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30V / 1000 Amps. DC POWER SOURCE SUPPLY |
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(Uese for testing and starting of SU-30 Aircraft)
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The DC power supply source 30V/1000A is used to start the engine of special
types of aircraft. The salient features of this Power Supply is to provide a
very stable output voltage which is less than 1% with the load current varying
from 0% to 120% of the rated current. Very low ripple contents in the output.
Protection against the load under voltage, over voltage and over load are
provided. |
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TECHNICAL SPECIFICATION OF DC POWER SUPPLY SOURCE |
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The total power supply source consists of one no. main Rectifier unit and two no. DC
Regulator units connected to it. |
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Their technical specifications are given below :- |
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A |
MAIN RECTIFIER UNIT |
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A1 |
INPUT |
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A1.1 |
Voltage |
415V ± 10% |
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A1.2 |
Phase |
Three |
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A1.3 |
Frequency |
50Hz. ± 3 Hz. |
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A1.4 |
Ambient (operating) |
-5°C to +55°C, 45% RH |
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A1.5 |
Abbient storage |
-20°C to +70°C |
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A1.6 |
Altitude |
Upto 1000 meter above main sea level |
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A2 |
OUTPUT |
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A2.1 |
Voltage |
32V-37V DC |
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A2.2 |
Current (continuous) |
1000A DC |
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A2.3 |
Current (Overload) |
150% for 60 Sec
120% for 10 Monutes |
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A2.4 |
Regulation (Auto mode) |
<3% |
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Ripple |
<1% RMS at resistance load. |
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A2.5 |
Indication |
R, Y, B Phase ON
Rectifier On
Single phasing/ Phase fail
Output Over voltage
Output Over load |
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A2.6 |
Protection |
Single Phasing/ Phase Fail
DC Over Voltage
Overload (by droop through electroincs feed back) |
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A2.7 |
Meters |
Incoming AC voltage
Incoming AC current
Total Output DC current & Output voltage |
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B |
VOLTAGE REGULATOR UNIT |
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B1 |
INPUT VOLTAGE |
32V-37V DC fed through 95 Sq. mm. Cable from the main rectifier |
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B2 |
OUTPUT |
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B2.1 |
Voltage |
28V-32V (Adjustable with potentiometer) |
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B2.2 |
Current (Continuous) |
600A each |
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B2.3 |
Current (overload) |
150% for 60Sec
120% for 10 minutes |
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B2.4 |
Regulation |
Regulation |
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B2.5 |
Ripple |
Less than 200 mV (P-P) |
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B2.6 |
Indications |
Input On
Output Ok
regulation Fail |
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B2.7 |
Protection |
Output Over voltage
Output over voltage
Output overload (fold back) |
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B3 |
DIMENSION (LxWxD) |
650x1070x650 mm (without wheel) |
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B4 |
TYPE OF ENCLOSURE |
Mounted on Rubberized wheels |
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BATTERY CAPACITY TESTER FOR INDIAN AIR FORCE |
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Fully Solid-State Battery Capacity Test Equipments designed and manufactured by
STATCON are very useful for discharging & Capacity checking of |
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Silver Zinc Oxide Aircraft Batteries
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Ni-Cd / Lead Acid Aircraft Batteries
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Any other type of Batteries
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The capacity range of Battery Capacity Testers are suitable for: |
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6V/ 12V/ 28V/ 30V Batteries.
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1V/ 2V single cell.
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Discharge current settable from 0.5A to 50A.
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Custom built designs for higher voltage and current.
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The Battery Capacity Tester is a fully Solid-State equipment
with built in solid-state resistance to discharge the battery. Thus it maintains
the discharge current within ±2% of set value irrespective of falling
Battery voltage. This is done because the resistance adjusts itself
as per the battery or even single cell voltage. The discharger uses
microprocessor-based control for all its measurements, controls and protections.
It is provided with following features. |
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- Option available for operation on mains/ service battery.
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- Controls available so as to test batteries at various conditions.
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- Fully solid state with microprocessor based control.
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- Protection against wrong battery selection/misuse
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- Measurement of voltage, current
and actual Ampere-Hour (AH) and their display.
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- Compact, light weight and user friendly.
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It is the reliability, accuracy and user friendliness that
IAF, Army, Navy and even Govt. Test House is using above equipment. The
equipment is tested as per JS 555 for environmental conditions. |
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6KW /28V RECTIFIER TRANSPORTABLE FOR INDIAN AIR FORCE |
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The Silent Ground STARTER MAINTENANCE UNIT for various Aircrafts
High current solid state DC power supply, 28KW / 24V for Aircraft ground
servicing and engine starting. The salient features of this power supply are
supplying a continous current upto 200A with a regulation of ± 1Volts for ground
servicing application, providing a load of 1500 A intermittently having a duty
cycle consisting of 1500A peak current which, gradually loweres to 200A in 30
second. The rectifier is designed to withstand three such duty cycle with a gap
of 30 seconds between each and remain undamaged in any embient temperature
between -40°C and -70°C and operate satisfactorily any where between -10°C and
+50°C. |
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Advantages of solid state technology are: |
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No moving parts, hence very little or nil maintenance.
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No exhaust fumes and very low noise pollution.
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Saves fuel when aircraft is on
ground.
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Useful in hangers due to low maintenance, no exhaust, fumes and no noise.
