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Dynamic Modeling for Simulation and ...

Elke, William James, III.

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Dynamic Modeling for Simulation and Experimentation Tools Used in the Analysis of Space Vehicle Trajectories.

紀錄類型:	書目-電子資源 : Monograph/item
正題名/作者:	Dynamic Modeling for Simulation and Experimentation Tools Used in the Analysis of Space Vehicle Trajectories./
作者:	Elke, William James, III.
出版者:	Ann Arbor : ProQuest Dissertations & Theses, : 2023,
面頁冊數:	149 p.
附註:	Source: Dissertations Abstracts International, Volume: 85-04, Section: B.
Contained By:	Dissertations Abstracts International85-04B.
標題:	Aerospace engineering. -
電子資源:	https://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=30688911
ISBN:	9798380599375

Dynamic Modeling for Simulation and Experimentation Tools Used in the Analysis of Space Vehicle Trajectories.
Elke, William James, III.

Dynamic Modeling for Simulation and Experimentation Tools Used in the Analysis of Space Vehicle Trajectories. - Ann Arbor : ProQuest Dissertations & Theses, 2023 - 149 p.

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

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

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

Current 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).

ISBN: 9798380599375Subjects--Topical Terms:

1002622
Aerospace engineering.
Subjects--Index Terms:

Dynamic modeling

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300 $a 149 p.
500 $a Source: Dissertations Abstracts International, Volume: 85-04, Section: B.
500 $a Advisor: Caverly, Ryan James.
502 $a Thesis (Ph.D.)--University of Minnesota, 2023.
506 $a This item must not be sold to any third party vendors.
520 $a Current 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).
590 $a School code: 0130.
650 4 $a Aerospace engineering. $3 1002622
650 4 $a Astronomy. $3 517668
650 4 $a Aeronomy. $3 2102064
653 $a Dynamic modeling
653 $a Spacecraft
653 $a Moon
653 $a Space vehicle trajectories
653 $a GNC systems
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690 $a 0367
690 $a 0606
710 2 $a University of Minnesota. $b Aerospace Engineering and Mechanics. $3 1681609
773 0 $t Dissertations Abstracts International $g 85-04B.
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792 $a 2023
793 $a English
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