Aircraft with low noise at take-off and landing

FIELD: transport.

SUBSTANCE: invention relates to aircraft with low noise at take-off and landing. Proposed aircraft comprises airframe, two wings arranged on both sides of airframe ant carrying engines, and tail unit. Vertical tale consists of at least two fins to make with airframe rear end a channel on airframe top. Airframe top accommodates at least one engine to make airflows created by it come into said channel and to engine rear noise is shut off by said channel in lateral and bottom directions. Sweep forward wings have their butt joints arranged behind airframe, nearby engine air intake, to shut off front noise in lateral and bottom directions by wings.

EFFECT: aircraft reduced noise.

2 dwg

 

The technical field,

The present invention relates to an aircraft with low noise levels, particularly during take-offs and landings.

Prior art

From patent US 3 017 936 known aircraft, containing the fuselage, two wings on the sides relative to the fuselage and not bearing engines, vertical tail, consisting of at least two fins and forming together with the rear part above the fuselage channel located on the back of the fuselage, and at least one gas turbine engine, located on the back of the fuselage, so that the gas flow generated by the gas turbine engine, fell into the canal.

Thus, due to the design of the rear tail unit in the form of a channel and the location of gas turbine engines at the entrance of the channel can significantly reduce back the noise (i.e. the noise is directed back and created by the rotating parts of gas turbine engines, and the noise generated by the combustion chamber), because the rear noise is absorbed by the channel and is removed along it upwards away from the fuselage, that is, away from the passengers in the rear cabin of the aircraft, and especially from residents living near airports. Rear noise generated by gas turbine engines, overlaps the I so the " tail of the fuselage, forming an acoustic screen.

As to reduce the front-to-noise (i.e. the noise is directed forward and created fan gas turbine engines), the patent US 3 017 936 is provided, on the one hand, a significant lengthening of the forward gondola gas turbine engines and, on the other hand, a movable plates between the wings of the aircraft and gas turbine engines. Thus, the wings are used in combination with movable flaps for the education of the screen, silencing front noise.

It should be noted that this design is very complex and that, furthermore, it can only be used for aircraft short length, as gondolas gas turbine engines must not be extended beyond measure, so as not to degrade the aerodynamic properties of the aircraft and the characteristics of gas turbine engines.

Summary of the invention

The technical task of the present invention is to remedy these disadvantages and provide a simple and effective reduction of the noise level of the front even on aircraft of great length, particularly during take-offs and landings.

The task according to the present invention is solved by the creation of the aircraft, containing fusel is W, two wings, located in the lateral direction relative to that of the fuselage and not bearing engines, vertical tail, consisting of at least two fins and forming together with the rear part above the fuselage channel located on the back of the fuselage, and at least one gas turbine engine, located on the back of the fuselage so that the gas flow generated by the gas turbine engine, fell into the canal and back to the gas turbine engine noise overlap in the lateral direction and the lower direction of the specified channel of the specified aircraft is characterized by the fact that

the wings have reverse sweep, and

butt connectors mentioned wings are made near the air intake of the gas turbine engine to the front the noise produced by the motor overlap in the lateral direction and the lower direction of the said wings.

The present invention is based on the fact that, as the wings have reverse sweep, it is possible (while maintaining satisfactory flight characteristics from the point of view of the position of the center of aerodynamic forces relative to the center of gravity of the aircraft) sufficiently to move back to the wing along the fuselage, so they blocked the front noise of a gas turbine engine in the lei.

In addition, it should be noted that due to the reverse sweep wing aircraft has excellent cruising flight characteristics, in particular, through the use of technology laminarinase stream.

Brief description of drawings

Further the present invention explained in the description of the preferred variants of the embodiment with reference to the accompanying drawings, on which:

Fig. 1 depicts a General view of the back and top of the aircraft according to the invention;

Fig. 2 is a top view of an aircraft according to the invention.

Description of the preferred embodiment variants of the invention

The aircraft 1 in accordance with the present invention (Fig. 1 and 2) contains two wings 2 and 3, located on the sides symmetrically with respect to the fuselage 4 with the longitudinal axis L-L.

Tail vertical tail plane 1 contains two keel 5 and 6, forming together with the rear part 7 of the fuselage 4 with the horizontal tail plane, channel 8 located on the back of the plane. Channel 8 is made open at the top, but closed bottom (mentioned back in part 7) and sides (fins 5 and 6).

Two gas turbine engine 9 and 10 is installed on the back of the fuselage 4 and are arranged so that gas flows generated by the aforementioned gas turbine engines is, got into the channel 8. Thus, the channel serves as an acoustic screen that lowers the rear of noise generated by gas turbine engines 9 and 10, in a downward direction and in the lateral direction.

In addition, the wings 2 and 3 have reverse sweep (i.e. their free ends 11, 12 are located closer to the front than their butt connectors 13, 14 on the fuselage 4), and butt connectors 13, 14 occupy a rear position relative to the fuselage 4, which are located near the air inlets 15, 16 gas turbine engines 9, 10. Under these conditions, the front noise created by gas turbine engines 9, 10, overlap in the lateral direction and the lower direction of the wings 2, 3.

Due to the above-described construction, the aircraft 1 is relatively quiet, particularly during take-offs and landings as the rear noise and foreground noise turbine engines 9, 10 respectively overlap a tail 5, 6, 7 and the wings 2, 3. In addition, cruising flight characteristics of the aircraft are excellent due to the backward sweep of the wings.

Aircraft containing the fuselage (4), two wings (2, 3)located in the lateral direction relative to the fuselage (4) and the non-structural engines, vertical tail, consisting of at least two fins (5, 6) and forming together with the rear part (7) fuse is aja (4) channel (8), located on the back of the fuselage, at least one gas turbine engine (9, 10)located on the back of the fuselage (4) so that the gas flow generated by the gas turbine engine (9, 10), fell into the channel (8), and back to the noise of a gas turbine engine (9, 10) overlap in the lateral direction and the lower direction of the said channel, characterized in that the wings (2, 3) have a reverse sweep (φ), with butt connectors (13, 14) of the wings (2, 3) are located at the rear in relation to the specified fuselage (4), so that are located near the air intake (15, 16) gas turbine engine (9, 10)to the front the noise produced by the motor overlap in the lateral direction and the lower direction of the said wings (2, 3).



 

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