RU2385257C1 - Hybrid aircraft - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to aerostatic transport systems. Hybrid aircraft comprise airframe, power plant, system of propellers, tail unit, multi-support chassis and nacelle. Nacelle represents an inflatable small-elongation wing with V-wing variable section span. Tail unit consists of inflatable rudder fin with vertical rudder. Two-circuit power plant comprise engine accommodated inside airframe above aforesaid nacelle. System of propellers is arranged on airframe ends and at nose. Multi-support chassis consists of running gear arranged on nacelle and auxiliary chassis arranged on airframe ends. Nacelle accommodates crew cab, passenger and cargo compartments and is secured to airframe from below.

EFFECT: simplified design.

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Description

The invention relates to aviation and aerostatic transport systems for passengers and cargo.

The transportation of passengers and goods by air is a complex technical task. In the case of using aircraft for this purpose, the creation of expensive and complex ground-based infrastructure, such as airfields, is required. The use of helicopters is limited by the dimensions of the payload, the technical complexity of the helicopter and the cost of its operation. The use of aircraft using aerostatic flight principles (airships and balloons) also poses a problem in terms of the dimensions of the aircraft themselves and the complexity of their operation: gas ballasting when the payload mass changes.

State of the art

Known hybrid airship [1], comprising a hull, a nacelle, wings with engines mounted on them with propulsion and tail. The bearing properties of the hull of the mentioned airship are determined by the volume of displaced air and its replacement with light gas. The wings provide only the placement of engines with propellers, balancing and dynamic unloading of the body of large elongation. This design does not solve the main problem of the operation of airships: ballasting when the mass of the payload changes.

Known hybrid aircraft [2], including an inflatable wing, a nacelle, a power plant with four elevating and one thrusting propellers. The push screw allows you to control the thrust vector. The crew cabin is located in the gondola, and the payload is located at the bottom of the wing outside. The wing has a symmetrical profile.

The main disadvantages that significantly limit the capabilities of the aforementioned aircraft [2] are:

- the complexity of the transverse balancing of aircraft in takeoff and landing modes;

- strong suction action of the jets of lifting propulsors, leading to the occurrence of unpaired and asymmetric transverse moments [3, p. 255];

- a significant reduction in the aerostatic component due to the placement of a large number of devices: a power plant (power generator) and lifting propulsors in the central part of the wing.

A hybrid aircraft is known [4], including a flattened hull with an outer shell and a recess in the hull, a payload module placed in the recess, an air cushion landing gear and a power plant.

However, such an aircraft, despite the use of aerodynamic lift, has unsatisfactory take-off and landing characteristics, requires a special aerodrome for deployment, and also does not solve the problem of ballasting when the payload mass changes.

The objective of the invention is to develop a transport hybrid aircraft, which allows to achieve the following technical result: transportation of the payload - cargo and passengers with take-off and landing on unprepared sites, eliminating the problem of ballasting of light gas when changing the mass of the payload.

The essence of the invention is a transport hybrid aircraft, including a hull, powerplant, tail, multi-landing gear and a nacelle. The aforementioned aircraft has a body in the form of an inflatable wing of small elongation, of complex shape in plan and with a variable value of the transverse V-wing in scope. The tail unit consists of an inflatable vertical keel with a rudder. The power plant of the aforementioned aircraft is made according to a two-vector circuit [5, p. 50] and has an engine - an energy unit located inside the hull above the gondola, a system of propulsion devices for taking off, landing and maneuvering the aircraft and placed in the end sections of the hull of the said aircraft at least one or more movers providing translational movement of the aircraft in a horizontal plane and placed in the aft of the said aircraft on q case. Mentioned movers receive energy from the engine - the energy center. The multi-bearing landing gear of said aircraft consists of a power landing gear located on the nacelle and a supporting landing gear located on the tips of the aircraft hull. The nacelle of said aircraft has a crew cabin, transport and passenger and cargo compartments and is attached from below to the hull of said aircraft.

The list of figures drawings.

Figure 1 - the proposed apparatus, side view;

Figure 2 is the same, a top view;

Figure 3 is the same front view;

Figure 4 is the same, side view, section.

