RU58211U1 - INTEGRATED RESERVE SYSTEM FOR PLANES AND HELICOPTERS - Google Patents

Abstract

The integrated backup instrument system for aircraft and helicopters refers to the backup measurement and display systems that provide piloting in the event of a failure of the main flight and navigation systems. The integrated backup instrument system for aircraft and helicopters (hereinafter referred to as the Aircraft), made in the form of a separate unit, contains an LCD indicator, full and static pressure sensors connected by pipelines with airborne probes of full and static pressure, electronic means for calculating total and static pressure , a spatial orientation module with autonomous inertial measurement sensors calculating the spatial position of the aircraft (pitch angle, roll angle), electronic means for calculating transmitting data on the instrument speed, barometric altitude, vertical speed and the number M, means for receiving information from the on-board navigation system BINS, information from the on-board magnetic probe, radio and braking temperature receiver, means for calculating the spatial position and course taking into account the correction according to the BINS , means for calculating the course with correction according to the information of the magnetic probe and data from the radio means, as well as electronic means for converting the corrected signals to the desired shape and displaying them on the indicator screen and on-board systems.

Description

The inventive system relates to backup measurement and display systems, providing piloting of aircraft and helicopters (hereinafter - aircraft) in the event of a failure of the main flight and navigation systems.

Usually aerobatic indicators are located on the dashboard of a modern aircraft, displaying the spatial position of the aircraft, data on altitude and speed according to data from the main airborne systems. The panel also has a backup flight horizon, a backup altimeter, a backup speed indicator and a backup variometer, which are not part of the main display system, which are necessary to display data on spatial position, altitude, instrument speed and vertical speed. These devices work autonomously without interaction with other systems and sensors. In case of failure of the main measurement and display system, the pilot can use the information necessary for piloting from these backup devices and continue the flight to the nearest landing point.

Also known patent "Combined backup devices for aircraft" [1]. This invention relates to backup devices that provide information on three basic parameters for an airplane pilot, namely: information about instrumental speed, which is calculated based on a measurement of dynamic pressure, on the barometric altitude of an airplane, calculated on the basis of measurement

static pressure, and about the spatial position of the aircraft, calculated on the basis of data from autonomous inertial sensors located in the spatial orientation module. Structurally, “Combined backup devices for aircraft” are made in the form of a separate unit.

In particular, it provides for the replacement of three mechanical backup pointers with electronic combined devices, the display of which is made on LCD crystals, the screen of which displays three main parameters that correspond to the flight mode, namely: altitude, instrument speed and spatial position of the aircraft. The backup device system has its own inertial means for determining the spatial position of the aircraft and its own measuring tools for measuring static and dynamic pressures, connected to airborne pneumatic measuring probes and electronic means for calculating altitude-speed flight parameters of the aircraft.

Instrument speed is measured in the usual way by calculating from dynamic pressure, which is the difference between total pressure and static pressure.

The barometric altitude measured by the backup system is also calculated by the conventional method based on static pressure using the Laplace equation for a standard atmosphere.

The object of the invention are combined backup devices for an aircraft, measuring and indicating the instrument speed, barometric altitude of the aircraft and the spatial position of the aircraft, and accordingly containing:

- two pneumatic inputs for measuring pressure: one for full pressure connected to the full pressure probe, which is located on board the aircraft, and the other for static pressure, connected to the static pressure probe;

- an electronic pressure sensor connected to the pneumatic input of the total pressure;

- an electronic sensor connected to a pneumatic inlet of static pressure;

- a module for measuring the spatial position of the aircraft, containing inertial sensors;

- an electronic computing device that calculates the instrument speed based on the total and static pressures, the barometric height based on the measured static pressure, the number M based on the ratio of dynamic pressure to static, the spatial position of the aircraft (pitch, roll angles) based on information from inertial sensors.

- electronic devices (calculator) to provide an indication of the instrument speed, barometric height and spatial position of the aircraft.

Combined backup devices [1] are an elongated single-block chassis, which houses pressure measuring sensors, an inertial sensor module, a computer, and a liquid crystal display that occupies the front of the panel.

The disadvantages of these backup devices include the limited information displayed on the indicator that is necessary to ensure flight safety, for example, the lack of heading information, as well as insufficient accuracy in measuring spatial orientation parameters due to insufficient accuracy of gyroscopic sensors and linear acceleration sensors built into the device.

