RU2789425C1 - Aircraft with a hybrid power plant - Google Patents

Abstract

FIELD: aircraft construction.

SUBSTANCE: invention relates to the field of aircraft construction, in particular to the development of cargo, passenger and multi-purpose short takeoff and landing aircraft, providing cargo and passenger transportation, rescue operations, etc. in areas with an underdeveloped airfield network and requiring a transportation shoulder of more than 600…1000 km. The aircraft with a hybrid power plant contains a fuselage, a wing, a power plant, a distributed electrical power plant located on a deflectable flap. The distributed power plant is made in the form of impellers, each of which is placed in a separate air intake attached to the lower part of the deflectable flap, which can be rotated about the rotation axis located downstream from the trailing edge of the wing at a distance of 20-30% of the wing chord.

EFFECT: proposed aircraft provides high aerodynamic characteristics (lift coefficient Su) when interacting with a sustainer power plant in takeoff and landing modes, can significantly reduce emissions of harmful substances into the atmosphere, reduce noise levels, improve operational characteristics and basing conditions (reduction in the length of the take-off, landing, descent and climb distance), can provide a cruising flight speed of up to 760 km/h and a practical range of up to 3000 km.

1 cl, 4 dwg

Description

The proposed invention relates to the field of aircraft building, in particular to the development of freight, passenger and multi -purpose aircraft of short take -off and landing, ensuring cargo -passenger transportation, rescue operations, etc. in areas with an underdeveloped airfield network and requiring a transportation shoulder of more than 600 ... 1000 km.

The proposed invention relates to aviation equipment, in particular, to the aircraft (LA) wings with air screws removed from the flow of air flow flowing. Air screws can get out of the stream to reduce the aerodynamic resistance of the la in flight in the case when the creation is not required for the flight.

Several layouts of aircraft with wing and air screws that are removed from the flow are known.

The work of NASA and the international airline Cape Air (Graham Warwick "Is Just First Step" Aviation Week & Space Technology, Jun 26, 2015) is known for the formation of the appearance of a light aircraft that uses the effect of blowing the wing with the help of additional air to increase lift during takeoff and landing. The screws in front of the front edge of the wing. To reduce thrust losses and minimize drag not required in cruise flight, additional propellers must be removed from the flow.

Known aircraft An-28, developed by OKB. Antonov (see www.aviawiki.com\antonov\an-28) and its analogues (DO-228NG, DHC-6-400, L-410UVP-E20, C-212-400, etc.). In the standard version, the aircraft have a takeoff run of 300÷400 m. Since the design case is an engine failure, the runway length required for them is 550÷900 m. The maximum flight range (mitigation) is 1300 ÷ 1800 km. The aircraft are made according to the normal aerodynamic scheme with a high elongation wing mechanized along the trailing edge. The power plant with turboprop engines (TVD) and relatively large diameter propellers is placed on a wing blown by a jet from propellers. Aircraft contain a fuselage in which the cockpit, equipment, cargo-passenger cabin are located. Horizontal and vertical tail mounted on the rear fuselage.

Also known are hybrid short takeoff and landing aircraft containing hybrid power plant engines on the wings (RF patent No.

The disadvantages of these aircraft are the large relative weight of the airframe and, as a consequence, relatively low cruising speed (up to 400 km/h) and flight range (up to 1500 km). In addition, the take-off and landing distance is more than 550 m.

Known project aircraft Onera Amhere (France, www.onera.fr\Fiche_AMPERE_VA) with a distributed electric power plant, which uses 32 electric tunnel fans installed above the leading edge of the wing. The aircraft is designed for a flight range of 400…500 km at a speed of 200…250 km/h.

The disadvantage of this aircraft is small cruising speed and flight range.

Known project of vertical takeoff and landing aircraft Lilium, developed in Germany (see felix.schoefer@lilium.com). It is assumed that the aircraft will be equipped with an electric power plant, carry out vertical takeoff and landing on a hard surface without additional special training and provide flight at an altitude of up to 3 km at a speed of up to 300 km/h for a range of up to 500 km. The aircraft is made according to the "tailless" scheme and contains a wing, a fuselage, a power plant and a line of fan propellers on deflectable flaps. To balance the aircraft in the takeoff and landing mode, electric-fan lifting engines retractable in flight into the nose of the fuselage are used. The aircraft has an almost straight wing of moderate elongation.

The disadvantage of this aircraft is small cruising speed and flight range.

