RU67062U1 - MULTI-FUNCTIONAL HIGHLY MANEUVED VERTICAL TAKEOFF AND LANDING AIRCRAFT - Google Patents

Abstract

The utility model relates to aircraft, contains a number of fundamentally new technical solutions and can be used in the design and development of various aircraft vertical take-off and landing. A multifunctional aircraft comprising a disk-shaped hull having cavities filled with carrier gas and cargo compartments, a power plant, front and rear cockpits, a control system and touchdown bodies, the hull being formed by a torus, an upper convex and a lower concave supporting surfaces covering the central cavity located inside the torus, which is made with radial niches, the power plant includes at least six stand-alone interchangeable mounted on bearing bearings neroblocks, each of which has two jet engines configured to reverse the thrust and mounted on rotary platforms, fuel tanks, a differential control system for engine modes and the position of the power unit relative to the specified casing and platform with the specified engines relative to the power unit, according to the utility model, equipped with power units with steering planes, which can additionally perform the functions of a wing, stabilizer, fairing and tail unit.

Description

The utility model relates to aircraft, contains a number of fundamentally new technical solutions and can be used in the design and development of various aircraft vertical take-off and landing.

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

Currently, there are a large number of different circuit and structural solutions used in the creation of aircraft for vertical take-off and landing, but all of them have a specific and narrow focus. All of them, as a rule, are designed to perform certain 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 does not apply 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 achieved high technical perfection and are widely used in various fields of human activity.

For example, various types of aircraft for vertical take-off and landing from combat high-speed fighter aircraft are known (see V.F.Pavlenko. Airplanes for vertical take-off and landing. Military Publishing

USSR Ministry of Defense, Moscow, 1966, pp. 54-72) to low-speed transport aircraft designed to move various cargoes in the air compartments or on an external sling (see ibid.).

Various types of helicopters are known (see 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 operating aircraft of non-traditional 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 in order to ensure vertical take-off and landing of an apparatus, it is necessary to use its power plant to create a vertical thrust component equal to or somewhat greater than the mass of the aircraft, i.e. the thrust-weight ratio of the aircraft (the ratio of the total thrust of its power plant to the mass of the aircraft) must 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 bearing surface - the wing. In our 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 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 the thrust of the engines is proportional to the fuel consumption, it is quite obvious that an increase in the thrust 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 such way

is the improvement of existing aircraft by reducing their mass through the use of light composite materials, the choice of optimal structural schemes, the use of 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, is a disk-shaped aircraft of vertical take-off and landing (see US Patent No. 3614030, class B64O 27/02, 1969), containing a large number of engines installed in wells along the periphery of the disk-shaped body, providing take-off, 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 to lift and transport bulky goods in their vertical position, for example: rockets, masts, power lines, pipes, etc. Piloting such an apparatus is difficult due to the limited control efforts created by the deflection of the gas jets behind the engines.

Also known is an aircraft lighter than air (see Aut. 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. 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 (see US Patent No. 5152478,

class 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.

A well-known aircraft is heavier than air, such as a flying saucer, equipped with jet engines pivotally mounted on the periphery, creating 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.

A well-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. 20701113, 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 a vertical position, for example, missiles. However, the horizontal flight of such an apparatus, with a vertical load at the time of launch, is carried out with 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, and, therefore, to a significant increase in the total mass and limiting the carrying 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.

Also known is an aircraft lighter than air (see Heb. Patent No. 0201309 A2, class B64B 1/00, 1986). This is the closest analogue,

adopted as a prototype. 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 sail, which complicates operation, low maneuverability and reliability.

Closest to the proposed one is a multifunctional highly maneuverable aircraft for vertical take-off and landing, containing a disk-shaped body having cavities filled with carrier gas, and cargo compartments, a power plant, front and rear cockpits, a control system and landing bodies, while the body is formed by a torus , upper convex and lower concave bearing surfaces covering the central cavity located inside the torus, which is made with radial niches, power plant includes at least six autonomous interchangeable power units mounted on bearing bearings, each of which has two jet engines configured to reverse the thrust and mounted on rotary platforms, fuel tanks, a differential control system for engine modes and the position of the power unit relative to the specified body and platform with the indicated engines relative to the power unit (RF Patent No. 2127693, B64C 29/00, publ. March 20, 1999).

The technical result of the proposed utility model is the expansion of control capabilities by introducing additional multifunctional elements.

The technical result is achieved in that in a multifunctional aircraft containing a disk-shaped body having cavities filled with a carrier gas, and cargo compartments, a power plant, front and rear cockpits, a control system and touchdown bodies, the hull being formed by a torus, an upper convex and the lower concave bearing surfaces covering the central cavity located inside the torus, which is made with radial niches, the power plant includes at least six autonomous interchanges power units mounted on bearings, each of which has two jet engines configured to reverse the thrust and mounted on rotary platforms, fuel tanks, a differential control system for engine conditions and the position of the power unit relative to the specified casing and platform with the indicated engines relative to the power unit, according to utility model steering units are installed on power units.

Being installed on power units that are mounted on rotary platforms, steering planes can perform, in addition to the function of the steering plane itself, the functions of a wing, stabilizer, fairing and tail unit, depending on where the unit is located and at what angle the rotary platform is located.

The proposed aircraft is a vehicle heavier than air, but lightweight through the use of light carrier gas, for example, helium. Depending on the aircraft loading option, its free cargo compartments, including the central space of the torus, are equipped with light elastic containers, fill

light gas, which leads to a decrease in the mass of the apparatus structure and increases its carrying capacity.

