Abstract
A trade study investigation the possibilities of delivering a small technology-demonstration satellite to a medium earth orbit are presented. The satellite is to be deployed in a 19,000 km orbit with an inclination of 55°. This payload is a technology demonstrator and thus launch and deployment costs are a paramount consideration. Also the payload includes classified technology, thus a USA licensed launch system is mandated. All FAAlicensed US launch systems are considered during a preliminary trade analysis. This preliminary trade analysis selects Orbital Sciences Minotaur V launch vehicle. To meet mission objective the Minotaur V 5th stage ATK-Star 37FM motor is replaced with the smaller ATK- Star 27. This new configuration allows for payload delivery without adding an additional 6th stage kick motor. End-to-end mass budgets are calculated, and a concept of operations is presented. Monte-Carlo simulations are used to characterize the expected accuracy of the final orbit. An optimal launch trajectory is presented.
Presentation Slides
Launch and Deployment Analysis for a Small, MEO, Technology Demonstration Satellite
A trade study investigation the possibilities of delivering a small technology-demonstration satellite to a medium earth orbit are presented. The satellite is to be deployed in a 19,000 km orbit with an inclination of 55°. This payload is a technology demonstrator and thus launch and deployment costs are a paramount consideration. Also the payload includes classified technology, thus a USA licensed launch system is mandated. All FAAlicensed US launch systems are considered during a preliminary trade analysis. This preliminary trade analysis selects Orbital Sciences Minotaur V launch vehicle. To meet mission objective the Minotaur V 5th stage ATK-Star 37FM motor is replaced with the smaller ATK- Star 27. This new configuration allows for payload delivery without adding an additional 6th stage kick motor. End-to-end mass budgets are calculated, and a concept of operations is presented. Monte-Carlo simulations are used to characterize the expected accuracy of the final orbit. An optimal launch trajectory is presented.
