DRDO - ADA EXHIBITION

Air Force Station Yelahanka, Bengaluru

20th (Wed) - 24th(Sun), February 2019

Aerial Delivery Research & Development Establishment

ADRDE


About Lab

Aerial Delivery Research & Development Establishment Agra made a humble beginning at Kanpur during the later part of 1950s, consisting of two Aerial Delivery Sections, namely – Chief Inspectorate of Textiles & Clothing (CIT & C) and Chief Inspectorate of General Stores (CIGS) under the control of Director General of Inspection (DGI). Primarily, these two sections were responsible for the indigenization of parachutes and related equipment’s for paradropping of men and materials. Subsequently, these sections moved over to Agra during 1965 and transfigured into a full-fledged establishment called Chief Inspectorate of Aerial Delivery Equipment (CIADE). This DGI establishment came under the fold of DRDO in May 1968 and ADRDE was established in January 1969 at Agra. The charter of duties of the establishment also got revised which included development of Heavy Dropping System, Brake Parachute System and Towed Target System. Thus, the lab which started as two small sections in the Textile & Clothing and General Stores Group underwent a series of transformations, expansions & matured into a R&D Establishment under DRDO. During the resurgence of DRDO in 1980s, the activities of this establishment were reviewed and ADRDE was brought under cover of Directorate of Aeronautics. With this, the scope of activities of ADRDE widened further to include programs like Aircraft Arrester Barrier, Air Cushion Vehicle and Balloon Technology. During last two decades ADRDE has taken up projects on Paratrooper’s parachute systems, Cargo and Heavy equipment dropping systems, Aircraft brake parachute system, Armament Delivery parachute system, Recovery parachute system, Balloon Barrage & Surveillance system, Aerostat of small and medium class capacities and recently on Airship and related applications. This establishment is poised to meet the ever increasing requirements of the Services & Space organizations by developing state-of-the-art systems

Today ADRDE parachute systems, productionised by OPF Kanpur, are being used by all of our Armed forces -Army, Navy and Air Force. ADRDE parachutes have been successfully used in space missions, fighter aircrafts and for para-dropping of heavy duty payloads (3 Ton, 7 Ton and 16T weight class) including BMP . Successful development of Medium size Aerostat based Surveillance system has paved the way for taking up challenge of development of Large Size Aerostat System. Endeavour in the area of small size Airship has opened up new horizons for setting up Airship based surveillance systems for national as well as homeland security.

Shri A K Saxena

Shri Arun Kumar Saxena, Scientist ‘G’ took over as Director, ADRDE Agra on 1st Jan 2018. Previously, he has served as Associate Director of ADRDE for 5 years. He graduated in 1984 (IIT, Roorkee) and post graduated in 1997 (IIT, Roorkee) in Mechanical Engineering. He joined DRDO in 1986 at ADRDE and started his scientific career with design/development of Parachute Recovery System for Agni payload during its Re-Entry phase.

A propagator of self-reliance, he has successfully spearheaded several Projects for their successful accomplishment including transfer of technology (ToTs) to the industries and finally induction in the Indian Armed Services (Indian Army, IAF & Indian Navy including ISRO). Over more than 3 decades in DRDO, he has been responsible for design/development of several systems i.e. Recovery Systems of Re-entry vehicles (Agni Payload, Space Recovery Experiment payload and Human Space Capsule), Pilot Parachute Systems (MIRAGE-2000 and SEA HARRIER Aircraft), Hovercraft, Aerostats, Balloon Barrage Systems, RADOME for Ground RADAR, Indigenisation Feasibility for Ejection Seats (ACES) for LCA, IJT & SU-30 A/C, Heavy Drop Systems for: AN-32 & IL-76 (P-7 & HDS-16T) aircrafts, Cheetah/Chetak Hepter Helinet for Aslesha Radar, CSAR System (underslung Chetak/Cheetah helicopter), Paradrop Systems for rapid induction of Marine Commandos (Operations in Sea), Mechanisms for Parachute Release and Test setup at RTRS.