Closest to the proposed invention is a short takeoff and landing aircraft (RF Patent No. 2728017. IPC B64C 23/00, 06/05/2020), taken as a prototype. Short takeoff and landing aircraft, contains a wing, a fuselage, a power plant and a line of fan propulsors on deflectable flaps, for articulating the wing with the fuselage and placing the power plant additionally contains a connecting fairing made in the form of a profiled root wing of small elongation with inclination angles of 10 ... 60 ° its lower and upper surfaces mating with the fuselage relative to the horizontal plane, with a relative profile thickness of 10 ... 20%,

The disadvantage of this aircraft are low cruising speed and range.

The objective and technical result of the present invention is the development of an aircraft with a hybrid power plant that provides high aerodynamic characteristics (lift coefficient Su) when interacting with a sustainer power plant in takeoff and landing modes, which makes it possible to reduce the takeoff and landing distance.

The solution to the task and the technical result are achieved by the fact that in a aircraft with a hybrid power plant containing a fuselage, a wing, an energy unit, a distributed power electric installation located on a deflected closing, a distributed power plant is made in the form of impeller, each of which is placed in a separate an air intake attached to the lower part of the deflectable flap, made with the possibility of rotation about the axis of rotation, located downstream from the trailing edge of the wing at a distance of 20-30% of the wing chord, while the power plant contains at least two sustainer engines.

The proposed invention is illustrated by drawings, which show the schematic diagrams of the cleaning of the propeller from the air flow around the aircraft and the placement of the constituent structural elements of one individual propeller on the wing as part of the distributed electrical power plant of the aircraft. A distributed power plant may consist of a different number of propellers - impellers located along the wing span.

In FIG. 1 shows a general view of the aircraft in cruise flight mode.

In FIG. 2 - shows a general view of the aircraft in the landing flight mode.

In FIG. 3 - The location diagram of the deflected click with the attached impeller in the air intake in the cruising mode of the LA flight.

In FIG. 4 is a diagram of the location of the deflected flap with an attached impeller in the air intake in the takeoff and landing mode of the aircraft flight.

The aircraft is made according to a normal aerodynamic scheme (see Fig. 1, 2), and contains fuselage 1; wing 2; a power plant, a distributed electric power plant, including air intakes 3, and impellers 4.

The wing of the aircraft consists of the main element 5, the deflected closing 6. The interceptor 7 (Fig. 3). The wing is made straight along the leading edge.

The distributed electrical power plant is made in the form of impellers 4, each of which is placed in a separate air intake 3, attached to the lower part of the deflectable flap 6, made with the possibility of rotation about the axis of rotation located downstream from the trailing edge of the wing at a distance of 20-30% of the chord wing. In FIG. 3, 4, the axis of rotation is marked with a cross, runs perpendicular to the plane of the sheet and is coaxial with the Z axis in the three-dimensional coordinate system adopted in aerodynamics, associated with the aircraft.

Thus, the hybrid power plant of the proposed aircraft consists of an energy installation and a distributed power plant with impeller, while the power plant contains at least two marching engines.

In cruising flight modes, a distributed power plant, consisting of air intakes 3 and impellers 4, is located below the wing (under the wing), where the interference is most favorable. In take-off modes, the flap 6 with an attached impeller in the air intake is deflected by turning around the specified axis of rotation at an angle δ=10÷15° so that the upper surface of the shell of the engine nacelle of the distributed power plant touches the rear edge of the spoiler 7 (not shown in Fig.). In the landing mode, the flap with an attached impeller in the air intake is deflected by turning around the specified axis of rotation at an angle δ=30÷40° so that the impellers 4 are installed behind the main element 5 of the wing (Fig. 4) above the upper surface of the spoiler 7 and provide additional lift due to the reactive and supercirculation components.

Thus, the objective and the technical result of the invention are achieved due to the proposed design and position of the distributed electric power plant, in cruising flight modes installed on the lower surface of the wing, where the interference is most favorable, and in takeoff and landing modes due to the rotation of the flap mounted above the upper surface of the main wing element, while the impellers in the air intakes are installed behind the main wing element, giving additional lift due to the reactive and supercirculation component.

The use of a power plant and the rational arrangement of an electric power plant with impellers in the air intakes, their interaction ensures the achievement of high load-bearing properties of the wing in takeoff and landing modes, a decrease in drag in cruising flight modes and a high level of weight and aerodynamic perfection of the aircraft.

Settlement and design studies show that, compared with the prototype, the aircraft made in accordance with the proposed technical solution provides the length of the run and run by 10% less, can provide cruising flight speed up to 760 km/h and a practical range of up to 3000 km.

Claims (1)

An aircraft with a hybrid power plant, containing a fuselage, a wing, a power plant, a distributed power plant located on a deflectable flap, characterized in that the distributed power plant is made in the form of impellers, each of which is placed in a separate air intake attached to the lower part of the deflected flap. a flap configured to rotate about an axis of rotation located downstream from the trailing edge of the wing at a distance of 20-30% of the wing chord.

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