The task to which the claimed technical solution is directed is to create a backup instrument system with advanced functionality.

The technical result is expressed in increasing the accuracy of the calculated flight and navigation parameters, as well as increasing the amount of information displayed on the indicator screen.

The solution to this problem is carried out by the fact that the inventive measuring system of backup devices for aircraft and helicopters is made in the form of a separate unit. The system contains an LCD indicator, sensors for total and static pressure, connected by pipelines to airborne probes for full and static pressure, a calculator for calculating the total and static pressures, a spatial orientation module with gyrometric and accelerometer inertial sensors, the computing tools of which calculate the spatial position of the aircraft (pitch angle, roll angle). The backup instrument system also includes a calculator for calculating and displaying on the indicator data on speed, barometric altitude, vertical speed and the number M. The system further comprises an input / output device for receiving information from the SINS navigation system, information from the onboard magnetic probe, radio and the receiver braking temperature.

The system also contains means for calculating the spatial position and course taking into account the correction according to the data from the SINS, means for calculating the course with correction according to the information of the magnetic probe and according to data from the radio, electronic means for indicating the calculated aerometric parameters (speed, altitude, vertical speed, numbers M), spatial position parameters (roll angles and pitch angles), as well as electronic means for outputting all corrected displayed parameters to the airborne systems.

On the front panel of the device there is a liquid crystal screen and control devices containing two multifunctional racks, controls: brightness adjustment of the LCD screen, an external sensor

screen brightness. Multifunctional kremalyera provide input barocorrection, a given height, a given course, a given speed, programming the flight route.

A distinctive feature of the claimed system is that the backup instrument system contains electronic means for calculating the corrected air parameters of the aircraft by combining the information of the air parameters calculated from the data from the static and total pressure sensors built into the backup system with information from the main air signal system (height, speed, M number, vertical speed) and the output of adjusted data to the LCD indicator and to the on-board systems.

Another distinctive feature of the inventive backup system is that it contains means for calculating the adjusted parameters of the spatial position of the aircraft by combining information about the spatial position of the aircraft from the spatial orientation module containing inertial sensors integrated in the backup system with information from the main navigation system, data from magnetic probe and the issuance of corrected data to a computer, which converts the received information into the desired form y and transfers it to the LCD display and on-board systems.

Another distinctive feature of the system is that the system contains a liquid crystal screen on the front panel, on the frame of which there are controls containing two multifunctional racks, a control element for adjusting the brightness of the LCD screen, and an ambient light sensor. Multifunctional kremalyeram provide input barocorrection, a given height, a given course, a given speed and programming of the flight plan.

The system also provides for the calculation of the gyromagnetic course and its indication, as well as interaction with the landing system and radio beacons.

The essence of the proposed technical solution is illustrated by the drawing, which indicates:

1 - full pressure sensor DD p _p ;

2 - static pressure sensor DD r _article ;

3 - a device for processing and converting UOPS signals;

4 - the first code line of communication CLS;

5 - computer B;

6 - module spatial orientation of the MPO;

7 - the second code line of communication CLS;

8 - input-output device;

9 - highway information exchange MIO;

10 - liquid crystal display LCD;

11 - device control brightness UUY;

12 - control device operating modes of the CID.

The inventive backup system operates as follows. During the flight, the signals from the sensors of the total and static pressures 1 and 2 built into the system and the signal from the on-board sensor of the flow inhibition temperature (not included in the system) are fed to the OOPS 3 signal processing and conversion device. The OOPS device processes these signals, calculates the total P _p and static pressure P _st and flow inhibition temperature (T _p ), and also corrects signals from pressure sensors depending on the ambient temperature. The corrected pressure signals (P _st , R _p ) and the signal T _p from the UOPS via the first code line 4 (RS-232 channel) are sent to the calculator 5. The calculator 5 calculates based on the received signals from the UOPS 3 unit

according to known dependencies, the main flight parameters: instrumental speed V _CR , true speed V _East , absolute height H _abs , relative height H _rel , vertical speed V _in , outdoor temperature T _article , number M.

Using gyroscopic sensors, linear acceleration sensors, and electronic computing tools located in the spatial orientation module MPO 6, the main parameters of the aircraft’s position along the X, Y, Z axes are calculated - the angle of heel, pitch angle, gyroscopic course. Data on the spatial position of the aircraft with MPO on the second code link 7 (channel RS-232) are transmitted to the calculator 5.

