RU2332331C2 - Multi-purpose high-maneuvrability frying vehicle taking off at whatever angle to take-off surface - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering. The flying vehicle comprises tore-like airframe (1), cargo compartments, a power plant, crew front and rear cockpits, control system and landing assemblies (18, 19). The airframe incorporates radial recesses accommodating rotary devices representing rings supporting rotary platform (4) with engine (5) and plane-wing (27), the platform being turned on forcing air in between the airframe recess and the ring planes.

EFFECT: better aerodynamics.

6 cl, 9 dwg

Description

The invention relates to aircraft, contains a number of fundamentally new technical solutions and can be used in the design and development of various aircraft.

The proposed aircraft is designed to solve a wide range of tasks of national, scientific and military significance.

Currently, there are a large number of different circuit and structural solutions used in the creation of aircraft, but all of them have a specific and narrow focus. All of them are usually designed to perform some specific functions, to solve specific problems in certain conditions. The inability to widely use them for different purposes in different conditions entails unreasonably high costs for the development and creation of a variety of aircraft. In addition, due to the limited time for the intended use of the devices, their payback is not ensured, operation and maintenance are complicated, and the established level of reliability and safety is not ensured. This aircraft does not belong to the well-known vertical take-off and landing aircraft of classical traditional schemes, that is, to vertical take-off and landing aircraft and helicopters, which currently have reached high technical perfection and are widely used in various fields of human activity.

The use of helicopters in the national economy is known / cm. I.I. Biryulin. Helicopters in the national economy. Publishing house "Transport", 1969 / for construction and installation works and in some industries, which has a number of disadvantages: they are not equipped with a device that provides visual observation by the pilot of the load on the external load; are not equipped with a lock in the lower part of the external suspension, as a result of which, in many types of work, after installing the load, it is necessary to drop the cables.

For example, various types of vertical take-off and landing aircraft from combat high-speed fighter aircraft / cm are known. V.F.Pavlenko. Aircraft vertical takeoff and landing. Military Publishing House of the Ministry of Defense of the USSR, M., 1966, pp. 54-72 / to transport low-speed aircraft designed to move various cargoes in the air compartments or on an external sling / cm. ibid.

Various types of helicopters / cm are known. Yu.S. Bogdanov and others. The design of helicopters, M., Mechanical Engineering, 1990, pp. 3-13 /. At the same time, there are many technical projects and really operated aircraft of unconventional schemes such as discoplans, "flying saucers", flying platforms, etc., which have not been widely used due to their inherent disadvantages mentioned above.

It is known that to ensure vertical take-off and landing of the apparatus, it is necessary to use the power plant to create a vertical thrust component equal to or slightly greater than the mass of the aircraft, that is, the thrust-weight ratio of the aircraft / the ratio of the total thrust of its power plant to the mass of the device / should be equal to unity / 100% / or slightly more than one / more than 100% /.

For conventional conventional airplanes, a propulsion system is needed to create a thrust force that ensures its forward motion, and the lifting force is created by the wing-bearing surface. In this case, the body performs the functions of a wing. This force is proportional to the square of the speed of flight and in horizontal flight is equal to the mass of the aircraft.

The thrust-weight ratio of conventional aircraft can be significantly less than one and make up only 20-40 percent. Since engine thrust is proportional to fuel consumption, it is quite obvious that an increase in the thrust-weight ratio, that is, the creation of an aircraft of vertical take-off and landing, is inevitably associated with a decrease in the carrying capacity and transport capabilities of the aircraft. This necessitates the search for ways to create new aircraft, increase their carrying capacity and efficiency. One of such ways is to improve existing aircraft by reducing their mass through the use of lightweight composite materials, choosing optimal structural designs, and using new economical engines.

Another way is the development of new non-traditional schemes and designs using the already known positive properties of aircraft heavier than air and properties of aircraft lighter than air. Known, for example, disk-shaped aircraft vertical take-off and landing / cm. US patent No. 3614030, CL. V64O 27/02, 1969 /, containing a large number of engines installed in wells along the periphery of the disk-shaped body, providing takeoff, landing and horizontal flight of the device. However, the known aircraft is characterized by low maneuverability, low carrying capacity, difficulty in piloting, which limits the possibilities of its use. In addition, the known apparatus does not allow lifting and transporting bulky goods in their vertical position, for example, rockets, power line masts, pipes, etc. Piloting such an apparatus is difficult due to the limited control efforts created by the deflection of gas jets behind the engines.

