KR101751387B1 - Apparatus for controlling and power supply for instrumentation of aircraft - Google Patents

Apparatus for controlling and power supply for instrumentation of aircraft Download PDF

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Publication number
KR101751387B1
KR101751387B1 KR1020150173714A KR20150173714A KR101751387B1 KR 101751387 B1 KR101751387 B1 KR 101751387B1 KR 1020150173714 A KR1020150173714 A KR 1020150173714A KR 20150173714 A KR20150173714 A KR 20150173714A KR 101751387 B1 KR101751387 B1 KR 101751387B1
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South Korea
Prior art keywords
aircraft
relay
power
measurement equipment
measurement
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KR1020150173714A
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Korean (ko)
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KR20170067259A (en
Inventor
노병찬
강경우
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한국항공우주산업 주식회사
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Priority to KR1020150173714A priority Critical patent/KR101751387B1/en
Publication of KR20170067259A publication Critical patent/KR20170067259A/en
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    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J9/00—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting
    • H02J9/04—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source
    • H02J9/06—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source with automatic change-over, e.g. UPS systems
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D41/00—Power installations for auxiliary purposes
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J1/00—Circuit arrangements for dc mains or dc distribution networks
    • H02J1/10—Parallel operation of dc sources
    • H02J1/102—Parallel operation of dc sources being switching converters
    • H02J2009/068—

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  • Engineering & Computer Science (AREA)
  • Power Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Business, Economics & Management (AREA)
  • Emergency Management (AREA)
  • Testing Or Calibration Of Command Recording Devices (AREA)

Abstract

The present invention relates to a power supply and control apparatus for an aircraft measurement instrument, and more particularly, to an apparatus and method for monitoring an aircraft, And controlling power supplied from the battery when the power of the aircraft to the measurement instrument during flight is cut off, thereby enabling measurement data acquisition in an emergency situation.

Description

BACKGROUND OF THE INVENTION 1. Field of the Invention [0001] The present invention relates to a power supply and control apparatus for an aircraft measurement instrument,

The present invention relates to a power supply and control apparatus for an aircraft measurement instrument, and more particularly, to an apparatus and method for monitoring an aircraft, And controlling power supplied from the battery when the power of the aircraft to the measurement instrument during flight is cut off, thereby enabling measurement data acquisition in an emergency situation.

In general, the aircraft under development is equipped with measurement sensors (temperature, pressure, voltage, etc.) at certain positions of the aircraft in order to verify the design details and performance, and to measure, Respectively. The metering device is powered by an aircraft generator during flight of the aircraft.

In this connection, a technology utilizing measurement equipment for aircraft performance flight test has been disclosed in Korean Patent Laid-Open No. 10-2014-0060023 ("Aircraft Performance Flight Test Standardization Apparatus and Control Method").

On the other hand, in case the generator that supplies power to the various devices of the aircraft does not operate normally during the flight of the aircraft, the aircraft is equipped with an auxiliary generator which can supply power only to the core devices of the aircraft and enable safe landing .

In the case of measurement equipment, it is installed only during the verification of the development airplane and is not connected to the auxiliary generator, so that if the generator of the aircraft fails, the power supply is interrupted and does not operate.

However, as described above, the measurement equipment is designed for the design and performance verification of the aircraft. In order to identify the cause of the failure of the generator or whether there is a problem occurring in another part, measurement data is acquired from the measurement equipment in an emergency .

Nevertheless, up to now, there is no additional auxiliary means for supplying power to the measuring equipment in the emergency situation. For the reason as described above, in order to utilize the measuring data of the measuring equipment, power is supplied to the measuring equipment in an emergency, A device that can do this is required.

Korean Patent Laid-Open No. 10-2014-0060023 ("Aircraft Performance Flight Test Standardization Apparatus and Its Control Method")

SUMMARY OF THE INVENTION The present invention has been made in order to solve the above-mentioned problems, and it is an object of the present invention to provide an air conditioner capable of acquiring measurement data and utilizing the measurement data, And to provide a power supply and control device for an aircraft measurement instrument.

The present invention relates to an apparatus for supplying and controlling power to a measurement instrument for receiving, storing, and managing measurement values from a measurement sensor mounted at a predetermined position of an aircraft to verify design matters and performance of an aircraft, A battery for a measuring instrument provided to supply power to the measuring instrument; And a control circuit for controlling the supply of power from the battery for the measurement equipment to the measurement equipment in a predetermined time in an emergency situation in which the aircraft generator that supplies power to the measurement equipment is turned off.

