RU2223542C2 - Active on-board flight-safety system - Google Patents

Abstract

FIELD: measurement technology. SUBSTANCE: proposed system designed for monitoring, control, and rescue of flying vehicle and crew has analysis and control unit, on-board digital computer, data acquisition and reception unit, electronic computer, unit of functional meters, biomedical parameter metering unit, on-board electronic equipment monitoring system, general-purpose equipment monitoring system, unit of mass meters, output unit, remote-control system, system control console, optical-sighting navigation system, fire alarm system, and unit of fuel level sensors. EFFECT: enlarged functional capabilities, enhanced operating reliability. 1 cl, 1 dwg

Description

 The proposed invention relates to measuring equipment, namely to control systems, control and rescue aircraft and crew.

 The closest in technical essence to the claimed device is, selected as the closest analogue, a device for monitoring and controlling the functional and physiological state of the pilot in flight, containing blocks of functional meters and measurements of biomedical parameters connected through an information reception and collection unit with analysis and control units, to which is connected to the output unit (US Pat. RF 2170953, class IPC G 09 B 9/10, A 61 V 5/16, publ. July 20, 2001, BI 20).

 The disadvantage of this device is the limited number of systems that ensure the rescue of the aircraft (LA), which can lead to its death, as well as people on board.

 The technical task of the proposed invention is to expand the functionality of the device and increase the reliability of its operation.

 The task is achieved by the fact that an electronic computer and connected to it are connected to the on-board active flight safety system, containing blocks of functional meters and measurements of biomedical parameters, connected via an information reception and collection unit to the analysis and control unit to which the output unit is connected on-board digital computer, system control panel, optical-sighting navigation system, fire alarm system associated with an electronic computer The first remote control system connected to the information reception and collection unit is the on-board electronic equipment control system, the general-purpose equipment control system and the mass meter system, the fuel level sensor system connected to the optical-sighting navigation complex and the electronic computer.

 Moreover, the information reception and collection unit and the output unit are connected to the electronic computer and the on-board digital computer, and the optical sighting navigation system and the fire alarm system are connected to the automatic control system included in the output unit, the remote control system being connected to remote control system.

 The proposed invention is illustrated using the schemes shown in FIG. 1.

 In FIG. 1 shows a diagram of an on-board active flight safety system (hereinafter referred to as the system), comprising an analysis and control unit (BAU) 1, an on-board digital computer (BCM) 2, a data acquisition and reception unit (BSPI) 3, and an electronic computer (computer) 4 , a block of functional meters (BFI) 5, a block for measuring biomedical parameters (BIBP) 6, a system for monitoring on-board electronic equipment (SCBREO) 7, a system for monitoring general-purpose equipment (UNSC) 8, a system of mass meters (SIM) 9, an output block (WB ) 10, the system is remote th control (CDS) 11, the remote control system (CCP) 12, optical sighting navigation system (OPNK) 13, the fire alarm system (BSC) 14, system fuel level sensors (contraction) 15.

 The device operates as follows.

 The system is included in the work on a command from ICP 12, before the flight, the integrity and operability of the electrical and control and measuring circuits, the state of the on-board electronic equipment, general-purpose equipment, and the functioning of all components of the system are checked. Information from SIM 12 on BAU 1, BTsVM 2 and computer 4 receives information about the pre-flight mass of the aircraft, the location of the center of gravity of the aircraft. SIM 12 can be made in the form of pressure sensors installed in the landing gear of the aircraft.

 During the flight, signals from BFI 5, BIBP b, SKBREO 7, and UNSC 8 through BSPI 3 are fed to BAU 1 and BTsVM 2, where they are analyzed by comparison with the maximum permissible values. When the deviation of the data coming from the measuring systems 5, 7 and 8 from the data taken as the basis, with the permissible deviations of the data coming from the unit 6, the BAU 1, the BCVM 2 and the computer 4 generate and transmit signals to the WB 10 for transmitting information to the crew about the threat. The crew must in a limited period of time eliminate the emergency situation. In this case, BAU 1, BTsVM 2 and computer 4 cancel the given command and the crew continues to fly normally.

