RU2462394C2 - Vertical take-off and landing aircraft - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to VTOL aircraft. VTOL aircraft comprises fuselage 1, compressed air source and gas-jet nozzles 3. Note here that fuselage top surface comprises central part 4 and peripheral part 5 located along fuselage outline. Aircraft central part 4 is arranged above peripheral part 5. Gas-jet nozzles 3 are arranged under central part 4 above peripheral part 5 and directed at negative angle to horizontal plane toward peripheral part 5. The latter is trimmed along gas-jet nozzle jet lengthwise contour.

EFFECT: higher operating performances.

4 dwg

Description

Technical field

The invention relates to air vehicles of vertical take-off and landing, and is intended for the transport of passengers and goods by air.

State of the art

Aircraft of vertical take-off and landing are known, containing a fuselage, a source of compressed gas and gas-jet nozzles, the upper surface of the fuselage including a central and peripheral parts along the fuselage branch so that the central part is located above the peripheral and gas-jet nozzles are located under the central part above the peripheral part under the negative angle to the horizontal plane and directed towards the peripheral part (SU 835023 A1, 06.23.1992, Aksenov Yu.V .; RU 2151717 C1, 06.27.2000, Bezrukov Yu.I .; RU 86560 U1, 09/10/2009, Tytarenko O. L. ; RU 2008108373 A, 09/10/2009, Pikulev N.M .; RU 2374133 C1, 11/27/2009, Kovalchuk V.A.). Common essential features of the known and claimed aircraft are the presence of the fuselage, a source of compressed gas and gas-jet nozzles.

The closest analogue to the invention is an apparatus for movement in a fluid medium according to patent RU 2374133 C1 of 11.27.2009 (Kovalchuk V.A.). This analogue is selected as a prototype. During the operation of the aircraft according to the prototype, the efficiency of the ejection action of the gas jet decreases when moving along the arcuate profile of the peripheral part of the upper surface of the aircraft due to an increase in the distance from the jet to the upper surface when the jet is fed according to the prototype tangentially to the arc of the profile. This fact reduces the lifting force, which is the disadvantage of the prototype.

Disclosure of invention

The basis of the invention is the task of improving the aircraft of vertical take-off and landing, in which by changing the design of the device it is possible to eliminate this drawback of the prototype, due to which the technical result is achieved: improving reliability and improving the operational characteristics of the aircraft.

The problem is solved in that the peripheral part is profiled along the longitudinal contour of the jet of a gas-jet nozzle.

Between the totality of the essential features of the claimed invention and the achieved technical result there is the following causal relationship.

For equally effective ejection of the space above the peripheral part along the entire path of movement of the jet of ejecting gas over it, it is necessary that along this path the distance from the longitudinal contour of the jet to the surface of the peripheral part be the same. The smaller this distance, the greater the absolute ejection efficiency (the greater the depth of reduction of static pressure over the peripheral part, which means more lift). To increase the specific efficiency of the ejection gas (to reduce the mass flow of gas), its temperature should be increased, for example, to the temperature of the products of combustion of fuel and oxidizer in the gas generator. The distance from the longitudinal contour of the jet to the surface of the peripheral part should be large enough to exclude an unacceptable increase in the convective component of the heat flux from the jet to the surface to prevent burnout of the surface. By jointly solving these problems, they establish the profile of the peripheral part, depending on the purpose of the aircraft. For aircraft intended for stratospheric flights, the absolute efficiency of ejection is a priority, and the temperature of the gas-generating gas is reduced to a sufficient level. For aircraft designed for tropospheric flights, specific ejection efficiency is a priority. The profiling of the peripheral part along the longitudinal contour of the jet of the gas-jet nozzle provides an effective ejective action of the jet in the path of its movement over the peripheral part, which reliably provides an increase in lift, increases reliability and improves the operational characteristics of the aircraft.

Thus, the invention and in specific forms of execution ensures the achievement of the specified technical result.