The control circuit may further include: a first relay for applying power of the aircraft generator to the measurement equipment when an enable signal is input; A second relay for applying a power source of the battery for the measuring instrument to the measuring instruments when an enable signal is inputted; A first switch for connecting the battery for the measuring instrument and the second relay when the aircraft generator is turned off; And a weight on wheel (WOW) relay installed on the landing gear of the aircraft to determine whether the aircraft is taking off or landing, and to apply an enable signal to the first and second relays when the aircraft is in the take-off state .

The control circuit is also enabled when the instrument control switch is on and the aircraft generator is on and applies an enable signal to the first relay and the second relay, And a time delay relay for blocking the enable signal to the first relay and the second relay after a predetermined time elapses when the generator is turned off.

The control circuit may further include a second switch for controlling whether the enable signal is applied to the second relay regardless of the WOW relay and the time delay relay.

The control circuit may further include a reverse voltage prevention diode provided between the first relay and the measurement equipment.

Finally, when a heater for preventing freezing of a nose boom, which is a measuring instrument provided for acquiring aircraft standby data, is mounted, the control circuit receives an enable signal from the WOW relay when the aircraft is in the take-off state, And a heater relay for applying power from the aircraft generator or the battery for the measuring instrument to the heater.

The present invention can solve the problem of stopping the power supply to the measuring equipment even in an emergency situation in which the aircraft generator is not operated during the flight test of the development aircraft and thus it is possible to acquire and utilize the measurement data for detecting the cause of the failure even in an emergency situation There is an advantage.

Further, the present invention further includes a time delay relay, so that the power supply to the measuring equipment is cut off after a set time (about 10 seconds) even if the control switch is not turned off after the landing of the measuring equipment by mistake of the pilot, There is an advantage that the life shortening problem due to the complete discharge can be prevented and the possibility of failure of the measuring equipment due to the continuous power supply can be eliminated.

BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a schematic configuration diagram of a power supply and control apparatus for an aircraft measurement instrument according to an embodiment of the present invention; FIG.
2 is a configuration diagram of a control circuit according to the first embodiment of the present invention;
3 is a configuration diagram of a control circuit according to a second embodiment of the present invention;
4 is a timing diagram of a time delay relay applied to the second embodiment of the present invention;

In the case of an aircraft under development, measurement sensors are mounted at certain positions on the aircraft to verify the design and performance of the aircraft. In addition, measurement instruments for transmitting, receiving, storing and managing measurement data from each measurement sensor and transmitting the measurement data in real time are also mounted on the aircraft.

The measurement equipment is operated while receiving power from an aircraft generator 10 during flight. At this time, the measurement equipment operates in an emergency situation in which power supply is interrupted due to a problem in the aircraft generator 10 Can not.

The present invention relates to a device for supplying power to a measuring instrument to acquire measurement data of the measuring sensor in such an emergency situation and controlling the same, and the technical idea of the present invention will be described in more detail with reference to the accompanying drawings.

BRIEF DESCRIPTION OF THE DRAWINGS The accompanying drawings, which are included to provide a further understanding of the technical concept of the present invention, are incorporated in and constitute a part of the specification, and are not intended to limit the scope of the present invention.

1 is a schematic configuration diagram of a power supply and control apparatus for an aircraft measurement instrument according to an embodiment of the present invention.

As shown in the figure, the power supply and control apparatus for an aircraft measurement instrument according to the first embodiment of the present invention includes a battery 100 for a measuring instrument and a control circuit 200.

The battery 100 for a measurement instrument is mounted on an aircraft to supply power to the measurement instrument separately from the aircraft generator 10.

The control circuit 200 controls the power supply to the measuring equipment from the battery 100 for the measuring instrument in an emergency situation where a problem occurs in the airplane generator 10 that has supplied power to the measuring instrument and is turned off . At this time, the control circuit 200 is preferably configured to supply power to the measurement equipment within a predetermined time after the power supply from the aircraft generator 10 is stopped.

That is, when the aircraft power source (generator) 10 is shut off, if the time for the power source to be changed by the battery 100 for the measuring instrument becomes long, the operation of the measuring equipment may be shut down or a failure may occur It is very important to configure the control circuit 200 so that there is no power interruption.

In this case, it is desirable to eliminate the possibility that the data measurement and measurement equipment fail due to stopping and rebooting of the measurement equipment by setting the time for changing the power source within 50 ms as stated in the military specification MIL-STD-704 aircraft power characteristics Do.

2 is a configuration diagram of the control circuit 200 according to the first embodiment of the present invention. As shown, the control circuit 200 may include a first relay 210, a second relay 220, a first switch 230, and a WOW (Weight On Wheel) relay 240.