In case of unacceptable deviation of the data coming from the BIBP 6, in comparison with the data taken as a basis, information on unacceptable deviations will be received on BAU 1, BTsVM 2 and computer 4. Based on the results of processing the data received from BFI 5, SKBREO 7 and UNSC 8, BAU 1, BTsVM 2 and EVM 4 decide on the forced return of the aircraft to normal flight mode. Also, BAU 1, BTsVM 2 and computer 4 form and transmit the following commands to WB 10:
- to transfer aircraft to safe flight mode;
- on the inclusion of an automatic control system;
- the inclusion of a crew recovery system, if possible;
- the inclusion of aircraft safety systems in case of an external threat.

 If, according to the results of processing data from BIBP 6, it turns out that the crew is able to control the situation and control the aircraft, BAU 1, BTsVM 2 and computer 4 decide to form and transmit commands to VB 10 according to the results of processing data received from BFI 5, SKBREO 7 and UNSC 8. After that, one of the crew members through ICP 12 cancels all the commands of the system and takes control.

 If during the flight some components of general-purpose equipment, avionics, or the crew fails to adequately control the flight, BAU 1 or the dispatcher from the command post located on the ground blocks SDC 12 through the CDS 11, after which access to the system for the crew will be closed, and then flight control will be carried out automatically by the commands of BAU 1 or through the CDS 11.

 During the flight, OPNK 13 receives information from the SDUT 15 on the amount of fuel remaining in the fuel tanks, and through computer 4 gives it to the crew, in addition, it constantly calculates the conditions for ensuring the return of the aircraft to the nearest airfield based on the remaining fuel. With a critical fuel balance, OPNK 13 instructs the crew to land the aircraft at the nearest airfield. If OPNK 13 receives information from computer 4 about the loss of crew performance or an emergency, then it generates and issues to the automatic control system the information necessary to ensure the landing of the aircraft at the nearest airfield. If, with the maximum fuel remaining necessary for landing at the nearest airfield, the crew does not start landing, OPNK 13 issues computer commands 4 to block manual control of the aircraft and stop issuing all commands to the crew, and the automatic control system, which is part of WB 10, performs landing at the nearest airfield.

MSP 14 detects overheating or fire in the engine compartment and, if detected, performs the following functions:
- gives a signal "fire" on the computer 4, to provide information to the crew and to turn on the fire extinguishing system;
- generates and issues to the automatic control system, which is part of WB 10, commands to turn off the engine.

 If during the flight BAU 1 and BTsVM 2 issue different commands to the computer 4, then the computer 4 prohibits the issuance of all commands to the VB 10 from the BAU 1 and the BTsVM 2, sends commands to the BAU 1 and BTsVM 2 to enable testing programs, and further flight control takes to myself. After testing is completed, computer 4 allows the transfer of all commands from a system capable of operating in normal mode (BAU 1 or BTsVM 2). If, as a result of testing, it turns out that both systems (BAU 1 and BTsVM 2) are faulty, the flight will take place according to commands received from computer 4.

 Thus, by introducing an on-board digital computer, an electronic computer, a unit for comparing and issuing commands and a remote control system to the on-board active flight safety system, the accuracy of the commands received at the output unit increases, and with it the reliability of the device itself. And due to the introduction of a control panel, an optical-sighting navigation system, a fire alarm system and control systems for avionics and general equipment, the device’s functionality is expanding.

Claims (1)

On-board active flight safety system, containing blocks of functional meters and biomedical parameters measurements, connected through an information reception and collection unit to an analysis and control unit, to which an output unit is connected, characterized in that an electronic computing unit connected to the analysis and control unit is connected to it the machine and the on-board digital computer connected to it, the system control panel, the optical-sighting navigation complex, the fire alarm system associated with the electric a digital computer, a remote control system connected to an information reception and collection unit, an onboard electronic equipment monitoring system, a general purpose equipment system and a mass meter system connected to an optical aiming navigation complex and an electronic computer, a fuel level sensor system, the unit receiving and collecting information and the output unit are connected to an electronic computer and an on-board digital computer, and the optical-aiming navigation Complex insulating and fire alarm system are connected to a part of the output unit automatic control system, the remote control system associated with the system control panel.