He has published more than 30 technical papers in national & international seminars/workshops. He is recipient of several Awards i.e. IGMDP Award, Agni team award, Path Breaking Tech Team award, DRDO group Technology award and several DRDO Cash awards. He is also affiliated to professional societies e.g. Life Member Aeronautical Society of India (AeSI), Indian National Society of Aerospace Related Mechanism (INSARM) & Administrative Staff College of India.

He is also the Chairman of the Agra chapters of Aeronautical Society of India (AeSI) and Agra Chapter of Indian National Society of Aerospace Related Mechanism (INSARM).

products of ADRDE

Personnel Parachutes

Parachute Tactical Assault – Main (PTA-M)

The Parachute Tactical Assault – Main i.e. PTA (M) is an import substitution for GQ Low Level Parachute. It is an advanced personnel parachutes system which has been used by Indian Armed Forces for deployment of troops from aircraft like AN-32, C-130 etc. This parachute system is equipped with advanced aerodynamic shape design like anti-inversion net, air scoops and mesh covered stability slots for smooth opening and flight performance.

Figure 1: PTA-HS deployment Sequence

PTA-HS is a two stage parachute system comprising of stabilizer parachute and main parachute. The Stabilizer parachute is deployed through static line and is remained connected with the paratroopers till predetermined time or altitude as preset in automatic activation device (AAD). Once the paratrooper attained the preset time AAD releases the Stabilizer parachute which in turn extracts and deploy Main parachute.

Sl No. Parameters PTA-M (India)
1 Payload (AUW) 120 kg
2 Deployment Speed Up to 240 km/hr
3 Deployment Altitude 250 m (AGL)
4 Drop Zone Altitude Sea Level to 4000 m AMSL
5 Main Parachute type Aeroconical
6 Diameter, Do 10 m
7 Packed Weight 15 kg
8 Rate of Descent 5-6 m/s at Sea Level
9 Other Features Anti-inversion design
Air scoops for smooth opening
Stability slots for low oscillations

Parachute Tactical Assault System – High Speed and Static Line (PTA-HS & PTA-SL)

ADRDE has developed an advanced and unique parachute system which is based on Common Main Parachute and Harness System and is capable of being deployed from all types of aircrafts owned by Indian army with modular changes. The Main Parachute has got advanced features and performance as compared to existing Indian parachute system and worldwide in terms of deployment, operation, control, pack volume, mass and flight performance.

The Parachute Tactical Assault system includes a family of variants with same canopy and harness, and can be customized to suite varied mission requirements as follows:
PTA-HS – For high speed deployment from aircraft like IL-76.
PTA-SL – For static line deployment from low flying and low speed aircrafts & helicopters like AN-32, C-130, C-17, MI-17 etc.

PTA-HS

PTA-SL

Parachute Tactical Assault – Main (PTA-M)

PTA-HS is an advanced version of existing PTA (G) personnel parachutes system. The PTA-HS parachute system will enhance the capability of paratroopers in term of deployment speed and deployment altitude. With this system the paratroopers can carry 50 kg combat load and deployed up to speed of 400 Kmph keeping maximum shock value within permissible limit.

Figure 1: PTA-HS deployment Sequence

PTA-HS is a two stage parachute system comprising of stabilizer parachute and main parachute. The Stabilizer parachute is deployed through static line and is remained connected with the paratroopers till predetermined time or altitude as preset in automatic activation device (AAD). Once the paratrooper attained the preset time AAD releases the Stabilizer parachute which in turn extracts and deploy Main parachute.

