Aeronautical Development Establishment [ADE] [DRDO institute]

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The Aeronautical Development Establishment is a laboratory of India's Defence Research and Development Organisation (DRDO). Located in Bangalore, its primary function is research and development in the field of military aviation.[2]Its recent successful projects include Lakshya (an aerial target), Nishant (a reconnaissance UAV), flight simulators (LCA, Ajit, Kiran, Mig-21) and avionics packages for Tejas-LCA (display and FCC). It earlier worked on Sparrow (mini-uav) and Ulka (aerial target). Many new projects are being planned there.This establishment was the place where former Indian president A.P.J. Abdul kalam started his career.http://en.wikipedia.org/wiki/Aeronautical_Development_Establishment

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AERONAUTICAL DEVELOPMENT AERONAUTICAL DEVELOPMENT ESTABLISHMENT ESTABLISHMENT

AERONAUTICAL DEVELOPMENT ESTABLISHMENT Defence Research and Development Organisation, Govt. of India, Ministry of defence New Thippasandra PO, Bangalore 560075

CORE COMPETENCE Aerodynamic Configuration Structural Design including Composites Flight Controls & Avionics Propulsion and System Integration Airborne Sensor Stabilization Aerial Image Exploitation Flight Testing & Evaluation Ground Control Stations

Flight Simulation Development of Pilot Training Simulators Simulation to support Aircraft Design & Aeronautical Research

Design & Development of Systems for Combat Aircraft Fly-By-Wire Flight Control System Cockpit Displays Air Weapons Integration

UPCOMING TECHNOLOGIES & PRODUCTS Design and development of Medium Altitude and Long Endurance (MALE) Unmanned Aerial Vehicle (UAV) - Rustom Development of External piloting (EP) technology and skills

REMOTELY PILOTED VEHICLE [NISHANT]TECHNICAL HIGHLIGHTS: Flight endurance : 4 hrs Altitude : 3600 m AMSL : 125 - 150 kmph Speed Cruise Command Range : 175 km (160km). Payload data link : 175 km(100km). Launch : Mobile Hydro Pneumatic : Parachute/ Landing bags Recovery All Up Weight : 370 kg. Multi mission UAV with Day/Night capability using advanced EO payloads like FLIR,DLTV Autonomous flight capabilities Mobile hydro-pneumatic launcher User friendly Ground Control Station

ROLES: Day/ Night Battle field reconnaissance Target tracking and localization Artillery fire correction using105mm & 155mm guns Damage assessment

INTEGRATED AVIONICS PACKAGE Control law computation based on remote inputs from pilot and vehicle dynamics Auto-pilot for in-flight programmable way point navigation Airborne Encoder-Decoder for pilot interface Inbuilt IAS & altitude sensors & interfaces

GIMBALLED PAYLOAD ASSEMBLY Advanced , light weight, remotely steerable Two axis stabilized system Consists of 2 payloads: CCD and FLIR Degree of freedom: Azimuth 360 and Elevation-110 to 10 Stabilization: < 100 Micro radians

GROUND CONTROL STATION Electronic Map Display Mission planning & validation UAV semi automatic checkout UAV simulator for pilot training Remote antenna control

GROUND IMAGE EXPLOITATION SYSTEM (GIES)The GIES is state-of-the-art image exploitation system developed to acquire, store, retrieve, process, analyze, interpret, display and disseminate information from imagery obtained during UAV mission. The major activities involved are Adaptive Preprocessing of Aerial imagery Image Mosaicing High resolution reconstruction of target imagery Terrain Classification Segmentation of EO/SAR images

TERRAIN CLASSIFICATION

IMAGE MOSAICING

PILOTLESS TARGET AIRCRAFT [LAKSHYA]TECHNICAL HIGHLIGHTS: High performance, reusable aerial target system Realistic simulation of enemy aircraft threat to artillery crews, for training of firing air-to-air and surface-to-air weapons Land/ ship launched Zero length launcher, Rocket assisted take-off Carries two tow bodies which are IR & RF signature augmented Maximum maneuverability :3g Structural limit load factor : 6g Maximum all up weight (incl. Tow bodies) : 705 kg Booster thrust : 3750 kgf Sustainer thrust at sea level : 420 kgf Fuel capacity : 190 kg Endurance at 1.5 km at 0.56 Mach : 50 min Maximum speed in clean configuration: 0.65 Mach Max. speed in one stow + one tow configuration : 0.5 Mach Maximum altitude clean configuration : 9 km Maximum altitude with Tow bodies : 5 km Minimum altitude : 300 mtr Rate of climb at sea level : > 25 m/s

Ground Control Station (GCS) for Lakshya Generates a parameter display and trajectory displayfor pilot to remotely fly Lakshya

Built in Simulator to train pilots for flying Lakshya Tracking System provides the command uplink,telemetry downlink & tracks Lakshya during mission

Acoustic Miss Distance Indicator (AMDI) system

measures the miss distance of projectiles from airborne targets & evaluates the proficiency of the artillery crew.

