RU2673754C2 - Rotary-wing aircraft - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: invention relates to the field of aviation, particularly to the rotorcrafts designs. High-speed rotorcraft with increased flight range contains coaxial rotor, fuselage, power plant, gearbox, wings, stabilizer, chassis, control system. Rotary wing also contains a wing, made closed, located under a coaxial rotor, located in the center of gravity, a stabilizer with controlled gas-dynamic and mechanical steering wheels, coaxial autorotal gyroplane bearing screw, power plant with an additional air compressor, pulling marching jet engines, motor-generator. At the same time, the reactive exhaust gas flows of the jet engine, coming out of the nozzles with a controlled thrust vectoring, ensure the balance of the rotor wing with the operation of the gas-dynamic rudders of the keel and stabilizer using the Coanda effect.

EFFECT: increase in flight range and speed is provided.

1 cl, 4 dwg

Description

The invention relates to the field of aviation technology and can be used in helicopter engineering.

Rotorcraft are known made according to one, two or multi-rotor schemes (domestic: Ka-22, Ka-35, American - "Bell V-22 Osprey", British - "Rotodine", experimental X2, X3). Their common advantage is that they do not require a runway, and using a wing in their design can increase the speed and range. Their main disadvantages are the non-use of additional propulsion in helicopter modes (hovering, vertical climb and lowering, flying at low speeds). At the same time, the wing in these flight modes is not only inefficient, but also creates additional resistance to flow from the rotor. In airplane modes (flying at cruising speed) - the main rotor operates in the mode of generating propulsive force in the direction of flight, while the main rotor creates the main resistance to flight on the advancing blades where the flow velocity approaches the speed of sound and the growing losses in the aerodynamic quality of the helicopter as an aircraft. The combination of different helicopter and aircraft systems in a rotorcraft leads to a complication of the design and leads to a decrease in the useful weight return of the rotorcraft.

Their main disadvantages are that rotorcraft have a lower aerodynamic quality compared to an airplane, and there are insurmountable difficulties on the way to increasing that, with existing rotorcraft designs. For rotorcraft with increased speed and flight range are characteristic - overweight and complicated design with the lack of an optimal hybrid power plant, the high cost and complexity of manufacturing and operation, the high risk of emergencies are a deterrent to the widespread introduction of rotorcraft.

Known transport rotorcraft Ka-22, which is a combination of a helicopter and an airplane with a transverse arrangement of rotors and a fixed mechanized wing of a large scale with flaps rotated 90 °, with a combined power plant having two turboprop engines with two pulling propellers and two rotors located at the ends of the wings of a large scale, with fixed gear three support chassis with a bow rack.

Among the disadvantages are the low aerodynamic quality at cruising flight speed, the small resource of the power plant and the associated constant need to replace engines and gearboxes, the non-optimal arrangement of rotors, the complexity and bulkiness of the structure, track instability with a high risk of emergency situations, complexity, and sometimes and unpredictability in management, lack of maneuverability, great complexity in manufacturing and the inability to start mass production.

Known high-speed over-maneuverable rotorcraft (patent RU 2480379). The design is a three-stage tier screw circuit with two rotors in the rotary annular channels located at the end of the tail boom, and a high-speed rotor, the ends of the blades of which are bent in the opposite direction of its rotation. The rotorcraft is equipped with a power plant with two gas turbine engines that transmit torque through the main gearbox and the drive system through a synchronization mechanism, consisting of transmission connecting shafts to the main and lower rotary screws, gas-jet steering and longitudinal control rudders, and three support chassis. The rotorcraft has a low weight return, a complex mechanical scheme for converting an aerodynamic configuration with a helicopter - three rotors with different-sized rotors into a pulling system with rear rotary rotors - into a rotorcraft - consisting of a rotor of the front rotor and two lift-pull rotors at the end of the beam. Thanks to this, an increase in flight speed is achieved, but with an increased specific fuel consumption characteristic of helicopters with low aerodynamic quality

The design presented has significant drawbacks. Increased weight due to a large number of gearboxes, due to additional rotors, elongated tail unit and transmission. The mutual influence of the main bearing and auxiliary counter-rotating rotors impairs aerodynamics of the rotorcraft. The rotor at high flight speeds creates a large aerodynamic drag and increased vibration. The main disadvantage is the complex drive and synchronization system for rotating all the propellers in different flight modes, the complexity of the control system in transient flight modes and low aerodynamic quality. The great complexity of manufacturing and refinement.

