Reusable Lunar Surface Access Vehicle

Project Synopsis

As the ongoing need for exploration presses forward the need for a lunar outpost becomes even more vital. To support this objective, a spacecraft capable of supplying the needed equipment and astronauts to the lunar surface is critical. This paper discusses a design to fulfill and exceed this need. Two designs were developed to address this critical need and one was selected. A Non-Modular and Modular spacecraft were developed to take two separate paths regarding mission design. Non-Modular utilizes the SLS Block 2 as its primary launch vehicle while the Modular architecture utilizes the Falcon Heavy. This approach was taken to develop two options that provided the most feasible launch vehicles that meet derived requirements based on mission needs. A study was conducted after the Conceptual Design Review of both architectures which led to a down-selection. 

The spacecraft selected to proceed forward with was the Non-Modular spacecraft. The down-selection will later be discussed in the Design Process section of this paper. The selected architecture emphasizes a robust propulsion system providing a thrust-to-weight ratio of 2 during full operation and 1.5 during engine failure. The architecture incorporates ample spacing for usable crew space and resting being 68m3 and 6m3 respectively. The loading and unloading of cargo have been simplified via a unique lifting crane capable of loading and unloading, as well as organizing cargo. Lastly, the spacecraft provides an astronaut abort system referred to as Lumos in-case an event arises where astronaut safety becomes threatened.

Modular Vehicle Architecture (Left) and Non-Modular Behicle Architecture (Right)

Project Structure

Structural Analysis of the Vehicle

Personal Contribution

As the Deputy Team Lead, I fulfilled a managerial role responsible for the integration of all the varying subteams. One primary way I did that was by ensuring our requirements compliance throughout the architecture development. In this, I had a direct hand validating all requirements including those within NASA STD 3001 for human spaceflight. 

In addition to this, I was also the lead CAD designer for maintaining and updating the model and all subassemblies within it. From this, I also created most of the renders as well to accurately depict the vehicle in all configurations and highlight each component system. 

I also carried out the structural and vibrational analysis of the craft as well. This consisted of two separate loading configurations, one as a static case under max payload and the other was a lunar surface launch case with max payload. Within this three unique areas of the craft were surveyed. These included the landing legs, the structural frame, and the pressurized crew vessel.