An important feature of the proposed aircraft is its power plant, which includes at least six autonomous interchangeable rotary power units made in the form of cylinders pivotally mounted in radial niches of the aircraft body. Each power unit is equipped with a platform rotatable relative to its radius, on which there are two gas turbine engines reversible with rotary nozzles, as well as fuel tanks, additional electric drive units, a differential control system for engine operation and platform rotation relative to the power unit radius, as well as the power unit itself relative to the aircraft body .

The toroidal hull of the aircraft is equipped with sectional removable upper convex, lower concave bearing surfaces covering the inner space of the torus. Thus, externally, with the closed inner space of the torus, the apparatus is a symmetrical disk-shaped body of revolution. Such a body when moving in the air under the fragile to the horizon (under the attack) acts as a disk wing and creates lift. The implementation of this condition allows to reduce the thrust-weight ratio of the apparatus in flight by throttling or even turning off individual engines and increasing its efficiency.

Structurally, the aircraft consists of a rigid toroidal hull, in the radial openings of which rotary power units are installed, on which steering planes are installed. The inner space of the torus is used to accommodate vertical bulky goods or a light elastic container for carrier gas, when the goods are placed in the cargo compartments of the torus or external cable-stayed suspension. In this case, the central cavity of the torus with capacity

for light gas, for example, helium, it is closed by the upper and lower bearing surfaces, which improves the aerodynamics of the aircraft, 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 surfaces are removed, the central space of the torus is used to accommodate the cargo, the cargo compartments of the torus equipped with light elastic containers are filled with light gas.

The aircraft is equipped with two pilot cockpits, controls and touchdown bodies. Pilot cockpits are identical, equipped with duplicated control systems, are interconnected by annular channels for passage of crew members and provide the ability to control the device from one cockpit and adjust it from another cockpit. This ensures accuracy of landing, facilitates the reception and unloading of goods transported on external sling, 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 landing bodies made in the form of telescopic support rods ensure a smooth landing of the device not only on a horizontal, but also on an inclined surface of up to 30 degrees. Moreover, the absence of mechanisms at the bottom of the apparatus allows the apparatus to land on a water surface, which is especially important when using the apparatus in a fire variant, when hanging containers are used to transport water, and the time for filling containers with water is extremely limited.

For transportation of the device for technical purposes on the airfield, special airfield carts can be installed under the support rods and airfield machines can be used.

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

figure 1 - structural diagram of the aircraft in the parking position, front view;

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 vertical cargo in the parking position;

on Fig - aircraft with a load on the external (cable-stayed) suspension in flight.

The multifunctional highly maneuverable vertical take-off and landing aircraft depicted in the above figures includes a rigid, lightweight toroidal hull 1 with radial openings (niches) 2, power units 3 rotatable relative to axes II, and platforms 4 rotatable relative to radii, on which paired reversible gas turbine engines 5 are mounted with rotary nozzles. All power units 3 are the same and interchangeable, which reduces the cost of production and facilitates operation. Steering planes are installed on power units 3. Inside the power units 3 there are fuel tanks, additional electric drives, as well as elements of a differential control system for engine operation and rotation

platform 4 relative to the radius of the power unit 3 and power unit 3 relative to the axis I-I. The hull 1 of the aircraft is equipped with removable upper 6 convex and lower 7 concave bearing surfaces that, if necessary, cover the internal space of the toroidal hull 1. 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 8 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 this end, there are fastening devices 15 on the walls of the shaft that provide rigid (see Fig. 7) and cable-stayed external (see Fig. 8) suspensions and automatic discharge of loads.

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 installation and fixation of the upper bearing surface 6. Bearing supports are made on the reinforced walls of the radial niches 2 for installing rotary power units 3.

The length of the telescopic rods 18 and 19 when extended automatically locks when meeting an obstacle, which ensures

the apparatus is landing on an inclined surface, and the sealed torus body with the landing bodies removed allows the apparatus to land on a water 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-sized ones over a long distance, then part of the cargo compartments of the torus is filled with goods, and the remaining part of the cargo compartments with removed floors 11 and the central space of the torus are equipped with light elastic containers 23, 24 filled with light gas. The upper 6 and lower 7 bearing surfaces are installed and the aircraft is capable of transporting cargo in this embodiment to the maximum distance. If it is necessary to transport large loads over a short distance, for example, transportation of rockets or multiple air flights with suspended containers of water to extinguish large fires (see Figs. 7 and 8), then all the cargo compartments of the torus are freed from floors 11 and filled with light carrier gas moreover, when transporting large loads, for example, containers of water (Fig. 8) on a cable-stayed suspension, the free central space of the torus can also be used to accommodate a container with light carrier gas.

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 (1)

A multifunctional aircraft comprising a disk-shaped hull having cavities filled with carrier gas and cargo compartments, a power plant, front and rear cockpits, a control system and touchdown bodies, the hull being formed by a torus, an upper convex and lower concave bearing surfaces covering the central cavity located inside the torus, which is made with radial niches, the power plant includes at least six stand-alone interchangeable mounted on bearing bearings neroblocks, each of which has two jet engines configured to reverse the thrust and mounted on rotary platforms, fuel tanks, a differential control system for engine modes and the position of the power unit relative to the specified casing and platform with the specified engines relative to the power unit, characterized in that on power units steering planes are installed.