CN108657450A - Aircraft optical fiber aviation attitude system method of modifying - Google Patents
Aircraft optical fiber aviation attitude system method of modifying Download PDFInfo
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- CN108657450A CN108657450A CN201810428636.4A CN201810428636A CN108657450A CN 108657450 A CN108657450 A CN 108657450A CN 201810428636 A CN201810428636 A CN 201810428636A CN 108657450 A CN108657450 A CN 108657450A
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- 238000000034 method Methods 0.000 title claims abstract description 16
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- 239000004973 liquid crystal related substance Substances 0.000 claims abstract description 6
- 238000012545 processing Methods 0.000 claims description 57
- 239000000306 component Substances 0.000 claims description 56
- 238000012857 repacking Methods 0.000 claims description 49
- 238000009434 installation Methods 0.000 claims description 25
- 238000004458 analytical method Methods 0.000 claims description 23
- 238000009413 insulation Methods 0.000 claims description 20
- 238000006243 chemical reaction Methods 0.000 claims description 9
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- 238000013461 design Methods 0.000 claims description 7
- 230000005611 electricity Effects 0.000 claims description 7
- 238000012986 modification Methods 0.000 claims description 7
- 230000004048 modification Effects 0.000 claims description 7
- 230000003044 adaptive effect Effects 0.000 claims description 6
- 238000004132 cross linking Methods 0.000 claims description 6
- 230000006872 improvement Effects 0.000 claims description 6
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- 235000003140 Panax quinquefolius Nutrition 0.000 claims description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 3
- 229910052782 aluminium Inorganic materials 0.000 claims description 3
- 239000004411 aluminium Substances 0.000 claims description 3
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- 235000008434 ginseng Nutrition 0.000 claims description 3
- 230000006698 induction Effects 0.000 claims description 3
- 230000005389 magnetism Effects 0.000 claims description 3
- 238000012544 monitoring process Methods 0.000 claims description 3
- 238000004080 punching Methods 0.000 claims description 3
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- WBWWGRHZICKQGZ-HZAMXZRMSA-M taurocholate Chemical compound C([C@H]1C[C@H]2O)[C@H](O)CC[C@]1(C)[C@@H]1[C@@H]2[C@@H]2CC[C@H]([C@@H](CCC(=O)NCCS([O-])(=O)=O)C)[C@@]2(C)[C@@H](O)C1 WBWWGRHZICKQGZ-HZAMXZRMSA-M 0.000 claims description 3
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Classifications
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- 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
- B64D43/00—Arrangements or adaptations of instruments
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Abstract
The invention discloses a kind of aircraft optical fiber aviation attitude system method of modifying, and replacement in situ is carried out to HZX 1/1M types aviation attitude systems with HJL 31/31A optical fiber aviation attitude systems；Original machine electric top is substituted using optical fibre gyro, is shown using liquid crystal display replacement original machine electric-type instrument；And the power supply mode of HJL 31/31A optical fiber aviation attitude systems is redesigned, left and right system is independently-powered, solves to lead to left and right system while the possibility of failure because of power failure；HJL 31/31A optical fiber aviation attitude systems use 8 school magnetic deviation modes, aircraft is pushed away 360 degree, and error logs are carried out in 8 orientation, are stored in navigation attitude computer, aircraft is pushed away 360 degree again, two or three of orientation are selected to be verified, the school magnetic deviation of aircraft can be completed twice by substantially pushing away, and greatly reduced workload, saved maintenance time.
Description
Technical field
The present invention relates to a kind of aircraft optical fiber aviation attitude system method of modifying.Aviation attitude system is that important on aircraft airborne sets
It is standby, it provides aircraft real-time navigational parameter, aircraft current tilt angle, pitch angle, course angle etc. is on the one hand shown by instrument；Separately
On the one hand direct current true course signal is exported to fire control computer；To machines such as flight parameter recorder, weather radar, automatic pilots
The signals such as upper miscellaneous equipment output course angle, pitch angle, inclination angle, are parameters necessary to aircraft.
Background technology
The HZX-1/1M type aviation attitude systems of aircraft first wife dress belong to left and right system configuration, since there are failure rates for it
The problems such as height, poor reliability, and left and right system is controlled by the same power supply, if there is power failure, can lead to left and right system
Function fails simultaneously, and prodigious harm is brought to flight.
The HZX-1/1M types aviation attitude system of first wife's dress need to complete the work of primary school magnetic deviation every 12 months, when school magnetic deviation need by
Aircraft pushes away 360 degree, and error log, adjustment are carried out in 24 orientation, and adjustment terminates to still need to that aircraft is pushed away 360 degree again, and
It is verified in 24 orientation, it is such as undesirable, it also needs to repeat to push away aircraft, until verification is qualified, workload and required match
Conjunction personnel are more.
Invention content
The present invention changes the technical solution adopted is that providing a kind of aircraft optical fiber aviation attitude system to solve above-mentioned technical problem
Dress method, wherein specific technical solution is：
The repacking of department enclosure：
1) HJZ-8C navigation attitudes component
HJZ-8C navigation attitude components are the core components of HJL-31/31A aviation attitude systems, are used for the course angle and appearance of survey aircraft
State angle is exported by digital bus interface RS422 and gives signal boxcar, is exported to each bearing indication by HB6096 digital interfaces
Device；And the RS422 digital signals that real-time reception control box is sent, latitude amendment is carried out to navigation attitude component, passes through digital output modul
Navigation attitude component operation in magnetic/half, assist state soon；
Do not deviate from screw by 4 on HJZ-8C navigation attitude components, HJZ-8C navigation attitude components are fixed on pinboard, turns
Fishplate bar is fixed on by the mounting screw of former full attitude integration gyro on former full attitude integration gyro supporting plate；
For the characteristic of HJZ-8C navigation attitude components, need to calibrate pinboard；When calibration, by adjusting gasket
By pinboard levelling, ensure that it is horizontally mounted precision ± 0.2 °, the requirement of orientation installation accuracy ± 0.2 °；
2) EXZ-18C signals boxcar
EXZ-18C signal boxcars are used to the RS422 flight attitude signals of the HJZ-8C digital quantities exported being converted to analog quantity
Synchronizer signal, be output on machine comprehensive pathfinder, indicate the magnetic heading of aircraft, output to horizon indicator on machine,
Indicate the posture of aircraft, while miscellaneous equipment exports the navigation attitude information of analog quantity on machine；And output monitoring effective information；
EXZ-18C signal boxcars are electronic unit, and shape is rectangle chassis design；Because original machine is only fitted with 1
Amplifier supporting plate, and EXZ-18C signal boxcar sizes are big, group amplifier is too many, need to separately increase by 1 group amplifier supporting plate
