RU2070529C1 - Light aircraft - Google Patents

Abstract

FIELD: aeronautical engineering; light single-engined aeroplanes. SUBSTANCE: light aircraft has fuselage, rectangular in section, high-mounted wing with bracing strut, fin, horizontal tail located below plane of wing and single-engined power plant. Wing aspect ratio λ ranges from 10.3 to 10.6 and static moment of horizontal tail A_h.t. ranges from 1.15 to 1.25. EFFECT: enhanced reliability. 2 cl, 1 dwg

Description

 The invention relates to aircraft, in particular: to light single-engine aircraft of the normal category, designed for flight vehicles.

 Light aircraft are known from the prior art, comprising a rectangular fuselage, a highly planed wing with a strut, keel, horizontal tail and a single-engine power unit [1] Moreover, the wing and horizontal tail have a rectangular shape in the plane, which determines insufficient aerodynamic quality and Requires increased engine power.

The closest to the invention in terms of features is a light aircraft of the type DRS-2 "Beaver", containing a rectangular fuselage, a highly rectangular wing with a strut, keel, horizontal tail, located below the wing plane, and a single-engine power unit [2]
The disadvantage of this aircraft is the significant dependence of operational characteristics on changes in load and centering at a relatively low, even for an aircraft of this class maximum payload.

 The aim of the invention is the creation of a light single-engine aircraft with high aerodynamic quality and improved performance.

l размах крыла;
b_а средняя аэродинамическая хорда крыла;
S_г.о площадь горизонтального оперения;
L_г.о плечо горизонтального оперения;
S площадь крыла.This is achieved by the fact that a light aircraft containing a rectangular fuselage, a highly rectangular wing with a strut, keel, horizontal tail, located below the wing plane, and a single-engine installation, according to the invention, is made with wing extension λ = 10.3-10, 6, while the static moment of horizontal plumage is A _go 1.15-1.25,
Where

l wing span;
b _{a the} average aerodynamic chord of the wing;
S _{g o the} area of horizontal plumage;
L _{g o} shoulder horizontal plumage;
S wing area.

 In addition, from the point of view of simplicity of design, it is preferable that the horizontal tail has a rectangular shape in plan.

 The proposed ratio of the interrelated geometric parameters of the aerodynamic surfaces of the aircraft in combination with their shape and location relative to each other provide improved performance characteristics, namely: maintaining high aerodynamic quality and a slight change in longitudinal stability over a wide range of changes in the centering of the aircraft, regardless of the loading option, which leads to an improvement in take-off landing characteristics and reduced fuel consumption in cruising flight.

 The drawing shows a General view of the aircraft in plan.

;

l размах крыла;
b_а аэродинамическая хорда крыла;
S_г.о площадь горизонтального оперения;
L_г.о плечо горизонтального оперения;
S площадь крыла.The light aircraft is made according to the classical scheme with a single-engine power plant and contains the fuselage 2, a highly rectangular wing 3 with a strut, keel 4, horizontal tail 5, which is located below the plane of the wing 3 and also has a rectangular shape in plan. Moreover, the elongation "λ" of the wing 3 is from 10.3 to 10.6, and the static moment of the horizontal tail A _{g °} lies in the range from 1.15 to 1.25,
Where

;

l wing span;
b _and aerodynamic chord of the wing;
S _{g o the} area of horizontal plumage;
L _{g o} shoulder horizontal plumage;
S wing area.

 Using the strut wing 3 of large elongation (up to 10.6) allows to reduce the weight of the structure and to obtain high aerodynamic quality, which makes it possible to increase the payload to a value of 35-45% of the take-off weight of the aircraft.

 At the same time, the engine power required for takeoff and cruising is significantly reduced.

 The aircraft has a wide range of centering changes of up to 30% of the wing chord with various loading options, due to the short wing chord and the large payload.

At takeoff, landing and cruising acceptable variation longitudinal stability within the above range, while maintaining a low center of gravity the mass aerodynamic design and high quality is provided by using the horizontal stabilizer 5 with the increased static torque A _g.o 1.15-1.25.

Claims (2)

1. A light aircraft containing rectangular fuselages, a highly rectangular wing with a strut, keel, horizontal tail, located below the wing plane, and a single-engine power unit, characterized in that the wing elongation λ lies in the range from 10.3 to 10, 6, and the static moment of horizontal plumage And _{g . about .} ranging from 1.15 to 1.25.  2. The aircraft under item 1, characterized in that the horizontal tail is made rectangular in plan.