RU2301762C2 - Aircraft of simplified arrangement - Google Patents

Abstract

FIELD: flying vehicles.

SUBSTANCE: proposed aircraft has fuselage, pilot's cabin in nose section and turbo-jet engines. Fuselage has rounded-off top and hull-type bottom with landing units on shock-absorber struts and hatches. Turbo-jet engines are provided with controllable nozzle for change of angle of inclination of gas jet; they are mounted on pylons on sides of fuselage; pylons are mounted above longitudinal axis of fuselage and on surface of its tail section. Piloting and maneuvering of aircraft are performed through change of angle of inclination of nozzle of turbo-jet engines and their thrust. Fuselage may be provided with passenger saloon and cargo compartment. Tail section of flying vehicle fuselage is provided with hatches and mechanisms for pan-caking of detachable fuel tanks or cargoes under adverse conditions of flight.

EFFECT: simplified arrangement.

3 cl, 2 dwg

Description

Aircraft with a simplified layout according to cl. IPC B64C 15/00, B64C 29/00. The invention relates to aircraft used for the transport of passengers and goods for various purposes, including military in any area without a runway and airfield services.

Known aircraft and aerodromeless aircraft (BARS) complex layout with a bearing wing, vertical and horizontal tail, landing gear, large take-off mass.

The prototype of the present invention is an aerostatic unloading aerodrome unloading aircraft (BARS) developed by Tyumenekotrans OJSC, and leaflets prepared by the Ural Center for International Cooperation, 620014, Yekaterinburg, Sovetskaya St., 19, building 2, office 36, phone 369-19-97 (exhibition advertisement of 2005 is attached).

The disadvantage of this prototype is the complex layout and control system, low speed and limited flight altitude.

The aim of the invention is to simplify the layout and maneuver control system, as well as increasing the speed of horizontal flight and flight altitude.

This goal is achieved by creating an aircraft according to a fundamentally new, simplified layout and flight control system both on take-off, climb, and planning for landing, landing on any site with a hard surface or on the surface of a reservoir (in calm weather).

The aircraft consists of a fuselage hull with a passenger compartment and cargo compartments, with a rounded top surface and a boat bottom profile, and with landing elements on suspension struts, and are equipped with hatches. In addition, the turbojet engines of the vessel are equipped with a controlled nozzle for changing the angle of inclination of the gas stream and at the same time are installed on the sides of the hull of the vessel on pylons mounted above the longitudinal axis of the hull and on the surface of the tail of the hull. Piloting and maneuvers of the aircraft are carried out by changing the angle of inclination of the nozzle of the turbojet engines and their traction power. The tail of the hull is equipped with hatches and mechanisms for parachuting removable fuel tanks or cargo, for example, in difficult situations in flight.

A change in the angle of inclination of the nozzle relative to the longitudinal axis of the engine controls the direction of the outflow of gases and the thrust vector, changing the "angle of attack" of the thrust force. The pilot of the aircraft, by changing the angle of inclination of the nozzle of the turbojet engine and its traction power, controls the forces that affect the maneuvers of the aircraft. So, the vertical and horizontal speeds of an air ship depend on the angle of inclination of the thrust vector and thrust power of the engines. When you take off and climb, the thrust vector has a maximum angle of inclination ("angle of attack") and creates an excess of lift (Yu), i.e. the lifting force becomes greater than the weight force (G) of the vessel, and the horizontal speed (V) is still minimal and compensates for the drag force (Q). Upon reaching the required flight altitude, the pilot reduces the angle of inclination of the nozzle, changes the direction of the thrust vector and creates conditions for acceleration, increase in horizontal flight speed (V), creates conditions for continued horizontal flight at the required speed. The traction force developed by the tail engine is also used to change the course of flight, i.e. performing the steering function of the course.

The layout of the aircraft is shown in figure 1. Aircraft body 1, pylons 2p and 2l, turbojet engines 3p, 3l and 3x, their jet nozzles 4p, 4l and 4x, pilot's cabin 5, hatches 6 and 6p, observation windows 7, landing elements 8 for landing on a solid platform, bottoms hulls with a boat profile 9 for landing on a water surface.

Figure 2 shows a diagram of the distribution of forces acting on an aircraft with a simplified layout. The longitudinal axis 10 of the hull of vessel 1, thrust force P, Pu, flight speed V, drag force Q, weight force G ₁ , G ₂ , ΣG, lifting force V, Vu, center of gravity of the central heating center, center of pressure of the central cylinder, turbojet engines ДПР ( 3p), RDl (3l), RDh (3x), Pc1, Pc2 - the direction of the jet of gas.

The force vectors are indicated by solid and dashed lines. Vectors with solid lines indicate the distribution of forces on takeoff and climb, vectors with dashed lines indicate the distribution of effective forces in horizontal flight. Piloting an aircraft.

On takeoff and climb, the pilot thrusts the power of the turbojet engines (3p, 3l, 3x - RDpr, RDl, RDh) to the maximum value (levers of gas feeds forward) and the angle of the jet nozzle of the turbojet engines with respect to their longitudinal axis sets to create the necessary lifting force (V) with minimum horizontal speed (V).

Upon reaching the planned flight altitude, the angle of inclination of the jet nozzle decreases, it is set to develop the necessary horizontal speed (V), in balance of the lifting force (V) with the force of weight (SG). When planning for landing, the traction capacities of turbojet engines are reduced, and the angle of inclination of the nozzle is set to reduce the height with an acceptable minimum vertical and horizontal speed.

When performing maneuvers to change the course of flight, slip with loss of altitude, turns, the jet nozzle (4x) of the engine (3x) creates an angle of inclination with a deviation to the left or to the right. For example, for sliding to the left, the lifting force of the right engine (3p) increases, forming the left roll of the aircraft, and a force pushing the tail to the right is created, for which the jet nozzle (4x) creates an angle of inclination to the left and directs part of the thrust force to the left, respectively.

Piloting an aircraft is to regulate the direction of thrust of turbojet engines and their traction power.

The invention can be used for the production of light and heavy, civilian and military aircraft, capable of being based on the terrain without a runway, and airfield services.

Claims (3)

1. Aircraft with a simplified layout, comprising a hull, a cockpit in the bow, turbojet engines, characterized in that the hull is made with a rounded top and bottom of the boat profile with landing elements on suspension struts and is equipped with hatches, in addition, turbojet engines are equipped controlled nozzle to change the angle of inclination of the gas stream and at the same time mounted on the sides of the hull on pylons mounted above the longitudinal axis of the hull and on the surface of its tail, and the pilots ment and aircraft maneuvers performed by changing the inclination angle of the nozzle jet engines and their traction power. 2. The aircraft according to claim 1, characterized in that its hull may have a passenger compartment and a cargo compartment. 3. The aircraft according to claim 1 or 2, characterized in that the tail of its hull is equipped with hatches and mechanisms for parachuting removable fuel tanks or cargo, for example, in a difficult situation in flight.

Images