(Y8-7707-65) and one, 20 bugle aluminium, by the way that 2 EXZ-18C signal boxcars are mounted on supporting plate with punching on supporting plate
On；When repacking, left EXZ-18C signals boxcar is installed on group amplifier position in left and right in original machine, right EXZ-18C signals conversion
Box is installed on newly-increased group amplifier supporting plate；
3) GCJ-10 (I) Magnetic Sensor
Ground magnetic component of GCJ-10 (I) sensor on sensitive earth magnetic field in the horizontal direction two quadrature axis, and will
Earth magnetism component signal is transferred to HJZ-8C navigation attitude components, and navigation attitude component calculates the magnetic heading of aircraft accordingly；With two GCJ-10
(I) Magnetic Sensor substitutes original two GHC-5 induction type magnetic course transmitters, the GHC-5 phases that installation dimension is equipped with original machine
Together, in situ to replace；
4) SCX-23/23A Comprehensive Signal Processings machine
Conversion, built-in mould of the SCX-23/23A Comprehensive Signal Processing machines for the connection and working condition of system integral unit
Number conversion lines, telecompass, inertial navigation/strapdown on machine are whipped lead, the simulation letter of microwave landing/course downslide system input
Number, switching signal is transformed to HB6096 digital signals and gives each liquid crystal indicator to show；
The EJ-7P relay boxes that original machine is equipped with are replaced with into SCX-23/23A Comprehensive Signal Processing machines, installation dimension in situ
It is constant；There are ten sockets on SCX-23/23A Comprehensive Signal Processing machines, the symbol being connected with miscellaneous equipment be labelled on panel,
4 screw locks in the upper and lower part of Comprehensive Signal Processing machine；
5) EK-3F control box
EK-3F control box uses Design of digital, cancels orientation setting knob, amount of unbalance in former control box and corrects current potential
Device, retain left-often-right cut is changed, magnetic-half is converted, north-south conversion, rapid coordination button and latitude debugging functions, and by reservation
Each signal is converted to digital signal and gives navigation attitude component；EK-3F control box is installed on the controls of the EK-3 on original machine navigator's instrument board
Box position processed, shape installation dimension is identical as the EK-3 that original machine is equipped with, in situ to replace；
6) ZEH-9 course positions indicator, ZEH-9A course position indicators
ZEH-1R (B) course position indicator phase that ZEH-9 course positions indicator (2) installation dimension is installed with original machine
Together, it is respectively arranged on left and right instrument board, it is in situ to replace；
ZEH-1S (B) course position indicator of ZEH-9A course positions indicator (1) installation dimension and original machine installation
It is identical, it is installed on navigator's instrument board, it is in situ to replace；
7) ZHL-6 navigator's indicator
ZHL-6 navigator's indicator (1) is installed on navigator's instrument board the indicator post that navigates,
It is in situ to replace；8) ZHZ-4A integrates pathfinder
Original two ZHZ-4A synthesis pathfinder retains constant on machine；
9) cancel product
Cancel two FZ-3B group amplifiers；
Cancellation system is crosslinked relationship with angular velocity signal device.
The repacking of power-supply system
Optical fiber aviation attitude system power type is identical as original system, be direct current 28V, single phase ac 115V, three-phase alternating current 36V,
The reference that system single phase ac 36V, 26V, three-phase alternating current 36V power supplys are only converted as synchronizer excited signal and digital-to-analog
Power supply uses；
After optical fiber navigation attitude adaptive improvement, system power supply consumption power is adjusted, the power consumption of direct current 28V by
Being adjusted to no more than 70W originally is not more than 500W (low temperature limit), single phase ac 115V consumption power and three-phase alternating current 36V
Consumption power is reduced；
1) DC electrical load and power supply capacity analysis
A) direct current power supply-distribution system situation of change
Fig. 5 is shown in the front and back direct current 28V loads variation of repacking.
B) direct current power load is analyzed
Direct current emergency load variable quantity is：" it is emergent to cancel equipment "+" it is emergent to be installed in addition with equipment "=(- 10+15) × 0.7 × 28
× 10-3=0.098kW (0.7 is fuse correction factor), i.e. direct current emergency load increases 0.098kW；Direct current normal load
Variable quantity is：(0.7 is fusing to " it is normal to cancel equipment "+" it is normal to be installed in addition with equipment "=15 × 0.7 × 28 × 10-3=0.294kW
Device correction factor), i.e. direct current emergency load increases；DC load variable quantity adds up to：Direct current emergency load variable quantity+direct current
Normal load variable quantity=0.098+0.294=0.392kW；
C) power supply capacity is analyzed
A) QF12-1 capacity analysis
8 QF12-1 direct current 28V power supply capacities are 86.4kW.Then by b) item it is found that the appearance of aircraft direct current 28V power supplys
It is 38% to measure nargin.So it could be assumed that：8 QF12-1 dc generators power supply capacities can meet full machine direct current 28V just
Normal power demands；
When into emergency service state, the emergent busbar power supply of the 4th, No. 5 QF12-1 generator direct current of normal work, always
Power is 21.6kW (taking electric correction factor 0.9), can meet aircraft direct current emergency service demand；By b) load analysis
As a result, direct current emergency load increases 0.098kW after repacking；
B) QF-24 capacity analysis
When flying height in 4200m hereinafter, WDZ-1 auxiliary power units can be started, powered from QF-24 to emergent power grid,
Capacity is 18kW；By b) load analysis as a result, direct current emergency load increases 0.098kW after repacking；
C) 12-HK-28 capacity analysis
The power supply capacity of separate unit 12-HK-28 batteries is 28AH, and four battery parallel operation capacity are 112AH, 8
When platform QF12-1 whole failures to direct current meet an urgent need busbar power supply；By b) load analysis as a result, the direct current after repacking is emergent negative
0.098kW is increased before carrying opposite repacking, so, 12-HK-28 DC storage battery cell group emergency service capacity can also meet repacking
Direct current emergence power demand afterwards；
2) direct current 27V power supplys
To adapt to the power supply characteristic of new equipment, when repacking, meets an urgent need from 24 frames and increase by 1 road 27V power supply (fuses on block terminal
For TB-15) the H plugs of SCX-23/23A Comprehensive Signal Processing machines are connected to by the power switch of navigator's instrument board, it is used for
The work of the right system of navigation attitude, 1 road 27V power supplys (fuse is changed to TB-15 by TB-10) originally are used for the work of the left system of navigation attitude
Make；
3) exchange 36V400Hz (three-phase)
Newly-increased 1 road three-phase 36V power supplys, make left and right aviation attitude system possess independent current source, do not interfere with each other；When repacking, from 8 frames
Increase by 1 road three-phase 36V power supplys (fuse TB-10) on 36V block terminals to be connected to by the power switch of navigator's instrument board
The H plugs of SCX-23 (A) Comprehensive Signal Processing machine, are used for the work of the right system of navigation attitude, and 1 road three-phase 36V power supplys originally are used for
The work of the left system of navigation attitude.
