AE4830 Spacecraft Systems I

This course emphasizes the systems analysis of geosynchronous spacecraft and covers the analysis of GNC (orbit and attitude control), structures, propulsion, thermal and electrical power subsystems. Basic mathematical equations will be used in the preliminary design of the subsystems and the tradeoff studies involved. The differences and similarities between dual-spin and three-axis stabilized spacecraft will be covered in detail. Systems aspect of a typical mission profile will be illustrated. Throughout, emphasis will be on the spacecraft bus. Students will be engaged in problem solving during most of the laboratory period.

Prerequisite

Completion of Space Operations core-curriculum

Lecture Hours

3

Lab Hours

2

Course Learning Outcomes

Upon successful completion of this course, students will be able to:

• Differentiate between a mission statement and its objectives for a mission architecture.
• Identify which mission requirements are functional, operational, and constraints for a spacecraft.
• Derive preliminary system requirements from mission requirements for a spacecraft.
• Apply systems engineering tools and principles and conduct trade studies to assess system and subsystem performance, as well as the trade-offs between performance, cost, and risk, when given key spacecraft design parameters.
• Assess system performance and determine if the mission requirements have been met for a set of subsystem specifications.