UHF TRANSRECEIVER COM-1150A - Hindustan Aeronautics Limited

Transcription

UHF TRANSRECEIVER COM-1150A
PURPOSE: TO PROVIDE AIR-TO-AIR AND AIR-TO-GROUND RADIO
TELEPHONY COMMUNICATION OVER UHF BAND.
SALIENT FEATURES:
FULLY SOLID STATE
MODULAR CONSTRUCTION
MEETS STRINGENT ENVIRONMENTAL CONDITIONS
HYBRIDIZED CIRCUITS AND MICROPROCESSOR
CONTROLLED
SPECIFICATIONS :
FREQUENCY OF OPERATION :
SENSITIVITY
:
225 TO 399.975 MHz
3 μ VOLTS
TRANSMITTER POWER
:
4 WATTS (NOMINAL)
CHANNEL SPACING
:
25 KHz
AVAILABLE CHANNELS
:
7000
PRESET CHANNELS
:
10
ALTITUDE
:
21.3 Km
APPLICATIONS: Fitted in following Aircraft
JAGUAR
HAWK-AJT
MiG27
Bison
AUDIO MANAGEMENT UNIT (AMU)
PURPOSE:
TO PROVIDE INTERCOMMUNICATION
BETWEEN COCKPIT CREW & GROUND
CREW, INTERFACE AND CONTROL OF
MIKE & AUDIO LINES OF RADIO SETS
AND WARNING AUDIO INTERFACE
SALIENT FEATURES:
 ‘VOICE OPERATED SWITCH’ IN INTERCOM MODE FOR HANDS FREE
OPERATION
 BUILT IN DUAL REDUNDANCY FOR RELIABLE OPERATION
 CENTRAL CONTROL FOR COMMUNICATION & NAVIGATION
EQUIPMENT
 AUDIO OUTPUT FOR VOICE RECORDER
 LRUs
1. STATION BOX (COCKPIT MOUNTED)
2. JUNCTION BOX (MOUNTED IN EQUIP. BAY)
SPECIFICATIONS:
 MIKE INPUT
:
2 mV / 150 ohms
 AUDIO OUTPUT
:
150 mW / 150 ohms
 POWER SUPPLY :
28V DC ( Complying to MIL-STD-704D )
 OPERATING
TEMPERATURE
 CROSSTALK
:
- 400 TO + 710 C
:
50 dB minimum
 SIGNAL TO NOISE
RATIO
:
≥ 50 dB
PLATFORMS:
ALH (AMU-1311A), LCA (AMU-1310A) & IJT (AMU-1305A)
DACS 2300A SERIES – DIGITAL AUDIO CONTROL SYSTEM
In modern aircrafts, the Pilot is engrossed in a
wide range of communication signals viz.,
The Digital Audio Control System design is
Transceiver audios, Receiver audios, Warning
derived from the extensive experience from
audios
audios.
analog Audio Management Unit configurations
Digital Audio Control System (DACS) eases
developed for and being used in LCA, IJT, ALH,
the Pilot’s burden by efficiently minimizing
MiG21 BIS Upgrade and MiG27 Upgrade
the controls, interfacing all the signals in a
aircrafts.
logical manner and provides the following
Solid-state
functions:
construction provides long life, high reliability

Intercommunication between Flight
and excellent maintainability for both new and
Crew and Ground Crew.
retrofit applications on fixed wing and rotary
Interface and control of mike and
wing platforms. The DACS is a compact,
headset audio signals of various
lightweight and low cost system.
transceivers.
The DACS 2300A series meets stringent MIL

Interface of warning signals.
STD requirements like MIL STD 810F and MIL

Interface
and

Intercommunication
to
the
Cockpit
Voice
Recorder and Voice Data Recorder.
Digital
Audio
Control
System
(DACS)
implements audio signal conditioning in digital
domain using digital signal processing techniques
and provides better signal quality by using
efficient Adaptive Noise Cancellation (ANC)
algorithm.
STD 461C/E.
modular
design
and
rugged
Key features





Lightweight, compact & solid-state design
DSP based Adaptive Noise Cancellation (ANC)
& Voice operated switch (VOS) algorithms
Extensive Self-test and Built In Test
Automatic change over to standby Power
Supply path in case of failure in Normal power
supply path
Reliable dual redundant functional channels
for safe operation
DACS 2300A







In-situ adjustment of Mike and Audios through
USB interface
Front panel VOS adjustment
NVG compatible panel illumination
MIL STD 1553B Interface
ARINC 429 interface
ETHERNET Interface
USB Interface
configurations:

DACS-Single LRU version: DACS Qty:1 no for Fighter aircrafts
146mm (W) X 67mm (H) X 180mm (D)
Wt: 1.5 Kg max

