EA016905B1 - Multi-purpose highly-maneuver flying vehicle - Google Patents

Abstract

The invention relates to aviation. A flying vehicle comprises a toroid-shaped body embodied with radial apertures, cargo compartments, a power unit, front and rear crew cabins, a control system and landing means. Rotating members are arranged in the radial apertures, a pivoting platform with an engine and a circular plane-wing consisting of segments are mounted on both of which. The rotating members are adapted to pairwise symmetrical blasting off. An elastic capacity for heated gas is located inside the central section along its perimeter and is fixed to a capacity filled with helium and coupled with a removable upper convex carrying surface and with the body. Winches are mounted on walls of a cylindrical shaft and arranged in the tore central space for regulating the volume of the elastic capacity. Along their circumference the cargo compartments are provided with retractable elastic capacities. The control system is equipped with a gyroscope. The invention results in increasing load capacity.

Description

Technical field

The invention relates to aircraft, contains a number of fundamentally new technical solutions and can be used in various sectors of the modern economy of the country. The aircraft can be used as an aerostat, and as an airship, and as an airplane, and as an ekranolet, and as a thermoplane.

State of the art

Known disk-shaped aircraft vertical take-off and landing (see US patent No. 3614030, CL No. 64Ό 27/02, 1969), containing a large number of engines installed in the wells on the periphery of the disk-shaped body, some of which are auxiliary and are ballast in flight time. A known aircraft does not allow the transport of goods in an upright position, it is impossible to transport masts, pipes, etc., and has a limited carrying capacity.

Also known is an aircraft lighter than air (see ed. St. USSR No. 687728, class B64B 1/58, 1976), equipped on the periphery with engines with controlled nozzles and a central cargo compartment, providing lifting and transportation of bulky goods in a vertical position . A disadvantage of the known aircraft is the limited carrying capacity, low maneuverability, difficulty in piloting and limited application.

Known toroidal aircraft heavier than air with a propeller located in the center (see US patent No. 5152478, CL 64C 29/00, 1990). The device has the same disadvantages: low maneuverability, low and limited carrying capacity, difficulty in piloting and inconvenience of operation. The central part of the torus is occupied by the main rotor and cannot be used for cargo placement.

A well-known aircraft is heavier than air, such as a flying saucer-platform, equipped with pivotally mounted peripheral jet engines that create not only efforts to lift and move the aircraft in the air, but also significant control efforts (see French application No. 2104709, class B64C 29 / 00, 1972). With improved controllability, this unit has a low and limited carrying capacity and many of the disadvantages mentioned above.

Known aircraft is lighter than air, made in the form of an annular wing, in the housing of which there are several turbojet engines equipped with rotors (see RF patent No. 2070143, class B64C 39/06, 1996). Fuel tanks, cargo and passenger compartments, a cockpit and other devices are located in the wing cavities of a known aircraft. The central space of the annular wing can be used to accommodate bulky loads in an upright position, such as missiles. However, a horizontal flight of such an apparatus, with a vertical load at the time of launch, is carried out in its horizontal position, which inevitably leads to a complication of the load securing system, violation of the cable-stayed suspension, necessitates the use of shaped fastening elements, which means a significant increase in the total weight and limiting the carrying capacity. Such a device is controlled by changing the engine thrust, which makes it difficult to pilot and reduces maneuverability.

Also known is an aircraft lighter than air (see patent EP No. 0201309 A2, class B64B 1/00, 1986). The device is a toroidal body filled with helium. One or two propulsors are installed on the crossbar in the center of the device’s casing, which provide vertical control of the device. On the outside of the body, lateral gas turbine engines are installed, providing horizontal flight and heading control. It is also possible to place engines on an outboard platform with the ability to rotate them to control flight.

A well-known aircraft has the same disadvantages: limited carrying capacity mainly in terms of size, difficulty in piloting due to the large windage, which complicates operation, low maneuverability and reliability.

Known multi-functional aircraft vertical take-off and landing (see RF patent No. 2127693, class, B64C 29/00), which is a toroidal body containing cargo compartments, crew cabs, a power plant with power units, radial niches, controls and landing bodies.

