RU19323U1 - HELICOPTER HELICOPTER-NAVIGATION INDICATOR FORMAT - Google Patents

Abstract

The format of a helicopter flight-navigation indicator, containing a horizon, indicators of altitude-speed, positional and navigation parameters and a field of signal messages, characterized in that in addition to the traditional navigation indicator, a special flight-navigation and positional-speed indicator for the mode is formed on it "hovering", containing a circular, rotating scale of courses, azimuths, directions of the directional velocity vector, respectively, true, or magnetic; on the scale are located and moving, depending on the information received from the calculator, indices of the given course, course angle of the selected geo-point, bearing of the helicopter; positional strips showing, relative to the X and Z axes of the helicopter, the location of the geo-point selected in advance or fixed at the time of its passage; the zero point located in the center of the indicator, from which the deviations of the positional bars and the indicator of the lateral, longitudinal, components of the ground speed are measured in the form of white "columns" of variable length, depending on the value of the components of the ground speed; an index of the longitudinal and lateral components of the ground speed, in the form of white "columns" growing up left-right and back-and-forth relative to the center of the position-speed indicator, depending on the current values of the components of the ground speed, the path vector, in the form of a thin blue line color of variable length, depending on the value of ground speed, rotating from the center relative to the course scale of the navigation indicator; true and magnetic heading meters located above the navigation indie

Description

MKI: 6QSH.§2fS2- (Z6Lo

HIiZpKATOPA HELICOPTER-HELICOPTER FORMAT FORMAT

Authors Senkov K.A., Andrienko S.S.

The invention relates to the field of aviation technology and can be used in helicopters equipped with digital flight-navigation systems, satellite, inertial navigation systems and Doppler indicators of ground speeds.

The format of the helicopter flight-navigation indicator, proposed by the authors, was created in accordance with the requirements. Aviation Rules of the Interstate Aviation Committee, part 29, published in 1995 and approved by the Council on Aviation and Airspace Use, Section F, clauses 29.1321, (a), (b) - (1), (2), (3 ),(4).

There is a method of displaying information on an electronic indicator for solving pilot-navigation problems on all types of aircraft (LA) described in RU 2129699 C1 6 G 01 C23 / 00, B64 D 43/00, as a way of piloting an aircraft along a given path with a given speed from 06/23/99 Author Titov A.A.

The proposed format of a helicopter flight-navigation indicator will allow the helicopter pilot to more effectively use the available flight-navigation information when landing out of sight of the earth in hovering mode due to the compact and ergonomically-based location of the indicator elements on the indicator screen (format field).

The aim of the invention is to increase the safety of helicopters landing on limited sites in the absence of natural visibility (dust, snow vortices, dense fog) in manual pilot mode.

This goal is achieved by the fact that in the standard flight display format of the helicopter display, in addition to the mandatory horizon and other indicators of flight and navigation parameters, a specially formed flight and navigation indicator is introduced.

The format contains a horizon, a field of signaling messages, a number of indicators of flight and navigation parameters, for example, such as indicators of high-speed, angular-rangefinder and a number of other functional blocks.

When hovering and landing with the existing set of electromechanical or even electronic indicators, the helicopter pilot in conditions of poor visibility is forced to use the indicators of necessary information dispersed over the dashboard. The composition and location of these indicators does not provide optimal collection and processing of information. Optical illusions arise, which can lead to a loss of spatial position and severe consequences.

Therefore, in conditions when there may be snow or lesser vortices, when there is no natural visibility and it is necessary to land on a limited landing site, additional and easily perceived information must be provided to the pilot to ensure the possibility of a safe landing in such conditions.

It is proposed a new generation of additional information on the available navigation and aerobatic parameters about the current position of the helicopter relative to the vertical of descent to the landing point and the rate of change of this position. It is proposed that they be placed on the on-board flight and navigation display to meet the requirements of the Aviation Rules to provide manual control of the helicopter in the hover-landing mode outside the visual visibility of the landing surface. See FIG. 1.

Pa fig. 1 located:

1 - an additionally introduced, specially formed positional navigation and navigation indicator, which contains:

2- circular, rotating scale of courses, azimuths, direction of the directional velocity vector, respectively, true, or magnetic;

the indices are located and move on the flap, depending on the information received from the calculator:

3- set course;

4-course angle of the selected geo-point (drive radio station, or any place of hovering, landing);

5- bearing of the helicopter;

position bars showing the location of the selected geo point:

6- relative to the X axis of the helicopter - horizontal bar;

7- relative to the Z axis of the helicopter - a vertical bar;

8 is a zero point located in the center of the indicator 1, from which the deviations of the position bars 6 and 7 are counted, and

9- side indicator;