The repacking of cable on machine
Optical fiber aviation attitude system changes the outfit former cable on full utilization machine, is adjusted, is being crosslinked to the definition of original machine cable interface
Increase transit cable between component, it is constant to be crosslinked relationship on guarantee machine, it is specific as follows：
1) GCJ-10 (I) Strapdown Magnetometer Sensor replaces GHC-5 in situ, and the cable on product connection machine can utilize original insert
Head docking, but because the signal transmission of GCJ-10 (I) Strapdown Magnetometer Sensor changes, transit cable need to be installed additional, cable routing is 13 frames
JL3 (P32J3AQ) banjos on ceiling along leader cable move towards to the cable trough on the left of 9 frame hatch doors down to floor under it is straight again
It connects and is docked with HJZ-8C navigation attitude components, former dressing of cable and insulation processing；
2) direct line between EXZ-18C signals boxcar and HJZ-8C navigation attitude components, does not utilize cable on machine；
3) SCX-23/23A Comprehensive Signal Processings machine reequips outer cable；
N, Q multi-plug cables are directly connected to by transit cable and EXZ-18C, HJZ-8C；
L cables are connect with navigator's instrument board ZHL-6, and prototype utilizes original machine cable, and without modification, prototype need to be by L
It is supplied to the course signal of TCAS to be changed to L27, L28, L29 by L23, L24, L25 on cable, remaining is constant；
J cables are connected with external cross-linking equipment on machine, using original machine cable, without modification；
H cables are connect with power supply on machine, to ensure that left and right system is independently-powered, are improved aircraft safety, need to be increased all the way
28V direct currents input, and increase by one group of three-phase 36V input, and H cables need to carry out adaptive improvement；
Cancel connecting cable between SCX-23/23A Comprehensive Signal Processings machine I, G plug and 2 FZ-3B, original machine cable is empty
It sets；
It is specific as follows：
A) cancel in original machine EJ-7P relay boxes to left attitude gyro cable entirely；
B) cancel in original machine EJ-7P relay boxes to right attitude gyro cable entirely；
C) cancel in original machine EJ-7P relay boxes to left group amplifier cable；
D) cancel in original machine EJ-7P relay boxes to right group amplifier cable；
E) left and right comprehensive indicator cable of cancellation 13 frame ceiling JL, III plugs to cockpit；
F) in situ to replace original+27V emergency service cables, it is used for the left system power supplies of HJL-31A；
G)+27V normal power supply cables are increased newly, are used for the right system power supplies of HJL-31A；
H) three exchange 36V service cables all the way are increased newly, are used for the right system power supplies of HJL-31A；
I) SCX-23A Comprehensive Signal Processings machine is increased newly to the left navigation attitude components of HJZ-8C and EXZ-18C left signals boxcar electricity
Cable；
J) SCX-23A Comprehensive Signal Processings machine is increased newly to the right navigation attitude components of HJZ-8C and EXZ-18C right signals boxcar electricity
Cable；
K) left and right HJZ-8C navigation attitude component cable of newly-increased 13 frame ceiling JL, III plugs to cockpit；
L) 12 groups of non-twisted-pair shielded wire signal cable in original machine is replaced, HJL-31A aviation attitude systems are used for transmission
ARINC429 bus signals；
M) cancel in original machine (A plugs) on EJ-7P 6,7,11,24,25,26,27,28,34,35,36,37,41,42,
43,44,45,51,52 foot leads do insulation processing；
N) cancel in original machine (C plugs) on EJ-7P 6,7,11,24,25,26,27,28,34,35,36,37,41,42,
43,44,45,51,52 foot leads do insulation processing；
O) 31,41,42,43,44,45,46,47, the 52 foot leads for cancelling (E plugs) on EJ-7P in original machine do insulation position
Reason；
P) by wire size is TCS25A, TCS26A, TCS27A after 23,24, the 25 foot leads of (L plugs) on EJ-7P in original machine
Separation crimps hole stick and is inserted into 28,29, the 30 of the plug again；
Q) by (H plugs) redefines on EJ-7P in original machine, cancel 44 foot leads after plug, do insulation processing；Original 34
The taking-up of foot lead is pressed into 44 feet again；Former 43 foot leads taking-up is pressed into 34 feet again；Former 45 foot leads taking-up is pressed into 43 feet again；
+ 27V (from the emergent busbar) power cord newly laid is pressed into 1 foot；+ the 27V newly laid (carrys out) electricity from normal busbar
Source line is pressed into 45 feet；The three-phase alternating current 36V power cords newly laid are pressed into 11,12,13 feet；
R) cancel in original machine after the left and right ZEH-9 plugs of cockpit 6,7,11,24,25,26,27,28,34,35,36,
37,41,42,43,44,45,51,52 foot leads do insulation processing；
S) cancel 31,41,42,43,44,45,46,47,52 foot leads in original machine after navigators cabin ZEH-9A plugs to leave no room for manoeuvre
Edge processing；
T) be HH197A, HH198A by wire size dock with left full attitude gyro in original machine, HH199A, HH217A,
6 conducting wires of HH218A, HH219A are docked with 65,64,63,76,75,74 pins on left signal boxcar, to fly ginseng, TCS
Etc. systems provide attitude signal；
U) it is 4 of HH430A, HH431A, HH441A, HH442A by the wire size docked with right full attitude gyro in original machine
Conducting wire docks (76,65 ground connection on right signal boxcar) with 64,63,75,74 pins on right signal boxcar, for meteorological thunder
Up to etc. systems provide attitude signal；
V) by 2,3,4,5, the 6 foot lead (wire size of XKE30R42Q plugs after navigator's instrument board boat position indicator in original machine
For ZJ625, ZJ626, ZJ627, ZJ454, ZJ455) with 64,63,75,74 pins dock (76,65 on right signal boxcar
Ground connection), provide attitude signal for systems such as weather radars；
W) 36,35 pins at the plug of the former ends TNL2101 are moved on into 58,57 pins；Again a twisted pair line connection is laid
P, q pin of SIU-108 interconnection of signals box J-2 plugs to Comprehensive Signal Processing machine J plugs 8,9 pins, for show GPS system
The drift angle of offer and yaw away from；
X) yaw on navigator's instrument board is cancelled away from original machine circuit on/navigation channel lever switch, insulating wrapping；Yaw is away from end
Ground connection, navigation channel rod end is hanging, and 7 pins of centre termination Comprehensive Signal Processing machine J plugs are effectively believed to provide GPS to aviation attitude system
Number；
Y) twisted-pair feeder is laid again for controlling " left side to/right side to " signal, connection Comprehensive Signal Processing machine A plugs
46,47 pins drive the intermediate ends on " left side to/right side to " for instrument board to a left side, a left side to an end connection left side drive boat position indicator plug 46,
46,47 pins of boat position indicator plug are driven on 47 pins, the right side to the end connection right side.
In addition, the compass calibration mode of optical fiber aviation attitude system changes, magnetic deviation binding device is accessed by ATE interfaces,
Bearing of aircraft position is adjusted by magnetic deviation calibration request, and magnetic heading true value is bound by magnetic deviation binding device, eight are carried out to aircraft
The calibration of position magnetic deviation, HJL-31/31A optical fiber aviation attitude system first installation or replace GCJ-10 (I) Strapdown Magnetometer Sensors or
Magnetic deviation calibration should be carried out to system, after HJZ-8A navigation attitude components to ensure system magnetic heading precision.
The present invention has the advantages that compared with the existing technology：
1, replacement in situ is carried out to HZX-1/1M types aviation attitude system with HJL-31/31A optical fiber aviation attitude system；
2, original machine electric top substituted using optical fibre gyro, shown using liquid crystal display replacement original machine electric-type instrument；
3 and to the power supply mode of HJL-31/31A optical fiber aviation attitude systems redesign, left and right system is independently-powered, solve
Because power failure leads to left and right system while the possibility of failure；
4, HJL-31/31A optical fiber aviation attitude system uses 8 school magnetic deviation modes, and aircraft is pushed away 360 degree, and 8 orientation into
Row error log is stored in navigation attitude computer, then aircraft is pushed away 360 degree, selects two or three of orientation to be verified, substantially pushes away twice
The school magnetic deviation that can complete aircraft, greatly reduces workload, has saved maintenance time.
Description of the drawings
Fig. 1 is that HJL-31/31A optical fiber aviation attitude systems are crosslinked relational graph.
Fig. 2 is HJL-31/31A optical fiber aviation attitude system power supply the principle figures.
Fig. 3 is school magnetic deviation 8 positions schematic diagram.
Fig. 4 is power supply the principle figure.
Fig. 5 is the front and back direct current 28V loads variation table of repacking.
