RU47509U1 - COMMAND AND PILOT INSTRUMENT OF THE LOGIC INDICATION OF THE POSITION AND MANAGEMENT OF THE AIRCRAFT IN SPACE - Google Patents

Abstract

The application for the utility model “Flight-control device for logical indication of the position and control of an aircraft in space.” The solution relates to aeronautical engineering and can be used by crew members when piloting aircraft (LA), namely, flight-control devices. It is proposed in the flight pilot device containing a three-dimensional model of the aircraft, equipped with two drives for its movement, a concave pitch scale and other scales indicating the necessary parameters for the movement of the aircraft, to provide the model of the aircraft with a third drive for moving it to the left and to the right of the middle vertical of the screen parallel to the line of the conventional horizon, apply additional scales that more fully characterize the movement of the aircraft. The solution improves flight safety by expanding the capabilities of displaying flight parameters, position and movement of aircraft, landmarks, landing objects, and mechanisms of the aircraft itself.

Description

The invention relates to aircraft and can be used by crew members when piloting aircraft (LA), namely, to flight control devices.

Known flight indicator (US Pat. RF №2207514, G 01 C 23/00, 2003), containing a screen and means for displaying symbols on the screen, displayed on the screen, fixed and moving reference indices in the form of a simplified image of the aircraft, means moving index management.

Disadvantages - inconsistency of the display image of the aircraft on the screen for external signs. Lack of compliance, inconsistency, flight process and its display:

The aircraft is mobile in flight, and its display index on the indicator screen is stationary, which reduces the reliability of the information presented to the pilot and increases the risk of error when piloting the aircraft.

As a prototype, as the closest in purpose and in the sum of signs, a device was adopted for determining the position of an aircraft in space (USSR author's certificate No. 1119406, G 01 С 23/00 published May 27, 2002, Official Bulletin "Inventions, Utility Models No. 15 (2 part) 2002. In fact, this device is a flight control device for logical indication of the position and control of the aircraft in space.

This device contains a concave pitch scale on the inner surface of the casing, with a transparent light indication screen fixed to the outer side of the casing with a roll scale, a conditional horizon indicator, an average vertical screen, an altimeter scale, the zero of which coincides with the conditional horizon line, a movable curtain with a drive for its movement, a volumetric model of the aircraft, the bow of which is fixed on a concave pitch scale and is connected with two drives for its movement along the roll and pitch.

Disadvantages - incomplete display of the parameters of the position, movement and control of the aircraft in space, which may affect flight safety. These shortcomings are eliminated by the proposed solution.

The task at hand is to increase flight safety.

The technical result is the expansion of the ability to display flight parameters, the position and movement of the aircraft relative to the environment, landmarks, landing objects, the position of the takeoff and landing mechanisms of the aircraft.

This technical result is achieved by the fact that in the pilot-flight device of a logical indication of the position and control of the aircraft in a space containing a concave pitch scale on the inner surface of the hull with a transparent light indication screen fixed to the outer side of the hull with a roll scale applied to it, a conditional indicator horizon, the middle vertical of the screen, the altimeter scale, a movable curtain with a drive for moving it, a volume model of the aircraft, the bow of which is fixed to a concave pitch scale and connected two drives of its movement along the roll and pitch,., - in the upper part of the concave pitch scale, parallel to the index of the conditional horizon to the left and to the right of the reference center, which coincides with the average vertical of the screen, the scale of glancing angles and lateral movement is plotted, and the bow of the volumetric layout LA equipped with a third drive for moving it left and right from the middle vertical of the screen parallel to the line of the conventional horizon, on the surface of the lower part of the body and the movable curtain there is a display screen with the ability to display on I eat during landing point at which the aircraft is reduced, and the reduction position glideslope approach to a runway, and the strip itself formed in

the angular dimensions of those observations, depending on the height and distance from the front end of the strip, target designation, and in the low-altitude flight mode, the terrain; under the keel of the aircraft’s volumetric mockup, a radiation source is installed with the ability to indicate the velocity vector and the angle of attack on the pitch scale, on the wing part on the left and right and on the cylindrical part of the aircraft’s mockup, the indicators for the released and retracted position of the chassis and brake flaps are located.

The proposed ixpn6op is shown in the drawings:

Figure 1 is a General front view. Figure 2 is a structural diagram of the control device.

The composition of the device includes: body 1, concave pitch scale 2, transparent screen 3 of light indication, roll scale 4, indicator of conditional horizon 5, middle vertical of screen 3, altimeter scale 7, movable shutter 8, drive 9 for moving movable shutter, volumetric aircraft model 10, bow 11, roll movement drive 12, pitch movement drive 13, sliding angle and lateral movement scale 14, third movement sliding and lateral movement drive 15, indication screen on the lower body 16 and the shutter 8, drop point 17 LA, glide path underreporting 18, the runway 19, target designation 20, terrain 21, the velocity vector 22, the angle of attack 23, signaling 24 issued and harvested chassis brake flaps 25.

