RU171939U1 - Short takeoff and landing airplane - Google Patents

Abstract

The utility model relates to aviation technology and can be used in the development of short take-off and landing aircraft, namely: local and regional airlines, general aviation, special purpose and cargo aircraft. The aircraft contains: a fuselage, a wing with an auxiliary distributed electric power unit with propellers removed in cruise flight, a tail unit, as well as a main (marching) power unit. A distributed electric power unit removed during cruise flight to the wing can significantly increase the wing lift, providing a short take-off and landing mode and / or an increase in cruising flight speed and aerodynamic quality by reducing the wing area. In patrol modes, a distributed power plant allows for minimum patrol speeds.

Description

The proposed utility model relates to aircraft. The utility model can be used in the development of short take-off and landing aircraft, namely: local and regional airlines, general aviation, special purpose and cargo aircraft.

The most pressing tasks for local and regional aviation is to ensure the economic and physical availability of air travel. The first is associated with a reduction in transportation costs. The second - with the ability to use for take-off and landing small airfields and runways.

A certain scientific reserve has been accumulated in the world on the creation of short take-off and landing aircraft with advanced wing mechanization. Traditional methods of mechanization of the leading and trailing edge of the wing (slats and flaps of various types) can provide maximum values of the coefficient of the lifting force of the wing up to Su _max ~ 3.5. To further increase Su _max, it is necessary to use energy methods for increasing the lifting force associated with an increase in the energy of the boundary layer, deflection of the jet, and an increase in velocity around the wing, as compared with the speed of the incident flow. The use of energy metols allows to provide Su _max up to 7-8.

One of the energy methods for increasing the lift of a wing is to blow it with propellers of a power plant. However, current airworthiness standards prohibit the use of this method for safety reasons, since engine failure not only reduces traction, but also reduces lift.

The use of many engines mounted on the wing - a distributed power plant (DCS), can solve the security problem, because failure of one engine has little effect on overall performance.

However, in the case of using, for example, turboprop engines for DCSs, their characteristics significantly deteriorate and the price rises due to the negative effect of a decrease in size (and power).

Currently, there are modern brushless electric motors that have a number of advantages over internal combustion engines (ICE), namely: high efficiency, simplicity and reliability, small size, low noise and vibration, environmental friendliness. By specific weight and price parameters, electric motors are not inferior, and sometimes surpass traditional ICEs. Their use for DCS can be promising.

Work in this direction has intensified significantly recently. The prototype of the proposed technical solution is the NASA Maxwell demonstration aircraft project (Fig. 1, see the website http://www.nasa.gov/press-release/nasa-hybrid-electric-research-plane-gets-x-number -new-name-0).

On the prototype, the power plant (Fig. 1) consists of 2 marching electric motors installed at the ends of the wing and providing traction at all flight modes, as well as a distributed power plant consisting of 12 auxiliary electric motors located in the fairings in front of the front edge of the wing . In the take-off and landing modes, the blades of the propellers are in the working position (Fig. 2), providing blowing of the wing, and in cruising flight mode they are folded around the nacelles (Fig. 3). The disadvantage of this solution is the increase in the washed surface of the aircraft due to the nacelles of the distributed electric power plant (RES), which leads to an increase in aerodynamic drag, as well as the unfavorable interference of the wing with the RESU engine nacelles, which can lead to premature flow stall. In addition, the individual folding of each rotor blade of the auxiliary power unit complicates the entire system and reduces its reliability.

The objective and technical result of the proposed utility model is the development of a short take-off and landing aircraft with improved indicators of speed, efficiency and safety.

The technical result consists in increasing the coefficient of lift of the wing and reducing, compared with the prototype, the surface of the aircraft being washed, therefore, its resistance, increasing speed, improving the economy of the aircraft (reducing fuel consumption) and increasing safety.

The solution of the problem and the technical result are achieved by the fact that in a short take-off and landing aircraft containing the fuselage, wing, main marching power plant, auxiliary distributed electric power plant with propellers, tail unit, auxiliary distributed electric power plant with propellers located on the wing with the ability to be put in the wing on a cruise mode.

In this case, the marching power plant may consist of two turboprop engines located on the wing on the sides of the fuselage, two double-circuit turbojet engines located on the sides of the fuselage under the wing on the pylons, four electric motors with screws located on the ends of the wing opposite each other.