Specific implementation mode
This method is reequiped suitable for aircraft optical fiber aviation attitude system.
1. the repacking of department enclosure
1) HJZ-8C navigation attitudes component
HJZ-8C navigation attitude components are the core components of HJL-31/31A aviation attitude systems, are used for the course angle and appearance of survey aircraft
State angle gives signal boxcar by digital bus interface (RS422) output, is exported by HB6096 digital interfaces and referred to each course
Show device；And the RS422 digital signals that real-time reception control box is sent, latitude amendment is carried out to navigation attitude component, passes through switching value control
Navigation attitude component operation processed in magnetic/half, assist state soon.
Do not deviate from screw by 4 on HJZ-8C navigation attitude components, HJZ-8C navigation attitude components are fixed on pinboard, turns
Fishplate bar is fixed on former full attitude integration gyro supporting plate (the frame floor of 12 frames~13 by the mounting screw of former full attitude integration gyro
Under).
For the characteristic of HJZ-8C navigation attitude components, need to calibrate pinboard.It, can be by adjusting pad when calibration
Pinboard levelling is ensured that it is horizontally mounted precision ± 0.2 °, the requirement of orientation installation accuracy ± 0.2 ° by piece.
2) EXZ-18C signals boxcar
EXZ-18C signal boxcars are used to the RS422 flight attitude signals of the HJZ-8C digital quantities exported being converted to analog quantity
Synchronizer signal, be output on machine comprehensive pathfinder, indicate the magnetic heading of aircraft, output to horizon indicator on machine,
Indicate the posture of aircraft, while miscellaneous equipment exports the navigation attitude information of analog quantity on machine；And output monitoring effective information etc..
EXZ-18C signal boxcars are electronic unit, and shape is rectangle chassis design.Because original machine is only fitted with 1
Amplifier supporting plate, and EXZ-18C signal boxcar size great synthesis amplifiers are too many, need to separately increase by 1 group amplifier supporting plate
(Y8-7707-65) and one, 20 bugle aluminium, by the way that 2 EXZ-18C signal boxcars are mounted on supporting plate with punching on supporting plate
On.When repacking, left EXZ-18C signals boxcar is installed on group amplifier position in left and right in original machine, right EXZ-18C signals conversion
Box is installed on newly-increased group amplifier supporting plate.
3) GCJ-10 (I) Magnetic Sensor
Ground magnetic component of GCJ-10 (I) sensor on sensitive earth magnetic field in the horizontal direction two quadrature axis, and will
Earth magnetism component signal is transferred to HJZ-8C navigation attitude components, and navigation attitude component calculates the magnetic heading of aircraft accordingly.
Two GHC-5 induction type magnetic course transmitters, installation dimension and original are substituted with two GCJ-10 (I) Magnetic Sensors
The equipped GHC-5 of machine is identical, in situ to replace.
4) SCX-23/23A Comprehensive Signal Processings machine
Conversion, built-in mould of the SCX-23/23A Comprehensive Signal Processing machines for the connection and working condition of system integral unit
Number conversion lines, telecompass, inertial navigation/strapdown on machine are whipped lead, the simulation letter of microwave landing/course downslide system input
Number, switching signal is transformed to HB6096 digital signals and gives each liquid crystal indicator to show.
The EJ-7P relay boxes that original machine is equipped with are replaced with into SCX-23/23A Comprehensive Signal Processing machines, installation dimension in situ
It is constant.There are ten sockets on Comprehensive Signal Processing machine, be labelled with the symbol being connected with miscellaneous equipment on panel, at integrated signal
4 screw locks in the upper and lower part of reason machine.
5) EK-3F control box
EK-3 control box uses Design of digital, cancels orientation setting knob, amount of unbalance in former control box and corrects current potential
Device, retain left-often-right cut is changed, magnetic-half is converted, north-south conversion, rapid coordination button and latitude debugging functions, and by reservation
Each signal is converted to digital signal and gives navigation attitude component.
EK-3F control box is installed on the control box positions of the EK-3 on original machine navigator's instrument board, shape installation dimension and original
The equipped EK-3 of machine is identical, in situ to replace.
6) ZEH-9 course positions indicator, ZEH-9A course position indicators
ZEH-1R (B) course position indicator phase that ZEH-9 course positions indicator (2) installation dimension is installed with original machine
Together, it is respectively arranged on left and right instrument board (in situ to replace).
ZEH-1S (B) course position indicator of ZEH-9A course positions indicator (1) installation dimension and original machine installation
It is identical, it is installed on navigator's instrument board (in situ to replace).
7) ZHL-6 navigator's indicator
ZHL-6 navigator's indicator (1) is installed on navigator's instrument board the indicator post that navigates, in situ to replace.
8) ZHZ-4A integrates pathfinder
Original two ZHZ-4A synthesis pathfinder retains constant on machine.
9) cancel product
Cancel two FZ-3B group amplifiers；
Cancellation system is crosslinked relationship with angular velocity signal device.
2. the repacking of power-supply system
Optical fiber aviation attitude system power type is identical as original system, be direct current 28V, single phase ac 115V, three-phase alternating current 36V,
System single phase ac 36V, 26V (being provided by special 115V transformers on machine), three-phase alternating current 36V power supplys are only used as synchronizer excitatory
Signal and the reference power source of digital-to-analog transformation use.
After optical fiber navigation attitude adaptive improvement, system power supply consumption power is adjusted, the power consumption of direct current 28V by
Being adjusted to no more than 70W originally is not more than 500W (low temperature limit), single phase ac 115V consumption power and three-phase alternating current 36V
Consumption power is reduced.System power supply schematic diagram is shown in Fig. 4.
1) DC electrical load and power supply capacity analysis
The * * CH-BG72-4 provided according to Shan Fei companies《Aircraft DC electrical loads and power supply capacity analysis report
It accuses》, calculated by the analysis of the variation and DC power source capacity nargin that are loaded to exchangeable device direct current, finally provide direct current
Source system designs accordance conclusion.
A) direct current power supply-distribution system situation of change
Fig. 5 is shown in the front and back direct current 28V loads variation of repacking.
B) direct current power load is analyzed
Direct current emergency load variable quantity is：" it is emergent to cancel equipment "+" it is emergent to be installed in addition with equipment "=(- 10+15) × 0.7 × 28
× 10-3=0.098kW (0.7 is fuse correction factor), i.e. direct current emergency load increases 0.098kW；Direct current normal load
Variable quantity is：(0.7 is fusing to " it is normal to cancel equipment "+" it is normal to be installed in addition with equipment "=15 × 0.7 × 28 × 10-3=0.294kW
Device correction factor), i.e. direct current emergency load increases；DC load variable quantity adds up to：Direct current emergency load variable quantity+direct current
Normal load variable quantity=0.098+0.294=0.392kW.
It is about 53.225kW according to * * CH-BG72-4 aircraft direct current total loads, aircraft DC is always born after repacking
Load becomes 53.617kW；Direct current emergency load increases 0.294kW.
C) power supply capacity is analyzed
A) QF12-1 capacity analysis
8 QF12-1 direct current 28V power supply capacities are 86.4kW.Then by b) item it is found that the appearance of aircraft direct current 28V power supplys
It is 38% to measure nargin.So it could be assumed that：8 QF12-1 dc generators power supply capacities can meet full machine direct current 28V just
Normal power demands.
