KR101370241B1 - Electronic Display System of Flight Paramters for an Aircraft - Google Patents

Abstract

An electronic display system for displaying flight parameters for an aircraft comprises: a series of electronic sensors (2) for collecting flight data of the aircraft; A central processing unit (3) for collecting said data from said sensors and processing said data to visually display said data; And an electronic graphics unit 4, controlled by the central processing unit, that uses a projector to determine the display of the data on a screen or transparent crystal.

Description

Electronic display system of aircraft flight parameters {Electronic Display System of Flight Paramters for an Aircraft}

1 is a schematic representation of an electronic display system in accordance with the present invention.

2 is a view showing a display crystal protruding flight attitude symbology of the aircraft according to the present invention.

The present invention relates to an electronic display system of aircraft flight parameters. In particular, the present invention relates to an electronic display system of flight parameters that performs a so-called head up display (HUD).

The HUD allows the pilot of the aircraft to monitor parameters that are visualized on a display located in front of the pilot, beyond the field of view in flight. This display is made by a transparent crystal, so these parameters can be visualized by superimposing on the actual field of view of the surrounding environment.

Information visualized in the HUD is generally related to speed and aircraft head, roll and pitch angles, lateral acceleration, and the like.

It is an object of the present invention to allow such a display to be used to visualize other information about the aircraft flight attitude under certain flight conditions (eg, during takeoff or landing).

To achieve this object of the invention, the takeoff phase is defined as starting from the moment when the aircraft exceeds the rotational speed. The rotational speed corresponds to the speed at which the wheels of the landing gear leave the ground.

For the purposes of the present invention, the landing phase refers to the phase in which the landing device exits from the aircraft and begins when the aircraft reaches a preset slow speed for landing, which ends when the wheels of the aircraft touch the ground. .

Applicants of the present invention have made an electronic display system of aircraft flight parameters that visualizes the flight attitude of the aircraft on the head of the display using preset symbology at takeoff and landing stages.

In one aspect of the present invention, an electronic display system of aircraft parameters comprises a series of sensors that collect aircraft flight data, a central processing unit that collects data from the sensors and processes them to represent prominently, and the central processing It is controlled by the device and includes a graphical electronic unit that determines the display of the data on a screen or transparent crystal using a particular projector. Here, during takeoff / landing of the aircraft, the symbology regarding flight attitude conditions of the aircraft is projected on the screen.

With reference to the above figures, the electronic display system according to the present invention is a series of sensors (2) suitable for collecting flight data (e.g., flight speed of the aircraft, conditions of the landing device (open, closed, blocked)) of the aircraft. And sensors suitable for measuring the pitch angle, roll angle, heading angle of the aircraft.

The sensors are connected to the central processing unit 3. The central processing unit collects and processes the above data, making it easier for the pilot to understand. This central processing unit 3 controls the electronic graphics unit 4. The electronic graphics unit 4 uses a particular projector and optical system to determine the data display on the screen or transparent crystal 5. The optical system includes a lens and a mirror (not shown).

FIG. 2 shows, as an example, a screen or generally used surface on which a symbology protruding from the aircraft's flight posture state in take-off and landing conditions.

The symbology according to the invention comprises information relating to the aircraft flight posture, in particular information relating to the wing area and landing gear of the aircraft, with reference to the pitch angle of the aircraft represented by itself.

The wing area is represented by a pair of horizontal rods 6, 6 ′ which face each other, and the landing device is represented by a pair of spheres 7, 7 ′ which are respectively connected with one of the rods.

Within the scope of the present invention, both the wing area and the landing gear can be represented using different symbology with the same purpose.

Moreover, a continuous pair of angle indicators 8, 8 ′ protrude on the screen. The angle indicators are aligned vertically on the screen and represent the pitch scale at which the wing regions overlap, visualizing the pitch angle of the aircraft in real time.

The symbology shown in the figure is represented in the HUD prior to takeoff and is maintained while satisfying the following conditions.

Aircraft landing gear lowered and blocked

Aircraft landing gear lifts and shuts off, at approximately 185 KTS or higher at takeoff

Aircraft landing gear up and shut down, slow down to about 180 KTS or smaller (at landing)

The symbologies described above represent fuselage references that radiate to infinity.

For accurate takeoff, the pilot must maintain the aircraft so that after reaching the rotational speed, a 10 degree flight posture symbol reference overlaps with the symbols.

In this way, the aircraft can successfully take off without overturning or stalling.

In the landing phase, the pilot uses a reference to continue to control the parameters as follows.

Reference for display of flight attitude

Initiation Marking Angle (AOA): The optimum AOA for landing is 14 degrees.

● AOA index: Error index for the optimal AOA of 14 degrees

FPM aircraft vector velocity (orbit), VV.

By immediately observing these parameters, the pilot can have important information (indications) to safely control the landing flight.

Accordingly, according to the present invention, it is possible to provide an electronic display device that visually and simultaneously displays important parameters for the flight attitude, so that the pilot can safely control the aircraft during takeoff and landing.

Claims (5)

An electronic display system for displaying flight parameters for an aircraft, the electronic display system comprising: A series of electronic sensors (2) for collecting flight data of the aircraft; A central processing unit (3) for collecting said data from said sensors and processing said data to prominently display said data; And An electronic graphics unit 4, controlled by the central processing unit, that uses a projector to determine the display of the data on a screen or transparent crystal, During the takeoff and landing phase of the aircraft, a symbology regarding flight attitude conditions of the aircraft is projected on the screen, The symbology represents the wing area and the landing device of the aircraft with reference to the pitch angle of the aircraft itself, The wing area is represented by a pair of opposing vertical rods 6, 6 ′, each with a pair of spheres 7, 7 ′ where the landing gear is each connected to one of the rods. Expressed, A pair of angle indicators 8, 8 ′ protrude on the screen and display on the screen a pitch scale that is vertically aligned and superimposed by the wing region so that the pitch angle of the aircraft is visualized in real time. And an electronic display system. delete delete delete The method of claim 1, The series of sensors measure the flight speed of the aircraft, the condition of the landing gear, the pitch angle, the roll angle and the heading angle of the aircraft.

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