The reasons that impede the achievement of the technical result indicated below when using the known device include the fact that platforms with engines located outside the aircraft’s hull create significant resistance at high flight speeds.

The closest aircraft of the same purpose to the claimed invention in terms of features is a highly maneuverable aircraft (see RF patent No. 2332331, CL B64C 29/00), containing a toroidal hull, cargo compartments, power plant, front and rear cockpits, control system and touchdown bodies. The housing is made with radial niches. In the niches are placed rotary devices, each of which is made in the form of a ring with a rotary platform mounted on it with an engine and a wing plane with the possibility of rotation of the platforms.

The reasons that impede the achievement of the technical result indicated below when using the known device include the fact that the device has a limited carrying capacity.

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Disclosure of invention

The objective of the invention is the creation of a universal highly maneuverable aircraft with obtaining a technical result, which consists in providing a wide range of possibilities for its application, in particular, one of the options for use as an air crane of high efficiency and operational manufacturability, increasing load capacity through the use of an elastic tank.

The specified technical result in a universal highly maneuverable aircraft is achieved by the fact that it contains a toroidal shape made with radial openings, with rotary devices placed in them, each of which has a rotatable platform with an engine and a wing plane, cargo compartments power plant, front and rear cockpits, control system and touchdown bodies.

The peculiarity is that inside the central compartment around its perimeter there is an elastic container for heated gas with the possibility of moving it up outside the aircraft body, attached to a container filled with helium, and connected to a removable upper convex bearing surface covering the top of the central compartment, and with housing; on the walls of a cylindrical shaft located in the central space of the torus, winches are installed that provide regulation of the volume of the elastic tank; cargo compartments around the circumference are equipped with retractable elastic containers; rotary devices are made with the possibility of pairwise symmetrical shooting, the plane-wing is made annular and consists of segments, and the control system is equipped with an electronic gyroscope.

Also a feature is that the elastic container is made cylindrical with two-layer walls.

Rotary devices are made in the form of cylinders.

The proposed aircraft is a vehicle heavier than air, but lightweight through the use of a light carrier gas, such as helium. Depending on the aircraft loading option, its free cargo compartments, including the central space of the torus, are equipped with light elastic containers and filled with light gas, which leads to a decrease in the mass of the aircraft structure and increases its carrying capacity.

The invention is illustrated by graphic materials, which depict:

in FIG. 1 (a, b) is a structural diagram of the aircraft in the parking position, front view, a) in preparation for horizontal take-off, b) with vertical take-off;

in FIG. 2 - the same top view, half of the upper bearing surface is removed;

in FIG. 3 - toroidal hull of the aircraft without rotary power units, top view, upper bearing surface conditionally removed;

in FIG. 4 is a view along AA in FIG. 3;

in FIG. 5 is a view along BB in FIG. 3;

in FIG. 6 is a view along BB in FIG. 3;

in FIG. 7 - aircraft with a vertical load in the parking position, prepared for vertical take-off;

in FIG. 8 - aircraft with a load on the external (cable-stayed) suspension in flight, FIG. 9 - aircraft with deployed elastic capacity.

A universal highly maneuverable aircraft includes a rigid lightweight toroidal hull 1 (Fig. 1 a and 1b), inside which there are cavities filled with a carrier gas - helium. In the radial openings (niches) 2 (Fig. 3) of the toroidal housing 1 there are six rotary devices 3 (Figs. 2 and 6) in the form of cylinders with platforms 4 mounted on them that are rotatable relative to the radii (Fig. 2). In the middle of each rotary platform 4, one engine 5 can be fixed, having a changing thrust vector, or two conventional jet engines with rotary nozzles and an annular plane - a wing 6 above the engine 5, or turbojet.

Fuel tanks are located in the cavities of the turntable 4. Above the engines 5, an annular wing plane 6 is installed (Fig. 1b), which can either function as a wing, or a stabilizer, or a steering plane, depending on the position of the engines 5 relative to the torus-shaped body 1 of the aircraft .