When into emergency service state, the emergent busbar power supply of the 4th, No. 5 QF12-1 generator direct current of normal work, always
Power is 21.6kW (taking electric correction factor 0.9), can meet aircraft direct current emergency service demand.By b) load analysis
As a result, direct current emergency load increases 0.098kW after repacking, so：The the 4th, No. 5 QF12-1 generator of aircraft is for meeting an urgent need
When power supply, capacity can meet requirement completely.
B) QF-24 capacity analysis
When flying height in 4200m hereinafter, WDZ-1 auxiliary power units can be started, powered from QF-24 to emergent power grid,
Capacity is 18kW.By b) load analysis as a result, direct current emergency load increases 0.098kW after repacking, so：Aircraft
QF-24 dc generators capacity can also meet the direct current emergence power needs after repacking, basic with the power supply capacity before repacking
It is identical.
C) 12-HK-28 capacity analysis
The power supply capacity of separate unit 12-HK-28 batteries is 28AH, and four battery parallel operation capacity are 112AH, 8
When platform QF12-1 whole failures to direct current meet an urgent need busbar power supply.By b) load analysis as a result, the direct current after repacking is emergent negative
0.098kW is increased before carrying opposite repacking, so, 12-HK-28 DC storage battery cell group emergency service capacity can also meet repacking
Direct current emergence power demand afterwards, before the emergency service time is slightly worse than repacking.
2) direct current 27V power supplys
After repacking, the main power source of HJL-31/31A optical fiber aviation attitude systems is changed to direct current 27V, the consumption power of direct current 27V
Increase, normal work about needs 300W or so, because liquid crystal display heats when low-temperature working, about needs 500W or so, former HZX-1/1M navigation attitudes
The power of system dc 27V is only 70W.To adapt to the power supply characteristic of new equipment, when repacking, meets an urgent need from 24 frames and increase on block terminal
1 road 27V power supplys (fuse TB-15) are connected to by the power switch of navigator's instrument board at SCX-23/23A integrated signals
The H plugs of reason machine, are used for the work of the right system of navigation attitude, and 1 road 27V power supplys (fuse is changed to TB-15 by TB-10) originally are used
In the work of the left system of navigation attitude.Can meet the needs of HJL-31/31A optical fiber aviation attitude system direct current maximum 500W after repacking, and
Solve the problems, such as that 27V power failures cause left and right aviation attitude system idle simultaneously.
3) exchange 36V400Hz (three-phase)
Three-phase alternating current 36V consumption power needed for system and difference before repacking are little, but in order to improve repacking optical fiber navigation attitude
The reliability of system increases 1 road three-phase 36V power supplys newly, so that left and right aviation attitude system is possessed independent current source, do not interfere with each other.
When repacking, from 8 frame 36V block terminals increasing by 1 road three-phase 36V power supplys (fuse TB-10) passes through navigator's instrument
The power switch of dash board is connected to the H plugs of SCX-23 (A) Comprehensive Signal Processing machine, is used for the work of the right system of navigation attitude, originally
1 road three-phase 36V power supplys, be used for the left system of navigation attitude work.
4) exchange 115V400Hz (single-phase)
After repacking, the single phase ac 115V of HJL-31/31A optical fiber aviation attitude systems (is transformed to blow-up by ZBY-300A
Flow 36V, 26V) it is used mainly as excited signal, consumption power is about 100VA (former aviation attitude system consumption power is 250VA),
Consumption power greatly reduces, and is not influenced on system power supply, therefore this repacking is not related to the repacking to single-phase 115V power supplys.
3. the repacking of cable on machine
Optical fiber aviation attitude system changes the outfit former cable on full utilization machine, is adjusted, is being crosslinked to the definition of original machine cable interface
Increase transit cable between component, it is constant to be crosslinked relationship on guarantee machine.It is specific as follows：
1) GCJ-10 (I) Strapdown Magnetometer Sensor replaces GHC-5 in situ, and the cable on product connection machine can utilize original insert
Head docking, but because the signal transmission of GCJ-10 (I) Strapdown Magnetometer Sensor changes, transit cable need to be installed additional, cable routing is 13 frames
JL3 (P32J3AQ) banjos on ceiling along leader cable move towards to the cable trough on the left of 9 frame hatch doors down to floor under it is straight again
It connects and is docked with HJZ-8C navigation attitude components, former dressing of cable and insulation processing.
2) direct line between EXZ-18C signals boxcar and HJZ-8C navigation attitude components, does not utilize cable on machine.
3) SCX-23/23A Comprehensive Signal Processings machine reequips outer cable
N, Q multi-plug cables are directly connected to by transit cable and EXZ-18C, HJZ-8C.
L cables are connect with navigator's instrument board ZHL-6, certain prototype utilize original machine cable, without modification, certain type machine need by
It is supplied to the course signal of TCAS to be changed to L27, L28, L29 by L23, L24, L25 on L cables, remaining is constant.
J cables are connected with external cross-linking equipment on machine, using original machine cable, without modification,
H cables are connect with power supply on machine, to ensure that left and right system is independently-powered, are improved aircraft safety, need to be increased all the way
28V direct currents input, and increase by one group of three-phase 36V input, and H cables need to carry out adaptive improvement.
Cancel connecting cable between SCX-23/23A Comprehensive Signal Processings machine I, G plug and 2 FZ-3B, original machine cable is empty
It sets.
It is specific as follows：
A) cancel in original machine EJ-7P relay boxes to left attitude gyro cable entirely；
B) cancel in original machine EJ-7P relay boxes to right attitude gyro cable entirely；
C) cancel in original machine EJ-7P relay boxes to left group amplifier cable；
D) cancel in original machine EJ-7P relay boxes to right group amplifier cable；
E) left and right comprehensive indicator cable of cancellation 13 frame ceiling JL, III plugs to cockpit；
F) in situ to replace original+27V emergency service cables, it is used for the left system power supplies of HJL-31A；
G)+27V normal power supply cables are increased newly, are used for the right system power supplies of HJL-31A；
H) three exchange 36V service cables all the way are increased newly, are used for the right system power supplies of HJL-31A；
I) SCX-23A Comprehensive Signal Processings machine is increased newly to the left navigation attitude components of HJZ-8C and EXZ-18C left signals boxcar electricity
Cable；
J) SCX-23A Comprehensive Signal Processings machine is increased newly to the right navigation attitude components of HJZ-8C and EXZ-18C right signals boxcar electricity
Cable；
K) left and right HJZ-8C navigation attitude component cable of newly-increased 13 frame ceiling JL, III plugs to cockpit；
L) 12 groups of non-twisted-pair shielded wire signal cable in original machine is replaced, HJL-31A aviation attitude systems are used for transmission
ARINC429 bus signals；
M) cancel in original machine (A plugs) on EJ-7P 6,7,11,24,25,26,27,28,34,35,36,37,41,42,
43,44,45,51,52 foot leads do insulation processing；
N) cancel in original machine (C plugs) on EJ-7P 6,7,11,24,25,26,27,28,34,35,36,37,41,42,
43,44,45,51,52 foot leads do insulation processing；
O) 31,41,42,43,44,45,46,47, the 52 foot leads for cancelling (E plugs) on EJ-7P in original machine do insulation position
Reason；
P) by wire size is TCS25A, TCS26A, TCS27A after 23,24, the 25 foot leads of (L plugs) on EJ-7P in original machine
Separation crimps hole stick and is inserted into 28,29, the 30 of the plug again；
Q) by (H plugs) redefines on EJ-7P in original machine, cancel 44 foot leads after plug, do insulation processing；Original 34
The taking-up of foot lead is pressed into 44 feet again；Former 43 foot leads taking-up is pressed into 34 feet again；Former 45 foot leads taking-up is pressed into 43 feet again；
+ 27V (from the emergent busbar) power cord newly laid is pressed into 1 foot；+ the 27V newly laid (carrys out) electricity from normal busbar
Source line is pressed into 45 feet；The three-phase alternating current 36V power cords newly laid are pressed into 11,12,13 feet；
R) cancel in original machine after the left and right ZEH-9 plugs of cockpit 6,7,11,24,25,26,27,28,34,35,36,
37,41,42,43,44,45,51,52 foot leads do insulation processing；
S) cancel 31,41,42,43,44,45,46,47,52 foot leads in original machine after navigators cabin ZEH-9A plugs to leave no room for manoeuvre
Edge processing；
T) be HH197A, HH198A by wire size dock with left full attitude gyro in original machine, HH199A, HH217A,
6 conducting wires of HH218A, HH219A are docked with 65,64,63,76,75,74 pins on left signal boxcar, to fly ginseng, TCS
Etc. systems provide attitude signal；
U) it is 4 of HH430A, HH431A, HH441A, HH442A by the wire size docked with right full attitude gyro in original machine
Conducting wire docks (76,65 ground connection on right signal boxcar) with 64,63,75,74 pins on right signal boxcar, for meteorological thunder
Up to etc. systems provide attitude signal；
V) by 2,3,4,5, the 6 foot lead (wire size of XKE30R42Q plugs after navigator's instrument board boat position indicator in original machine
For ZJ625, ZJ626, ZJ627, ZJ454, ZJ455) with 64,63,75,74 pins dock (76,65 on right signal boxcar
Ground connection), provide attitude signal for systems such as weather radars.