DACS -Split LRU version : Remote Junction Box (RJB) Qty:1 no
Dimensions: 227mm (W) X 113mm (H) X 153mm (D)
Wt: 2.2 Kg max
Audio Control Panel (ACP) Qty: 2 no’s to 4 no’s depending up on the platform
Dimensions: 146mm (W) X 67mm (H) X 122mm (D)
Wt: 0.9 Kg max
Specifications
Specifications Contd…
III.SYSTEM SPECS
I.ELECTRICAL SPECS
Power Supply
Power Consumption
Current Rating
II.INTERFACE SPECS
Digital I/O
Audio Input
Audio Output
Discrete Input
28 V DC as per MIL-STD-704D
45 W Max
1.5 A Max at 28 V DC
SNR
Distortion
Frequency response
MIL STD 1553B, ARINC 429,
ETHERNET & USB.
a)2.5 V to 5.5 V rms from avionics
on board
b)4mV rms from Microphone
a)Headset output : 150mW across
150 Ω
b)Recording output: 2 to 15mW
across 600 Ω and NLT 4.5V across
10K Ω
5V and 28V
For more information:
Strategic Electronics Research & Design Center
Hindustan Aeronautics Limited
Balanagar, Hyderabad – 500042
Ph- +91-40-23878281 Ext: 6200
Fax: +91-40-23879570
www.hal-india.com
Cross talk
Self test
IV.QUALIFICATION
and COMPLIANCE
EMI/EMC
Environmental
Reliability(MTBF)
PLATFORMS
NLT 40 dB
NMT 5%
NMT3 dB from 300Hz to 3500Hz
NLT 50 dB
POST, IBIT and CBIT.
MIL STD 461E
MIL STD 810F
>5000 Hours as per as per MIL
HDBK 217
LCA Mk I, LCA Mk II, LCH, LUH and
HTT40
INTEGRATED RADIO COMMUNICATION SYSTEM
INCOM 1210A & VARIANTS WITH CONTROLLERS
PURPOSE:
FOR PROVIDING AIR–AIR & AIR–GROUND
RADIO COMMUNICATION IN NORMAL /
SECURE, AM / FM / FSK & VOICE / DATA
MODES WITH ECCM FEATURES
SALIENT FEATURES:
 COMMUNICATION SECURITY (COMSEC) IN BOTH VHF / UHF &
TRANSMISSION SECURITY (TRANSEC) IN UHF BAND
 FREQUENCY HOPPING & DIRECT SEQUENCE SPREAD
SPECTRUM
 VOICE / DATA SECURITY
 HOMING AND GUARD PRECEDENCE MODES
SPECIFICATIONS:
 FREQUENCY RANGE
:
108 MHz - 399.975 MHz
 TOTAL NO. OF CHANNELS
:
9240
 Rx. SENSITIVITY
:
2 MICRO VOLTS
 Tx. POWER
:
20 WATTS
 WEIGHT
:
10 Kgs.
PLATFORM:
MiG 21 BIS UPGRADE, LCA, HJT-36, AJT, MiG 27 UPGRADE,
JAGUAR UPGRADE, DORNIER (NAVY)
Advanced Communication System – ACS 235
For critical flight regimes, HAL’s V/UHF Tactical
Airborne Transceivers provides today’s flight
crews with dependable, highly accurate air to air
and air to ground communication.
ACS-235, lightweight
airborne V/UHF Tactical
Airborne Transceiver is a highly versatile, all solidstate, digital, high frequency radio communication
system intended for both fixed- and rotary-wing
airborne applications.
HAL has
Advanced features include digital signal processing
communication system design and our systems have
(DSP) technology to provide new embedded features
hard won, proven performance in various aircrafts
in an exceptionally lightweight, compact system.
like SU-30, MIG-29UPG, MIG-29K/KUB, IJT, MIG-
Control options for the system provide MIL-STD-
21UPG (BISON), JAGUAR/DARIN-III, ALH, MIG
1553B .Extensive built-in test equipment (BITE) is
27 etc. Our unique combination of deep experience
utilized for diagnostic testing and monitoring.
with a modern digital implementation makes HAL
Built on a strong foundation of quality, ACS-235
Radios the only affordable choice for serious users.
provides users with tactical advantages and lower life
cycle costs.
over 30
years’ experience in airborne
Key features




Multi-mode, multi-band, V/UHF Airborne Transceiver
Direct sequence spread spectrum for low probability of interception
Good co-location for multiple radio installations
Emergency guard receiver for 40.5, 121.5, 156.8 and 243 MHz
GENERAL CHARACTERISTICS
Frequency Range
30 – 407 MHz
Channel Spacing
8.33 kHz; 12.5 kHz; 25 kHz
Modulation Formats
AM, FM, FSK, OQPSK
Power supply
28V DC Nominal
Control
MIL-STD-1553B
MAIN RECEIVER
Sensitivity (10dB Sinad)
< -101 dBm (FM 3kHz modulation)
< -101 dBm (AM 30% modulation)
IF / Image Rejection
Co-location rejection
> 60 dB
+5 dBm Unwanted ≥ 10 % from Fo
GUARD RECEIVER
Frequencies
Sensitivity
40.5 MHz, 121.5 MHz, 156.8 MHz, and 243 MHz
< -95 dBm (FM), < -95 dBm (AM)
TRANSMITTER
RF Output Power
10W (AM), 32.4W (PEP AM)
15W (FM)
Harmonics
< -50 dBc
Spurious emissions
< -60 dBc
ENVIRONMENTAL
Operating Temperature
Vibration, Shock
Supply variations
-40 to + 65 °C
MIL-STD-810F
MIL-STD-704E
EMC
MIL-STD-461C
Altitude
18Kms
PHYSICAL
Size (D x H x W) mm
Weight
PLATFORMS
318 x 195 x 124 (½ ATR Short)
8kg
Advanced Light Helicopter (Dhruv) , Chetak
Hindustan Aeronautics Ltd
Balanagar , Hyderabad – 500042
Ph- +91-40-23878281 Ext: 6200
www.hal-india.com
SOFTNET RADIO
SDR-2010
ROLE
SoftNET radio (SDR-2010) is state-of-the-art 2channel Software Defined Radio working in
V/UHF and L-band to provide simultaneous
voice and data radio communication on both
fixed wing and rotary wing aircrafts for tactical
/ Network Centric Operations. Can be configured
for
Ground
Operation
with
HighPower
amplifiersThe radio is capable of working with
legacy systems and is inter-operable with
existing radio systems.
SDR-2010 can be programmed with different
waveforms to cater to the needs of the operator
using Radio Waveform Manager.
SALIENT FEATURES
SoftNET Radio SDR-2010
.