The first relay 210 is arranged such that the input pin I is connected to the aircraft generator 10 and the output pin O is connected to the metering devices so that when the enable signal E is input, Lt; / RTI > to the metering devices.

The second relay 220 is connected to the input pin I of the battery 100 for the measuring instrument and the output pin O to be connected to the measuring instruments. When the enable signal E is input, And operates to apply the power of the battery 100 for the equipment to the measuring equipment. At this time, the battery 100 for the measurement equipment can be connected to supply power only to predetermined main measurement equipment, and can be appropriately connected as needed.

The first switch 230 operates to connect the battery 100 and the second relay 220 for the measurement apparatus when the aircraft generator 10 is turned off.

Finally, the WOW relay 240 is installed on the landing gear of the aircraft to determine whether the aircraft is in the take-off or landing state. When the take-off state is established, the WOW relay 240 applies an enable signal to the first relay 210 and the second relay 220 And the enable signal is cut off when the vehicle is in a landing state. That is, when an emergency situation occurs in which the aircraft power source 10 is turned off in the take-off state, power is supplied to the measurement equipment by the battery 100 for the measurement equipment.

In this way, the measurement instruments are connected to the aircraft generator 10 and the battery 100 for the measurement instrument at the same time. When the power of the aircraft generator 10 is shut off while the power is supplied from the aircraft generator 10 during the flight, (230) to receive power from the battery (100) for the measurement equipment. According to the present invention, since the control circuit 200 is constructed as described above, it is possible to prevent the stopping or failure of the measuring equipment due to the power source change.

In addition, as shown in the drawing, the present invention preferably includes a reverse voltage prevention diode 250 between the first relay 210 and the measurement equipment.

This is because the power is supplied from the battery 100 for the measuring instrument to the measuring instrument in the emergency situation in which the aircraft power source 10 is turned off and the reverse voltage is applied from the measuring instrument to the aircraft generator 10 will be. Similarly, a diode may be provided between the second relay 220 and the measurement equipment.

3 is a configuration diagram of the control circuit 200 according to the second embodiment of the present invention. The illustrated embodiment has been added to the first embodiment shown in FIG. 2, and only different portions will be described in detail. For reference, in the drawing, C1 and C2 denote a connector having a plurality of pins. For example, an aircraft generator 10 mounted on an aircraft, a battery 100 for a measuring instrument, etc., And output terminals of the relays 210, 220 and 280 are connected to various measuring instruments (not shown) through a connector C2.

The second embodiment of the present invention may further comprise a time delay relay 260.

3, the DAS control switch 30 turns on the pilot for driving the measuring instrument, the measuring instrument control switch 30 is on, When the power supply (generator) 10 is applied, the time delay relay 260 is enabled to apply an enable signal to the first relay 210 and the second relay 220.

At this time, the time delay relay 260 may be configured such that, after the aircraft has landed, the pilot has turned off the aircraft power supply 10, but the measurement equipment control switch 30 has not been turned off, 2 < / RTI >

Fig. 4 shows a timing chart thereof. That is, when the measuring instrument control switch 30 is turned on (t1), a signal is applied to the A2 pin and the X1 pin (Enable_1). When the aircraft power supply 10 is turned on (t2) The enable signal is applied to the first relay 210 and the second relay 220 connected to the A1 pin as the time control relay is enabled.

Thereafter, when the control of the instrument control switch 30 is turned on when the aircraft generator 10 is turned off or when there is no power source (in an emergency situation), a predetermined time t4 (t3) - t3) (delay time), the power supply of the battery 100 for the measuring instrument is stopped.

This is because the power supply is automatically cut off after a set time (approximately 10 seconds) even if the control switch 30 is not turned off after the landing of the measuring instrument due to a mistake of the pilot, so that the life shortening problem due to the full discharge of the battery can be prevented There are advantages.

At this time, since the first relay 210 and the relay are enabled by the WOW relay 240 separately from the time delay relay 260, even if the aircraft power source 10 is turned off due to an emergency during the flight, 100), the instrument can continue to operate.

Also, as shown, the second switch 270 may further include the second switch 270 in the second embodiment of the present invention. The second switch 270 controls whether the enable signal is applied to the second relay 220 regardless of the WOW relay 240 and the time delay relay 260.

That is, when the second switch 270 is turned on, the power of the battery 100 for the measurement equipment can be supplied to the measurement equipment even when the aircraft power source 10 is in the off state and the aircraft is in the landing state.

