Power supply system of aircraft flight data recording system

Abstract

The invention belongs to the technical field of avionics design of aviation technology, and relates to a power supply system of an aircraft flight data recording system, which is provided with a relay and an associated control circuit, and ensures that the flight data recording system can start to work before the time of required data recording by associating other control circuits, so that the flight data recording system can work more accurately. Working is stopped after recording is not needed, the accuracy, operability and convenience of power-on and power-off time of the system are improved, and meanwhile other bad influences cannot be caused.

Description

Technical Field

[0001] The invention belongs to the field of aviation technology and avionics design technology, and relates to a power supply system for an aircraft flight data recording system. Background Art

[0002] The flight data recorder is the main real-time objective recording system on the aircraft. It records important flight data of various onboard equipment and engines, as well as pilot voice and aircraft environment audio data when the aircraft is powered on and in flight. In daily situations, ground crew can fully understand the working status, fault conditions, pilot driving skills and operating status of various onboard equipment and engines when the aircraft is powered on and in flight by analyzing the recorded data; after a flight accident occurs, experts can restore the truth of the accident by analyzing the data before and after the accident recorded by the flight data recorder. Therefore, the flight data recorder plays a very important role in flight situation analysis, flight fault troubleshooting, flight accident analysis and daily ground maintenance.

[0003] At present, there are usually two ways to power on the flight data recording system of existing aircraft: one is to set up a special ground power switch; the other is not to set up a switch and only associate it with the "onboard-ground" power switch. The two power-on methods have different power-on times. The first method can meet the needs of manual connection and disconnection of the ground power of the flight data recording system at any time. The disadvantage is that if the relevant personnel forget to turn on the switch before the flight, the flight data will be missed. If the aircraft fails or an accident occurs, there will be no objective data for analysis; if the relevant personnel forget to disconnect the switch after the flight, the flight data recording system is directly connected to the 28V DC emergency bus, and the DC emergency bus is powered by the aircraft battery when there is no engine power supply and ground power supply vehicle power supply, which may exhaust the aircraft battery. The second method is to not set a switch, but only associate it with the "on-board-ground" power switch. That is, by setting an associated circuit, when the "on-board-ground" power switch of the aircraft is turned on or off, the power supply of the flight data recording system can be connected or disconnected. The advantage is that the "on-board-ground" power switch must be operated to the "on-board" position before the aircraft takes off, so that the power supply from the ground power supply vehicle can be switched to the engine power supply. Therefore, when the aircraft takes off and flies normally, there is no situation of forgetting to turn on the switch, which ensures the data recording during the flight. The disadvantage is that the "on-board-ground" power switch is switched to the "on-board" state after the first engine starts normally, and there is a situation where the data of the first engine is missed. However, engine data is very important data, and it is necessary to record it throughout the process. Summary of the invention

[0004] The present invention provides a power supply system for an aircraft flight data recording system, which solves the disadvantage that the power-on time of the existing flight data recording system does not match the required power-on time, and provides a method for completing the associated forced power-on of the flight data recording system before the first engine is started, and forcing the power to be cut off after the aircraft control surface lock is locked.

[0005] The present invention provides a power supply system for an aircraft flight data recording system, comprising: a first relay and a second relay;

[0006] A first end of the control circuit of the second relay is grounded, and a second end is connected to the control circuit of the aircraft's control surface lock; a first end of the first switch circuit is grounded, and a second end is connected to the first end of the control circuit of the first relay;

[0007] The second end of the control circuit of the first relay and the first end of the switch circuit of the first relay are connected to the aircraft's onboard power supply through a fuse; the second end of the switch circuit of the first relay is connected to the flight data recording system;

[0008] Before the first engine of the aircraft is started, when the rudder lock control circuit unlocks the rudder, the control circuit of the second relay is connected, and the switch circuit controlling the second relay is closed, causing the control circuit of the first relay to be connected, and the switch circuit controlling the first relay is closed, and the flight data recording system is powered by the onboard power supply; when the flight is completed and the aircraft is parked on the ground, when the rudder lock control circuit locks the rudder, the control circuit of the second relay is disconnected, and the switch circuit controlling the second relay is disconnected, causing the control circuit of the first relay to be disconnected, and then the switch circuit controlling the first relay is disconnected, and the onboard power supply stops supplying power to the flight data recording system.

[0009] Optionally, it also includes: a switch; the switch model is MJK-2;

[0010] The first end of the switch is connected to the second end of the first relay control loop, and the second end of the switch is grounded.

[0011] Optional, fuse model is TB-5.

[0012] Optionally, the first relay model is 2JT5-3.

[0013] Optionally, the second relay model is 2JGXM-2.

[0014] Optionally, the onboard power supply is a 28V DC emergency busbar.