SCA 2.2.2 compliant

Reconfigurable architecture

Scalable
architecture
with
growth
potential for UHF Satcom and S-band.

Network Centric Operation ready with
Dynamic Masterless Adhoc Networking
over Frequency Hopping @ 500Hops/Sec
(upgradable to 1000 Hops/Sec)

Handles user data rates upto 1 Mbps.

High level of COMSEC AND TRANSEC
FEATURES

Networking Scenario
Embedded GPS receiver with standard
aircraft control interfaces
DEPLOYMENT: Fixed wing & Rotary wing Aircraft
Strategic Electronics Research & Design Center (SLRDC)
Balanagar, HYDERABAD – 500 042 INDIA
Ph: +91-40-2387 8438 Ph: +91-40-2387 8438
web: http://www.hal-india.com/randd/strategicelectronics/strategicelectronics.asp
SLRDC
AUTOMATIC DIRECTION FINDING SYSTEM
ADF - 610A
PURPOSE:
TO PROVIDE INDICATION TO THE PILOT
OF THE DIRECTION OF A GROUND
BEACON
SALIENT FEATURES:
 MODULAR CONSTRUCTION
 PROGRAM FACILITY DURING
FLIGHT
 BUILT IN TEST FACILITY
 MICROPROCESSOR BASED
SPECIFICATIONS:
 FREQUENCY RANGE
: 190 KHz TO 1700 KHz
 CHANNEL SPACING
: 0.5 KHz
 BEARING ACCURACY
:  2
 SENSITIVITY
: 25 MICROVOLTS PER METER(ANT)
50 MICROVOLTS PER METER(ADF)
 RESOLUTION TIME
:  6 Sec
 AUDIO OUTPUT
:  100 MILLIWATTS
PLATFORM:
AN-32, KIRAN, AVRO, DORNIER, JAGUAR, CHETAK & MIG-BIS
UPGRADE
ANS SERIES - VOR/ILS/MARKER RECEIVER
For critical flight regimes, HAL’s ANS series VOR-
Solid-state modular design and rugged construction
ILS systems provide today’s flight crews with
provide long life, high reliability and excellent
dependable, highly accurate bearing and landing
maintainability for both new and retrofit applications
information.
on fixed-wing aircrafts.
This
real-time
system
enhances
operational safety during all-weather approaches
The receiver combines all VOR/ILS/MKR functions
and Landings.
in one compact, lightweight, low-cost system.
The ANS family of VOR/ILS/MKR systems are
The ANS series meets multiple stringent MIL-STD
recognized as a value added solution on multiple
requirements assuring peak performance under the
military platforms. The ANS series systems quickly
harshest Military aircraft environments. With support
gained acceptance as robust VOR-ILS solution and
for both analog and digital interfaces, the ANS is
are installed on a multitude of platforms including
compatible with a variety of aircraft architectures. The
SU-30, MIG-29UPG, MIG-29K/KUB, IJT, LCA
ANS1100A/ANS1101A/ANS2810A/ANS2820A
(A/F),
available
LCA
(NAVY),
MIG-21UPG
(BISON),
JAGUAR/DARIN-III, HAWK-AJT.
The ANS 1100A/ANS1101A/ANS2810A/ANS2820A
is a proven design derived from extensive experience
in navigation, precision approach and landing
systems.
to
meet
FM
broadcast
is
immunity
requirements as defined in ICAO Annex10.
.
Key features









Low power, lightweight solid-state design
Digital Radial/bearing Output
Intensive Self-test and BIT
FM broadcast immunity per ICAO Annex 10
Marker receiver for runway approach
VOR receiver for route navigation
ILS receiver for landing
DSP technology





No of channels :
VOR : 160 channels
LOC / GS: 40 channels
MIL-STD-1553B / ARINC-429 interface
VOR as per RTCA DO-196
LOC as per RTCA DO -195
GS as per RTCA DO -192
Marker as per RTCA DO -143
Additional Options:


ARINC based VOR/ILS controller
ARINC based Interface Unit (IFU) to drive the INPR display
Specifications
PHYSICAL SPECS
Dimensions
Number of channels
318mm x 194mm x 57.2mm
(1/4 ATR short)
Weight
NMT 3.3 Kg (without mounting
tray)
NMT 4.3 Kg (with mounting tray)
Sensitivity:
ELECTRICAL SPECS
Power Supply
Power Consumption
35 W (Max)
Current Rating
INTERFACE
Digital Outputs
MIL-STD-1553B, ARINC 429
Audio Output
ILS/VOR :
10 to
(adjustable)/600 ± 20 Ω
MARKER :
10 to
(adjustable)/600± 20 Ω
Accuracy:
Self-test
100mW
100mW
LOC : 108.10 to 111.95 MHz
GLIDE : 329.15 to 335 MHz
VOR : 108.00 to 117.95 MHz
MKR : 75 MHz
Ph- +91-40-23878281 Ext : 6200
www.hal-india.com
40
40
160
LOC : - 99dBm
Glide : - 87dBm
VOR : - 99dBm
MKR : - 67dBm ± 3dBm (High
Sensitivity),
-53dBm ±3dBm (Low Sensitivity)
LOC: –72dBm to –33dBm < 5%
Glide: –76dBm to –33dBm <13%
VOR : –93dBm to –27dBm < ±3°
POST, IBIT and CBIT.
QUALIFICATION and
COMPLIANCE
EMI/EMC
MIL-STD 461
Environmental
MIL-STD 810F
Reliability(MTBF)
SYSTEM
PARAMETERS
Frequency Range:
LOC
:
GLIDE :
VOR
:
PLATFORMS
>5000 Hours as per as per MIL
HDBK 217
SU-30, MIG-29UPG, MIG-29K/KUB,
IJT, LCA (A/F), LCA (NAVY), MIG21UPG(BISON), JAGUAR/DARIN-III,
HAWK-AJT
TACTICAL AIR
NAVIGATION
Function
TACAN is navigation system to provide crew the slant range
and bearing information from beacon.
TACAN 2901A
Salient Features:
 High speed 32 bit ADSP processor for acquisition of bearing information, distance acquisition and system operation.
 1553B Bus compatibility for both input and output functions.
 Dual Antenna ports with automatic selection.
Platforms:
 Pilot selectable channel type (252 channels:126X and
126Y) and frequency through Mission Computer/Display.
Jaguar DARIN III,
 Bit facility is available for checking the unit serviceability.
DARIN III,Su 30 MKXI,  Solid-state 250W transmitter.
 Beacon identification facility in the output.
Mig 29K,
 Operating Modes: a) Transmit / Receive (with ground
Mig 29 Upgrade,
beacon and airborne beacon)
b) Receive (ground or airborne beacons)
LCA
c) Transmit / Receive (air to air with
same TACAN system)
Operational on 28V dc supply.
 3/8 ATR size (330mmX 91mm X 193mm) and wt: 6.3Kg

H I N D U S TA N
A E RO NAU T I C S
LIMITED
BALANAGAR
HYDERABAD
Pin - 500042
Phone: 040-23775336
Fax:
040-23879570
IDENTIFICATION OF FRIEND OR FOE
IFFT-2410A/IFFT-2420A
Role :
The
IFF
Mode
’S”
Transponder
IFFT
2410A/2420A are airborne electronic identification
equipment to identify aircraft. The system
supports Mode 1, 2, 3/A, C, Civil Mode S Level 2
and Indian Secure Mode.
Salient Features :

High-Speed 32-bit SHARC Processor and
FPGA for
acquisition of interrogation
pulse information & system operation.

Dual Channel Digital receiver for space
diversity operation.

Solid State L-Band Transmitter with active
wave shape control to meet pulse
Spectrum requirements.

Interrogation/Response
Identification
system for MKX, Mode S Level 2 and
Secure Identification through Indian Secure
Mode1 (IS1) (equivalent of NATO Mode 4).

Air Traffic Management through Elementary
and Enhanced Surveillance which aids in
enhanced situational awareness.

Mode S provides Air-Air Data-Link, GroundAir Data-Link, Air-Ground Data-Link.

Facilitates Air-Air Data Exchange between
TCAS Equipped Aircraft during Coordination
for Collision Avoidance

RTCA
DO-181C
Compliance
Transponder Specifications.

ARINC 735A Compliance for TCAS-IFFT
Interface.
IFFT-2420A
for
Status :
.

SIL1, SIL2 Lab units and FAI unit Delivered
to Boeing P8I.

Four SOF units delivered to Jaguar DARIN
III.