10-longitudinal components of ground speed in the form of white bars of variable length, depending on the value of the components of ground speed;

11 is the directional velocity vector starting from zero point 8, the direction of which is measured along the circular rack 2, and the quantity, qualitatively, along the length of this vector and quantitatively, along

12-digital counter;

13 - counter of the general pitch of the rotor;

14- radio altitude counter, which appears in the pictured place only in the hover mode; in the entry mode, this counter is located to the right of the director plank assembly;

15 - distance meter to the selected geo-point, or radio engineering device;

16- true course counter;

17 - counter magnetic course;

In FIG. 2 shows a block diagram of the information support and navigation indicator of a helicopter, with the technical part on the upper part of FIG. 2 and the hovering functional diagram on the lower part.

18 - block of sensors for flight and navigation parameters;

19 - helicopter computing system calculator - BCB;

20- signal conversion unit;

21- display control panel;

22- radio control panel (KPRS), autopilot (AP);

23- multifunction indicators (IFIs)

The format of the helicopter flight-navigation indicator, for manual control in the hover-landing mode outside the visual visibility of the landing surface, is used as follows.

When flying along a route (route indication mode), the pilot enters the geographical coordinates of the hovering point (landing), a given approach angle of approach (ZPU), the angle of inclination of the descent glide path through the control panel of the helicopter’s slow-acting system (VVS), and switches on call.

The approach is made according to the director or position indicators, when using sleep (satellite navigation system) without differential mode with an accuracy of ± 150 meters, and using the differential mode, location accuracy is ensured up to + 0.7 m.

When approaching the hovering height (50-10 m) and in the presence of visual visibility, the pilot displays the helicopter vertically at the hovering point at a height where snow or dust vortices from the main rotor have not yet arisen and are fixed above the selected point by pressing the corresponding button on the on-board computer control panel relative coordinates of the point that fixes the current coordinates from the SNA, or (and) BINS (strapdown inertial system).

As a result, the indication is transferred from the entry format to the hover format. Hanging and landing is performed using the flight and navigation indicator 1 according to the horizontal bar 6 (range to the geo-point along the X axis of the helicopter) and vertical bar 7 (distance to the geo-point along the Z axis), calculated according to the SNA and / or SINS and to change the readings path speeds along the X and Z axes, calculated according to the SNA, SINS, and DISS. The height and speed of descent are ascertained by the readings of an accurate radio altimeter counter with a resolution of 1 m.

This combination of parameters and the location of their indicators on the display screen allows the pilot to have an idea (flight image) not only in positional data, but also in speed values, and in changes in speeds, i.e. acceleration, which is a prerequisite for directorial management. Unlike directorial management, such an indication retains a detailed image of the flight. In addition, the relative positioning of the necessary indicators in the central viewing angle allows you to spend minimal time and effort reading the necessary information.

By controlling these parameters with the help of the common step lever, the cyclic leverage lever and pedals, the pilot provides the helicopter with almost horizontal position with minimal horizontal and vertical speeds in the required direction.

Currently, a mathematical model of the format’s functioning has been developed and tested on a simulating aerobatic helicopter stand. The model received a positive response from the pilots.

In the future, the model will adapt to the proposed on-board indicator of the helicopter.

The authors:

K.A. Senkov. S.S. Andrienko.

Claims (1)

The format of a helicopter flight-navigation indicator, containing a horizon, indicators of altitude-speed, positional and navigation parameters and a field of signal messages, characterized in that in addition to the traditional navigation indicator, a special flight-navigation and positional-speed indicator for the mode is formed on it "hovering", containing a circular, rotating scale of courses, azimuths, directions of the directional velocity vector, respectively, true, or magnetic; on the scale are located and moving, depending on the information received from the calculator, indices of the given course, course angle of the selected geo-point, bearing of the helicopter; positional strips showing, relative to the X and Z axes of the helicopter, the location of the geo-point selected in advance or fixed at the time of its passage; the zero point located in the center of the indicator, from which the deviations of the positional bars and the indicator of the lateral, longitudinal, components of the ground speed are measured in the form of white "columns" of variable length, depending on the value of the components of the ground speed; an index of the longitudinal and lateral components of the ground speed, in the form of white "columns" growing up left-right and back-and-forth relative to the center of the position-speed indicator, depending on the current values of the components of the ground speed, the path vector, in the form of a thin blue line color of variable length, depending on the value of ground speed, rotating from the center relative to the course scale of the navigation indicator; true and magnetic course counters located above the navigation indicator to the left and right of it; ground speed counter located in the middle and to the left of the navigation indicator; range counter located under the track speed counter; screw pitch counter located in the middle and to the right of the navigation indicator; radio height counter located under the screw pitch counter.