System Specification for PTA-HS

System Performance
All Up Weight 140 kg (Max)
Max Release Speed 400 Kmph (IAS)
Drop Altitude 250 m (AGL) – 8000 m (AMSL)
Rate of Descent <5 m/s for 140 kg AUW
Steerability Steering 360℃ in either direction via control toggles
Equipment Data for Main Parachute
Parachute Type Toroidal
Canopy Area 100 m2
System Weight <14 kg (excluding Reserve)
Deployment Method
Main Static Line deploys Stabilizer Parachute
Reserve AAD deploys Main Parachute after 5 sec delay Reserve Ripcord
Canopy Construction (Main)
Canopy Fabric 32 gsm Nylon Fabric
Suspension Line 250 kgf Nylon Cordage 318 kgf Polyester Cordage
Other Equipment
Stabilizer Parachute Solid Canopy with Canopy cap and vanes at suspension lines for improved stability
Reserve Parachute Flat circular with Canopy cap for quick deployment

Paratroopers Tactical Assault – Static Line

System Description

PTA-SL is an advanced version of existing PTA-M personnel parachutes system and it will enhance the capability of Indian Armed Forces in terms of added flight performance and maneuverability. This is a single stage paratroopers parachute system which can be deployed via Static line to speed of 240 Kmph.

Features

  • Lowest Rate of Descent among all paratroopers parachute worldwide
  • Lowest Opening shock
  • 360o Steering capability
  • Light Weight and compact packing
  • Universal Harness

System Specification for PTA-SL

System Performance
All Up Weight 140 kg (Max)
Max Release Speed 240 Kmph (IAS)
Drop Altitude 250 m (AGL) – 8000 m (AMSL)
Rate of Descent <5 m/s for 140 kg AUW
Steerability Steering 360℃ in either direction via control toggles
Equipment Data for Main Parachute
Parachute Type Toroidal
Canopy Area 100 m2
System Weight <12 kg (excluding Reserve)
Deployment Method
Main Static Line deploys Stabilizer Parachute
Reserve AAD deploys Main Parachute after 5 sec delay Reserve Ripcord
Deployment Method
Main Static Line
Reserve Reserve Ripcord
Canopy Construction (Main)
Canopy Fabric 32 gsm Nylon Fabric
Suspension Line 250 kgf Nylon Cordage 318 kgf Polyester Cordaget
Other Equipment
Reserve Parachute Flat circular with Canopy cap for quick deployment

Universal Reserve for PTA-HS & PTA-SL

System Description

Universal Reserve Parachute has been designed to be used in both PTA-HS and PTA-SL. The unique canopy design aided with elastic assisted pack cover enables quick extraction and deployment of canopy without the need of auxiliary parachute. The parachute can be deployed by either hand and reserve ripcord is designed to be pulled in any direction for the deployment.

Features

  • Quick and Clean Deployment process
  • Canopy Cap eliminates requirement of Drogue
  • Increased Drag due to special canopy shape
  • Elastic assisted Pack cover flap for quick opening
  • Can be deployed even in case of partial Main failure

System Specifications

System Performance
All Up Weight 140 kg (Max)
Max Release Speed 400 Kmph (IAS)
Drop Altitude 250 m (AGL) – 8000 m (AMSL)
Rate of Descent <8.5 m/s for 140 kg AUW
Equipment Data for Canopy
Parachute Type Flat Circular with Canopy Cap
Canopy Area 50 m2
System Weight < 6 kg
Deployment Method
Main Static Line deploys Stabilizer Parachute
Reserve AAD deploys Main Parachute after 5 sec delay Reserve Ripcord
Deployment Method
Main Static Line
Reserve Centrally located reserve rip cord handle allow the deployment by either hand.

Combat Free Fall System (CFF)

Combat Free Fall System provides total solution to paratrooper for jumping from as high as 30,000 feet, gliding upto 30 km range and landing at desired target. The system consists of 9 cell Ram Air Parachutes, state-of-the-art Oxygen System, Safety devices, jumpsuits, Helmet Mounted hands- free Communication System, Navigation Aids, Gloves, Shoes, etc. The System can be used in High Altitude High Opening (HAHO) and High Altitude Low Opening (HALO) modes.

