Session
Technical Session VI: Advanced Concepts
Abstract
This paper describes a study that examined using the Pegasus launch vehicle and small spacecraft for missions to the atmospheres of Venus and Mars. The launch vehicle can deliver approximately 820 lb (371.9 kg) into a 0° inclination circular orbit of 200 nm (370.4 km) altitude. With convential solid propellant rocket motors, a spacecraft of 73.8 kg (162.7 lb) would be delivered to Venus or Mars. A spacecraft using a currently existing 10 kW xenon-ion engine system with specific impulse of 3500 sec would deliver 143.4 kg (316.2 lb) to Venus or Mars. The spacecraft can fit inside the Pegasus fairing if folding solar array blankets are used.
Small Satellite Design for Inner Solar System Exploration
This paper describes a study that examined using the Pegasus launch vehicle and small spacecraft for missions to the atmospheres of Venus and Mars. The launch vehicle can deliver approximately 820 lb (371.9 kg) into a 0° inclination circular orbit of 200 nm (370.4 km) altitude. With convential solid propellant rocket motors, a spacecraft of 73.8 kg (162.7 lb) would be delivered to Venus or Mars. A spacecraft using a currently existing 10 kW xenon-ion engine system with specific impulse of 3500 sec would deliver 143.4 kg (316.2 lb) to Venus or Mars. The spacecraft can fit inside the Pegasus fairing if folding solar array blankets are used.
