BG65998B1 - Aircraft with jointed wing - Google Patents

Abstract

The invention relates to a highly maneuverable aircraft with jointed wing, which can be used to perform flights, piloted or without a pilot on board, for sports purposes, extinguishing fires, monitoring and prevention of hail. The high maneuverability of the aircraft is achieved by combined control of the steering-wheels and the thrust vector of the propulsor, thus achieving direct and indirect variation of the aerodynamic forces. The jointed wing is resistant to the overloads occurring during the evolutions. The highly maneuverable aircraft with jointed wing consists of a front wing (1) and a rear wing (2) with ailerons (10), slats (8) and flaps (9) connected to each other by streamlined power units (3 and 4). A propulsor (5) is joined to a central power unit (3) by means of hinges (6 and 7).

Description

Technical field

The invention relates to an articulated wing airplane which can be used in manned and unmanned aerial vehicles, especially in aircraft, which requires high maneuverability, resistance to high loads and direct control of aerodynamic forces.

BACKGROUND OF THE INVENTION

An articulated airplane is known, consisting of a front wing with a body and a rear wing connected to each other by side streamlined power elements flaps, flaps and ailerons gripped to the wings and a motor and a vertical stabilizer at its rear end. The front wing is joined to the front of the body and the rear wing is joined to the upper end of the vertical stabilizer, the ends of the wings connected to each other by side streamlined members (US 4365773).

The main problem is that the forces between the two wings are transmitted through the body and the vertical stabilizer, which aggravates them, and also that this aircraft does not have very high maneuverability due to the firm grip of the engines, which does not allow control of the thrust vector.

SUMMARY OF THE INVENTION

It is an object of the invention to provide an airplane with high maneuverability, reduced dimensions and deformability, high strength, improved aerodynamic performance and reduced run and mileage.

The task is accomplished by an articulated airplane consisting of a front wing with a body and a rear wing connected to each other by side streamlined force members flaps, flaps, and ailerons engaged by the guard and the engine. According to the invention, the central portions of the wings are connected by a streamlined central force member, forming a space frame with them and the lateral streamline force members. An engine is mounted to the central streamlined force element by means of the frame (s) and the thrust vector, through which the thrust vector is through the center of mass of the aircraft and is capable of deflection.

According to an embodiment, the engine includes a propeller in the engine nozzle.

The engine can also be a jet engine.

The streamlined force members at the end of the wings are angled to the airflow and have rudders.

The rudder, ailerons and the vector of the thrust of the engine have the possibility of combined deviation.

The flaps, flaps of the front and rear fenders and the engine are capable of combined actuation as the load capacity is increased and the range of centering of the airplane is extended.

The flaps, flaps, ailerons and the thrust vector of the engine are all capable of combined deflection.

The advantages of the aircraft according to the invention are:

The wings can be used in combination, depending on the maneuver performed. In this case, the flaps and ailerons can act as rudders for height, for turning and for direct control of the lifting and lateral forces.

The simultaneous deflection of the mechanization of both wings allows the aircraft to sharply increase its maximum carrying capacity without creating additional moments that need to be balanced, for example by changing the angle of placement of the horizontal stabilizer. With synchronized deflection of mechanization, the range of service centers can be significantly extended.

The hinged attachment of the motor allows it to deflect at large angles and to control the thrust vector in the horizontal and vertical planes.

The simultaneous combined deflection of the rudder and the engine allows direct and indirect control of the aerodynamic forces and the execution of maneuvers with a sharp change in the direction of movement and the angular position of the aircraft.

65998 Bl

The aircraft will be able to take off and land with sufficient traction and upright. The proposed aircraft can only take off with one engine, which also provides horizontal flight. Take-off and landing stability can be ensured by small deflections of the engine so that its thrust vector always passes through the center of mass.

The aircraft can be used in a manned and unmanned variant. In the piloted version, planes with much larger payloads can be designed, the same size as the existing ones so far.

In addition, the articulated wing, together with the central power element, make it possible to perform maneuvers with the very high congestion required for drones.

The streamlined lateral force members at the end of the wings are angled with the air flow and provide resistance to course and tilt deviations. They can have rudders for bends and direct lateral force control. The combined deflection of the rudder and the thrust vector from the control system give the airplane the properties of ultra-agility and agility. it may perform maneuvers that are not possible for aircraft with other schemes.