The closest analogue to the principle of operation and technical execution of the present invention relates to a single-rotor helicopter Ka-92 with autorotating, coaxial rotor and flat shortened wings, which we took as a prototype. The presence of wings makes it possible to consider it a rotorcraft. Ka-92 has the best tactical and technical characteristics among aircraft of the middle class. Its main design advantages are: the absence of a tail boom, transmission, intermediate gears and tail rotor like a Mi-8 helicopter; ease of converting it into a high-speed rotorcraft; the presence of a simplified control system compared to a single-rotor helicopter of the Mi-8 type; the possibility of using the Coanda effect; well-established serial production; the simplest design in comparison with multi-rotor rotorcraft, convertiplanes; the presence of a large, hidden reserve in terms of its further modernization; small wingspan, not interfering with the operation of the rotors, the Ka-92 design is compact.

The Ka-92 helicopter contains a keel fuselage, two coaxial rotors located in the center of gravity, a pushing propeller, a power plant consisting of two turboprop gas turbine engines, a main gearbox, a fan and a launch system, a landing gear.

The small wingspan contradicts the basic requirements for the wing of an aircraft: in terms of optimal wingspan, elongation, area, configuration, strength, stiffness, weight and, as a result, in aerodynamic quality. This is the main disadvantage in creating a high-speed rotorcraft. Another disadvantage is the sharp increase in the aerodynamic drag of the main rotor as cruising and maximum flight speed. The use of obsolete power plants with an increased specific gravity also does not allow to achieve high flight speeds in the previous layout and ensure a reduction in specific fuel consumption. Traditionally, for all helicopters, including for the Ka-92 helicopter, it is not typical to carry out a silent flight. The helicopter does not use a wing to accommodate fuel. Complicated retractable chassis design. Increased wear and reduced engine life from dust, dirt and aggressive inclusions. The inability to independently move around the territory with the engines turned off. Use a heavy gear. Lack of convenient sites for repair personnel.

The objective of the invention is the creation of a high-speed rotorcraft design with increased transport and (or) combat efficiency, reduced vibration and noise, and increased flight safety, capable of flying over longer distances with an increased number of passengers or cargo, including by means of quick modernization available fleet of mass-produced helicopters.

An object of the invention is to increase flight speed and range by increasing the aerodynamic quality of the aircraft as a whole and the reduced weight of the rotorcraft and reducing the cost of flights and operating costs.

The technical task in the rotorcraft containing the fuselage, power plant, wing, keel, stabilizer, rotor, landing gear, control system is achieved by the fact that it contains a closed wing mounted under the rotor concentrically relative to the fuselage, with the fuel placed in it; an autogyro rotor, a power plant with additional marching WFD and controlled traction vectors, a stabilizer with controlled gas-dynamic and mechanical rudders.

The technical result obtained by the implementation of the claimed invention is the creation of a rotorcraft with a coaxial rotor, which, according to the tactical and technical parameters, belongs to the best rotorcraft models in its class, possessing the properties of a gyroplane, helicopter and aircraft with an increased flight range of over 1400 km and a flight speed over 450 km / h.

Analysis of the known technical solutions in this technical field showed that the proposed rotorcraft design has features that are not found in the known technical solutions, and their use in the claimed combination of features makes it possible to obtain a new technical result, therefore, the proposed technical solution has an inventive step compared to the existing prior art.

The proposed technical solution is industrially applicable, as it can be manufactured industrially, efficiently, feasibly and reproducibly, therefore, it meets the patentability condition “industrial applicability”.

Comparison of scientific, technical and patent documentation on the priority date in the main and related sections of the MKI shows that the set of essential features of the claimed solution was not previously known, therefore, it meets the patentability condition of “novelty”.

The design and principle of operation of the proposed invention are illustrated by drawings, in which:

FIG. 1 - rotorcraft with coaxial screws and a closed wing and stabilizer (side view);

FIG. 2 is a schematic drawing of a power plant;

FIG. 3 - rotorcraft (front view);

FIG. 4 - rotorcraft (rear view).

A rotorcraft contains: a fuselage (1), autogyro-autorotating coaxial rotor (2) of a rigid or articulated design with a cowl (3), keel (5), a stabilizer (6), a closed direct or inclined wing (4), aerodynamic fairings (8, 10) the wheels of the front (9) and the main chassis (7), the power plant, consisting of jet engines (14) for driving the rotor (2), the main gearbox (16), the clutch (12), the motor generator ( 13), a gearbox (16), a brake device (11), and pulling jet engines (17).

