RU2820358C1 - Method of controlling pitch of convertiplane - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: in tail part of convertiplane, directly behind rotary fan, there is a rudder plate, and there are also hatch and shutters interacting with fan. During takeoff/landing, as well as during transition from vertical flight to horizontal flight and vice versa, fan is installed in horizontal position, wherein the curtains are closed and the hatch is opened, thereby providing a downward air flow when thrown by the fan to create an aerodynamic force acting on the arm from the center of mass of the aircraft to the axis of rotation of the fan and creating a moment from the aerodynamic force on this arm. During horizontal flight, the curtains are opened, the hatch is closed, air is forced onto the rudder plate by means of a fan, at the same time creating moment from aerodynamic force with arm from center of mass to center of pressure of plate-rudder arising at flow around plate-rudder.

EFFECT: higher maneuverability, longitudinal stability and safety of convertiplane during takeoff and landing, during transition from vertical flight to horizontal flight and vice versa, as well as throughout the flight.

1 cl, 8 dwg

Description

The invention relates to the field of aircraft construction, and more precisely to methods and systems for controlling the pitch of a tiltrotor, and can be used to control the pitch of a tiltrotor.

The technical solution “Three-propeller tiltrotor” is known (patent No. RU2656957C1, IPC B34C 37/00, published 06/07/2018). A three-propeller tiltrotor consists of a fuselage with a wing attached to it according to the high-wing design, a two-fin tail unit, engines with propellers located on the leading edge of the wing, and a rotary mechanism that allows you to change the thrust vector by 110° relative to the horizon to change flight modes. There is an additional power unit with a horizontal propeller located in the tail section of the horizontal fin and serves to stabilize the aircraft in pitch in helicopter flight mode, control the direction of movement of the tiltrotor, and is also equipped with a rotating mechanism that allows you to deflect the thrust vector in the vertical plane to compensate for the torque generated by the front power units and control the yaw of the aircraft in helicopter and transient flight modes.

The disadvantage of this technical solution is the vulnerability of the additional power plant with a horizontal propeller during takeoff and landing from unevenness of the underlying surface.

The DOAK VZ-4 tiltrotor was the closest in technical essence, the engine nozzle of which was mated to a pipe of the required length, which passed through the entire tail boom. A special device with several gas rudders was installed on it. Such control systems had a very simple design. At the pipe nozzle there was a frame on which movable vertical and horizontal plates-rudders were placed. Flow control was carried out by deflecting the rudders in the desired directions.

However, a significant drawback of this method of pitch control is the inability to quickly respond to changes in the vertical position of the aircraft, which can increase the risk of a tiltrotor crash.

The technical problem being solved is the creation of a highly effective method for controlling the pitch of a tiltrotor, which makes it possible to increase the maneuverability of the tiltrotor, the longitudinal stability and safety of this aircraft during takeoff and landing, during the transition from vertical to horizontal flight and vice versa, as well as throughout the entire flight.

The technical result of the invention is to increase the maneuverability, longitudinal stability and safety of the tiltrotor during takeoff and landing, during the transition from vertical to horizontal flight and vice versa, as well as throughout the entire flight.

The technical result is achieved by the fact that during takeoff/landing, as well as during the transition from vertical to horizontal flight/when transitioning from horizontal to vertical flight, to counteract the pitching moment, a moment from the action of the aerodynamic force is created by installing a rotary fan (hereinafter referred to as the fan) in horizontal position, which, in turn, rejects the air coming from the environment, due to which an aerodynamic force is generated, directed downwards and acting on the shoulder from the center of mass of the tiltrotor to the axis of rotation of the fan. During horizontal flight, due to the location of the rudder plate in the tail part of the tiltrotor directly behind the fan installed in a vertical position, to counter the pitching moment, a moment from the aerodynamic force is created, which appears due to the aerodynamic force acting on the shoulder from the center of mass of the tiltrotor to the center of pressure of the plate - the steering wheel, and resulting from the flow of air blown around the steering wheel plate by the fan. This increases the maneuverability and pitch control of the tiltrotor, increases the stability and safety of the tiltrotor during takeoff and landing, during the transition from vertical to horizontal flight and vice versa, as well as throughout the entire flight.

Description of drawings:

• Figure 1 shows a diagram of the horizontal flight of a tiltrotor in a top view;

• Fig. 1.1 shows the section GG presented in Fig. 1;

• Fig. 1.2 shows view B shown in Fig. 1.1;

• Fig. 1.3 shows view B, shown in Fig. 1.1;

• Fig. 1.4 shows view B, shown in Fig. 1.1;

• figure 2 shows a diagram of the vertical flight of a tiltrotor in a top view;

• Fig. 2.1 shows view B, shown in Fig. 2;

• Figure 3 shows a diagram of the horizontal flight of a tiltrotor in front view.

