RU2101215C1 - Aircraft wing - Google Patents

Abstract

FIELD: aeronautical engineering; development of rotary-wing flying vehicles. SUBSTANCE: aircraft wing is made in form of thin-walled axis-symmetrical revolving disk whose cavity is divided into two parts by means of diametral partition. One part is used for extensible blades and other part is used for stowage of compressed air escaping from nozzles mounted over periphery tangentially relative to wing circle which create torque. Extensible blades are connected by means of ropes with drum mounted in central portion of wing. Blades are extended and retracted under various conditions of flight due to rotation of drum and section of centrifugal forces during rotation of wing. EFFECT: enhanced efficiency. 3 cl, 1 dwg

Description

 The invention relates to the field of aviation technology, in particular to aircraft and helicopter engineering, and can be used to create a high-speed aircraft (LA) with vertical take-off and landing, as well as to perform the rescue operation of the aircraft as a whole.

 Known wing, direct or swept [Zhitomirsky G.N. The design of the aircraft. M. Engineering, 1991.400 p. (p. 44)] requiring for the takeoff or landing of an aircraft the horizontal speed, and therefore the runway, which is an expensive multi-kilometer concrete structure, the absence of which, when the engines stop in flight, usually leads to disaster.

 Known methods and devices for vertical takeoff and landing of aircraft [Design and experimental studies of high-speed helicopters and rotary-wing vehicles. Surveys of the BNTI TsAGI N 296, 1969.62 p. Helicopters with propellers stopped in flight were developed (p. 38). The classification of such aircraft is shown in FIG. 44, p. 39. After take-off on the propellers, their rotation stops and the lifting force in horizontal flight is created by an ordinary wing or blades of stopped rotors.

 The closest to the invention according to the technical solution, taken as a prototype, may be the wing of the Hughes company Rotorving helicopter (page 52), which is a thin-walled shell with blades: rigid, fairly short fixed wings are installed around the perimeter of the triangular wing-shell, turning the wing into a main rotor during take-off and landing of the aircraft, for which the expiration of air from the ends of the blades organizes the rotation of the wing relative to the vertical axis.

 The main disadvantages of the Rotorwing wing are the limitation of flight speed created by the constant presence of blades in the stream, as well as a decrease in lift on take-off and landing, since the blades, which are not retractable and in horizontal flight, cannot be performed long.

 The invention solves the problem of creating a wing for vertical take-off and landing with retractable blades, wings for high-speed passenger or transport aircraft that do not need airfields with a large runway. This wing can be used as a means of rescue in case of engine failure.

 This is achieved by the fact that in the wing of the aircraft, which is a thin-walled shell with blades, nozzles are made around its perimeter for the outflow of compressed air, which creates a rotational movement of the wing. In the inner cavity of the wing there are blades connected by cables with a drum mounted on the fixed axis of the wing. The blades have the ability to move out of the wing cavity by centrifugal forces during its rotation, forming a rotor, and be removed by folding the cables onto the drum during its braking.

 To reduce the loss of gas pressure, the possibility of creating a temperature regime and facilitate the release and cleaning of the blades, the wing cavity, being a disk, can be divided into an air and blade axisymmetric partition. The air cavity has nozzles for the outflow of compressed gas, and blades are installed in the second cavity.

 The proposed wing-disk combines the capabilities of a wing of a high-speed aircraft, which creates a lifting force when flowing over a stream of air in horizontal flight, with a rotor in vertical flight.

 In horizontal flight, the blades are retracted into the cavity of the wing-disk and do not interfere with the high-speed capabilities of the aircraft. In take-off and landing mode, the blades are extended and form the main rotor. The length of the blades is determined only by the radius of the wing-disk, and for folding blades this restriction does not apply. This means that the aircraft’s lift with the proposed wing-wing during takeoff and landing is easily realized up to the lift in horizontal flight.

 The outflow of gas along the perimeter of the wing-disk allows you to blow large volumes at low pressure, which is not possible when the gas flows through the blades.

 The drawing shows one embodiment of the invention.

 The wing contains a disk 1, the axis of the disk, the air cavity 3, the blade cavity 4, the blades 5, the cables for attaching and cleaning the blades 6, the drum for winding the cables 7, the device for braking the drum 8, the channels-nozzles for air leakage 9.

 The disk 1 having an air chamber 3 and a blade chamber 4 is mounted on a fixed axis 2.

 A drum 7 is mounted on the axis 2, to which are attached 6 cables for fastening and cleaning the blades 5.

 On the axis 2, the brake device 8 is fixedly mounted for braking the drum 7.

 A hole is made in the upper (or lower) part of the disk in the area of its axis for supplying excess gas pressure to the air cavity (the direction of gas movement is indicated by arrows). Excessive pressure in the air cavity of the disk causes gas to flow out through the nozzle channels 9. The reactive forces of the air jets create rotation of the disk 1.

 The blades 5, located in the cavity of the disk and held by ropes 6, rolled up on the drum, receive a load of inertial forces that tend to push them out of the cavity of the disk. The process of extending the blades occurs smoothly, if the corresponding function of braking the drum 7 with the brake device 8 is set. After the blades are fully extended, the disk-wing, rotated by the reactive forces of the jets emerging from the nozzles 9, turns into a main rotor, allowing vertical take-off or landing, as well as aircraft rescue , including when stopping engines in flight, using autorotation.

 In horizontal flight and before stopping the rotation of the wing-disk on the ground, the blades 5 are retracted into the blade cavity 4, for which the rotations of the drum 7 are reduced due to braking by its device 8. In this case, the revolutions of the drum 7 are less than the revolutions of the disk 1, which causes the cables to collapse 6 to the drum 7 and, therefore, the cleaning of the blades 5 in the blade cavity 4 of the wing disk 1.

 To release the blades 5 from the cavity of the disk 4 before take-off or landing, it is enough to apply pressure to the air cavity 3, after spin-up of the wing-disk 1, reduce the braking moment holding the drum 7, so that the blades 5 begin to extend from the cavity of the disk 4 until the cables are fully unwound 6 from the drum 7 and the full release of the blades 5.

 The proposed wing is able to work in horizontal flight at very high speeds, including supersonic ones, and is able to create large lifting forces in the hover mode, which can reach many hundreds of tons.

 Aircraft with such a wing have a means of saving the apparatus as a whole. With the transition of all types of aircraft to the proposed wing, the concept of creating aerodromeless aviation can be implemented, which will free humanity from the cost of building and operating huge runways and fundamentally change the problems of safe flights.

Claims (3)

 1. The wing of the aircraft, which is a thin-walled shell with blades, characterized in that along the perimeter of the wing there are nozzles for outflow of compressed air creating rotational movement of the wing, in the cavity of which there are blades connected by cables with a drum mounted on the fixed axis of the wing, with the possibility their extension by centrifugal forces during the rotation of the latter, forming a rotor, and cleaning them into the wing cavity by folding the cables onto the drum during its braking.  6. The wing according to claim 1, characterized in that it is made in the form of a hollow axisymmetric wing disk.  3. The wing according to claim 1 or 2, characterized in that the wing-disk cavity is divided into the air and blade cavities by an axisymmetric partition, the first of which has slots for compressed air to flow out, and the blades are installed in the second.