On a rotorcraft with one coaxial rotor in the center of gravity, a closed wing (9) is mounted concentrically with upper and lower gaps relative to the fuselage (1). The wing (9) has a high aerodynamic quality, relatively low weight, great rigidity and strength. Such a wing, in comparison with the traditional one, is “flat,” with equal load-bearing areas it has a smaller scale. This allows the high-speed air flow from the rotor, which has a significantly larger diameter than the wingspan, with little resistance to pass by the wingspan with a small wingspan and without loss of loss to maintain the bearing properties. In this process, the most active part of the high-speed air flow is used, formed by the ends of the rotor blades, the speed of which decreases as you approach the rotor hub. The small wing span, increased strength and stiffness due to the elimination of the cantilever attachment to the fuselage assembly occurring at the flat wing, provide a design lacy, lower wing thickness with a decrease in drag coefficient C _x , a significant reduction in rotorcraft weight and a decrease in drag. The formation of lift occurs around the entire perimeter of the closed wing, above and below the surface of the fuselage (such as a biplane), which cannot be obtained from a rotorcraft with a flat wing. A closed wing reduces inductive losses at the ends of flat wings, and eliminates losses that occur with flat thickened wings at the points of their mating with the fuselage. The closed wing has high load-bearing capabilities, providing continuous flow at angles of attack up to 43 ° ÷ 55 °. An increase in the aerodynamic quality of a rotorcraft at maximum speed is provided by a decrease in the revolutions of the autorotating rotor, the installation of the rotor blades in the minimum resistance position, the aerodynamic contours of the fuselage, the aerodynamic fairings of the landing gear and the swashplate, and the placement of the main fuel in the wing. To improve the aerodynamic quality of rotorcraft designed for high flight speeds, a closed wing is performed with forward or reverse sweep. For landing on an airplane with a large tonnage angle with a short fuselage, the rear of the fuselage can be used for a retractable fan tail, similar to the tail of a bird released upon landing.

As the maximum flight speed is set, the main lifting force is redistributed from the autorotating coaxial rotor (2) to the wing (4) with a simultaneous gradual decrease in the rotor speed to the calculated value. In flight, the plane of rotation of the rotor blades is in a stable autorotation position with minimal resistance to the incoming flow, and when landing on autorotation, the ring wing is located at the angles of attack with the highest possible lifting force. The fuselage is streamlined, designed for high flight speeds. The keel (5) and the stabilizer (6) are attached to the power elements of the fuselage (1). The stabilizer (6) is made geometrically similar to the wing (4) and placed in the zone of effective airflow from the pulling marching WFD (17).

The wheel (9) of the front landing gear with an extended strut retracts into the fuselage (1) and is closed by a cowl (10). The wheels (7) of the main chassis are retracted into the aerodynamic fairing-ridges (8) located on the wing (4).

In a power plant, jet engines (14) are used to drive rotors (2), to drive an additional compressor, and to drive a motor generator (13). An additional compressor (15) is used for boosting air into the marching air-propelled thrusters (17). The motor generator (13) is used to start the WFD (14) and to provide power to the rotorcraft, including for recharging the onboard power sources and heating the rotor blades. Pulling the WFD (17), located near the center of gravity of the rotorcraft on a common power frame, provide the creation of propulsive thrust. Jet propellant exhaust flows (17) emerging from nozzles with a controlled thrust vector provide balancing of the rotorcraft with the work of gas-dynamic rudders of the keel (5) and stabilizer (6) using the Coanda effect. The wheels (7, 9) of the chassis are made with electric drives for independent movement of the rotorcraft on the ground without starting the main engines.

Rotorcraft works as follows. Take-off and flight is possible to carry out options: by helicopter, plane or gyroplane. In the autogyro variant, flight is performed at maximum range with maximum speed. Take-off balancing, hovering over the “object” and in flight is carried out using a jet nozzle with a variable thrust vector and gas-dynamic rudders using the Coanda effect. Silent flight is performed using an electric motor-generator.

For the practical implementation of the invention, patented components of power plants have been created: pulling silent WFDs, highly efficient motor generators, lightweight silent gears, energy-intensive power supplies, laser spark plugs, high-life reversing nozzles. All of the above is superior in technical characteristics to foreign samples. The main and main advantage in the creation of a rotorcraft is that it is created by modernizing existing, improved to perfection serial domestic or foreign helicopters at serial plants, with an unchanged production cycle and the established staff of experienced specialists. In the process of creating a rotorcraft, a simplified modernization is possible due to the use of components and assemblies that do not require modifications or with minimal modifications. These include: the fuselage and passenger compartment, cockpit, coaxial rotor of the helicopter, helicopter control systems, instrumentation and support systems. In order to reduce the cost of experimental research and development work and the creation of a prototype, it is possible to use helicopters with a small residual resource.

Claims (1)

High-speed rotorcraft with increased flight range, containing a coaxial rotor, fuselage, power plant, gearbox, wings, stabilizer, landing gear, control system, characterized in that it contains a wing made closed, located under the coaxial rotor located in the center of gravity, the stabilizer with controlled gas-dynamic and mechanical rudders, coaxial autorotating autogyro rotor, power unit with additional air compressor, pulling mid-flight propulsive thrusters, motor-generator, and overt flows WFD exhaust exiting the nozzles with thrust vector control, provide balancing rotorcraft work gasdynamic rudders keel and stabilizer using a Coanda effect.

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