Salient Features are as follows

System Specifications

  • Ram Air Parachute for Main Reserve parachute.
  • 9 cell
  • Lift to Drag Ratio of 3.3:1
  • Forward Speed of 40 kmph
  • Load Bearing capacity of 150 kg
  • Equipment Carrier bag.
  • Automatic Activation Device for opening of parachutes.
  • PPK-U Unit for Main Parachute
  • Cypers for Reserve Parachute
  • Pre Breather Console in aircraft
  • Personal Bail-Out Oxygen System (PBOS)
  • Protective clothing.
  • Jump Suit, Gloves, Helmet, Anti-glare Goggles, Jump Boots, Socks, Jack Knife.
  • Communication System
  • Navigation Devices
  • Wrist/Hand Mounted Altimeter GPS, Wrist Compass

Emergency Escape Parachute System – SU-30

System Description

The Aircrew ejection parachute systems provide an avenue of escape for the pilot from disabled SU-30 aircraft both over land and water. The parachute system consists of stabilizer parachute and pilot parachute. ADRDE has developed Parachute System and RCMA(K), CEMILAC provided Airworthiness coverage during indigenisation

System Specifications

Specifications
Mass of Pilot 138 kg (Max.)
Mass of Parachute 10 kg
Deployment Speed 650 Kmph (TAS)
Terminal Speed 6 m/s
g-load < 16 g

Recovery System for Human Spaceflight Programme

ISRO’s objective of the Human Spaceflight Programme (HSP) is to carry three astronauts in a crew module into low earth orbit by launch vehicle GSLV MK-III. On completion of mission, the crew module will re-enter into earth’s atmosphere and finally it will land over the sea with the help of Recovery Parachute System. The design of the parachute system should cater all mission abort situations followed by redundancy in each subsystem to avoid any single component failures

Recovery Concept Apex Cover Separation at 15.3 km altitude and at speed of 276 m/s
Deployment of Drogue Parachute with the aid of pilot chute which stabilizes and decelerates the system to 70 m/s up to altitude of 3 km

Extraction and deployment of Main Parachute using Drogue parachute which decelerate the Crew Module to safe landing speed of 10-11 m/s and disconnect on touchdown by pyrotechnically actuated release units.

Total system level test in real time environment was conducted in “Crew Module Atmospheric Re-entry Experiment (CARE)” mission. The module was launched by GSLV MK-III from Satish Dhawan Space Center, SHAR, Sriharikota. The objective of the test was to test the re-entry of Crew Module and its safe landing on sea by parachute system.

The crew module was released from GSLV MK-III vehicle at 126 km above earth surface. The parachute recovery command initiated at 15.4 km. All the parachutes were worked as expected. The main parachutes were disconnected form crew module at touchdown

LAKSHYA Recovery Parachute Mk-II

CADS is used for precise delivery of payload upto 500 kg at predetermined location by making use of maneuvreable capabilitites of Ram Air Parachute(RAP). CADS uses Global Positioning Systems for the coordinates, altitude and heading sensors for the heading information during its flight.CADS with its onboard electronics unit autonomously steers its flight path towards target location by operating control lanyards of RAP.

Controlled Aerial Delivery System (CADS)

System Description

CADS is used for precise delivery of payload upto 500 kg at predetermined location by making use of maneuvreable capabilitites of Ram Air Parachute(RAP). CADS uses Global Positioning Systems for the coordinates, altitude and heading sensors for the heading information during its flight.CADS with its onboard electronics unit autonomously steers its flight path towards target location by operating control lanyards of RAP.

System Specifications

Specifications
Parachute Ram Air Parachute
Payload Capacity 500 kg(including skid board)
Standoff Distance 2.5 times of the drop height (AGL)
Wind Conditions 15 Knots (surface winds)
Circular Error Probability 100 m
Descent Rate 4.25-1.5 m/s
Mode of Operation Autonomous with Manual override capability

Features

  • Mission data programmed before drop
  • Simple to use and maintain
  • Day and night operation possible.

Brake Parachutes

System Description

Brake Parachutes are used for reducing the speed of Aircraft after landing prior to application of frictional wheel brake. In addition to this, it provides an additional safety to the aircraft during emergency like aborted take off or malfunctioning of brakes or landing at short and/or wet runways.

