated because of multiple units and parts available. It is known an analogous combined aircraft, whereon the carrying propeller is equipped with the weight balance [2, 3]. Conversion from the propeller- wing configuration into the aircraft one is carried out by way of blade approaching with the balance with a fuselage forming a common aerodynamic surface. Construction of the aircraft is complicated because of the conversion system. It is known an aircraft with the disk-shaped hull with a cabin, air pump inserted in the hull, engine, suction and air charge duct, interacting with the atmosphere through nozzles [4]. Nozzles are equipped with the switched on/off guide devices supplying air under the central part of the hull during an aircraft taking off. After taking off of the aircraft by way of switching the lever system, the guide devices change the inflow value of ducts and supply a flow of air to the ducts located along the aircraft periphery providing its movement. The aircraft has a complicated configuration of the system of air feed. It is known an aircraft of vertical and horizontal flight containing rotors fixed on the rotor disk and form the lifting capacity [5]. To provide a horizontal flight rotors are drawn into the disk. There is a device in the form of gear at the central part of the disk providing manoeuvring capacity. The aircraft construction is complicated. It is known a disk-shaped aircraft containing an engine, rotor with propellers, the air circulating system providing lifting and horizontal movement of the aircraft [6]. As at the foregoing aircraft the air supply system available make the construction more complicated.

It is known an aircraft of horizontal and vertical movement comprising the hull made from a complicated frame of rectangular form, on which edges are mounted turboprop engines [7]. Each of the engines is enclosed in the internal and external rings providing engine rotation (turn) in the vertical plane and the aircraft movement. The aircraft construction is complicated and cumbersome. The closest solution to that being claimed that was chosen as the invention prototype is an aircraft with a vertical taking off and landing comprising the hull contained of two coaxial rings, the cabin with steering placed at the hull center, concentrically located in the clearance between the rings, engines with propellers rotating in the vertical plane that provide taking off, landing and horizontal movement of the aircraft, generator for generating power for the engines specified above [8]. Each of the engines individually interacts with the steering. Arrangement of engines with propellers in the clearance between the rings, stipulates reduction of the lift, insofar the air flow is dispersed in the clearance between the engines themselves, thereby worsening the conditions of the aircraft talcing off. The aircraft construction is complicated and its manoeuvring capacity adversely affected. This invention is aimed at the simplification of an aircraft construction and provision of the maneuvering capacity while moving in horizontal direction, as well as at providing safety at landing in case of emergency. The goal set is achieved owing to the fact that at the aircraft comprising the hull, cabin with the control system, engines, for example, with propellers, the hull is made in the shape of plane disk, at least with five engines installed in the hull seats. Four engines are connected in pairs with the parallel horizontal axes, being mutually firmly connected by the hawser. The axes are fixed on the hull in the manner that they may turn around its axis and interact with the control system with the help of hydraulic system. The fifth engine providing manoeuvring capacity is connected with the control system via the sliding hawser and axis, which is fixed to the engine revolving ring. In this case the engine is in addition equipped with worm-and-worm gear for being able to turn in the horizontal plane. The invention is explained applying the following drawings: Fig.l — proposed aircraft with the engines located in the horizontal plane (top view); Fig.2 - proposed aircraft with the engines located in the horizontal plane (section view A-A);

Fig.3 - proposed aircraft with the engines located in the horizontal plane (section view B-B);

Fig.4 - proposed aircraft with the engines located in the vertical plane (top view); Fig.5 - proposed aircraft with the engines located in the vertical plane (section view A-A);

Fig.6 - proposed aircraft with the engines located in the vertical plane (section view B-B); The aircraft comprises the hull (1) made in the shape of plane disc with the increased thickness to the center of the disk and rounding off towards the periphery. The cabin (2) with the control system is placed at the disk center; at least five engines (4) are concentrically placed around the cabin in the hull seats, foe example, with propellers, which start operating from the generator. All five engines are connected via the hydraulic system (5) with the control system and are able to turn in the vertical plane. Four engines are fixed in pairs on the common axes (6, 7), which, in its turn, are fixed in the bearings placed in the aircraft hull. Axes have a rigid connection between each other with the help of a hawser (8). The fifth engine intended for providing manoeuvring capacity is equipped with a coaxial revolving ring (9), wherein the axle (110) is fixed. A sliding hawser (11) interacting with the axle (6) is connected to the ends of the axis. The engine is equipped with the worm- and-worm gear turnover device, where the rack (12) is made on the surface of the revolving ring (9) within the limits of 90°, and the worm (13) interacting with it, is installed on the axis of a reduction gear with the engine (3). At vertical placement of all engines the fifth engine may be turned over at 90 ° in the horizontal plane too, which ensures manoeuvring capacity for the aircraft during the flight. The aircraft operates as follows: Helicopter taking off is carried out in a helicopter-like mode, at which the engines [4], for example, with propellers are in the operating horizontal position and create the required lift. Transient condition from the vertical helicopter to the horizontal movement, when achieving the required height is provided with the help of the control system by way of turning all engines [4] into the vertical position. To provide the aircraft manoeuvring capacity there is used the worm-and-worm gear turnover device of the fifth engine, providing a turn (down wind) of the engine with propeller in the required direction. The turn may be carried out within 90 °. When completing the flight all engines return to the rest position and the aircraft carries out landing. If necessary, the aircraft is able to hover in the air at a certain height. The aircraft construction is simple, as well as easy to operate and provide due manoeuvring capacity. In case of emergency the aircraft construction provides safe landing, provided all engines are switched off. Metrological conditions do not have a considerable effect on the aircraft flight.

Reference literature:

1. Patent RU 2061625, Cl, 6B64C27/22, 10.06.1996 2. Application RU 94017618, Al, 6B64C27/22, 27.07.1996 3. Application RU 2000114837, A, 7B64C29/02, 29.07.2002 4. Patent RU 2131378, Cl, 6B64C29/00, 20.10.1997 5. Application WO 01/56879, Al, 6B64C29/00, 10.06.1996 6. Application US 2003/0098388, Al, U.S.Cl. 344/12.2, 29.05.2003 7. Application US 2003/0080242, Al, U.S.Cl. 244/12.4, 01.05.2003 8. Application WO 01/30652, Al, B64C29/00, 23.10.2000

Claims

CLAIM

The aircraft with a vertical taking off and landing comprising the hull, the cabin with the control system, located at the center of the hull, concentric located around the cabin engines rotating in a vertical plane, providing taking off and landing and horizontal movement of the aircraft is characterized by the feature that the hull is made in the shape of plane disc, at least with five engines located in the seats of the hull; four engines are connected in pairs with the horizontal axes, being mutually firmly connected by the hawser, the axes are fixed on the hull in the manner that they may turn around its axis and interact with the control system by help of hydraulic system, the fifth engine ensuring the maneuvering capacity of aircraft is connected with the control system by help of the sliding hawser and axle, which is fixed to the engine by revolving ring, in this case the engine is, in addition, equipped with pair of worm gearings for its turning into horizontal plane.