FCS for manned Combat AircraftTejasDIGITAL FLIGHT CONTROL COMPUTER (DFCC) Intel 80960 mc based quad redundant Extensive analog and discrete interfaces with actuators, sensors, cockpit controls and indicators High performance analog servo systems MIL-STD-1552B interface to avionics Cross channel data link for redundancy management

DFCS SOFTWARE Executes identically in all channels synchronously in hard real time Developed as per DoD Standard Ada is used as HLL as per MIL-STD-1815A In- house developed process methodologies to ensure 100 per cent CSU/CSC testing capability

AIR DATA COMPUTER (ADC) HARDWARE AND SOFTWARE Intel 80960 mc based quad redundant ADC Built-in pressure transducers and signal conditioning interface Rotary Variable Differential Transformer sensor interface for Angle Of Attack (AOA) sensors ADC software : air data computations on static and total pressures, AOA, angle of sideslip & total air temperature

ACTUATORS LCA has total 13 actuators Comprise Elevon, rudder, leading edge slats, and airbrake actuators Elevons are quad electrical redundant Rudders are dual hydraulic redundant Slat and airbrake actuators are dual electric redundant single hydraulic Redundancy management is done by the OFP software

SENSORS inertial sensors comprise of quad redundant rate sensor assembly (RSA) RSA comprises of 12 rate gyros for sensing pitch, roll, Yaw rates, Quad redundant acceleration sensor assembly (ASA) package comprising eight accelerometers for sensing lateral and normal acceleration. Two angle of attack sensors One total air temperature probe,

Two-side air data probes and one nose air data probe Rate Gyro Mini-Bird (MB)

Real-time engineer-in-the-loop ground test facility for carrying out closed-loop hardware/software integration of the FCS Includes high fidelity LCA mathematical model

Engineering Test Station (ETS) Multi-processor-based real-time, automatic/ manual test station Used for the functional verification of FCS Capability to simulate, stimulate, monitor and generate failure for all the inputs/outputs of the DFCC Used for acceptance testing and real-time hardware/software integration of the DFCC, system integration, and testing of the LCA-FCS Can replace some or all simulated sensors and actuators with real hardware Interfaces with the mini-bird and iron-bird test facilities to monitor the DFCC performance during closed-loop & pilotin-the-loop testing

LCA MISSION SIMULATOR

SIMULATORS

Real Time Simulator, set up inside a 9 meter diameter dome Works as an engineering simulator for HQ evaluation, mission profile planning & execution and air combat simulation studies Visual cue generates seamless out-of-the-window view for the pilot with a FOV of 180 (Azimuth) x 80 (Elevation) Audio cues generated include the simulation of aircraft engine noise, tyre screech sound, landing gear thud, etc.

AERODYNAMICS Study of Qualitative Requirements

Aerodynamic configuration design - Airfoil design using CFD tool MSES - Wing design using CFD tool VSAERO - Airframe design using engg code AAA Wind tunnel testing - Design and fabrication of scaled down model - Testing using wind tunnel facilities

Flight performance evaluation Post flight data analysis

Mechanical Design Of UAVs Conceptual Design of UAVs 3D CAD modeling & Detailed Design Structural & Thermal Analysis using CAE techniques Design and synthesis of mechanisms & LRUs Experimental Validation

FCS FOR CONTROLLED AERIAL DELIVERY SYSTEM (CADS) Delivers a payload of 500kg autonomously to a designated target Circular error probability : within 100 m Manual and Autonomous modes of operation Low cost sensors based navigation Energy management maneuver based guidance for altitude control

COMPOSITE TECHNOLOGIESDesign & Development of lightweight composite airframe components for different UAV programs through conventional as well as novel fabrication processes like Resin Infusion Molding (RIM)