A combined aircraft is known (see USSR Patent No. 1496630 A3, class B64C 29/00, 39/06, 1989), comprising a round body, a supercharger installed in the body, mounted at the bottom of the body, horizontal and vertical tail, located in front under the body, behind, above, below and on the sides of the body.

The disadvantage is the presence of a large number of protruding parts that create resistance even at low flight speeds.

Also known is an aircraft lighter than air / cm. Auth. St. USSR No. 687728, cl. 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 an upright position. The disadvantages of the known aircraft are limited carrying capacity and low maneuverability. Due to the large windage and weak control efforts, the difficulty of piloting and limited application.

Known toroidal aircraft heavier than air with a screw propulsion located in the center / cm U.S. Patent No. 5152478, cl. B64C 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.

Known aircraft lighter than air, made in the form of an annular wing, in the body of which are placed several turboprop engines equipped with rotors / cm. RF patent No. 20701143, cl. 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, the horizontal flight of such an apparatus with vertical weights at the time of launch is carried out with its horizontal position, which inevitably leads to a complication of the load securing system, disruption of the cable-stayed suspension, necessitates the use of shaped fastening elements, which means a significant increase in the total weight and limitation of load capacity. The control of such a device is carried out by changing the thrust of the engines, which makes it difficult to pilot and reduces maneuverability.

The closest analogue adopted for the prototype is a multi-functional aircraft vertical take-off and landing (see RF Patent No. 2127693 C1, CL 6 B64C, 29/00). The aircraft is a toroidal body containing cargo compartments, crew cabins, a power plant with power units, radial niches, controls and touchdown bodies. A disadvantage of the known aircraft is that platforms with engines located outside the aircraft body create significant resistance at high flight speeds.

The aim of the present invention is to provide a fundamentally new combined highly maneuverable aircraft with a wide range of possibilities for its use, high efficiency and operational adaptability.

In contrast to the prototype, the aircraft structurally differs in that it consists of a rigid toroidal hull, in the radical openings of which six rotary devices in the form of rings are fixed, instead of a cylinder that limits the space, with rotary platforms mounted on them with 1 engine having a thrust vector , or with two conventional jet engines, or turbojet. A plane is installed above the engines, which can either perform the function of a wing, or a stabilizer, or a steering plane, depending on the position of the engines relative to the body of the aircraft. Removing the cylinders and replacing them with ring-shaped devices in the aircraft’s hull frees up space for free passage along the entire corridor and space for cargo or passengers, or for filling the cavity with gas for other models with a different purpose. The turntable can rotate in any direction around its axis and moves in any direction along the niches of the device in the form of a ring, and the engine with a plane above it will perform the function of a marching engine, and the plane will perform the functions of a wing, otherwise the engine will perform the function of a steering engine , and the plane is a function of the steering plane. When taking off in a limited space, all engines are mounted vertically (see diagram No. 1b) and become traction engines, and the wing plane becomes a stabilizer. The internal space can also be used to accommodate vertical bulky goods or the passenger compartment, or to place water that fills the internal space of the torus when it touches the water surface (see diagram No. 5) through the partially open side of the hatch. In this case, the central torus cavity is hermetically sealed by the upper and lower bearing surfaces, which improves the aerodynamics of the aircraft (the upper bearing surface is slightly convex, the lower one is slightly concave), reduces fuel consumption and increases flight range. If the aircraft is used for lifting and moving loads over short distances or for crane, installation work, its upper and lower surface, consisting of segments, opens, raising the plane of the segments vertically, thereby reducing drag, or removes the entire central space of the torus for bulky goods. The aircraft is equipped with two pilot cockpits and touchdown bodies (landing gear, telescopic racks, or skids). Pilot cockpits 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 device in space. The control system includes a gyro-stabilized platform that provides stabilization of the aircraft in the air, automatic control of the power plant elements and flight modes of the device. Automatically controlled touchdown bodies made in the form of telescopic support rods ensure a smooth landing of the apparatus not only on a horizontal, but also inclined up to 30-40 ° surfaces, and a sealed torus body with the landing touchdown bodies allows landing on water, which is especially important when using apparatus in a fire variant.

