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Detection and Characterisation of Unknown Spacecraft Maneuvers.

紀錄類型:	書目-電子資源 : Monograph/item
正題名/作者:	Detection and Characterisation of Unknown Spacecraft Maneuvers./
作者:	Kaderali, Shaziana.
面頁冊數:	1 online resource (121 pages)
附註:	Source: Masters Abstracts International, Volume: 83-05.
Contained By:	Masters Abstracts International83-05.
標題:	Space stations. -
電子資源:	http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=28730955click for full text (PQDT)
ISBN:	9798544222255

Detection and Characterisation of Unknown Spacecraft Maneuvers.
Kaderali, Shaziana.

Detection and Characterisation of Unknown Spacecraft Maneuvers. - 1 online resource (121 pages)

Source: Masters Abstracts International, Volume: 83-05.

Thesis (M.E.)--McGill University (Canada), 2021.

Includes bibliographical references

Space Situational Awareness (SSA) is an important and pressing field, as the amount of space debris is growing due to the increase in spacecraft launches. Space agencies like NASA and ESA keep track of over 5,000 spacecraft and 20,000 spacecraft-related debris objects currently orbiting the Earth. These spacecraft may undergo trajectory changes through artificial impulsive maneuvers without warning, posing a risk to other spacecraft in the vicinity. Additionally, measurement data often consists of uncertainties, where usual spacecraft maneuver detection and characterisation methods are often computationally expensive. The goal of this work is to develop a quick, reliable, computationally inexpensive method for spacecraft maneuver detection and characterisation, which would be used to assist satellite operators in collision avoidance measures. This dissertation utilises such a technique, which is applied to simulated measurement data of an orbiting spacecraft taken from one ground site. With these objectives, a method using a modified Extended Kalman Filter (EKF) with covariance inflation from previous research was explored and simplified. Through building on this set of research, a new parameter definition is presented for maneuver detection and characterisation, named K, with focus on transverse apogee and perigee maneuvers. A relationship was then found between the detection parameter (both the original parameter, Ψ, and the new parameter, K) and the magnitude of the impulsive artificial maneuver. The detection and characterisation method was tested in several different scenarios, varying ∆v magnitude and scale, ∆v direction, maneuver orbital location, orbit geometry, noise covariance, detection parameter threshold, state covariance inflation threshold, and maneuver duration. In general, it was found that as the ∆v magnitude increases, so does the magnitude of the detection parameter. This relationship was found to be nonlinear, of either a quadratic (Ψ) or logarithmic (K) relation through best fit curve testing. Possible future work includes: testing multi-maneuver scenarios, multi-sensor data collection and fusion, break-up or berthing events, rendezvous or mating events, and MATLAB EKF protocol implementation.

Electronic reproduction.
Ann Arbor, Mich. :
ProQuest,
2023

Mode of access: World Wide Web

ISBN: 9798544222255Subjects--Topical Terms:

