Introduction and Systems Engineering
Introduction to spacecraft subsystems, the design approach from an industrial perspective
Payload
Types, operation, interface requirement
Mission Analysis
Orbit selection, Keplerian (idealised) orbits, co-planar orbit transfers
Attitude Control
Spacecraft angular momentum, types of spacecraft stabilisation, the closed loop system and impacts on the spacecraft design
Propulsion
Types, fundamental performance parameters, chemical systems, electrical systems
Power
Power sources, solar arrays, power storage (batteries), sizing up the system component
Communications
Frequencies, encoding, modulation, bandwidth, the communications link analysis
Thermal Control
Material properties, spacecraft thermal balance, thermal control
A spacecraft design case study
A specific spacecraft type and mission (remote sensing) is treated as a case study to illustrate spacecraft design features. This case study includes:
Overview of Mission Objectives
Spacecraft Payload
Review of payload types suitable/available for proposed mission.
Selection of payload. Study of payload operation to provide a mission
and payload interface requirements.
Mission Analysis
Assessment of payload derived mission requirements to establish
candidate mission orbits. Orbit trade-off and mission specification.
Spacecraft System Design
Identification of subsystem design requirements, and system design
drivers. Establishment of candidate configurations. Feasibility study
phase trade-off. Selection of spacecraft configuration.
Subsystem Design
Overview of subsystem design, taking account of interactions and
drivers for the particular mission: attitude control, propulsion,
spacecraft power, thermal control, communications, structures.
Impact of ground segment and operations.
Coursework Briefing