자료유형  

 학위논문

Control Number  

0016935319

International Standard Book Number  

9798380599375

Dewey Decimal Classification Number  

629.1

Main Entry-Personal Name  

Elke, William James, III.

Publication, Distribution, etc. (Imprint  

[S.l.] : University of Minnesota., 2023

Publication, Distribution, etc. (Imprint  

Ann Arbor : ProQuest Dissertations & Theses, 2023

Physical Description  

1 online resource(149 p.)

General Note  

Source: Dissertations Abstracts International, Volume: 85-04, Section: B.

General Note  

Advisor: Caverly, Ryan James.

Dissertation Note  

Thesis (Ph.D.)--University of Minnesota, 2023.

Restrictions on Access Note  

This item must not be sold to any third party vendors.

Summary, Etc.  

요약Current and future missions to send humans to the Moon and beyond will have increasingly strict requirements on the performance and robustness of the mission vehicles. These requirements will push all aspects of the vehicles to advance to ensure mission safety and success. This includes the guidance, navigation, and control (GNC) systems operating on board.Novel GNC systems must be matured in an environment analogous to those they operate in, but these operating conditions are difficult to replicate. The first part of this dissertation presents the Cost- and Risk-Reducing Quadcopter System (CRQS, pronounced "circus"), a platform proposed to provide a low-cost, low-risk setting to mature novel GNC systems. The system is modeled, then implemented in numerical simulations to analyze a control system's ability to track a generated trajectory. The work done to fabricate a physical flying inverted pendulum, a necessary step to reach the complete CRQS, is then presented.As spacecraft grow to accommodate larger payloads and more distant destinations, the amount of liquid propellant on board grows. The interactions between a spacecraft and the liquid propellant can have detrimental effects on the performance of the spacecraft's GNC systems. The second part of this dissertation develops a low-order approximate dynamic model of a spacecraft and its liquid onboard propellant in a low-g environment. The model is then implemented in numerical simulations to analyze the trajectory of the Apollo-era service module (SM) for the probability of recontact after jettison from the command module (CM).

Subject Added Entry-Topical Term  

Aerospace engineering.

Subject Added Entry-Topical Term  

Astronomy.

Subject Added Entry-Topical Term  

Aeronomy.

Index Term-Uncontrolled  

Dynamic modeling

Index Term-Uncontrolled  

Spacecraft

Index Term-Uncontrolled  

Moon

Index Term-Uncontrolled  

Space vehicle trajectories

Index Term-Uncontrolled  

GNC systems

Added Entry-Corporate Name  

University of Minnesota Aerospace Engineering and Mechanics

Host Item Entry  

Dissertations Abstracts International. 85-04B.

Host Item Entry  

Dissertation Abstract International

Electronic Location and Access  

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Control Number  

joongbu:639716