789352
Space stations.
Index Terms--Genre/Form:

542853
Electronic books.

Detection and Characterisation of Unknown Spacecraft Maneuvers.
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100 1 $a Kaderali, Shaziana. $3 3694397
245 1 0 $a Detection and Characterisation of Unknown Spacecraft Maneuvers.
264 0 $c 2021
300 $a 1 online resource (121 pages)
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500 $a Source: Masters Abstracts International, Volume: 83-05.
500 $a Advisor: Misra, Arun K.
502 $a Thesis (M.E.)--McGill University (Canada), 2021.
504 $a Includes bibliographical references
520 $a Space Situational Awareness (SSA) is an important and pressing field, as the amount of space debris is growing due to the increase in spacecraft launches. Space agencies like NASA and ESA keep track of over 5,000 spacecraft and 20,000 spacecraft-related debris objects currently orbiting the Earth. These spacecraft may undergo trajectory changes through artificial impulsive maneuvers without warning, posing a risk to other spacecraft in the vicinity. Additionally, measurement data often consists of uncertainties, where usual spacecraft maneuver detection and characterisation methods are often computationally expensive. The goal of this work is to develop a quick, reliable, computationally inexpensive method for spacecraft maneuver detection and characterisation, which would be used to assist satellite operators in collision avoidance measures. This dissertation utilises such a technique, which is applied to simulated measurement data of an orbiting spacecraft taken from one ground site. With these objectives, a method using a modified Extended Kalman Filter (EKF) with covariance inflation from previous research was explored and simplified. Through building on this set of research, a new parameter definition is presented for maneuver detection and characterisation, named K, with focus on transverse apogee and perigee maneuvers. A relationship was then found between the detection parameter (both the original parameter, Ψ, and the new parameter, K) and the magnitude of the impulsive artificial maneuver. The detection and characterisation method was tested in several different scenarios, varying ∆v magnitude and scale, ∆v direction, maneuver orbital location, orbit geometry, noise covariance, detection parameter threshold, state covariance inflation threshold, and maneuver duration. In general, it was found that as the ∆v magnitude increases, so does the magnitude of the detection parameter. This relationship was found to be nonlinear, of either a quadratic (Ψ) or logarithmic (K) relation through best fit curve testing. Possible future work includes: testing multi-maneuver scenarios, multi-sensor data collection and fusion, break-up or berthing events, rendezvous or mating events, and MATLAB EKF protocol implementation.
520 $a La connaissance de la situation spatiale est un domaine important et pressant, a cause de ` la quantite de d ´ ebris spatiaux qui s'accumulent avec l'augmentation des lancements ´ d'engins spatiaux. Les agences spatiales comme la NASA et l'ESA tracent de plus de 5000 satellites et 20000 debris li ´ es aux satellites en orbite autour de la Terre. Ces satellites ´ peuvent effectuer des changements de trajectoire par des manoeuvres artificielles et impulsives sans avertissement, ce qui peut representer un risque pour d'autres satellites ´ a proximit ` e. En plus, les donn ´ ees de mesure sont souvent constitu ´ ees d'incertitudes, ce ´ qui fait que les methodes habituelles de d ´ etection et de caract ´ erisation des manoeuvres ´ spatiales sont souvent couteuses en calcul. Le but de ce travail est de d ˆ evelopper une ´ methode rapide, fiable et peu co ´ uteuse en calcul pour la d ˆ etection et la caract ´ erisation ´ des manoeuvres des satellites, qui serait utilisee pour aider les op ´ erateurs de satellites ´ dans les mesures d'evitement des collisions. Cette th ´ ese utilise une technique, qui est ` appliquee´ a des donn ` ees de mesure simul ´ ees d'un satellite artificiel en orbite, prises ´ a` partir d'un site au sol sure la Terre. Avec ces objectifs, une methode utilisant un ´ "Extended Kalman Filter (EKF)" modifie avec inflation de covariance ´ a partir de ` recherches anterieures a ´ et´ e explor ´ ee et simplifi ´ ee. En s'appuyant sur cet ensemble de ´ recherches, une nouvelle definition de param ´ etre est pr ` esent ´ ee pour la d ´ etection et la ´ caracterisation des manoeuvres, nomm ´ e K, avec comme but les manoeuvres d'apog ´ ee et ´ de perig ´ ee transversales. Une relation a ensuite ´ et´ e trouv ´ ee entre le param ´ etre de ` detection (le param ´ etre d'origine, du ` Ψ et le nouveau parametre, K) et l'amplitude de la ` manoeuvre artificielle et impulsive. La methode de d ´ etection et de caract ´ erisation a ´ et´ e´ examine aux plusieurs sc ´ enarios diff ´ erents, par variant de la magnitude et l' ´ echelle de ´ ∆v, la direction de ∆v, la position orbitale de la manoeuvre, la geom´ etrie de l'orbite, la ´ covariance du bruit de la mesure, la valeur seuil du parametre de d ` etection, la valeur ´ seuil de l'inflation de la covariance d'etat et la dur ´ ee de la manoeuvre. En g ´ en´ eral, il a ´ et´ e´ constate que lorsque l'amplitude de ´ ∆v augmente, l'amplitude du parametre de ` detection augmente aussi. Cette relation s'est av ´ er´ ee non-lin ´ eaire, soit quadratique (´ Ψ) ou logarithmique (K), grace ˆ a des techniques d'ajustement de courbe. Les travaux futurs ` possibles incluent: le test de scenarios multi-manoeuvres, la collecte et la fusion de ´ donnees multi-capteurs, les ´ ev´ enements de rupture ou d'accostage, les ´ ev´ enements de ´ rendez-vous ou d'amarrage, et l'implementation du protocole EKF en ´ MATLAB.
533 $a Electronic reproduction. $b Ann Arbor, Mich. : $c ProQuest, $d 2023
538 $a Mode of access: World Wide Web
650 4 $a Space stations. $3 789352
650 4 $a Algorithms. $3 536374
650 4 $a Surveillance. $3 3559358
650 4 $a Space surveillance. $3 875591
650 4 $a Artificial satellites. $3 1242303
650 4 $a Aerospace engineering. $3 1002622
650 4 $a Computer science. $3 523869
650 4 $a Engineering. $3 586835
655 7 $a Electronic books. $2 lcsh $3 542853
690 $a 0538
690 $a 0984
690 $a 0537
710 2 $a ProQuest Information and Learning Co. $3 783688
710 2 $a McGill University (Canada). $3 1018122
773 0 $t Masters Abstracts International $g 83-05.
856 4 0 $u http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=28730955 $z click for full text (PQDT)

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