Transport hybrid aircraft is an inflatable body 1, filled with light gas, in the form of a wing with a gondola 2 attached to the body from the bottom (figure 1). The hull of the aforementioned aircraft is made in the form of an inflatable wing of small elongation, of complex shape in plan and with a variable value of the transverse V-wing in scope. This provides a reduction in windage during lateral airflow, lateral stability, layout of the components of the aircraft, a decrease in the gas-dynamic effect of the underlying surface during vertical take-off and landing, and an increase in the screen effect with horizontal movement near the earth's surface. To ensure vertical takeoff and landing, control of pitch, roll and heading, balancing the aforementioned aircraft at low flight speeds in the end sections of the hull, a propulsion system 3 is installed (Figs. 1, 2). Such an installation of propulsors in combination with the shape of the hull will not only reduce the influence of the suction effect [3, p. 255], but it will also create additional lifting force from forcing air into the space between the lower surface of the hull and the underlying earth surface. To ensure the directional stability of the aircraft in the aft of the aforementioned aircraft installed vertical tail 4 with a rudder. The translational motion of the aforementioned aircraft is ensured by the installation of at least one mover 5 in the aft of the aircraft. Thus, the power plant is made according to a two-vector scheme: when the aircraft moves in a vertical plane, movers 3 are installed, installed in end sections on the hull 1. When translating in the horizontal plane, movers 5 work. All movers operate on the transition sections of the flight from vertical to horizontal : 3 and 5. However, the thrust of the propulsors 3 depends on the speed of translational movement in the horizontal plane: the higher the speed, the less the thrust of the propulsors 3 until they are completely turned off. This allows for high fuel efficiency. To ensure the balance of the aforementioned aircraft in horizontal flight and roll control on the rear edges of the housing 1 (figure 2) installed steering surfaces 6. In the front edge of the Central part of the housing 1 (figure 3) there is an air intake 7 (figure 3, 4) for engine - energy center 10 (figure 4), providing energy propulsion 3 and 5 and other on-board consumers. Mentioned engine - power unit 10 (figure 4) is installed in the aircraft on the gondola 2, which facilitates access to it, its maintenance and repair. The chassis of the aforementioned aircraft is multi-bearing. In order to reduce its weight and reduce the load on the aircraft’s power structure, the power chassis 9 (Fig. 3) is mounted on a nacelle, and a supporting chassis is installed in the end sections of the hull 8. The nacelle 2 (Fig. 1) of the aforementioned aircraft is divided into compartments and has a crew cabin 11 (figure 4), transport - passenger 12 and cargo 13 compartments.

The flight of the aforementioned aircraft occurs under the influence of aerodynamic, aerostatic lifting forces, vertical and horizontal components of the thrust of the aircraft power plant. The value of the aerostatic force is selected so that, in the absence of thrust of the power plant and flight speed, its value corresponds to the mass of the structure of the aforementioned aircraft without payload. The missing part of the vertical force for vertical take-off or landing is compensated by the vertical component of the thrust of the power plant from propulsors 3 (Fig.2). In horizontal flight with the propellers 3 off, the missing part of the vertical force to ensure horizontal flight is compensated by the aerodynamic lifting force of the housing 1 (Fig. 1). This ensures the achievement of the technical result: transportation of the payload of goods and passengers with take-off and landing on unprepared sites and elimination of the problem of ballasting of light gas when the mass of the payload changes.

Information sources

1. "OHIO". Dynalifter. Jane's All the World's Aircraft 2004-2005. Jane's Information Group Inc. USA, 2004.

2. AMSAT MAHTHA X001. Jane's All the World's Aircraft 2004-2005. Jane's Information Group Inc. USA, 2004.

3. Pavlenko V.F. Power plants of aircraft vertical takeoff and landing. - M.: Mechanical Engineering, 1972, p. 284., Ill.

4. Patent RU 2264315 C2, cl. B60V 3/08, B64C 1/00.

5. Hafer K., Sachs G. Technique of vertical take-off and landing: TRANS. with him. M .: Mir, 1985 .-- 376 p., Ill.

Claims (1)

Hybrid transport aircraft, including a hull, powerplant, tail, multi-landing gear and a nacelle, characterized in that the aircraft has a hull in the form of an inflatable wing of small elongation of complex shape in plan and with a variable transverse V-wing in scope, tail consists of an inflatable vertical keel, the power plant of the aforementioned aircraft is made according to a two-vector circuit and has an engine-power unit located inside the body above the gondola, propulsion system th, providing take-off, landing and maneuvering of the aircraft and placed in the end sections of the hull of the aforementioned aircraft, at least one or more movers, providing translational movement of the aircraft in a horizontal plane and placed in the stern of the aforementioned aircraft above the hull, said movers receive energy from the engine-energy unit, the multi-support chassis of the aforementioned aircraft consists of a power chassis placed on the gondola le, and supporting the chassis, which is located on the airframe endings, and the nacelle of said aircraft has a crew cab, transport and passenger and cargo compartments, and is attached to the bottom of the body of said aircraft.

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