W) 36,35 pins at the plug of the former ends TNL2101 are moved on into 58,57 pins；Again a twisted pair line connection is laid
P, q pin of SIU-108 interconnection of signals box J-2 plugs to Comprehensive Signal Processing machine J plugs 8,9 pins, for show GPS system
The drift angle of offer and yaw away from.
X) yaw on navigator's instrument board is cancelled away from original machine circuit on/navigation channel lever switch, insulating wrapping；Yaw is away from end
Ground connection, navigation channel rod end is hanging, and 7 pins of centre termination Comprehensive Signal Processing machine J plugs are effectively believed to provide GPS to aviation attitude system
Number.
Y) twisted-pair feeder is laid again for controlling " left side to/right side to " signal, connection Comprehensive Signal Processing machine A plugs
46,47 pins drive the intermediate ends on " left side to/right side to " for instrument board to a left side, a left side to an end connection left side drive boat position indicator plug 46,
46,47 pins of boat position indicator plug are driven on 47 pins, the right side to the end connection right side.
Note：W, x, y are directed to certain prototype aircraft.Since the aviation attitude system of certain prototype aircraft receives the analog signal that GPS comes
(drift angle, yaw away from), and the optical fiber aviation attitude system after reequiping only receives HB6096 signals (drift angle, yaw away from), to keep
Normal crosslinking between the two carries out insulation shielding, by the inclined of GPS to the drift angle of GPS, yaw away from analog signal (35,36)
Angle, yaw P, Q away from digital signal (57,58) access SIU-108 interconnection of signals boxes are flowed, other make adaptability change.
4. compass calibration
The compass calibration mode of optical fiber aviation attitude system changes, and magnetic deviation binding device is accessed by ATE interfaces, by magnetic deviation
Calibration request adjusts bearing of aircraft position, and binds magnetic heading true value by magnetic deviation binding device, and 8 positions sieve is carried out to aircraft
Difference calibration.HJL-31/31A optical fiber aviation attitude system is in first installation or replaces GCJ-10 (I) Strapdown Magnetometer Sensors or HJZ-8A boats
Magnetic deviation calibration should be carried out to system, after appearance component to ensure system magnetic heading precision.
It summarizes：
1. by installation site of the former HZX-1M aviation attitude systems department enclosure on machine, HJL-31/31A optical fiber navigation attitudes are drawn out
The installation diagram of system；By former HZX-1M aviation attitude systems to external crosslinking relationship, draws out and grasp HJL-31/31A optical fiber navigation attitudes system
Schematic diagram, the feed patten of system；Arrangement and method for construction, reform technology, repacking record are reequiped by retrofit technology programming；Reequip equipment
Selection has qualification production of units；Technical support is provided for the smooth development of repacking.
2. the conducting wire replaced all using shielding line, avoids the electromagnetic interference caused by new system is reequiped.
3. the switch and label that more renew.
4. customized new magnetic deviation binds box, magnetic deviation calibration is carried out using new method.
Although the present invention is disclosed as above with preferred embodiment, however, it is not to limit the invention, any this field skill
Art personnel, without departing from the spirit and scope of the present invention, when can make a little modification and it is perfect, therefore the present invention protection model
It encloses to work as and is subject to what claims were defined.
Claims (8)
1. a kind of aircraft optical fiber aviation attitude system method of modifying, it is characterised in that：
The repacking of department enclosure：
1) HJZ-8C navigation attitudes component
HJZ-8C navigation attitude components are the core components of HJL-31/31A aviation attitude systems, are used for the course angle and posture of survey aircraft
Angle is exported by digital bus interface RS422 and gives signal boxcar, is exported to each bearing indication by HB6096 digital interfaces
Device；And the RS422 digital signals that real-time reception control box is sent, latitude amendment is carried out to navigation attitude component, passes through digital output modul
Navigation attitude component operation in magnetic/half, assist state soon；
Do not deviate from screw by 4 on HJZ-8C navigation attitude components, HJZ-8C navigation attitude components are fixed onPinboardOn, pinboard
It is fixed on former full attitude integration gyro supporting plate by the mounting screw of former full attitude integration gyro；
For the characteristic of HJZ-8C navigation attitude components, need to calibrate pinboard；When calibration, it will turn by adjusting gasket
Fishplate bar levelling ensures that it is horizontally mounted precision ± 0.2 °, the requirement of orientation installation accuracy ± 0.2 °；
2) EXZ-18C signals boxcar
EXZ-18C signal boxcars are used to the RS422 flight attitude signals of the HJZ-8C digital quantities exported being converted to the same of analog quantity
Device signal is walked, comprehensive pathfinder is output on machine, indicates the magnetic heading of aircraft, output is to horizon indicator on machine, instruction
The posture of aircraft, while miscellaneous equipment exports the navigation attitude information of analog quantity on machine；And output monitoring effective information；
EXZ-18C signal boxcars are electronic unit, and shape is rectangle chassis design；Because original machine is only fitted with 1 amplification
Device supporting plate, and EXZ-18C signal boxcar sizes are big, group amplifier is too many, need to separately increase by 1 group amplifier supporting plate (Y8-
7707-65) and one, 20 bugle aluminium, by the way that 2 EXZ-18C signal boxcars are mounted on supporting plate with punching on supporting plate；
When repacking, left EXZ-18C signals boxcar is installed on group amplifier position in left and right in original machine, right EXZ-18C signals boxcar
It is installed on newly-increased group amplifier supporting plate.