FIG. 1 - NASA Maxwell Demonstrated Aircraft with a Distributed Electric Propulsion System

FIG. 2 - Propeller of the distributed electric power plant of the Maxwell aircraft in the unfolded (takeoff and landing) position

FIG. 3 - The propeller of the distributed electric power plant of the Maxwell aircraft folded around the nacelle (cruising) position

FIG. 4 - The proposed short take-off and landing aircraft with marching turboprops located on the wing in a cruising configuration

FIG. 5 - The proposed short take-off and landing aircraft with mid-flight turboprops in the take-off and landing configuration

FIG. 6 - Propeller distributed electric power plant of the proposed aircraft short take-off and landing in the folded (cruising) position, removed in the wing

FIG. 7 - Propeller distributed electric power plant of the proposed aircraft short takeoff and landing in the released (takeoff and landing) position

FIG. 8 - Suggested short take-off and landing aircraft with marching turbojet engines

FIG. 9 - The proposed short take-off and landing aircraft with 4 marching electric engines located in pairs at the ends of the wing

The short take-off and landing airplane (Fig. 4) contains a wing 1, a fuselage 2, a T-tail 3, a mid-flight power plant of two turboprop engines with propellers 4 and an auxiliary distributed electric power plant 5 (Fig. 5). The fuselage 2 serves to accommodate commercial load, crew and equipment. The tail unit 3 T-shaped has a keel with a rudder and a stabilizer with a elevator.

The upright straight wing 1 of a rectangular or trapezoidal shape in plan has a trailing edge mechanization to reduce the take-off and mileage. The wing is equipped with a distributed electric power plant 5, consisting of electric motors with propellers, located between the sliding slat 7 and the wing box (Fig. 6). In cruising flight, the propellers 6 are oriented along the wing, the slats 7 are moved to the wing box, forming a smooth profile (Fig. 6). In the take-off and landing mode (Fig. 7), the slat 7 is extended, the propellers 6 blow the wing. Electric power supply to RESU engines is carried out at the expense of generators installed on mid-flight engines, which can be used as gas turbine, turboprop or turbojet engines, as well as an electric battery.

Marching power plant may consist of:

- two turboprop engines 4 with propellers mounted on the wing on the sides of the fuselage (Fig. 4 and Fig. 5). In this case, the propellers of the auxiliary RESU at take-off and landing provide airflow to the remaining part of the wing, not provided with airflow propellers of the propulsion system.

- two turbofan engines 8, located on the sides of the fuselage under the wing on the pylons (Fig. 8). In this case, the propellers of the auxiliary RESU at take-off and landing provide airflow over the entire wing in scope.

- 4 electric motors 9 located at the ends of the wing (Fig. 9). In this case, the propellers of the auxiliary RESU at take-off and landing provide airflow over the entire wing in scope.

The location of the engines at the ends of the wing during rotation of the propellers, directed against the twist of the end vortex, reduces the inductive drag of the wing and increases the efficiency of the screw. The use of 4 marching engines, and not 2, as in the prototype, ensures safety in case of failure of one of the engines or the destruction of one of the marching propellers.

The distributed electric propulsion system, which is cleaned during cruise flight into the wing, can significantly increase the wing lift, providing a short take-off and landing mode, as well as increase cruising flight speed and aerodynamic quality by reducing the wing area. In patrol modes, a distributed power plant allows for minimum flight speeds.

Thus, it is possible to create a short take-off and landing aircraft with an increased level of safety and comfort for passengers, improved environmental performance.

Claims (4)

1. A short take-off and landing airplane comprising a fuselage, a wing, a main marching power plant, an auxiliary distributed electric power plant with propellers, a tail unit, characterized in that the auxiliary distributed electric power plant with propellers is located on the wing with the possibility of being removed cruising wing. 2. A short take-off and landing aircraft, made according to claim 1, characterized in that the marching propulsion system consists of two turboprop engines located on the wing on the sides of the fuselage. 3. A short take-off and landing aircraft, made according to claim 1, characterized in that the marching power plant consists of two double-circuit turbojet engines placed on the sides of the fuselage under the wing on the pylons. 4. A short take-off and landing aircraft, made according to claim 1, characterized in that the main propulsion system consists of four electric motors with propellers located at the ends of the wing opposite each other.

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