ADRDE has developed brake parachutes for different Aircrafts like LCA, Su-30,Mig-series of Airccrafts, Jaguar, Mirage-2000 etc. Today all the leading fighter aircrafts in service with IAF are equipped with Brake parachutes developed by ADRDE. These parachutes have been successfully deployed and are under production at Ordnance Parachute Factory. Till date, Brake Parachutes worth Rs. 84.33 Crores have been produced by Ordnance Parachute Factory Kanpur. The parachutes developed by ADRDE are cost effective and reliable. They have a long shelf and service life are at par with imported OEM parachutes in performance.
Brake Parachutes for all the IAF fighter aircrafts have been indigenously designed by ADRDE.

Unicross LCA Brake Parachute

Ring Slot Brake Parachute for Hawk (AJT)

Unicross Brake Parachute for MiG-29

Unicross Twin Canopy Brake Parachute for SU-30

Heavy Drop Systems

System Description

Heavy Drop System is used for Para drop of military stores (vehicle/ ammunition/ equipment) . Heavy Drop Systems’ paradrop is one of the specialized areas, in which, the growth of expertise at ADRDE has reached a stage matching with the international standards. Some of these have been attempted only by few developed countries.
ADRDE has developed various types of Heavy Drop Systems so far for transport aircraft such as AN-32 & IL-76 for 3 tons, 7 tons and 16 tons weight class of military stores respectively. HDS for 3 tons & 7 tons have already been inducted into Indian Army and Indian Navy.
The Heavy Drop (P-7) System for IL-76 Aircraft consists of a platform & parachute system. Parachute System comprises of 5 Main canopies, 5 Brake chutes, 2 Auxiliary chutes, 1 Extractor parachute. The platform is a metallic structure made up of Aluminum/steel alloys.

The specifications for heavy drop system are
All Up Weight 8500 kg
Payload 7000 kg
Platform mass 1000 kg approx
Parachute System 500 kg approx
Drop Speed 260 – 400 kmph
Overall Dimensions 4216 X 2802 X 193 mm

Naval Version of the system has also been developed and delivered to Navy.
Heavy Drop System(HDS) -16T comprising of Platform and parachute subsystem, is used for Para dropping of military stores of 16T weight class such as BMP, supplies and ammunition from IL-76 heavy lift aircraft. The system has been designed and developed with 100% indigenous resources and has demonstrated its paradrop capabilities in plain, desert and high altitude areas(HAA).

Drop Life5 drops/10 years

Payload mass(max.) 15000 kg
Platform size 7210 X 3210 X 220 mm
Mass of Platform 2700 kg
Material High Strength Steel Alloy
Mass of Parachutes 2000 kg
Parachute System Cluster of parachutes
Drop Altitude 1000-4000 m
Flight Speed 320 – 400 kmph

Air Supported Inflatable Radome

Air supported Inflatable Radome of 80 feet diameter has been developed indigenously by ADRDE with an objective to serve as a shelter to provide controlled environment for effective and continuous functioning of expensive electronic and strategic systems for civil and military applications.

Inflatable Radome system comprises of Radome Envelope with Airlock Tunnel., Air Blower Units, Electrical Control System, Air Conditioning Units and Emergency Generator.
The Radome envelope is fabricated with EM. transparent PVC coated Polyester specially designed to sustain harsh, highly degrading environmental conditions for desired operational life. The envelope is inflated with heavy duty Air Blowers. The PLC based, closed loop, electrical control system monitors the wind conditions and maintains the temperature and the pressure inside the Radome envelope to desired limits.

The system is operational 24X7 and it meets the demanding high degree of reliability. High degree of reliability has been achieved using high quality components, adequate redundancy and state-of-the-art manufacturing and integration processes.