Brief Description of the Drawings

The essence of the proposed invention is illustrated by drawings, where in Fig.1 shows a top view of an aircraft of the type "aeromobile", and Fig.2 is a top view of an aircraft of the type "airbus" of modular design; figure 3 shows a section aa in figure 1 and figure 2 when using outside air, figure 4 shows a section aa in figure 1 with an autonomous on-board gas source.

The implementation of the invention

The aircraft of vertical take-off and landing contains the fuselage 1 (Fig. 1, 2), a source of compressed gas 2 and gas-jet nozzles 3, (Fig. 3, 4), the upper surface of the fuselage includes a central 4 and peripheral 5 along the contour of the fuselage of the part, the central part 4 is located above the peripheral part 5. Gas jet nozzles 3 are located under the central part 4 above the peripheral part 5 at a negative angle to the horizontal plane. In this case, the peripheral part is profiled along the longitudinal contour of the jet of the gas-jet nozzle. In figure 1, 2, 3, 4 it can be seen that on the surface of the aircraft there are no details and feathers cluttering up the space, which makes it possible for it to be all-azimuthal without changing its orientation in space. As a source of compressed gas (Fig.3) can be used in a gas generator system, including a gas turbine compressor 6, a gas generator 7 and a fuel tank 8, located in the mine 9 of the aircraft. The gas generator circuit allows you to increase the volume of gas supplied to the gas-jet nozzle, as well as increase its specific efficiency by increasing the temperature in the gas generator. The gas turbine compressor 6 is a stand-alone unit operating in a stationary mode, since the variable modes for such equipment are harmful and lead to rapid breakdown. All variable modes are assumed by the gas generator, the mode of which is determined by the supply of fuel to it.

The modular design of the aircraft type "airbus" (figure 2) eliminates the catastrophic outcome of the failure of one or more sources of compressed gas due to compensation by sources of compressed gas of other modules.

The space 10 under the central part of the surface (Figs. 3, 4) can be used as a crew compartment with the placement of control systems in it, and the space 11 under the peripheral part can be used as a cargo-passenger compartment. For aircraft of the "aeromobile" type for mass individual use, the crew compartment 10 and the cargo-passenger compartment 11 can be combined so that only gas-jet nozzles 3 remain under the central part.

The installation on board the aircraft autonomous compressed gas production system (figure 4), including a tank with liquid oxygen 12, a tank with liquid hydrogen 13, a gas generator 7 and a plasma generator 14, can completely eliminate the influence of the environment on the operation of the source of compressed gas, make it environmentally friendly clean and apply the plasma as an ejection gas without the use of auxiliary external devices such as electrodes, etc.

Moreover, in all cases, the peripheral part 5 of the upper surface of the aircraft is protected by a heat-protective coating 15.

When the aircraft (Fig. 3), the gas turbine compressor 6 is launched and brought to stationary mode according to the assignment (depending on the weight of the cargo). Air from the compressor 6 and fuel from the tank 8 is supplied to the gas generator 7 and the gas generator 7 is started (ignition). The gas generator gas from the gas generator 7 is supplied to the gas-jet nozzles 3 and then towards the peripheral part 5, over which the static pressure decreases as a result of the ejection action jets from gas-jet nozzles, which leads to the emergence of some lifting force. Further, the fuel supply from the tank 8 to the gas generator 7 is increased, the lifting force increases, overcomes the weight of the aircraft, the aircraft begins to rise and its further flight. Landing of the aircraft is carried out after stopping horizontal movement by reducing the supply of fuel from the tank 8 to the gas generator 7.

Thus, vertical take-off and landing of an aircraft with a peripheral part profiled along the longitudinal contour of the jet of a gas-jet nozzle is carried out, which increases reliability and improves the operational characteristics of the aircraft.

Claims (1)

A vertical take-off and landing aircraft containing a fuselage, a source of compressed gas and gas-jet nozzles, the upper surface of the fuselage including a central and peripheral part along the contour of the fuselage, so that the central part is located above the peripheral part, and gas-jet nozzles are located under the central part above the peripheral part under the negative angle to the horizontal plane and directed towards the peripheral part, characterized in that the peripheral part is profiled along the longitudinal contour of the gas ruby nozzle.

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