The ring plane - wing 6 in one case turns engine 5 if it crashes for some reason, in the other it changes the thrust vector, in other cases 50-55% works as a wing and ~ 30-35% as a stabilizer.

The annular plane-wing 6 consists of segments that change the profile.

The rotary platform 4 can rotate in any direction around its axis and move in any direction along the radial openings (niches) of the aircraft 2, and the engine 5 with the annular plane-wing 6 above it will perform the function of the marching engine, and the annular plane wing 6 will perform the functions wing, in another case, the engine 5 will perform the function of the steering engine, and the annular plane-wing 6 - the function of the steering plane.

The aircraft has a channel for easy access throughout the corridor and a place for

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The toroidal hull 1 of the aircraft is equipped with removable upper 7 convex and lower 8 concave bearing surfaces (Fig. 1a), hermetically closing, if necessary, the internal space of the toroidal hull 1.

Inside the central compartment 30, a retractable elastic container 9 for heated gas is attached along its perimeter, attached to a container 10 filled with helium and connected to a lightweight removable upper convex bearing surface 7 (removable lid) (Fig. 9), covering the top of the central compartment 30, and with a toroidal housing 1.

In the lower surface there is a hatch 11 for water intake at the moment of touching the water surface during flight, the sashes of which automatically close after filling the inside of the torus with water. The cavities of the toroidal hull 1 formed between the radial openings (niches) 2 are used to arrange the cargo compartments 12 (Fig. 5), the front 13 and the rear 14 (Fig. 4) of the pilot cabins and rigging equipment. The cargo compartments 12 are also provided around the circumference with retractable elastic containers.

Pilot cockpits 13 and 14 are identical, equipped with duplicated control systems, which provides control from one cockpit and adjustment from another. This ensures accuracy of landing, facilitates the reception and unloading of goods transported on the external sling and inside the torus in a vertical position, provides control over all operations of the crew in flight and the position of the aircraft in space.

The cargo compartments 12 are provided with easily removable floors 15 (Fig. 5) and hinged hatches 16 with cargo ramps 17. A cylindrical shaft 18 (Fig. 4) is installed in the central space of the torus, which is included in the power system of the aircraft body and provides cable-stayed cargo suspension. To do this, on the walls of the cylindrical shaft 18 there are fastening devices 19 that provide rigid (Fig. 7) and cable-stayed external (Fig. 8) suspensions and automatic discharge of loads.

The internal space between the toroidal casing 1 and the walls of the cylindrical shaft 18 is used to accommodate the annular power structural elements, power compartments 20 and 21 and the annular channel 22, which provides communication between the front 13 and rear 14 of the pilot's cabs, as well as free access to elements of various systems located in the power compartments 20 and 21. These compartments also house equipment and devices for braking and fixing the power units 23 rotatable relative to the Ι-Ι axes. In the power compartments 20 and 21 are placed e front 24 and rear 25 sliding telescopic rods - touchdown organs. Outside the upper power compartment 20, an annular power element 26 is located, which also provides for the installation and fixation of the upper bearing surface 7. The rotary devices 3 are attached to the power walls of the radial openings (niches) 2, which, when the engine ignites, are fired off symmetrically in pairs with the opposite rotary platform 4, This ensures the autonomy of propulsion systems and balancing the aircraft.

The control system includes an electronic gyroscope that provides stabilization of the aircraft in the air, automatic control of the power plant elements and flight modes of the device. Automatically controlled landing organs ensure a smooth landing of the apparatus not only on a horizontal, but also inclined to 30-40 ° surface, and a sealed torus housing with the landing organs removed allows landing on water, which is especially important when using the apparatus in a fire variant.

Landing bodies are made in the form of telescopic wheeled platforms and have a frame with a removable bottom and top. The length of the telescopic rods 24 and 25 when extended automatically locks when meeting an obstacle, which ensures the landing of the apparatus on an inclined surface.

The operation of the aircraft, basically, boils down to the lifting and transportation by air of various cargoes 27, 28. In this case, there may be various options for loading it and various use cases.