[0015] Optionally, the second end of the control circuit of the second relay is connected to the control circuit of the aircraft's control surface lock;

[0016] When the control circuit of the rudder lock is energized, the control circuit of the second relay is energized.

[0017] Optionally, a first end of a second switch circuit of the second relay is connected to a start button, and a second end is connected to a start circuit of a first engine of the aircraft;

[0018] When the control circuit of the rudder lock is energized, the control circuit of the second relay is energized, the start button is turned on, and the first engine starts.

[0019] Compared with the existing methods, the beneficial effects of the present invention are as follows: unlocking the rudder lock is an operation step that must be completed before the engine is started. By associating the rudder lock unlocking control circuit, it is ensured that the flight data recording system has been working before the first engine is started, and can normally record the data of the engine working status and other equipment data during the process, providing an important basis for ground maintenance and troubleshooting for ground staff; when the rudder lock is locked, the flight data recording system stops working, and will not cause the flight data recording system to exhaust the battery power through the DC emergency bus. At the same time, a recorder ground inspection switch is set. When the aircraft is only powered on for ground inspection, the ground staff can turn on and off the switch as needed to complete the ground power inspection of the flight data recording system. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 Flight data recording system power supply circuit designed for existing solutions. DETAILED DESCRIPTION

[0021] The present invention will be further described in detail below in conjunction with the accompanying drawings.

[0022] like Figure 1 As shown, the present invention provides a power supply system for an aircraft flight data recording system, comprising: a first relay and a second relay;

[0023] A first end of the control circuit of the second relay is grounded, and a second end is connected to the control circuit of the aircraft's control surface lock; a first end of the first switch circuit is grounded, and a second end is connected to the first end of the control circuit of the first relay;

[0024] The second end of the control circuit of the first relay and the first end of the switch circuit of the first relay are connected to the aircraft's onboard power supply through a fuse; the second end of the switch circuit of the first relay is connected to the flight data recording system;

[0025] Before the first engine of the aircraft is started, when the rudder lock control circuit unlocks the rudder, the control circuit of the second relay is connected, and the switch circuit controlling the second relay is closed, causing the control circuit of the first relay to be connected, and the switch circuit controlling the first relay is closed, and the flight data recording system is powered by the onboard power supply; when the flight is completed and the aircraft is parked on the ground, when the rudder lock control circuit locks the rudder, the control circuit of the second relay is disconnected, and the switch circuit controlling the second relay is disconnected, causing the control circuit of the first relay to be disconnected, and then the switch circuit controlling the first relay is disconnected, and the onboard power supply stops supplying power to the flight data recording system.

[0026] Optionally, it also includes: a switch; the switch model is MJK-2;

[0027] The first end of the switch is connected to the second end of the first relay control loop, and the second end of the switch is grounded.

[0028] Optionally, the fuse model is TB-5, the first relay model is 2JT5-3, and the second relay model is 2JGXM-2.

[0029] Optionally, the onboard power supply is a 28V DC emergency busbar.

[0030] Optionally, the second end of the control circuit of the second relay is connected to the control circuit of the aircraft's control surface lock;

[0031] When the control circuit of the rudder lock is energized, the control circuit of the second relay is energized.

[0032] Optionally, a first end of a second switch circuit of the second relay is connected to a start button, and a second end is connected to a start circuit of a first engine of the aircraft;

[0033] When the control circuit of the rudder lock is energized, the control circuit of the second relay is energized, the start button is turned on, and the first engine starts.

[0034] The present invention arranges two relays (relay 1 and rudder lock disconnect engine start interlock relay) and one control switch (recorder ground inspection switch) on the aircraft, the A end of the coil of relay 1 is connected to an on-board 28V DC emergency busbar power supply, and at the same time, a circuit is connected in parallel to the static contact 3 of the relay 1, and the static contact 2 is connected to the power input plug hole of the flight data recording system. The B end of the coil of relay 1 is connected to two circuits, one circuit is connected to the static contact 5 of the rudder lock disconnect engine start interlock relay, and the static contact 6 is grounded, and the other circuit is connected to the static contact 7 of the recorder ground inspection switch, and the static contact 8 is grounded. When the aircraft rudder lock is unlocked, the rudder lock disconnects the engine start interlock relay and works. The relay coil attracts the moving contact 4 to the static contact 6, and the circuit is grounded. At this time, the 28V power supply circuit is connected, and the relay 1 coil attracts the switch moving contact 1 to the static contact 3. The flight data recording system power is connected and the flight data recording system starts working; when the rudder lock is locked, the rudder lock disconnects the engine start interlock relay and stops working, the moving contact 4 is disconnected from the static contact 6, the power supply circuit is disconnected, and the flight data recording system stops working.

