| Kapothaka | |
|---|---|
| Role | Reconnaissance UAV |
| National origin | India |
| Designer | Aeronautical Development Establishment |
| Primary user | Indian Army |
Kapothaka was a technology demonstrator mini-UAV for reconnaissance. The Kapothaka (also spelled Kapothaha) which means “dove” is believed to be a predecessor of Nishant UAV system.
History
Following the successful deployment of a remotely piloted vehicle by Israel during Lebanon war in 1982 Aeronautical Development Establishment (ADE) undertook the development of a remotely piloted vehicle kapothaka in 1983 to develop the necessary technologies. During the next 4 years ADE developed a small RPV to validate in-flight video transmission capabilities and to implement ground take off and parachute recovery.
Characteristics
Kapothaka had an all-up-weight (AUW) of 130 kg (290 lb) and was powered by an conventional twin boom configuration 26 bhp piston engine. It had a very small, low radar cross-section and was launched from a rail with rocket assistance. The system had a 4.5 m (14 ft 9 in) wingspan, a length of 3.67 m (12 ft). Operating ceiling was 3,000 m (9,800 ft). The integral wing-boom-tail unit was made of Glass Fibre Reinforced Plastic (GFRP) material whereas the fuselage is a combination of aluminium and GFRP; the aircraft has an endurance of 90 minutes while carrying payload of 20 kg (44 lb) and can achieve a speed of 180 km/h (110 mph) in flight. It is equipped with TV and panoramic cameras, providing real time imagery intelligence.[1][2][3][4]
This programme enabled ADE to cut teeth on the intricacies of UAV design development and deployment. The endeavour culminated in successful demonstration of aerial reconnaissance using an RPV during Operation Brasstacks in September 1987.[5] Indian Army, impressed by the unique capability provided by an RPV, formulated a "qualitative requirement" for a tactical UAV system for artillery leading to the development of Nishant UAV system.
Specification
General characteristics
- Crew: none on-board
- Length: 3.67 m (12 ft 0 in)
- Wingspan: 4.5 m (14 ft 9 in)
- Gross weight: 130 kg (290 lb)
- Powerplant: 1 × 2-cylinder 2-stroke engine , 19 kW (26 hp)
Performance
- Maximum speed: 180 km/h (110 mph, 96 kn)
- Endurance: 90 mins
- Service ceiling: 3,000 m (9,800 ft)
See also
References
- ^ "Unmanned Aircraft Systems and Technologies" (PDF). Archived from the original (PDF) on 2013-12-28. Retrieved 2012-08-17.
- ^ Kulshreshtha, A. K.; Vasile, Cornelia (2002). Handbook of Polymer Blends and Composites, Volume 1 edited by A. K. Kulshreshtha, Cornelia Vasile. ISBN 9781859572498. Retrieved 2012-08-17.
- ^ B Harry (8 Feb 2004). "DEFEXPO 2004 - Part 1". Retrieved 17 August 2012.
- ^ "Going global via self-reliance". Retrieved 17 August 2012.
- ^ "Unmanned Aerial Vehicles [UAV] for India - perspectives, vision & requirements". Retrieved 2012-08-17.
- ^ Kulshreshtha, A. K.; Vasile, Cornelia (2002). Handbook of Polymer Blends and Composites, Volume 1 edited by A. K. Kulshreshtha, Cornelia Vasile. ISBN 9781859572498. Retrieved Aug 17, 2012.
- ^ "UAV's in SOUTH ASIA". Archived from the original on March 4, 2016. Retrieved Aug 17, 2012.
This page was last edited on 4 January 2024, at 05:38