The invention contains a fuselage (1), which serves to accommodate the target load with a wing (2) attached to it according to the high-wing design; on the leading edge of the wing (2) there are engine nacelles (3) with engines, propellers and a rotating mechanism that allows you to change the thrust vector relative to the horizon; in airplane (cruising) flight mode, the main direction of the thrust vector is horizontal and the aerodynamic force is created due to the work of the wing profile (2), and when flying in helicopter mode (hovering / vertical takeoff and landing), the main direction of the thrust vector is vertical and lift force is created due to the air mass thrown by the propellers; rotary fan (4), which serves to counter the pitching moment during takeoff/landing and during transitions from vertical to horizontal flight and vice versa by creating an aerodynamic force when throwing air down, acting on the shoulder from the center of mass of the aircraft to the axis of rotation of the fan and creating on this shoulder moment from the aerodynamic force, and also during horizontal flight, which serves to force air onto the rudder plate (5), when air flows from the fan (4) around which an aerodynamic force appears, creating a moment from the aerodynamic force with the shoulder from the center of gravity of the tiltrotor to the center pressure of the rudder plate (5) and capable of counteracting the pitching moment; V-shaped tail (6), which serves to stabilize the aircraft in yaw and roll; metal curtains (7), which are closed during takeoff/landing, during transitions from vertical to horizontal flight and vice versa, to create a more directional air flow and open during horizontal flight in order to ensure that the rudder plate (5) is blown by the air flow forced by the fan (4 ); sliding hatch (8), which is opened during takeoff/landing, during transitions from vertical to horizontal flight and vice versa, and closed during horizontal flight in order to ensure the correct direction of the air flow forced by the fan (4); metal curtains (7) work on the principle of a simple door hinge and have guides (9) located along the internal contour of the fuselage (1) and necessary for the correct lowering and raising, depending on the flight mode, of the hinges (10) with metal plates attached to them (11 ).

The device works as follows.

The fuselage (1) serves to accommodate the target load; in airplane (cruising) flight mode, the main direction of the thrust vector is horizontal and the aerodynamic force is created due to the operation of the wing profile (2), and when flying in helicopter mode (hovering/vertical takeoff and landing) the main direction of the thrust vector is vertical and the lifting force is created by the air mass thrown back by the propellers. The V-shaped tail (6) serves to stabilize the aircraft in yaw and roll. When changing the direction of the thrust vector of the main power plants (3) from horizontal to vertical and back, as well as for hovering and vertical takeoff/landing modes, to stabilize the tiltrotor in pitch, the fan (4) is installed in a horizontal position, while metal curtains (7 ) are closed, and the sliding hatch (8) is opened, thereby providing, when thrown by the fan (4), a downward flow of air to create an aerodynamic force acting on the arm from the center of mass of the aircraft to the axis of rotation of the fan (4) and creating a moment on this arm from aerodynamic force. During horizontal flight, the metal curtains (7) are opened, the sliding hatch (8) is closed, air is pumped onto the rudder plate (5) using a fan (4), creating a moment from the aerodynamic force with the shoulder from the center of mass to the center of pressure of the plate -rudder (5), which occurs when flow around the rudder plate (5). The moment from the aerodynamic force aligns the aircraft relative to the horizon, and also allows the tiltrotor to maneuver in pitch.

Thus, the claimed technical solution makes it possible to increase the maneuverability, longitudinal stability and safety of the tiltrotor during takeoff and landing, during the transition from vertical to horizontal flight and vice versa, as well as throughout the entire flight. The propeller required for pitch control becomes protected due to its location inside the fuselage.

Claims (1)

A method for controlling the pitch of a tiltrotor, characterized by providing a plate-rudder in the tail section of the tiltrotor, directly behind the rotary fan, as well as a hatch and curtains interacting with the fan during takeoff/landing, as well as during the transition from vertical to horizontal flight and vice versa. installed in a horizontal position, while the curtains are closed and the hatch is opened, thereby providing, when thrown by the fan, a downward flow of air to create an aerodynamic force acting on the arm from the center of mass of the aircraft to the axis of rotation of the fan and creating a moment on this arm from the aerodynamic force , during horizontal flight, the curtains are opened, the hatch is closed, air is forced onto the rudder plate using a fan, creating a moment from the aerodynamic force with a shoulder from the center of mass to the center of pressure of the rudder plate, which occurs when flowing around the rudder plate.