The technical essence of the invention is illustrated by graphic materials, which depict:

figure 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.

figure 2 is the same, top view, half of the upper bearing surface is removed;

figure 3 is a toroidal hull of the aircraft without rotary power units, top view, the upper bearing surface is conditionally removed;

figure 4 is a view along aa in figure 3;

figure 5 is a view along bb in figure 3;

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

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

on Fig - aircraft with a load on the external / cable / suspension in flight.

The multifunctional highly maneuverable aircraft depicted in the above figures, capable of taking off at any angle, includes a rigid lightweight toroidal hull 1 with radial openings / niches / 2, with rotary devices 23, with platforms 4 rotatable relative to the radii, each of which has one jet engine 5 with rotary nozzles and a plane 27 above the engine in the middle of the platform. The turning plane in one case, if the engine is out of order or for some reason it is impossible to change the thrust vector, in other cases 60% works as a wing and = 20-30% as a stabilizer. The hull of the aircraft is equipped with removable upper 6 convex and lower 7 concave bearing surfaces, hermetically closing, if necessary, the inner space of the toroidal hull. In the lower surface there is a hatch 24 for water intake at the moment of touching the water surface during the flight, the wings of which automatically close after filling the inside of the torus with water. The cavities of the toroidal hull 1 formed between the niches 2 are used to arrange the cargo compartments 8, front 9 and rear 10 of the pilot cabins and rigging equipment. The cargo compartments are equipped with easily removable floors 11 and hinged hatches 12 with cargo ramps 13. A cylindrical shaft 14 is installed in the central space of the torus, which is included in the power system of the apparatus body and provides cable-stayed cargo suspension. To do this, on the walls of the shaft there are fastening devices 15, providing a rigid / cm. Fig.7 / and cable-stayed outside / see Fig / suspension and automatic discharge of goods.

The internal space between the torus 1 and the walls of the cylindrical shaft 14 is used to accommodate the annular power structural elements, power compartments 16 and 17 and the annular channel 26, which provides communication between the front 9 and rear 10 pilot cabins, as well as free access to the elements of various systems located in power compartments 16 and 17. These compartments also house equipment and devices for braking and fixing rotary power units 3. Front 18 and rear 19 retractable telescopes are also located in power compartments 16 and 17 opicheskie rod - landing organs. Outside the upper power compartment 16 is located an annular power element 20, which also provides for the installation and fixation of the upper bearing surface 6. The rotary device 23 is attached to the power walls of the radial niches.

The length of the telescopic rods 18 and 19 when extended automatically locks when meeting an obstacle, which ensures the landing of the apparatus on an inclined surface.

The operation of the apparatus basically boils down to lifting and transporting various cargoes 21, 22 by air. In this case, various loading options and various use cases can take place. If it is necessary to transport small loads over a long distance, the cargo compartments of the torus are filled with cargoes, upper 6 and lower 7 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 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.

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 (6)

1. A multifunctional aircraft taking off at any angle to the take-off surface, comprising a toroidal hull, cargo compartments, a power plant, front and rear cockpits, a control system and touchdown bodies, characterized in that the hull is made with radial niches, the apparatus is equipped with placed in these niches by 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 ability to rotate the platforms when pumped air between the housing niche and the planes of the ring. 2. The apparatus according to claim 1, characterized in that the casing is provided with an upper convex and lower concave bearing surfaces covering the central cavity located inside the torus. 3. The apparatus according to claim 1, characterized in that the rotary platforms are arranged to move on an air cushion in a niche of the ring and together with the ring in niches of the housing. 4. The apparatus according to claim 1, characterized in that the engines are engines with a variable thrust vector or jet engines, or turbojet engines. 5. The apparatus according to claim 1, characterized in that the lower part of the housing is sealed for landing on water and equipped with hatches for water intake. 6. The apparatus according to claim 1, characterized in that each wing plane is located in the middle of the corresponding rotary platform and is designed to perform several functions depending on the location of the rotary platform relative to the body.

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