RU2268846C1 - Supersonic multi-purpose aircraft - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: proposed aircraft has fuselage, wing, main power plant with two turbo-jet engines 1, auxiliary power plant 2, fin assembly and side air intakes. Power plant 2 includes two supersonic turbo-jet engines 1 which are mounted in widened tail section of fuselage for placing fin assembly root in between them. Auxiliary power plant 2 is located at the bottom of center section of fuselage behind pilot cabin. Inlet openings of air intakes are made under wing and are bounded by fuselage in lower parts. Wing is provided with controllable slotted louvres in upper part of air intakes for air replenishment. Boundary layer drainage slots are made between upper edge of air intakes and lower surface of wing.

EFFECT: enhanced efficiency of multi-purpose supersonic aircraft.

3 cl, 4 dwg

Description

The invention relates to aircraft, in particular to the layout and equipment of the aircraft, increasing its functionality, including in isolation from the main airfield, expanding its capabilities for use at supersonic flight speeds, and can be used to create multi-purpose aircraft, which are presented increased requirements for maneuverability and flight speed, including the creation of training aircraft.

The closest technical solution both in design and in tasks performed, selected as a prototype, is a maneuverable light multi-purpose aircraft (see RF patent No. 2210522 C1 of 08.20.2003).

The main disadvantage of the known aircraft is the provision of insufficient flight performance, because there are no structural elements necessary for the aircraft to perform the functions of a supersonic multipurpose aircraft.

The technical results obtained from the use of this invention include ensuring the efficient use of a supersonic multipurpose aircraft for flying under various conditions, including autonomous basing in isolation from the main airfield, by eliminating the above-mentioned disadvantages of the known technical solution.

The problem is solved, and the technical result is achieved in that a light multi-purpose aircraft containing a main power unit with two turbojet engines, an auxiliary power unit, wing-mounted side air intakes, according to the invention, has an expanded rear fuselage for accommodating supersonic engines of the main power unit, contains supersonic engines of the main power plant, located in the rear of the fuselage in such a way that the root the second part of the horizontal tail is located between them, contains an auxiliary power unit located at the bottom of the middle part of the fuselage behind the cockpit so that its longitudinal axis, for example, is directed along the axis of the aircraft, and the exhaust pipe is led out under the fuselage to the left side, contains air intakes made as follows so that the inlet is located under the wing and is bounded from below by the fuselage, the air intake channel in the front part is tilted up, and then at the engine level it goes smoothly to the horizontal position, in the upper part of the air intake limited by the wing, controlled slotted jalousies of air recharge are made, between the upper edge of the air intake and the wing there is a slit for draining the boundary layer.

The invention is illustrated by drawings, where

figure 1 shows the arrangement of supersonic engines of the main power plant and the design of the air intake;

figure 2 - arrangement of engines of the main power plant;

figure 3 - layout and location of the main and auxiliary power plant and air intake on the plane;

figure 4 - design of the drain gap of the boundary layer of the air intake and the placement of the auxiliary power plant.

A supersonic multi-purpose aircraft, contains a main power unit with two turbojet engines 1, an auxiliary power unit 2, side air intakes 4 limited by a wing 3.

The tail of the fuselage 5 is made expanded to accommodate supersonic engines 1 of the main power plant so that the root of the vertical tail 6 is located between them.

Auxiliary power unit 2 is located at the bottom of the middle part of the fuselage 5 behind the cockpit 7 so that its longitudinal axis is directed along the axis of the aircraft 8, and the exhaust pipe 9 is brought out under the fuselage 5 to the left side. The air inlets 4, made so that the inlet 10 is located under the wing 3 and is bounded below by the fuselage 5. The air intake channel 11 in the front part is inclined upward, and then at the level of engine 1 smoothly goes into a horizontal position, in the upper part of the air intake 4, limited by the wing 3 , combined controlled flaps 12 of additional make-up and pressure bypass at supersonic speeds of the “blinds” type were made, between the upper edge of the air intake 4 and the wing 3, a slit 13 was drained of the boundary layer.

The power plant of the aircraft includes two afterburner engines 1 and auxiliary power unit 2 (APU). The right and left engines 1 are interchangeable with each other. The power plant has an autonomous launch system from APU 2. Unregulated air intakes 4 provide sufficient performance at M <1.0, including large angles of attack, as well as minimizing traction loss at a flight speed of M = 1.4.

Two engines 1 are placed side by side in the rear part of the fuselage 5, air intakes 4 of the engines 1 are located on the sides of the fuselage 5 under the influxes and have separate S-shaped channels 11 before entering the engines 1. The channels 11 are equipped with combined controlled shutters 12 for additional recharge and pressure transfer with supersonic shutter speeds. The design of the air intake 4 provides drainage of the boundary layer arising on the side surface of the fuselage 5 and the lower surface of the influx.

The sections of the middle part of the fuselage 5 have upper arcuate contours smoothly conjugated with the influx of the wing and directly with the upper surface of the wing, under the influx the oval contours of the air intake 4 pass into the contours of the fuselage.

Behind the cockpit 7, below, an auxiliary power unit 2 is installed, which provides autonomous start of the main engines 1.

The auxiliary power unit 2 includes a gas turbine engine and a gearbox for driving auxiliary equipment.

The auxiliary power unit engine or all of it 2 may be located between the corresponding fuselage frames 5.

To start the engines 1 of the main power plants, an air start system consisting of air intake pipes and air supply pipes to air starters can be used.

Piping can be integrated with the air conditioning system.

In the mode of terrestrial small gas pressure and temperature in the cabin 5 are provided by an auxiliary power unit 2.

Claims (3)

1. A supersonic multipurpose aircraft comprising a fuselage, a wing, a main power unit with two turbojet engines, an auxiliary power unit, plumage and side air intakes, limited at least to part of its length by a wing, characterized in that the main power unit is made with two supersonic turbojet engines, which are located in the extended rear of the fuselage with the possibility of positioning the root of the plumage between them, the auxiliary power unit is at the bottom of the middle part of the fuselage behind the cockpit, the air inlet openings are located under the wing and are limited in the lower parts of the fuselage, while in the wing in the upper part of the air intakes there are controlled slotted air-feed shutters, and border drain slots are made between the upper edge of the air intakes and the lower wing surface layer. 2. The aircraft according to claim 1, characterized in that the longitudinal axis of the auxiliary power unit is located along the axis of the aircraft, and the exhaust pipe is brought out under the fuselage to the side. 3. The aircraft according to claim 1 or 2, characterized in that the channel of each air intake in the front is directed upward, and at the level of the corresponding engine is horizontal.

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