This can be used when the measurement equipment needs to be inspected on the ground without using the aircraft power source 10, so that the battery 100 for the measurement equipment can be used without using a separate power source when checking the measurement equipment.

On the other hand, the aircraft can be equipped with a nose boom as a measuring device for acquiring aircraft standby data. At this time, a heater is installed inside the nose boom to prevent freezing of the nose boom. The nose boom heater is configured to operate only when the second switch (270) is turned on and not necessarily in flight because the nose boom heater may be damaged by overheating when power is supplied when the aircraft is on the ground.

The control circuit 200 further includes a heater relay 280 to control the operation of the aircraft generator 10 or the battery 100 for the measurement instrument when the enable signal is input from the WOW relay 240 when the aircraft is in the take- And the power of the nose boom heater is applied to the nose boom heater.

However, it is preferable to separately provide a heater test switch (HTS) in case that it is necessary to confirm whether the heater operates normally on the ground.

It will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention as defined by the appended claims.

10: Aircraft generator
20: Measuring equipment
30: Measuring equipment control switch
100: Battery for measuring instrument
200: control circuit
210: first relay
220: second relay
230: first switch
240: WOW relay
250: Reverse-voltage prevention diode
260: time delay relay
270: second switch
280: Heater relay

Claims (6)

An apparatus for supplying and controlling power to a measuring instrument (20) for receiving, storing, and managing measured values from a measuring sensor mounted at a predetermined position of an aircraft to verify design specifications and performance of an aircraft,
A battery (100) for metering equipment provided to supply power to the metrology equipment (20) separately from the aircraft generator (10); And
A control circuit (not shown) for controlling the supply of power from the battery 100 for the measuring instrument to the measuring instrument 20 within a predetermined time in an emergency situation in which the aircraft generator that supplies power to the measuring instrument 20 is turned off 200)
The control circuit 200 includes a second relay 220 for applying the power of the battery 100 for the measurement instrument to the measurement instruments when the enable signal is input,
The second relay 220 can control whether the enable signal is applied or not, so that the power of the battery 100 for the measurement equipment can be supplied to the measurement equipment 20 And a second switch (270) for causing the second switch (270) to be turned on.
The method according to claim 1,
The control circuit (200)
A first relay (210) for applying power of the aircraft generator to the measurement equipment when an enable signal is inputted;
A first switch (230) connecting between the battery (100) and the second relay when the aircraft generator is turned off; And
A weight on wheel (WOW) relay installed on the landing gear of the aircraft to determine whether the aircraft is in the take-off or landing state and to apply an enable signal to the first relay 210 and the second relay 220 when the take- (240);
And a controller for controlling the power supply of the aircraft measurement equipment.
3. The method of claim 2,
The control circuit (200)
The first relay 210 and the second relay 210 are enabled when the measurement equipment control switch 30 which is turned on / off for driving the measuring instrument 20 is on and the aircraft generator is on, 220) for shutting down the enable signal to the first relay (210) and the second relay (220) after a predetermined time elapses when the aircraft is landed and the aircraft generator is turned off, (260);
Further comprising a controller for controlling the supply of power to the aircraft measurement equipment.
delete 3. The method of claim 2,
The control circuit (200)
A reverse voltage prevention diode (250) provided between the first relay (210) and the measurement equipment;
Further comprising a controller for controlling the supply of power to the aircraft measurement equipment.
3. The method of claim 2,
When a heater for preventing freezing of the nose boom, which is a measuring instrument provided for acquiring the air waiting data, is mounted,
The control circuit (200)
A heater relay 280 for receiving an enable signal from the WOW relay 240 when the aircraft is in a take-off state and applying power to the heater for the aircraft generator or the measurement equipment;
Further comprising a controller for controlling the supply of power to the aircraft measurement equipment.
KR1020150173714A 2015-12-08 2015-12-08 Apparatus for controlling and power supply for instrumentation of aircraft KR101751387B1 (en)

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Publication number Priority date Publication date Assignee Title
CN111756284B (en) * 2020-06-17 2024-07-16 江西洪都航空工业集团有限责任公司 Dual-channel aircraft generator control device with dual redundancy design
KR102631589B1 (en) * 2021-09-09 2024-01-31 엘아이지넥스원 주식회사 Multi-interface wow matrix structure for aircraft

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR101050424B1 (en) * 2010-02-25 2011-07-19 국방과학연구소 Instrumentation pod system for testing the flying of an aircraft

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR101050424B1 (en) * 2010-02-25 2011-07-19 국방과학연구소 Instrumentation pod system for testing the flying of an aircraft

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