2. a kind of aircraft optical fiber aviation attitude system method of modifying as shown in claim 1, it is characterised in that：
3) GCJ-10 (I) Magnetic Sensor
GCJ-10 (I) sensor is used for ground magnetic component of the sensitive earth magnetic field in the horizontal direction on two quadrature axis, and by earth magnetism
Component signal is transferred to HJZ-8C navigation attitude components, and navigation attitude component calculates the magnetic heading of aircraft accordingly；With two GCJ-10 (I) magnetic
Sensor substitutes original two GHC-5 induction type magnetic course transmitters, and installation dimension is identical as the GHC-5 that original machine is equipped with, former
It replaces position；
4) SCX-23/23A Comprehensive Signal Processings machine
Connection and the converting of working condition of the SCX-23/23A Comprehensive Signal Processing machines for system integral unit, built-in modulus turn
Telecompass, inertial navigation/strapdown on machine are whipped and lead, the analog signal of microwave landing/course downslide system input, open by thread-changing road
OFF signal, which is transformed to HB6096 digital signals, to be given each liquid crystal indicator and shows；
The EJ-7P relay boxes that original machine is equipped with are replaced with into SCX-23/23A Comprehensive Signal Processing machines in situ, installation dimension is constant；
There are ten sockets on SCX-23/23A Comprehensive Signal Processing machines, the symbol being connected with miscellaneous equipment is labelled on panel, it is comprehensive
4 screw locks in the upper and lower part of signal processor.
3. a kind of aircraft optical fiber aviation attitude system method of modifying as shown in claim 2, it is characterised in that：
5) EK-3F control box
EK-3F control box uses Design of digital, cancels orientation setting knob, amount of unbalance in former control box and corrects potentiometer,
Retain left-often-right cut is changed, magnetic-half is converted, north-south conversion, rapid coordination button and latitude debugging functions, and by each of reservation
Signal is converted to digital signal and gives navigation attitude component；EK-3F control box is installed on the controls of the EK-3 on original machine navigator's instrument board
Box position, shape installation dimension is identical as the EK-3 that original machine is equipped with, in situ to replace；
6) ZEH-9 course positions indicator, ZEH-9A course position indicators
ZEH-9 course positions indicator (2) installation dimension is identical as ZEH-1R (B) the course position indicators that original machine is installed,
It is respectively arranged on left and right instrument board, it is in situ to replace；
ZEH-9A course positions indicator (1) installation dimension is identical as ZEH-1S (B) the course position indicators that original machine is installed,
It is installed on navigator's instrument board, it is in situ to replace.
4. a kind of aircraft optical fiber aviation attitude system method of modifying as stated in claim 3, it is characterised in that：
7) ZHL-6 navigator's indicator
ZHL-6 navigator's indicator (1) is installed on navigator's instrument board the indicator post that navigates,
It is in situ to replace；8) ZHZ-4A integrates pathfinder
Original two ZHZ-4A synthesis pathfinder retains constant on machine；
9) cancel product
Cancel two FZ-3B group amplifiers；
Cancellation system is crosslinked relationship with angular velocity signal device.
5. aircraft optical fiber aviation attitude system method of modifying as claimed in claim 4, it is characterised in that：
The repacking of power-supply system
Optical fiber aviation attitude system power type is identical as original system, is direct current 28V, single phase ac 115V, three-phase alternating current 36V, system
The reference power source that single phase ac 36V, 26V, three-phase alternating current 36V power supplys are only converted as synchronizer excited signal and digital-to-analog
It uses；
After optical fiber navigation attitude adaptive improvement, system power supply consumption power is adjusted, and the power consumption of direct current 28V is by original
Be adjusted to no more than 70W be not more than 500W (low temperature limit), single phase ac 115V consumption power and three-phase alternating current 36V consumption
Power is reduced；
1) DC electrical load and power supply capacity analysis
A) direct current power load is analyzed
Direct current emergency load variable quantity is：" it is emergent to cancel equipment "+" it is emergent to be installed in addition with equipment "=(- 10+15) × 0.7 × 28 ×
10-3=0.098kW (0.7 is fuse correction factor), i.e. direct current emergency load increases 0.098kW；Direct current normal load becomes
Change amount is：" it is normal to cancel equipment " (0.7 is fuse to+" it is normal to be installed in addition with equipment "=15 × 0.7 × 28 × 10-3=0.294kW
Correction factor), i.e. direct current emergency load increases；DC load variable quantity adds up to：Direct current emergency load variable quantity+direct current is just
Normal load variation amount=0.098+0.294=0.392kW；
B) power supply capacity is analyzed
A) QF12-1 capacity analysis
8 QF12-1 direct current 28V power supply capacities are 86.4kW.Then by b) item it is found that the capacity of aircraft direct current 28V power supplys is abundant
Degree is 38%.So it could be assumed that：8 QF12-1 dc generators power supply capacities can meet full machine direct current 28V and normally supply
Electricity demanding；
When into emergency service state, the emergent busbar power supply of the 4th, No. 5 QF12-1 generator direct current of normal work, general power
For 21.6kW (taking electric correction factor 0.9), aircraft direct current emergency service demand can be met；By b) load analysis knot
Fruit, direct current emergency load increases 0.098kW after repacking；
B) QF-24 capacity analysis
When flying height in 4200m hereinafter, WDZ-1 auxiliary power units can be started, powered from QF-24 to emergent power grid, capacity
For 18kW；By b) load analysis as a result, direct current emergency load increases 0.098kW after repacking；
C) 12-HK-28 capacity analysis
The power supply capacity of separate unit 12-HK-28 batteries is 28AH, and four battery parallel operation capacity are 112AH, at 8
When QF12-1 whole failures to direct current meet an urgent need busbar power supply；By b) load analysis as a result, repacking after direct current emergency load
0.098kW is increased before opposite repacking, so, after 12-HK-28 DC storage battery cell group emergency service capacity can also meet repacking
Direct current emergence power demand；
2) direct current 27V power supplys
To adapt to the power supply characteristic of new equipment, when repacking, meeting an urgent need from 24 frames increases by 1 road 27V power supplys on block terminal (fuse is
TB-15 the H plugs of SCX-23/23A Comprehensive Signal Processing machines) are connected to by the power switch of navigator's instrument board, for navigating
The work of the right system of appearance, 1 road 27V power supplys (fuse is changed to TB-15 by TB-10) originally are used for the work of the left system of navigation attitude；
3) exchange 36V400Hz (three-phase)
Newly-increased 1 road three-phase 36V power supplys, make left and right aviation attitude system possess independent current source, do not interfere with each other；When repacking, match from 8 frame 36V
Increase by 1 road three-phase 36V power supplys (fuse TB-10) on electric box and SCX-23 is connected to by the power switch of navigator's instrument board
(A) the H plugs of Comprehensive Signal Processing machine, are used for the work of the right system of navigation attitude, and 1 road three-phase 36V power supplys originally are left for navigation attitude
The work of system.