Salient features of the system are as follows
Shape of Inflatable Radome Hemispherical
Size of Inflatable Radome 80 feet diameter
Working Pressure Normal working pressure 4 mbar (gauge) for wind speed up to 80 km/h
Maximum working pressure 9 mbar (gauge) for wind speed 80 to 120 km/h
Environmental Conditions Ambient Condition Temperature -20 to 55ºC and RH 20 to 95%
Inside Condition Temperature 20 to 25ºC and RH 40 to 50%
Power Supply 380-440 V, 50 Hz, 3 Ph
Electrical Control System PLC based
Emergency Generator 10 kVA silent DG set with AMF panel

Aerostat Systems

Aerostat systems are deployed for a wide variety of applications, viz. Monitoring, Surveillance, Intelligence gathering, Broadcasting, Communication relay etc. NAKSHATRA is a medium size, Aerostat surveillance system with COMINT functionality. It comprises of Helium filled balloon made of advanced PU Coated/Laminated Nylon, Active Pressure Control & Monitoring System, Remotely operable Power Supply, Electro-Optical Tether, Electro-Hydraulic Winching & Mooring System, High Voltage Power Transmission System, Electro-optic Analog and Digital links, Helium Gas Management System and Ground Support Systems.

BROAD SYSTEM SPECIFICATIONS
Aerostat type Re –locatable
Balloon size 38 m class
Balloon Volume ~3500 cum
Payload capacity 300 kg
Max Operating Altitude 1 km AMSL at STP
Endurance 14 days
Fabric Advance Multilayer PU Coated/Laminated
Lifting Gas Helium
Payload COMINT (Any combination of Payloads, viz., EO, ELINT, Radar etc with total weight upto 300 kg can also be integrated)
Monitoring Station Shelter 14 post inside EMI/EMC Shielded Trailer Mounted
Data link Multichannel Mixed Signal Electro Optic Link
Tether Electro-Optic Textile Cable
Winching & Mooring Electro- Hydraulic
Raising & Lowering Time 30 minutes
Power source Trailer Mounted Diesel Generators with requirement based power generation feature
Operating temperature -10ºC to + 55ºC
Winds 70 knots (survival), 50 knots (operational)
Installation On winch using Aerostat Inflation Net

Airship

An airship is an engine-driven lighter-than-air craft that can be moved & steered form one point to another point thus covering a trajectory of interest. The conventional airship is essentially a low speed vehicle with very high fuel efficiency. Moreover, its endurance, one of its key benefits, can be of several orders of magnitude greater than of a heavier than air craft.

Project for development of Unmanned Small Airship System (USAS) as a technology demonstrator with payload capacity of 25 kg, flying altitude of up to 1000 meter (AMSL) and an endurance of 04 hours is underway

Likely spin-offs including applications for civil use, if any

  • Aerial Photography
  • Surveillance and monitoring
  • Disaster Management etc.

Aircraft Arrester Barrier System

The purpose of aircraft arrester barrier system is to engage a fighter aircraft to halt its forward momentum in the event of aborted takeoff or landing over run with minimal damage to aircraft or injury to the crew.

The purpose of aircraft arrester barrier system is to engage a fighter aircraft to halt its forward momentum in the event of aborted takeoff or landing over run with minimal damage to aircraft or injury to the crew.

ADRDE has developed following two Types of Arrester Barriers:

Aircraft Arrester Barrier System for 6 to 20 Ton Class of Aircrafts

The Specifications are given belo
Aircraft Mass 6 to 20.4 Ton
Engagement speed 170 knot(max)
Run Out Distance 270 m
‘g’ load on the a/c < 3 g
Net Centre Height 3.5 to 3.9 m
No. of Barriers Installed 42 Nos

Aircraft Arrester Barrier System for 20 to 40 Ton Class of Aircraft

The Specifications are given belo
Aircraft Mass 9 to 40 Ton
Engagement speed 153 knot(max) for 9 to 11 ton 160 knot(max) for 11 to 40 ton
Run Out Distance 270 m
‘g’ load on the a/c < 3 g
Net Centre Height 4.7 to 4.9 m
No. of Barriers Installed 08 Nos

Coming Soon