TCAS-IFFT Interoperability
Completed.
Flight
Trials
Platforms: P8I (Boeing), Jaguar DARIN III, IJT SP, Coast Guard Helicopter.
Ph: +91-40-2387 8438 Ph: +91-40-2387 8438
IFF INTERROGATOR -3400A
ROLE:
The function of IFF interrogator is to interrogate in
the selected modes of operation (Modes 1,2,3/A,
and IS1) and identify the target as friend or foe.
The secondary information will be designated on the
target of interest on the primary radar display. It
caters for MKXII as per STANAG 4193 and ICAO
Annexure-10. Functional Modes for the Interrogator
include Challenge, Continuous and Tracking mode.
SALIENT FEATURES:
 M-Scan Antenna System.
 Frequency of Operation for Interrogator: 1030 ±
0.1MHz.
 Output Power of Interrogator : 2KW
 Frequency of Receiver
: 1090 ± 3 MHz.
 Modes of Operation for Interrogator are Mode 1, 2,
3, 3/A, C & IS1.
 Crypto Module Secure Mode 4 Encryption and
Decryption Functions
 Antenna Azimuth variation for Interrogator is from
–60°to +60°.
 1/2 ATR size (320mm x124mm x194mm),Weight
<10Kg Operational on 28V DC supply.
 High-Speed 32-bit Processor, FPGA with high
Processing Power for acquisition of interrogation
 Mono-pulse digital receiver for Interrogator.
 Ruggedization, Conduction Cooling, High shock and
vibration resistant.
STATUS:
 Project is under development and engineering
model will be ready by Mar’13
Deployment
: LCA MK II
Ph: +91-40-2387 8438 Ph: +91-40-2387 8438
COMBINED INTERROGATOR TRANSPONDER
CIT-4000A
ROLE:
The function of CIT is to interrogate in the selected
modes of operation (Modes 1,2,3/A, and IS1) and
identify the target as friend or foe. The secondary
information will be designated on the target of
interest on the primary radar display. This system
includes transponder and it will reply to the other
interrogations either
from
ground or airborne.
Transponder function
is
independent of
interrogation function. Both functions of MKXII as
per STANAG 4193 and ICAO Annexure-10.
Functional Modes for the Interrogator include
Challenge, Continuous and Tracking mode.
SALIENT FEATURES:
Combined Interrogator Transponder
MSCAN CIT-4000A
 M-Scan Antenna System.
 Frequency of Operation for Interrogator: 1030 ±
0.1MHz. Output Power of Interrogator: 2KW
 Frequency of Operation for Transponder: 1090 ±
0.5MHz.
 Modes of Operation for Interrogator are Mode 1, 2,
3, 3/A, C & IS1.
 Modes of Operation for Transponder Mode 1, 2, 3,
3/A, C IS1 and S.
 TCAS compatibility through ARINC 429 interface.
 Crypto Module Secure Mode 4 Encryption and
Decryption Functions
 Antenna Azimuth variation for Interrogator is from
–60°to +60°.
 1/2 ATR size (320mm x124mm x194mm) ,Weight
<12Kg Operational on 28V DC supply.
 High-Speed 32-bit Processor, FPGA with high
Processing Power for acquisition of interrogation
 Mono-pulse digital receiver for Interrogator.
 Dual Channel Receiver for Transponder for
Diversity application
 Ruggedization, Conduction Cooling, High shock and
vibration resistant.
STATUS:
 Project is under development and engineering
model will be ready by Dec’13
Deployment
: FGFA
Ph: +91-40-2387 8438 Ph: +91-40-2387 8438
Function:
BHEEM-EU is an avionics LRU consisting of onboard Power
PC based data acquisition and processing system. Detect for
BRAKE CONthe fault and exceedance conditions ,evolve the warning and
TROL,HYDRAULICS,
ENGINE& ELECTRICAL cautions to the pilot. The unit also provides information for onMONITORING SYTEM
line operation and off-line maintenance activities for ground
ELECTRONIC UNIT
personnel.
BHEEM 1506A
Platforms:
LCA
H I N D U S TA N
A E RO NAU T I C S
LIMITED
BALANAGAR
HYDERABAD
Pin - 500042
Phone: 040-23775336
Fax:
040-23879570
Salient Features:
 Controls the Wheel Brake ManagementSystem,Nose Wheel
Steering system, Undercarriage system .
 Monitoring of the Engine, Electrical and Hydraulic Power
supply distribution systems.
 System acts as a remote terminal on Avionics Bus to the
open architecture computer.
 Hybridised Circuits, Highly Software intensive
 It can handle 300 number of Input/Outputs.
 Vibrational Signal Processing Facility.
 Compatible for GE404-F2J3 and GE404-IN20 Engine.
 Software Compatibility with DOD-2167A standard.
r
Digital Engine Control Unit – DECU
Function:
Digital Electronic Control Unit (DECU)
provides full authority control of fuel
flow to the Pilot less Target Aircraft
Engine (PTAE). The unit, which is a
Micro-controller (87C51), based
system, implements a Proportional
Integral and Differential (PID) type of
control in providing fuel to the engine.
Salient Features:
 Power Supply