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TECHNICAL SPECIFICATION OF RECTIFIER TRANSPORTABLE |
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SL No. |
Details |
Particulars |
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1.0 |
Name of Equipment |
6KW/ 28V Rectifier Transportable |
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2.0 |
Conforming specification |
DTD & P (Air) E&1-239 Issue no. 3 with amendment &
supplement no. 01/96 to the specification. |
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3.0 |
Input |
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3.1 |
Voltage |
415V, +8%, -4% |
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3.2 |
Phase |
Three |
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3.3 |
Frequency |
50 Hz Nominal |
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3.4 |
Ambient (Operating) |
-10 degree centigrade to +50 degree centigrade 90-95% RH |
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3.5 |
Ambient (Storage) |
-40 degree centigrade to +70 degree centigrade |
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3.6 |
Altitude |
1000 M above MSL |
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4.0 |
Output |
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4.1 |
Voltage (Ground Service) DC |
28V ± 1 Volts, at 200 Amps conditions |
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4.2 |
Voltage (Aircraft Engine Starting) |
17.5 to 22V at 1500 Amps intermittely |
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4.3 |
(A) Current rating |
200 Amps continues |
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(B) Capacity |
6 KW |
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4.4 |
Voltage adjustment |
4 way voltage selector switch through control of incoming AC voltage
tappings of the transformer |
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5.0 |
Indication |
Rectifier 'ON' through pig tail lamp |
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6.0 |
Measuring Instrument |
One no DC voltmeter and ammeter |
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7.0 |
Dimension HxWxD (mm) |
1100 x 675 x 960 |
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8.0 |
Weight |
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9.0 |
Type of enclosure |
Wheel mounted trolley with cannopy at the top. |
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40KVA GROUND POWER UNIT (GPU) |
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Is used for ground starting and maintenance of Aircraft. It is self
propelled unit mounted on moving Trolley and gives 400Hz. AC as well as 28V DC
(upto 1250 Amps). Suitable for Russian and other Aircrafts, Helicopters.
GPU for other defence as well as commercial Aircraft is also available on
request. |
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SCHEDULE OF GUARANTEED TECHNICAL PARTICULARS OF GPU |
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SL No. |
Details |
Particulars |
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1.0 |
Name of Equipment |
Ground Power Unit (GPU) |
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2.0 |
Ambient |
-20°C to +55°C / 95% RH at +40°C |
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3.0 |
Altitude |
Upto 1500meter above MSL |
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4.0 |
Type of application |
Ground Starting of Aircraft (Helicopter) |
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5.0 |
Details of Engine |
Turbo changed, Air cooled, 2000 RPM Engine |
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5.1 |
Type of Govetnor |
Electronic Governor |
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5.2 |
Type of cooling |
Air Cooled |
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5.3 |
Type of Start/Stop |
Electric through 24V DC |
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5.4 |
Details of Engine protection |
Over Speed
Low Fuel
Low Lube Oil Pressure
High Cylinder head Temperature
V-Belt failure |
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5.5 |
Type of mounting |
Engine mounted on 4 nos anti-vibration mounting pads. |
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6.0 |
Details of Alternator |
Brushless, high reliability, 400Hz alternator |
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6.1 |
Output Frequency |
400Hz (393 to 407Hz) |
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6.2 |
Output voltage (P-N) |
115V (108V to 118V) |
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6.3 |
Voltage Phase difference |
116 to 124 |
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6.4 |
Voltage unbalance |
3V max |
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6.5 |
Crest Factor |
1.31 to 1.51 |
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6.6 |
Sistortion Factor |
5% max |
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6.7 |
Frequency Drift |
@ 15 Hz per minute |
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6.8 |
DC component |
+0.10 to -0.10 volts |
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6.9 |
Transient Characteristics |
Conforming to MIL Std 704D for both voltage and frequency transients |
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7.0 |
Output of the GPU |
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7.1 |
AC output |
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7.1.1 |
Power |
25KVA at 0.8 lag Power (Continuous) |
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7.1.2 |
Frequency |
400Hz nominal |
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7.1.3 |
Regulation |
Better then +2% |
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7.1.4 |
Output Protection |
*AC under voltage < 177 (P-P)
*AC over voltage 217V-220V -4 Sec
(P-P) 221V - 228V - 2 Sec.
228V - 1 Sec.
*Under Frequency <370Hz. - 5 Sec.
<320Hz. - 0.5 Sec.
*Over Frequency > 430Hz. - 5 Sec.
*Over Load 101% - 110% - 1 Hr.
111% - 125% - 5 min.
126% - 150% - 5 Sec.
>150% - 0.5 Sec.
* Phase Reversal
* Neutral Open |
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7.1.5 |
Indication |
AC output 'ON' indication |
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7.1.6 |
Type of output connection |
Through AC contacror and ON-OFF push buttons, extended through
15 meter cable and 6 pin NATO socket. |
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7.2 |
DC Output |
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7.2.1 |
Power |
28V + 1V / 10KW continuous on 18V to 22V at 1250Amps
intermittent for Engine starting. Thus 3 cycles of such engine
starting with 3 minutes gap for the next lot of 3 such cycles. |
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7.2.2 |
Voltage Range |
22V to 29V |
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7.2.3 |
Ripple |
< 1.5% |
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7.2.4 |
Transient |
Voltage transients conforming to MIL-std 704D |
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7.2.5 |
Protections |
* DC under voltage < 20V - 3 Sec.
* DC Overvoltage > 32V - 10 Sec
> 35V - < 1.5 sec
* DC overload 1257A-1500A - 7 sec
>1500A Instantaneous |
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7.2.6 |
Indication |
DC output 'ON' indication |
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7.2.7 |
Type of output connection |
Through input and output contacror and ON-OFF push buttons,
extended
through 15 meter cable and 3 pin NATO socket. |
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Suitable to connect two Aircraft simultaneously. |
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LOAD BANK |
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MOBILE BATTERY CHARGER |
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