Data from the on-board navigation system BINS, on-board magnetic probe, radio is received by the air-blast device I / O 8 and according to the instructions of the controller of the calculator 5 via the data exchange 9 are fed to the calculator, which converts the received signals into the desired form and transmits them to the module MPO 6. MPO contains computing tools with which, depending on the priority, the spatial position of the aircraft is adjusted based on the received data from the on-board systems. The signals of the corrected parameters of the spatial position from the MPO 6 are supplied to the calculator 5, which converts the received signals and the signals of the calculated flight parameters (V _CR , V _IST , N _abs , N _rel , V _in , T _article , number M) into a form convenient for indication , and issues them on the LCD 10.

The SINS signals are used in the backup system to correct the basic inertial parameters of the aircraft, calculated by autonomous gyroscopic sensors and linear acceleration sensors located in the MPO module 6. When the SINS system fails, the backup system corrects the calculated navigation parameters using information from the magnetic probe.

The backup system operates in the following modes:

- offline mode,

- mode with correction from SINS.

In standalone mode, the system at the expense of internal means measures, calculates and displays instrument speed, true speed, barometric altitude, vertical speed, M number, roll and pitch angles, and magnetic heading.

In the mode with correction from the SINS, the system measures, calculates the instrument speed, true speed, barometric height, vertical speed, number M, roll angles, pitch and performs inertial parameter correction using data from the SINS system, converts the calculated and adjusted parameters to the desired shape and displays them on the LCD screen. In this mode, instead of a magnetic heading, the system displays a gyromagnetic heading.

The system has the ability to interact with the radio system of near and far navigation and carry out radio navigation, while the following is displayed on the LCD screen:

- direction to the lighthouses,

- range to lighthouses.

The system also has the ability to interact with driven radio beacons and to land on a glide path.

In addition, the system allows the piloting of an aircraft along a given route using the planned intermediate points of the PPM route.

The system also has the ability to use the calculator to calculate the corrected spatial position and the corrected gyromagnetic course using data from the spatial orientation module, data from the on-board navigation system and the magnetic probe, as well as calculate the corrected aerometric data (altitude, speed, vertical

speed) according to the data from full and static pressure sensors and data from inertial sensors of the spatial orientation module, converting the corrected aerometric data and the corrected spatial position and course data to the desired shape and transferring them via the information exchange line to the LCD indicator and via input-output devices in on-board systems.

The backup system is designed as a separate unit. An LCD indicator is located on the front panel, and full and static pressure sensors are located on the rear panel. In the middle part there is a spatial orientation module, a power supply and a computer.

Pressure sensors, sensors for measuring inertial parameters are made in microminiature design, which allows to drastically reduce the dimensions of the system.

The electronic means of the system are based on modern elements. So the calculator is built on the basis of a processor like SMP5PC-266 f. Digital Logic;

signal processing and conversion device - based on the ATmega 128-16 AI microcontroller f. Atmel;

input-output device - based on FPGA ASEEH EP1K100Q 1208-2 and RAM (NVRAM) F. Aitera;

kremalyare - on the basis of optical kremalyer 62S11-H9-P f.Grayhill.

The system contains firmware.

Information sources:

1. US patent No. 6564628, IPC G 01 C 21/00, publ. May 20, 2003

Claims (3)

1. An integrated system of backup devices for airplanes and helicopters, made in the form of a separate unit, containing an LCD indicator, full and static pressure sensors connected by pipelines with airborne probes of full and static pressure, a spatial orientation module with autonomous inertial measurement sensors and electronic computing tools connected to the calculator, characterized in that it contains a signal processing and conversion device, the inputs of which are connected to the outputs of the sensors through full and static pressures and with an on-board brake temperature sensor, and the output is with a computer, an input-output device connected via an information exchange line to the computer, and on the front panel of the system there is an LCD indicator screen, on the frame of which controls containing the device are installed control the brightness of the LCD screen connected to the LCD indicator, and a device for controlling the operating modes of the system connected to the calculator. 2. The system according to claim 1, characterized in that the input-output device comprises an adapter for receiving information from the airborne signal system. 3. The system according to claim 1 or 2, characterized in that the input-output device contains an adapter for receiving information from the on-board magnetic probe.