-28V DC
19V - 32V as per MIL - STD 704
 Power Consumption
 Environmental Specs
 EMI/EMC Specs
-Less than 15W
-MIL - STD - 810D
- MIL - STD - 461C
Platforms
 Pilot less Target Aircraft Engine
(PTAE)
Hindustan Aeronautics Limited - Hyderabad
Air Data Unit (ADU)
Function:
Air data unit (ADU) calculates the air
data
parameters
Altitude,
calibrated
like
Pressure
Airspeed,
True
Airspeed, Mach number, Altitude rate,
Static
Air
temperature
based
on
electrical and pneumatic inputs from
the sensors (Ps, Pt and OAT probe).
Salient Features:
Air data parameters measured
 Indicated static pressure
 Indicated differential pressure
 Total temperature
 Baro correction
 ARINC-429 interface
Technology:
ARM Based Controller is used
MEMS Based Sensors is used
Platforms
 Advanced Light Helicopter (ALH)
HINDUSTAN AERONAUTICS LTD
HYDERABAD
Onboard Processor for AKASH missile
PURPOSE
This is a ruggedized
computer designed to
carryout various missile
borne functions.
FEATURES
• Missile checkout
• Missile control & guidance
• Mission Sequencing
• Telemetry data posting
SPECIFICATIONS OF OBP(AKASH)
Description
Specification
Processor
486 DX2/DX,24.576Mhz
Data rate
(Telemetry Interface)
512 Bytes @ 1M bits/sec
for 110ms
Data rate
(CGU Interface)
21 Bytes @ 1M bits/sec
for 100ms
Dimension of the Unit
310mm(L)x
270mm(W)x110mm(H)
Weight
3Kg
Production order
Customer
Platform
: 129
: BDL
: AKASH Missile
HYDERABAD
Radio Proximity Fuse for AKASH missile
PURPOSE
This is a radar that
detects the target
range & velocity,
generates firing pulse
when pre determined
conditions are met.
FEATURES
• KU band system incorporating.
• Transmitter/ Receiver/ Signal processing.
• Detects Target range & velocity.
SPECIFICATIONS OF RPF(AKASH)
Description
Specification
Frequency of
Operation
Ku-band
Detectable Range
2-45 Mtrs
Power Output
2W
Receiver Sensitivity
-90dBm
Dimension of the Unit
240mm(L)x
192mm(W)x40mm(H)
Weight
2kg
Production order
Customer
Platform
: 876
: BDL
: AKASH Missile
SLRDC
HYDERABAD
Radio Proximity Fuse for ASTRA missile
FEATURES
• High speed FPGA & DSP
Processor
•MMIC based Transmitter
& Receiver
• Software Development is
based on CWT & Neural
Networks
SPECIFICATIONS OF RPF(ASTRA)
FREQUENCY OF OPERATION
16.5 GHz
DETECTION RANGE
2–30 Mtrs
DETONATION RANGE
15 Mtrs
MISSILE –TARGET RELATIVE VELOCITY
100-1600 Mtrs/Sec
RECEIVER SENSITIVITY
-90 dBm(1PicoW)
TRANSMITTER POWER OUTPUT
30 dBm ( 1Watt)
DIMENSIONS OF THE UNIT
168mm (dia) X 98
mm (length)
WEIGHT
< 2.5 Kg
Expected PRODUCTION ORDER: 80 SETS
SLRDC
HYDERABAD
Radio Proximity Fuse for AD missile
FEATURES
• High speed FPGA for
signal processing.
•MMIC based Transmitter
& Receiver.
• Dual PRF scheme for
resolving range.
SPECIFICATIONS OF RPF(AD)
14.5 GHz & 16.5 GHz
DETECTION RANGE
5–150 Mtrs
DETONATION RANGE
<15 Mtrs
MISSILE –TARGET RELATIVE
VELOCITY
1000-4000 Mtrs/Sec
RECEIVER SENSITIVITY
-101 dBm(0.1PicoW)
TRANSMITTER POWER OUTPUT
33 dBm ( 2Watt)
DIMENSIONS OF THE UNIT
240 X190 X 55 mm
WEIGHT
< 2.5 Kg
r
Servo Controller Unit (SCU)
Function:
Servo Controller Unit (SCU) controls
the
4
fins
of
LR-SAM.
Command
received from OBC through RS422.
Actual linear displacement is sensed
using LVDT transducer. In closed loop
operation, LVDT output works as a
feedback to SCU.
Salient Features:
 4-channnel simultaneous control
 RS-422 interface
 Closed loop operation for smooth
control of actuators
 Over-current protection
Technology:
ADSP 21489 32-bit 4th generation processor
Spartan-3AN Xilinx FPGA based design
Platforms
 LR-SAM
RADIO ALTIMETER – RAM 703A
PURPOSE:
TO PROVIDE AN ACCURATE ALTITUDE OF
THE AIRCRAFT ABOVE THE OVERFLOWN
TERRAIN.
SALIENT FEATURES:
 MEASURES ALTITUDE UP TO 1500m AGL (ABOVE GROUND
LEVEL)
 LOW TRANSMITTER POWER ( > 250mW)
 ACCURATE ALTITUDE OUTPUTS
 ANALOG ALTITUDE OUTPUTS AS PER ARINC 552A
SPECIFICATIONS:
 ALTITUDE RANGE
: 0 TO 1500 METRES
 ALTITUDE ACCURACY
: 0 TO 1500:  (1m + 3%)
 TX-FREQUENCY
: 4200- 4400 MHz
 FREQUENCY DEVIATION : 123 ± 5 MHz
 POWER CONSUMPTION : 80VA ( FROM 115V,400Hz)
PLATFORMS:
AN-32, DORNIER, AvRO, MiG-21(MBU), CHEETAH, CHETAK & ALH.

RADIO ALTIMETER - RAM 2700A
For critical flight regimes, HAL’s Radio Altimeters
RAM 2700A Radio Altimeter deploys Digital signal
provide today’s flight crews with dependable, highly
processing
accurate and altitude above-ground-level (AGL)
RAM 2700A, with its MIL-STD-1553 data bus can be
information.
enhances
easily coupled with Aircraft display, mission computer
operational safety during approaches, night time
and instrumentation. Proven and precise, this system
operations, and hazardous flight above rough terrain
offers improved situational awareness for a broad range
Designed
of fixed and rotary wing aircraft.
This
real-time
system
for applications such as helicopter
and
techniques
for
altitude
extraction.
combat fighter operations where accuracy is needed
HAL has over 30 years’ experience in Radar
down to zero feet, RAM 2700A is the “State -of-the-
Altimetry and our systems have hard won, proven
art” FMCW Digital Radio altimeter operating in
performance in various aircrafts like SU-30, MIG-
C – Band and measures the accurate altitude of the
29UPG, MIG-29K/KUB, IJT, MIG-21UPG (BISON),
aircraft from the terrain being over flown., and
JAGUAR/DARIN-III, ALH, MIG 27 etc. Our unique
successor to very reliable and successful RAM 1700
combination of deep experience with a modern digital
series radio Altimeter system
implementation makes HAL altimeters the only
affordable choice for serious users.
Key features






