Interplanetary Orbit Transfers for Comet Interceptor Mission

This project involves the design and planning of the Comet Interceptor mission as part of the EMS610 coursework. The goal is to develop a spacecraft capable of launching into a halo orbit around the Sun-Earth L2 Lagrangian point, waiting for a comet target, and subsequently executing an interplanetary transfer to rendezvous with the comet.

Project Overview:

• Mission Concept: The Comet Interceptor will be launched as a secondary payload on an M-class mission, scheduled for 2028. Its unique design allows for operation without a predetermined target comet, capitalising on advancements in sky survey technologies that enable early detection of incoming comets.

• Orbit and Transfers: Using the Patched Conic Method, the coursework involves calculating the ∆V requirements for two primary manoeuvres:
  1. Transfer to L2: Estimating the ΔV needed to transfer the spacecraft from its parking orbit in the Earth’s equatorial plane to a halo orbit around the L2 point.
  2. Cruise to Target Comet: Once a comet is identified, determining the ΔV necessary to intercept the comet, bringing the spacecraft within 500 km of its surface.
• Fuel Efficiency: The design takes advantage of the stable gravitational balance at the L2 point, minimising fuel usage for both station-keeping and trajectory adjustments when approaching the comet.

Figure 1: Mission Phases

Figure 2: Sketch of the Comet Orbit

For more information, refer to my paper on the Comet Interceptor mission here.

Learning Outcomes:

This project has enhanced my understanding of orbital mechanics and spacecraft manoeuvring strategies, particularly in the context of designing flexible missions capable of adapting to unknown targets.

Key Skills: Orbital Mechanics, Patched Conic Method, Spacecraft Design, Mission Planning, Analytical Problem Solving.