The payload can be placed in the wing planes, the shape of which is shaped according to the volumes required.

The streamlined force members at the end of the wings are angled to the airflow, which contributes to providing resistance to course and slope deviations. They have rudders for bends and direct lateral force control. In addition, the flaps, flaps of the front and rear wings and the engine are capable of combined actuation to increase the carrying capacity and widen the range of centering of the aircraft.

The technical solution used reduces the required airworthiness and mass of the airplane structure, whereby it has less airiness and its own weight when compared to equivalent airplanes from other schemes, which provides it with advantages in flight and technical operation.

Other significant advantages are that the aircraft can be unmanned as well as take off and land vertically.

Explanation of the annexed figures

The invention is illustrated by an exemplary embodiment shown in the accompanying drawings, of which:

Figure 1 is an axonometric view of the front and top of the high-articulated articulated wing plane;

figure 2 - top view of the aircraft; Figure 3 - Front view of the aircraft.

Examples of carrying out the invention

The high-articulated articulated wing aircraft shown in FIG. 1, consists of a front wing with body 1 and a rear wing 2 connected in the middle by a central force element 3 and at the ends by side streamlined force elements 4. An engine 5 is pivotally attached to the central force element 3 by a frame 12 with a horizontal hinge 6 for horizontal rotation of the engine 5 and tilting hinge 7 for movement of the engine 5 vertically. The motor 5 includes a propeller in the nozzle and an engine or jet or rocket engine. The central force element 3, the wings 1,2 and the lateral streamlined force elements 4 form the spatial force frame, which imparts structural stability. The front 1 and rear 2 wings have mechanization including flaps 8, flaps 9, ailerons 10, and the side streamlined power members 4 have rudders 11 that can be used in combination, depending on the maneuver being performed. In addition, the flaps 9, ailerons 10 and rudders 11 act as rudders for height, for turning and for direct control of the lift and lateral forces.

There are variants with several power elements 3 for which several motors 5 are hinged.

Application of the invention

Aircraft with articulated wing and controllable thrust vector can be used in manned and unmanned aerial vehicles for road transport

65998 Blnks and loads, sports and training purposes, for monitoring, fire fighting and hail prevention.

The articulated wing aircraft has a controlled thrust vector, in which high maneuverability is required in acrobatic sports planes and in fires in mountainous areas.

On take-off and landing as an airplane (with reinforcement and thrust), the mechanics of the front 1 and rear 2 wings are lowered, which increases the lift coefficient and the engine 5, which is fixed in the center of mass, can rotate about horizontal hinge 6, creating additional lifting force and thus reducing mileage and run, and with sufficient traction, the aircraft can take off and land vertically.

Claims (7)

Claims 1. Airplane with articulated wing consisting of a front wing with a body and a rear wing connected to each other by side streamlined power elements flaps, flaps and ailerons gripped to the wings and an engine, characterized in that the central portions of the wings ( 1 and 2) are connected by a streamlined central force element (3) forming with them both lateral streamlined force elements (4) a space frame (12), and by a frame (12) and hinges (6) to the central streamline force element (3). and 7) the engine (5) is mounted, wherein the thrust vector is through the center of mass of the airplane and is capable of diverting. Airplane according to claim 1, characterized in that the engine (5) includes a propeller in the engine nozzle. Airplane according to claim 1, characterized in that the engine (5) is a jet engine. Airplane according to claims 1 to 3, characterized in that the streamlined force members (4) at the end of the wings (1, 2) are angled with respect to the air flow and have rudders (11). Airplane according to claims 1 to 4, characterized in that the rudders (11), ailerons (10) and the thrust vector of the engine (5) are capable of combined deflection. Airplane according to claims 1 to 4, characterized in that the flaps (8), the flaps (9) of the front (1) and the rear wing (2) and the engine (5) are capable of combined actuation upon elevation of the carrying capacity and the extension of the aircraft centering range. Airplane according to claims 1 to 4, characterized in that the flaps (8), flaps (9), ailerons (10) and the thrust vector of the engine (5) are capable of combined deflection. Attachment: 3 figures