Satellite Rescue- Luck of Skillful Application of Technology

Yendler, Boris

doi:10.2514/6.2012-5287

Cited by 3 publications

(2 citation statements)

References 2 publications

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“…As noted in Ref. 10, the fact "..that two methods of fuel estimation have provided the similar result does not mean that the result is correct". The neglect of this fact can have dire consequences 11,12 .…”

Section: Word Of Cautionmentioning

confidence: 84%

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Prediction of Spacecraft Remaining Life - Challenges and Achievements

Nariyoshi¹,

Chernikov²,

Yendler³

2013

49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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A successful mission planning, in particular, at End-of-Life (EOL) depends on many factors including an accurate knowledge of remaining propellant, as a one of the major factors. Achieving the highest accuracy of propellant estimation is very important to a successful mission management. The current paper discusses different methods of propellant estimation, such as, book-keeping, PVT (Pressure, Volume, Temperature) and thermal gauging. The current paper shows that the Thermal Gauging Method (TGM) provides more accurate estimation of propellant remaining than bookkeeping and PVT methods at End-ofLife (EOL). The current paper also discusses the difference between the various thermal gauging methods, namely, TPGT, PGS and TGM . While the TGM consists of several steps, the paper discusses problems related to finding load of a propellant tank, e.g., how to isolate tank temperature rise due to tank heaters from rise due to other heat sources: sun, equipment, etc. A "toolbox" of software tools has been developed for pre and post processing and debugging. Some of the tools could be very useful for general thermal analyses. For satellites with multi-tank propulsion system, regardless of mono-or bipropellant, estimation uncertainty of individual tank load is another factor affecting remaining spacecraft life. Therefore, a total usable propellant load could be less than the sum of the individual tank propellant estimate. The current paper shows how to derive the expected usable propellant from load of each component and uncertainties associated with the load estimates. Nomenclature  = standard deviation m = propellant load/mass p = model parameter which affects heating i = parameter index tot = total uncertainty fit = uncertainty related to curve fit BK

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Section: Word Of Cautionmentioning

confidence: 84%

“…Similar to the TGM, the PGS method employs a high fidelity tank model and satellite thermal model to determine thermal connection between propellant tank and environment 8,9,10 . However, the TGM uses more accurate tank model than the PGS approach.…”

Section: Propellant Gauging Systemmentioning

confidence: 99%

Prediction of Spacecraft Remaining Life - Challenges and Achievements

Nariyoshi¹,

Chernikov²,

Yendler³

2013

49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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Advanced fault detection and diagnosis in spacecraft attitude control systems: Current state and challenges

Pourtakdoust

Mehrjardi

Hajkarim

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part G:

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A review of advanced fault detection and diagnosis (FDD) techniques in attitude control systems (ACSs) of spacecraft is presented. In the first part of the paper, several types of ACS failure scenarios with their practical solutions are presented. Next, the existing approaches to FDD are considered and classified based on different criteria, including applications and design techniques. The literature of this part showed that to enhance ACS operational safety, predictability of failure of an ACS and/or of its components as well as reducing the possibility of failure occurrence is imperative. In addition, fast FDD of various kinds of failures is necessary to guarantee the required reliability of an ACS. The second part of this study highlights challenges involved with different FDD approaches, emphasizing their practical applicability. Current research gaps in FDD techniques such as insensitive residual signal, process monitoring methods, accurate plant model design, easy-to-use software development, FDD tuning process, dealing with noisy sensor measurements, time taken for fault management, the sensitivity of FDD system to faults, and FDD robustness are further elaborated on. Subsequently, the state-of-the-art FDD and its future needs are reflected on. The results of this study could direct spacecraft manufacturers and ACS providers to focus on future needs and improve ground testing for enhanced operational reliability and redundancy.

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System Resilience Framework and Modeling for a CubeSat System

Rodriguez

Madni

2014

SpaceOps 2014 Conference

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Satellite Rescue- Luck of Skillful Application of Technology

Cited by 3 publications

References 2 publications

Prediction of Spacecraft Remaining Life - Challenges and Achievements

Prediction of Spacecraft Remaining Life - Challenges and Achievements

Advanced fault detection and diagnosis in spacecraft attitude control systems: Current state and challenges

System Resilience Framework and Modeling for a CubeSat System

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