The elastic container 9 located inside the central compartment 30, when lifting the load with the help of a container 10 filled with helium, rises up and is filled with heated gas, thereby increasing the lifting force of the aircraft.

If the aircraft is used as an air crane for lifting and moving loads over short distances or for installation work, its removable upper convex bearing surface 7 is detached and with an attached container 10 filled with helium starts to rise up and pulls an elastic container 9, made, for example, in the form of a cylinder and filled with light heated gas. The elastic tank 9 is made with two-layer walls for thermal insulation. The elastic tank 9 is filled with hot exhaust gases from the engines 5 and mixed with the incoming air. An extra effort is created and the aircraft functions as a thermoplane.

When unloading the aircraft, the elastic tank 9 is deflated and, using winches 29 mounted on the walls of the cylindrical shaft 18, is returned to the central compartment 30, which makes it possible to efficiently use the aircraft when transferring from one installation area to another.

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Moving the elastic tank 9 upwards beyond the toroidal hull 1 of the aircraft allows increasing the volume of heated gas by increasing the volume of the elastic tank 9 (depending on the load lifted), regulated by winches 29, and if not necessary, the elastic tank 9 is folded around the circumference of the central compartment 30 s internal or external depending on the transported cargo.

Engines and steering planes achieve precision crane work.

If it is necessary to transport small-sized cargoes over a long distance, the cargo compartments of the torus are filled with cargoes, the upper 7 and lower 8 bearing surfaces are installed and the aircraft is able to transport cargo in this embodiment to the maximum distance. If necessary, carry large loads over a short distance, such as transporting missiles, all cargo compartments of the torus are freed.

When taking off in a limited space, all engines 5 are mounted vertically (Fig. 1b) and become traction engines, and the ring plane - wing 6 becomes a stabilizer. The inner space of the central compartment 30 can also be used to accommodate vertical bulky goods or the passenger compartment, or to place water that fills the inner space of the torus when it touches the water surface (Fig. 5) through the partially open side of the hatch 11. In this case, the central cavity torus is tightly closed by the upper 7 and lower 8 bearing surfaces, which improves the aerodynamics of the aircraft (the upper bearing surface is slightly convex, the lower is slightly concave), reducing a fuel consumption and increases the flight distance.

When extinguishing large fires, the proposed aircraft can be used in two versions: transportation of water containers on cable-stayed suspension or transportation of water in the inner space of the torus, which is filled at the moment of touching the water surface during flight.

The conversion of an aircraft from one variant to another is carried out by the operating units using standard equipment and tools.

There may be other, depending on the situation, options for the application and use of the aircraft, when high lift, high maneuverability in flight with cargo, aerodrome-free basing and work on unprepared sites are required.

Thus, the claimed aircraft can take various geometric shapes and have an adjustable load capacity. The invention improves the aerodynamics of the aircraft and its safe operation. The rapid movement of the aircraft allows you to solve any economic problems.

The absolute dimensions of the apparatus will be determined by its power capabilities, the total thrust of the engines and the required masses of cargo.

Claims (3)

CLAIM 1. Universal highly maneuverable aircraft containing a toroidal shape made with radial openings, with rotary devices located in them, each of which has a rotatable platform with an engine and a wing plane, cargo compartments, power plant, front and rear cockpit, control system and touchdown bodies, characterized in that inside the central compartment along its perimeter there is an elastic container for heated gas with the possibility of its changing stills beyond the aircraft’s hull, attached to a tank filled with helium, and connected to a removable upper convex bearing surface covering the top of the central compartment, and to the hull; on the walls of a cylindrical shaft located in the central space of the torus, winches are installed that provide regulation of the volume of the elastic tank; cargo compartments around the circumference are equipped with retractable elastic containers; rotary devices are made with the possibility of pairwise symmetrical shooting, the plane-wing is made annular and consists of segments, and the control system is equipped with an electronic gyroscope. 2. The apparatus according to claim 1, characterized in that the elastic container is made cylindrical with two-layer walls. 3. The apparatus according to claim 1, characterized in that the rotary device is made in the form of cylinders.