[0035] A power supply system for an aircraft flight data recorder system, which controls the power on and off of the flight data recorder system by setting relays, switches and associating other control circuits and utilizing the operation of the associated control circuits. Specifically:

[0036] like Figure 1 As shown, a relay 1 control circuit and a circuit of an associated rudder lock disconnecting engine start interlock relay are provided on the aircraft. The characteristic of the rudder lock disconnecting engine start interlock relay is that the rudder lock must be unlocked before the engine is started, and this time coincides with the time when the flight data recording system is required to be powered on.

[0037] The A end of the coil of relay 1 is connected to a 28V DC emergency bus power supply on the aircraft, and at the same time, a circuit is connected in parallel to the static contact 3 of relay 1, and the static contact 2 of relay 1 is connected to the power input plug hole of the flight data recording system. The B end of the coil of relay 1 is connected to a circuit to the static contact 5 of the rudder lock that disconnects the engine start interlock relay, and the static contact 6 of the relay is grounded; the B end of the coil of relay 1 is connected to another circuit to the static contact 7 of the recorder ground inspection switch, and the static contact 8 is grounded.

[0038] When the aircraft engine is started or before the aircraft flies, when the aircraft rudder lock is unlocked, the rudder lock disconnects the engine start interlock relay to work, and the relay coil pulls the moving contact 4 to the static contact 6, and the circuit is grounded. At this time, the 28V power supply circuit is connected, and the relay 1 coil pulls the switch moving contact 1 to the static contact 3, and the flight data recording system power is connected, and the flight data recording system starts to work. At the same time, the relay coil also pulls the moving contact 1 to the static contact 3, and the first engine start circuit is connected. When the start button is pressed, the circuit is connected, and the first engine starts at this time, ensuring that the flight data recording system starts to work before the first engine starts, and can completely record the data starting from the first engine start; when the aircraft engine is shut down or the aircraft is parked after the flight, when the rudder lock is locked, the rudder lock disconnects the engine start interlock relay to stop working, the moving contact 4 is disconnected from the static contact 6, the power supply circuit is disconnected, and the flight data recording system stops working. When the aircraft is powered on for inspection on the ground only, the recorder ground inspection switch is turned on, the flight data recorder system power is turned on, and the flight data recorder system starts working; after the ground power inspection is completed, the recorder ground inspection switch is turned off, the flight data recorder system power is disconnected, and the flight data recorder system stops working.

Claims

1. A power supply system for an aircraft flight data recording system, characterized in that: include: a first relay and a second relay; A first end of the control circuit of the second relay is grounded, and a second end is connected to the control circuit of the aircraft's control surface lock; a first end of the first switch circuit is grounded, and a second end is connected to the first end of the control circuit of the first relay; The second end of the control circuit of the first relay and the first end of the switch circuit of the first relay are connected to the aircraft's onboard power supply through a fuse; the second end of the switch circuit of the first relay is connected to the flight data recording system; Before the first engine of the aircraft is started, when the rudder lock control circuit unlocks the rudder, the control circuit of the second relay is connected, and the switch circuit controlling the second relay is closed, causing the control circuit of the first relay to be connected, and the switch circuit controlling the first relay is closed, and the flight data recording system is powered by the onboard power supply; when the flight is completed and the aircraft is parked on the ground, when the rudder lock control circuit locks the rudder, the control circuit of the second relay is disconnected, and the switch circuit controlling the second relay is disconnected, causing the control circuit of the first relay to be disconnected, and then the switch circuit controlling the first relay is disconnected, and the onboard power supply stops supplying power to the flight data recording system.

2. The power supply system of the aircraft flight data recording system according to claim 1, characterized in that: Also includes: switch; The switch model is MJK-2; The first end of the switch is connected to the second end of the first relay control loop, and the second end of the switch is grounded.

3. The power supply system of the aircraft flight data recording system according to claim 1, characterized in that: The fuse model is TB-5.

4. The power supply system of the aircraft flight data recording system according to claim 1, characterized in that: The first relay model is 2JT5-3.

5. The power supply system of the aircraft flight data recording system according to claim 1, characterized in that: The second relay model is 2JGXM-2.

6. The power supply system of the aircraft flight data recording system according to claim 1, characterized in that: The onboard power supply is a 28V DC emergency bus.

7. The power supply system of the aircraft flight data recording system according to claim 1, characterized in that: The second end of the control circuit of the second relay is connected to the control circuit of the aircraft's control surface lock; When the control circuit of the rudder lock is energized, the control circuit of the second relay is energized.

8. The power supply system of the aircraft flight data recording system according to claim 1, characterized in that: A first end of a second switch circuit of the second relay is connected to a start button, and a second end is connected to a start circuit of a first engine of the aircraft; When the control circuit of the rudder lock is energized, the control circuit of the second relay is energized, the start button is turned on, and the first engine starts.

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