6. aircraft optical fiber aviation attitude system method of modifying as claimed in claim 5, it is characterised in that：
The repacking of cable on machine
Optical fiber aviation attitude system changes the outfit former cable on full utilization machine, is adjusted to the definition of original machine cable interface, in crosslinking component
Between increase transit cable, on guarantee machine be crosslinked relationship it is constant, it is specific as follows：
1) GCJ-10 (I) Strapdown Magnetometer Sensor replaces GHC-5 in situ, and the cable on product connection machine can utilize original plug pair
It connects, but because the signal transmission of GCJ-10 (I) Strapdown Magnetometer Sensor changes, transit cable need to be installed additional, cable routing is 13 frame ceilings
On JL3 (P32J3AQ) banjos along leader cable move towards to the cable trough on the left of 9 frame hatch doors down to floor under again directly with
HJZ-8C navigation attitude components dock, former dressing of cable and insulation processing；
2) direct line between EXZ-18C signals boxcar and HJZ-8C navigation attitude components, does not utilize cable on machine；
3) SCX-23/23A Comprehensive Signal Processings machine reequips outer cable；
N, Q multi-plug cables are directly connected to by transit cable and EXZ-18C, HJZ-8C；
L cables are connect with navigator's instrument board ZHL-6, and prototype utilizes original machine cable, and without modification, prototype need to be by L cables
On be supplied to the course signal of TCAS to be changed to L27, L28, L29 by L23, L24, L25, remaining is constant；
J cables are connected with external cross-linking equipment on machine, using original machine cable, without modification；
H cables are connect with power supply on machine, to ensure that left and right system is independently-powered, improve aircraft safety, it is straight need to increase 28V all the way
Stream input, increases by one group of three-phase 36V input, and H cables need to carry out adaptive improvement；
Cancel connecting cable between SCX-23/23A Comprehensive Signal Processings machine I, G plug and 2 FZ-3B, original machine cable is vacant.
7. aircraft optical fiber aviation attitude system method of modifying as claimed in claim 6, it is characterised in that：
It is specific as follows：
A) cancel in original machine EJ-7P relay boxes to left attitude gyro cable entirely；
B) cancel in original machine EJ-7P relay boxes to right attitude gyro cable entirely；
C) cancel in original machine EJ-7P relay boxes to left group amplifier cable；
D) cancel in original machine EJ-7P relay boxes to right group amplifier cable；
E) left and right comprehensive indicator cable of cancellation 13 frame ceiling JL, III plugs to cockpit；
F) in situ to replace original+27V emergency service cables, it is used for the left system power supplies of HJL-31A；
G)+27V normal power supply cables are increased newly, are used for the right system power supplies of HJL-31A；
H) three exchange 36V service cables all the way are increased newly, are used for the right system power supplies of HJL-31A；
I) SCX-23A Comprehensive Signal Processings machine is increased newly to the left navigation attitude components of HJZ-8C and EXZ-18C left signal boxcar cables；
J) SCX-23A Comprehensive Signal Processings machine is increased newly to the right navigation attitude components of HJZ-8C and EXZ-18C right signal boxcar cables；
K) left and right HJZ-8C navigation attitude component cable of newly-increased 13 frame ceiling JL, III plugs to cockpit；
L) 12 groups of non-twisted-pair shielded wire signal cable in original machine is replaced, the ARINC429 for being used for transmission HJL-31A aviation attitude systems is total
Line signal；
M) cancel in original machine (A plugs) on EJ-7P 6,7,11,24,25,26,27,28,34,35,36,37,41,42,43,
44,45,51,52 foot leads do insulation processing；
N) cancel in original machine (C plugs) on EJ-7P 6,7,11,24,25,26,27,28,34,35,36,37,41,42,43,
44,45,51,52 foot leads do insulation processing；
O) 31,41,42,43,44,45,46,47, the 52 foot leads for cancelling (E plugs) on EJ-7P in original machine do insulation processing；
P) by original machine on EJ-7P after 23,24, the 25 foot leads of (L plugs) wire size be TCS25A, TCS26A, TCS27A detach,
Again crimping hole stick is inserted into 28,29, the 30 of the plug；
Q) by (H plugs) redefines on EJ-7P in original machine, cancel 44 foot leads after plug, do insulation processing；Former 34 feet draw
Line taking-up is pressed into 44 feet again；Former 43 foot leads taking-up is pressed into 34 feet again；Former 45 foot leads taking-up is pressed into 43 feet again；It is new to apply
If+27V (from emergent busbar) power cord be pressed into 1 foot；+ the 27V newly laid (carrys out) power cord from normal busbar
It is pressed into 45 feet；The three-phase alternating current 36V power cords newly laid are pressed into 11,12,13 feet；
R) cancel in original machine after the left and right ZEH-9 plugs of cockpit 6,7,11,24,25,26,27,28,34,35,36,37,41,
42,43,44,45,51,52 foot leads do insulation processing；
S) cancel 31,41,42,43,44,45,46,47,52 foot leads in original machine after navigators cabin ZEH-9A plugs and do insulation position
Reason；
T) be HH197A, HH198A by wire size dock with left full attitude gyro in original machine, HH199A, HH217A, HH218A,
6 conducting wires of HH219A are docked with 65,64,63,76,75,74 pins on left signal boxcar, are carried to fly the systems such as ginseng, TCS
For attitude signal；
U) it is 4 conducting wires of HH430A, HH431A, HH441A, HH442A by the wire size docked with right full attitude gyro in original machine
(76,65 ground connection on right signal boxcar) are docked with 64,63,75,74 pins on right signal boxcar, are weather radar etc.
System provides attitude signal；
V) by 2,3,4,5, the 6 foot lead of XKE30R42Q plugs after navigator's instrument board boat position indicator in original machine, (wire size is
ZJ625, ZJ626, ZJ627, ZJ454, ZJ455) with 64,63,75,74 pins dock that (76,65 on right signal boxcar connect
Ground), provide attitude signal for systems such as weather radars；
W) 36,35 pins at the plug of the former ends TNL2101 are moved on into 58,57 pins；Again a twisted pair line connection SIU-108 is laid
P, q pin of interconnection of signals box J-2 plugs show that GPS system provides to 8,9 pins of Comprehensive Signal Processing machine J plugs
Drift angle and yaw away from；
X) yaw on navigator's instrument board is cancelled away from original machine circuit on/navigation channel lever switch, insulating wrapping；Yaw is away from termination
Ground, navigation channel rod end is hanging, and 7 pins of centre termination Comprehensive Signal Processing machine J plugs are effectively believed to provide GPS to aviation attitude system
Number；
Y) lay twisted-pair feeder again for controlling " left side to/right side to " signal, connection Comprehensive Signal Processing machine A plugs 46,
47 pins drive the intermediate ends on " left side to/right side to " for instrument board to a left side, and a left side is driven 46, the 47 of boat position indicator plug to an end connection left side and drawn
46,47 pins of boat position indicator plug are driven on foot, the right side to the end connection right side.
8. aircraft optical fiber aviation attitude system method of modifying as claimed in claim 7, it is characterised in that：
The compass calibration mode of optical fiber aviation attitude system changes, and accesses magnetic deviation binding device by ATE interfaces, is demarcated by magnetic deviation
It is required that adjustment bearing of aircraft position, and magnetic heading true value is bound by magnetic deviation binding device, 8 positions magnetic deviation mark is carried out to aircraft
Fixed, HJL-31/31A optical fiber aviation attitude system is in first installation or replaces GCJ-10 (I) Strapdown Magnetometer Sensors or HJZ-8A navigation attitude groups
Magnetic deviation calibration should be carried out to system, after part to ensure system magnetic heading precision.
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| CN201810428636.4A CN108657450A (en) | 2018-05-07 | 2018-05-07 | Aircraft optical fiber aviation attitude system method of modifying |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109533359A (en) * | 2018-12-20 | 2019-03-29 | 西安飞机工业（集团）有限责任公司 | A kind of optical fiber navigation attitude instrument system using electromechanical data indicating equipment |
| CN109581245A (en) * | 2018-11-30 | 2019-04-05 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft electric load statistics and power supply capacity analysis method and system |
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Application publication date: 20181016 |