RU2175298C1 - Aircraft of "lifting fuselage" aerodynamic configuration with aerodynamic stall fences - Google Patents

Abstract

FIELD: aviation; passenger and transport aircraft of "lifting fuselage: aerodynamic configuration. SUBSTANCE: aircraft has fuselage in form of lifting surface at low aspect ratio and large relative thickness. Aircraft is provided with cabin for crew and payload, fuel tanks, power plant, control members and alighting gear. Lower surface of fuselage is provided with at least one pair of profiled fences. Profiled fences and control members are so arranged that effect of vortex sheet on control members is taken into account. Profiled fences may be mounted movably relative to fuselage. It is good practice to make fences detachable. Profiled fences may be formed by members of lower part of fuselage. EFFECT: improved stability and controllability; full use of lifting properties and maneuverability of aircraft. 4 cl, 3 dwg

Description

 The present invention relates to the field of aviation technology and can be used for the transport of passengers and goods.

 Known aircraft aerodynamic scheme "flying wing", the hull of which contains one or more cabins to accommodate the crew and payload, means of creating traction, controls and takeoff and landing device, made in the form of a wing, providing the creation of lifting force (USSR patent N 6676, C. B 64 c 39/10, 1920).

 The disadvantages of the known aircraft include low construction height and significant lengthening of the hull, providing the necessary load-bearing properties and, as a consequence, a decrease in lift, weight and maneuverability.

 Closest to the proposed invention is an aircraft of an aerodynamic design "bearing case" with a pair of front and a pair of rear rudders, made in the form of a bearing surface of small elongation and large relative thickness and containing a cabin for accommodating the crew and payload, fuel tanks, power plant, controls and a takeoff and landing device, and having aerodynamic ridges on the lower surface (see published application N 92012999 of 08.20.96).

 A disadvantage of the known design is the low stability and controllability characteristics due to the small shoulders of the controls (rudders), which leads to the incomplete implementation of the bearing properties and reduced maneuverability.

 This invention is aimed at improving the stability and controllability characteristics and, as a result, a more complete realization of the bearing properties and maneuverability of the aircraft.

 The specified result is achieved by the fact that in the aircraft of the aerodynamic scheme "supporting body", made in the form of a bearing surface of small elongation and large relative thickness, containing a cabin for accommodating the crew and payload, fuel tanks, power plant, controls and takeoff and landing device, as well as profiled ridges on the lower surface, and the profiled ridges and governing bodies are located taking into account the possibility of the impact of the eddy sheet formed by the ridges on the governing bodies I.

 Aerodynamic ridges can be fixed on the lower surface of the body movably (with the possibility of their rotation and movement) or can be formed by elements of the lower part of the body, in addition, these ridges can be made removable (interchangeable).

 The invention is illustrated by drawings.

 In FIG. 1 shows a side view of an airplane; FIG. 2 is a bottom view, in FIG. 3 is a section AA in FIG. 2.

 The aircraft consists of a bearing body 1, on which controls (aerodynamic rudders) 2, 3, engines 9 and a landing gear (landing gear) are installed 10. On the lower surface of the body 6 longitudinally-shaped ridges 4, 5 are created, creating aerodynamic channels. It is possible to install rotary nodes 7 to select the optimal position of the ridges.

 Profiled ridges 4, 5 are intended for the formation of a system of vortices that improve the redistribution of pressure between the upper and lower surfaces of the bearing body and thereby significantly increase the load-bearing properties of the aircraft. The vortex system 8 is indicated by arrows in FIG. 3.

 Vortices formed by ridges 4, 5 wash the lower surface of controls 2, 3, thereby significantly increasing their efficiency and critical angle of attack. When the ridges are movable relative to the hull, it is possible to regulate the effect of the vortices formed by them on the controls, ensuring their maximum efficiency.

 The proposed aerodynamic scheme is a radical step in the development of aircraft with bearing surfaces of small elongation, allowing you to combine their inherent low weight and high weight return with the aerodynamic quality of aircraft having bearing surfaces of large elongation.

This conclusion is confirmed by two series of pipe tests of the model aircraft of the proposed scheme, according to which its aerodynamic quality reaches 8.0 with an elongation of 0.5, the critical angle of attack is 27 ^o .

 Based on the calculations, it was found that when using the aircraft of the proposed scheme as a local airline and medium-haul aircraft, compared to existing analogues, ceteris paribus, kilometer fuel consumption is reduced by more than 2 times due to increased weight return.

 The aircraft of the proposed aerodynamic design can be used as passenger and cargo aircraft, including shortened and vertical take-off and landing, amphibians, flying boats, ekranoplanes, aerospace aircraft.

Claims (4)

 1. Aircraft of the aerodynamic scheme "bearing case" containing the fuselage in the form of a bearing surface of small elongation and large relative thickness with a cabin for accommodating the crew and payload, fuel tanks, power plant, controls and takeoff and landing device, having on the lower surface, at least one pair of profiled ridges, characterized in that the profiled ridges and controls are located taking into account the possibility of the impact of the eddy sheet formed by the ridges on the control organs Lenia.  2. The aircraft according to claim 1, characterized in that the profiled ridges are mounted movably relative to the hull.  3. Aircraft according to any one of the preceding paragraphs, characterized in that the profiled ridges are removable.  4. The aircraft according to claim 1, characterized in that the profiled ridges are formed by elements of the lower part of the hull.

Images