DSP-based C-Band FMCW Radio Altimeter
Capability to operate in all weather, including heavy
rain and snow & terrain like Land, water, Grass etc
Digital & analog outputs
Variable power output as per range
Roll & Pitch limit operation
Leading edge tracking technique
Specifications







High resolution accuracy
Doppler effect immune
Low radiated power
Frequency agility
Low Probability of Intercept (LPI)
No forced air cooling is required
Thermal drift recovery during flight
Altitude Accuracy
0 to 20,000ft ± ( 2ft + 1% H )
Pitch Limit
Roll Limit
± 30 ° with S67-2002
Antenna
± 30° with S67-2002 Antenna
Tx-Frequency
4200 to 4400 MHz
Frequency Deviation
123 ± 2.5 MHz
Tx – Power output
10 mW to 1 W Max (Variable)
Acquisition time
< 800 msec
AID
35 Ft
Radio Silence
Less than - 10 dBm
Self test
POST, IBIT & CBIT.
QUALIFICATION &
COMPLIANCE
EMI/EMC
MIL-STD 461 E
Environmental
MIL-STD 810F
Reliability
MIL-STD-217F
Software compliance
DO-178 B & DO-254 compliant
PLATFORMS
Jaguar Darin III , ALH Mk 3, LCH
PHYSICAL SPECS
Dimensions
Weight
124W X 159 D X 170 H mm
(without mounting tray)
135W X 220D X 192H mm
(with mounting tray)
NMT 3.5 Kg (without mounting
tray)
NMT 4.2 Kg (with mounting
tray)
ELECTRICAL SPECS
Power Supply
Power Consumption
35 W (Max)
Current Rating
INTERFACE
Digital Altitude Outputs
Analog Altitude Output
MIL-STD-1553B,RS 422 , ARINC
429
As per user requirement:
Antenna
S67-2002
SYSTEM PARAMETERS
Altitude Range
0 to 20,000ft
Hindustan Aeronautics Ltd
Ph- +91-40-23878281 Ext : 6200
www.hal-india.com
AIR DATA COMPUTER
ADC 2601 A
Function:
ADC calculates the air data parameters
like Mach Number, Pressure Altitude,
Calibrated Air Speed, True Air Speed,
Altitude Rate, Static Air Temperature
based on electrical and pneumatic inputs
from the sensors .
Salient Features:
ADC -2601A

Designed and developed to satisfy the
requirements of modern avionics systems.

Information is transmitted across digital data
bus.

Installation is Orientation insensitive ,
convection cooled .

Transmitter Power is less than 6watts.

Reliability is greater than 30,000hrs.

Operational on 28V DC supply

ADC unit size 5.54x4.0x3.133 inches (LxWxH),
and wt: 800g.
.
Deployment
: IJT, ALH
Ph: +91-40-2387 8438
Fax: +91-40-23879570
web: http://www.hal-ndia.com/randd/strategicelectronics/strategicelectronics.asp
AUTOMATIC FLIGHT CONTROL COMPUTER
AFCC
Role
Automatic Flight Control Computer (AFCC) is
PowerPC-7448 based system. It has two processing
channels with inter-processor synchronization and
data communication, and is interfaced with various
sensors, cockpit controls and actuators. It performs
all the processing and computations in real time
It generates commands for Series and Trim
actuators, in pitch, roll, yaw and collective axes for
basic control and stabilization of Light Combat
Helicopter. It has built in safety functions to with-hold
actuator commands in case of failure detection, and
has automatic reset features to restart after removal
of failures.
It processes various pilot commands from pilot
control unit for various mode selections, and provides
indications, warnings and failure status to cockpit
Salient Features:
AUTOMATIC FLIGHT CONTROL COMPUTER
AFCC

COTS , Modular design approach with Vxworks
6.4

18-Layer Flex-Rigid Mother Board. State-ofthe-art Surface Mount Devices, Hybrids & BGA
packages

Metal-Core
PCB’s
management

Power supply module upto 200W (Module
Dimension: 77mm X 124mm X 12mm)

Short circuit protection for Excitation for LVDT
/RVDT
sensors,
Excitation
for
RVDT
potentiometers, Analog outputs for servo
currents and Discrete outputs.