The housing 1 (figure 1) contains on the inner side a concave pitch scale 2 and a light indication screen 3, on the outside of which a roll scale 4 is applied, a conditional horizon indicator 5, an average vertical 6 of the shield 3. Behind the screen 3 are an altimeter scale 7, movable shutter 8, drive 9 moving the movable shutter 8 (figure 2), a volumetric model 10 of the aircraft, the nose part 11 of which, with the help of the movement drives on pitch 13, moves along the pitch 2 scale, and with the help of the movement drive on roll 12 rotates relative to the roll scale 4. At the top of the concave hk Ala of pitch 2, parallel to the index of conditional horizon 5, to the left and to the right of the middle vertical 6 of the screen 3, a scale of 14 angles of sliding and lateral movement is applied, the third drive 15 of which is located behind the scale of pitch 2.

On the surface of the lower part of the housing 1 and shutter 8 there is a drop point 17 LA 10, a glide path of drop 18, a runway 19 (its designation is made in the angular dimensions of its observation depending on the height and distance from the front end of the strip), target designation 20, terrain 21. Under the keel of the volumetric model 10 of the aircraft, a radiation source is installed on the pitch scale 2 of the velocity vector 22 and angle of attack 23. Light, infrared or ultraviolet light can be used as the radiation source, which will provide light mapping the velocity vector and the angle of attack.

On a voluminous mockup of 10 aircraft, bottom there are signaling devices 24 of the released and retracted position of the chassis, and above there are signaling devices 25 of the brake flaps.

The device operates as follows. When you rotate the aircraft to the left or right of the middle vertical 6 of the screen 3 in the horizontal plane, the actuator 15 moves the nose 11 of the layout 10 of the aircraft parallel to the pointer 5 to the left or right. The pilot observes the lateral glide or movement of the aircraft in space.

When approaching, on the surface of the lower part 16 of building 1 and shutter 8, there is a point of descent 17 aircraft, glide path of descent 18, runway 19, target designation 20, terrain 21, dimensions, size and location of which are calculated based on height, distance, and airspeed reduction rates.

In flight, when releasing and cleaning the chassis, brake flaps, the corresponding signaling devices 24, 25 of the released and retracted position of the chassis, brake flaps are switched on.

In flight, the pilot must observe the direction of movement of the aircraft, that is, the position and direction of the velocity vector 22, relative to the pitch scale 2, as well as the angle of attack 23, the deviation of the velocity vector from the indicator of the conventional horizon 5. The calculation of the parameters necessary for control is carried out using a computer. The proposed device can be used in a display system of flight parameters on the screens of cathode ray tubes and liquid crystal displays.

Claims (4)

1. Flight-control device for logical indication of the position and control of the aircraft in space, containing on the inner surface of the hull a concave pitch scale with a transparent light indication screen mounted on the outer side of the hull, with a roll scale, an indicator of a conditional horizon, and an average vertical screen , an altimeter scale, the zero of which coincides with the line of a conventional horizon, a movable curtain with a drive for its movement, a volumetric model of an aircraft, the bow of which is closed it is insulated on a concave pitch scale and connected with two drives of its movement along the roll and pitch, characterized in that in the upper part of the concave pitch scale, parallel to the index of the conditional horizon to the left and to the right of the reference center, which coincides with the average vertical screen, the scale of sliding angles is plotted and lateral movement, and the nose of the volumetric model of the aircraft is equipped with a third drive for moving it to the left and right of the middle vertical of the screen parallel to the line of the conventional horizon. 2. The flight control device for logical indication of the position and control of the aircraft in space according to claim 1, characterized in that on the surface of the lower part of the hull and the movable curtain there is a display screen with the ability to display on it when approaching: the point at which the aircraft is dropping; the position of the glide path of descent and landing on the runway and the strip itself, made in the angular dimensions of its observation, depending on the height and distance from the front end of the strip; target designation, and in low-altitude flight mode - terrain. 3. Flight-control device for logical indication of the position and control of the aircraft in space according to claim 1, characterized in that under the keel part of the volumetric model of the aircraft, a light, infrared or ultraviolet radiation source is installed with the ability to indicate the velocity vector and the angle of attack on the pitch scale . 4. The flight control device for logical indication of the position and control of the aircraft in space according to claim 1, characterized in that on the wing part of the left and right, and the cylindrical part of the volumetric model of the aircraft, there are signaling devices for the released and retracted position of the landing gear, brake flaps of the aircraft .