NDLI: Simulation of liquid rocket engine failure propagation using self-evolving scenarios

Content Provider	IEEE Xplore Digital Library
Author	Mathias, D.L. Motiwala, S.A.
Copyright Year	2015
Description	Author affiliation: NASA Ames Res. Center, Univ. Space Res. Assoc. (USRA), Moffett Field, CA, USA (Motiwala, S.A.) \|\| NASA Ames Res. Center, Moffett Field, CA, USA (Mathias, D.L.)
Abstract	Traditional probabilistic risk assessment approaches often require failure scenarios to be explicitly defined through event sequences that are then quantified as part of the integrated analysis. This approach becomes difficult when failure propagation paths change as a function of the system state and Mission Elapsed Time (MET). Additionally, if the propagation paths represent interactions among even a modest number of components, the number of possible scenarios becomes combinatorially intractable. This paper presents an alternate approach for quantifying failure propagation probabilities in such a case. Rather than explicitly defining scenario sequences, simple physical models are created for each of the components. In this way, only the physical states and rules of component interactions must be defined, rather than event sequences for each individual scenario. Initiating failures are introduced into the system (either randomly or as defined by relative likelihood) and the failures cascade through the system via the interaction rules. This process is repeated using Monte Carlo methods, allowing the most probable scenarios to “self-evolve” in terms of both sequence path and frequency. This approach was applied to failures occurring in the engine compartment of a space launch vehicle with four liquid rocket engines and four high-pressure helium tanks. Each engine was modeled with key components, such as turbomachinery, combustion chamber, propellant lines, and additional support systems. Three test cases were conducted with different high-energy engine failure initiators. End results of interest include loss of only a single additional engine and tank burst, which represent the loss-of-mission (LOM) and loss-of-crew (LOC) end states, respectively. We show that most scenario outcomes are unique and that many scenarios involve complex chain reactions that are difficult to predict, let alone enumerate. This demonstrates the importance of the modeling approach in capturing the majority of the involved risk, which can be used to assess the overall risks to the crew during a launch vehicle abort.
Starting Page	1
Ending Page	6
File Size	4207995
Page Count	6
File Format	PDF
e-ISBN	9781479967032
DOI	10.1109/RAMS.2015.7105129
Language	English
Publisher	Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Publisher Date	2015-01-26
Publisher Place	USA
Access Restriction	Subscribed
Rights Holder	Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Subject Keyword	Engines Solid modeling Vehicles Computational modeling Monte Carlo methods Liquids Rockets scenario generation spaceflight rocket engine dynamic risk assessment
Content Type	Text
Resource Type	Article

Sl.	Authority	Responsibilities	Communication Details
1	Ministry of Education (GoI), Department of Higher Education	Sanctioning Authority	https://www.education.gov.in/ict-initiatives
2	Indian Institute of Technology Kharagpur	Host Institute of the Project: The host institute of the project is responsible for providing infrastructure support and hosting the project	https://www.iitkgp.ac.in
3	National Digital Library of India Office, Indian Institute of Technology Kharagpur	The administrative and infrastructural headquarters of the project	Dr. B. Sutradhar bsutra@ndl.gov.in
4	Project PI / Joint PI	Principal Investigator and Joint Principal Investigators of the project	Dr. B. Sutradhar bsutra@ndl.gov.in Prof. Saswat Chakrabarti will be added soon
5	Website/Portal (Helpdesk)	Queries regarding NDLI and its services	support@ndl.gov.in
6	Contents and Copyright Issues	Queries related to content curation and copyright issues	content@ndl.gov.in
7	National Digital Library of India Club (NDLI Club)	Queries related to NDLI Club formation, support, user awareness program, seminar/symposium, collaboration, social media, promotion, and outreach	clubsupport@ndl.gov.in
8	Digital Preservation Centre (DPC)	Assistance with digitizing and archiving copyright-free printed books	dpc@ndl.gov.in
9	IDR Setup or Support	Queries related to establishment and support of Institutional Digital Repository (IDR) and IDR workshops	idr@ndl.gov.in

A Cluster Warhead Projection-Time Self-Adaptive Algorithm and Simulation

Study on risk scenarios of project failure based on Monte-Carlo simulation

Human space mission architecture risk analysis

Intelligent collision risk assessment based on Neural Network Ensemble

Physical simulation in space launcher engine risk assessment

PARALLEL UNSTEADY TURBOPUMP SIMULATIONS FOR LIQUID ROCKET ENGINES

Applying parallel block predictor-corrector methods to a Space Shuttle main rocket engine simulation

Research on simulation method for liquid rocket engines

Integrated simulation of solid propellant rockets (2000).

Simulation of liquid rocket engine failure propagation using self-evolving scenarios

Similar Documents

A Cluster Warhead Projection-Time Self-Adaptive Algorithm and Simulation

Study on risk scenarios of project failure based on Monte-Carlo simulation

Human space mission architecture risk analysis

Intelligent collision risk assessment based on Neural Network Ensemble

Physical simulation in space launcher engine risk assessment

PARALLEL UNSTEADY TURBOPUMP SIMULATIONS FOR LIQUID ROCKET ENGINES

Applying parallel block predictor-corrector methods to a Space Shuttle main rocket engine simulation

Research on simulation method for liquid rocket engines

Integrated simulation of solid propellant rockets (2000).

Simulation of liquid rocket engine failure propagation using self-evolving scenarios