Lightning protection (level 5 with Waveform
4) as per DO-RTCA 160D

Ruggedized, Conduction Cooled, High shock
and vibration resistant.
for
better
Thermal
Status:
Deployment

2 Engineering
integration
models
ready
for
S/W

4 SOF models under progress for Flight trials.
: LCH
Ph: +91-40-2387 8438 Ph: +91-40-2387 8438
CENTRALIZED WARNING SYSTEM
FOR HJT-36 AIRCRAFT
(CWS-1010A)
DISPLAY UNIT
FOR FRONT COCKPIT
ELECTRONIC UNIT
DISPLAY UNIT
FOR REAR COCKPIT
PURPOSE:
The Centralized Warning System (CWS-1010A) is a Microcontroller based
system custom built for HJT-36 aircraft. The unit is designed to indicate the occurrence
of any warning condition and alert the pilot through audio and visual means in both front
and rear cockpits. The CWS consists of an Electronic Unit (EU) located in the aircraft
and control & warning Display Unit (DU) located in the RH Quarter Panel of each
cockpit.
FEATURES:
¾ 30 legends to display red & amber warnings
¾ Generates audio tones for red & amber warnings
¾ Generates voice warnings for AOA Exceedance, Low altitude, Canopy unlock &
Under carriage extension.
¾ Checks the functionality of display unit lamps & external cockpit lamps
¾ Day-Night operation
¾ Interfaces with fire warning lamp & generates unmutable red tone
¾ Interfaces with master alarm lamp (flasher)
¾ Interfaces with AOA system
¾ Interfaces with RADALT system
¾ Capable to receive ARINC/Discrete signals from FADEC
¾ Complies to MIL-STD-810D & MIL-STD-461C
STRATEGIC ELECTRONICS RESEARCH & DESIGN CENTRE
AVIONICS DIVISION, BALANAGAR
HYDERABAD – 500 042
Weapon Control Panel
WCP-1020A
Weapon Control
Panel
About Design
The System is designed to be compact
WCP-1020A for HJT36 A/c
in size and low in weight. For these Mil
The Weapon Control Panel is custom
grade
miniature
components
are
built for HJT-36 trainer aircraft. The
selected. In order to reduce the power
unit consists of a Front Panel located in
consumption LEDs are used which
the Front cockpit, operated by trainee
have added advantage of low failure
and Rear Panel located in the Rear
rate and high brightness to be used
cockpit for monitoring by trainer.
direct sun light.
Functions
The
Front
selection
of
panel
is
Pylon,
designed
Weapon
for
Type,
LIVE/SAFE for Bomb and Ripple/Salvo
for Rockets by Trainee.
Rear Panel has indicators for displaying the
selection of Pylons, Weapons, LIVE/SAFE,
Ripple/Salvo, Armament test and Late-Arm
selections done by the trainee in front
cockpit.
Features
Complies to standards
¾ Day and Night Operational
9 Mil-Std-810F
¾ Sun light readable
9 Mil-Std-704E
¾ NVG compatible Legends
¾ Compact in size
¾ Low in Weight
¾ Integrally lit by LEDs
¾ LED Legends
¾ Low Power consumption
STRATEGIC ELECTRONICS RESEARCH
& DESIGN CENTRE
SLRDC
HYDERABAD
DIGITAL RADIO FREQUENCY MEMORIES (DRFM)
Based Target Simulator for RPF(ASTRA)
PURPOSE
Evaluates the performance of
RPF in real scenario, by
Simulating the Target with
various ranges and velocities.
FEATURES
•High Speed ADC for digitization.
•High Speed FPGA.
SPECIFICATIONS
16.5 GHz
No RF Channels Handled
3
Range Resolution
1.25 mts
Delay Range
1.5 micro Sec
Doppler Resolution
<1Hz
r
Power Control Unit (PCU)
Function:
Power
Control
regulated
28V
electronics
Unit
(PCU)
DC
voltage
subsystem
of
supplies
to
the
the
PTA
Lakshya aircraft. It is rated for power
of 1.2KW. It is designed in such a way
that output is available only when the
input reaches more than 35V DC.
Salient Features:
 Input : 35V DC to 60V DC
 Output : 28V Dc at 40Amps
 Short Circuit (for 30 sec)and Over-load
protection
Platforms
 PTA - Lakshya
Armament Configuration Panel
ACP1000HJT
Armament Configuration Panel
ACP10O0HJT for HJT36 A/c
Armament Configuration Panel is one of the major components of weapon
system on HJT-36 Trainer. It forwards the information of the weapon type
loaded on the pylon to different elements of the weapon control system. ACP
interfaces with Mission Computer of Integrated Avionics System to provide
the information of type of store installed on the pylon to generate the
symbology on HUD.
Features
¾ Compact in size
¾ Low in Weight
¾ Easy to install
¾ Simple in design
Complies to standards
9 Mil-Std-810F
9 Mil-Std-704E
STRATEGIC ELECTRONICS RESEARCH & DESIGN CENTRE
r
FLOATING DECK HIGH VOLTAGE (FDHV)
Function:
FDHV is subsystem of the Transmitter
of the PAR P2080C radar. It provides
the necessary Heater Voltage and Grid
Pulse Voltage to the TWT (with respect
to the Cathode Voltage of TWT.)
Salient Features:
 Heater Voltage: -6.3V DC
 Grid Bias: -280± 20VDC
 Grid Top: +135VDC to +235VDC
 PRF: 6KHz with 10% Duty Cycle
 Reference Voltage : Cathode of TWT
Platforms
 PAR P2080C Radar

UHF TRANSRECEIVER COM-1150A - Hindustan Aeronautics Limited

Transcription

Similar documents

The Shreveport Times

Receiver`s Application for Order to Show Cause as to why Andris

Website: http://sbtetap.gov.in TELEPHONE:

Receiver`s Application for Supplemental Relief Under Order Holding

Make the most of your transfer journeys.

GW-9400 Quick Operation Guide - G

ABnote DuoChrome is an exclusive, state-of-the

Organic - Royal Coffee New York