[1] This project was started by India during the early 1980s to develop technologies needed for a payload to be placed into a geostationary orbit.

The payload capacity of the ASLV was approximately 150 kg (330 lb) to an orbit of 400 km (250 mi) with a 47-degree inclination.

[4] The height to diameter ratio of ASLV was very large which resulted in the vehicle being unstable in flight.

This was compounded by the fact that many of the critical events during a launch like the core ignition and the booster separation happened at the Tropopause where the dynamic loads on the launcher was at the maximum.

[5] The aerodynamic characterization research was conducted at the National Aerospace Laboratories' 1.2m Trisonic Wind Tunnel Facility.