Mars reconnaissance lander: Vehicle and mission design

Williams, Hannah; Bridges, J. C.; Ambrosi, Richard M.; Perkinson, M. C.; Reed, J.; Peacocke, L.; Bannister, N.; Howe, Steven D.; O’Brien, Robert C.; Klein, Andrew C.

doi:10.1016/j.pss.2011.07.011

Cited by 7 publications

(4 citation statements)

References 23 publications

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“…These estimates are not supported by any data or calculations and no separate reliability discussion is provided for the propulsive descent stage of the EDL. Williams et al 7 provide some general lander reliability discussion, but provide no specific results. Edquist et al, 1 Braun and Manning, 8 and Stancliff et al 9 also discuss reliability of landers, but provide no examples.…”

Section: Lander Reliabilitymentioning

confidence: 99%

Correlated reliability and an application: Propulsive landing on Mars

Sarper

2019

Proceedings of the Institution of Mechanical Engineers, Part O:

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This article discusses reliability of landers and provides a review and examples of correlated reliability. Examples are cited to show generally beneficial effects of correlation in system reliability. Then, reliabilities of two near future landing systems are studied using two analytical (Downton, and Marshall & Olkin) bivariate exponential distributions and two simulation methods that incorporate correlation in reliability calculations. Both landing systems are composed of correlated two-unit subsystems. Numerical examples show mean system life, standard deviation of the system life, mean system life confidence interval, and reliability for each lander’s propulsive descent. Both simulation method results are in between the results obtained from the two analytical methods and Downton’s method yields the most conservative reliability. This article also shows how the Downton method–based reliability value can be predicted as a function of the reliabilities obtained from the other three methods. An up-to-date literature review of all related topics is also provided.

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Section: Lander Reliabilitymentioning

confidence: 99%

Correlated reliability and an application: Propulsive landing on Mars

Sarper

2019

Proceedings of the Institution of Mechanical Engineers, Part O:

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“…P ropulsion systems that deliver large thrusts and high specific impulses are in demand for space missions, and they have been successfully developed [1]. Bipropellant thrusters in the thrust range of ten to several hundreds of newtons play important roles in attitude control and orbital transfer, as well as in planetary landing and takeoff [2][3][4][5][6]. This is because they achieve higher thrust levels than electric thrusters and higher specific impulses than monopropellant thrusters.…”

Section: Introductionmentioning

confidence: 99%

Unsteady Stream-Tube Model for Pulse Performance of Bipropellant Thrusters

Oishi

Tauchi

Inoue

2023

Journal of Propulsion and Power

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We propose a theoretical model for predicting the impulse bit of bipropellant thrusters under pulse-firing operations. The present theoretical model, which considers the nonuniformity of the mixture ratios created inside the thrust chamber, extends the stream-tube approach, which is limited to the prediction of the steady performance. In pulse-firing operation, the fuel or the oxidizer alone can be injected in isolation due to the mismatched injection timing before the rated injection, which leads to the deterioration of performance as compared with the steady operation. The present approach (the unsteady stream-tube model) successfully implements a time-dependent stream-tube structure inside the thrust chamber, allowing for the prediction of the impulse bit as a straightforward function of the injection conditions. Three different pulse-firing tests using distinct hypergolic propellants demonstrate the validity of this model, typically reproducing the notable trend of deterioration in the impulse bit in the short-pulsed mode. We also examine the time-averaged specific impulse and mass flow rate to improve the impulse bit during short-pulsed operations.

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“…The current decade saw a rejuvenated interest in the exploration of Mars [1][2][3][4][5][6] . In late 2013, the first Indian mission to the red planet, i.e.…”

Section: Introductionmentioning

confidence: 99%

Lyman Alpha Photometer: a far-ultraviolet sensor for the study of hydrogen isotope ratio in the Martian exosphere

Sridhar¹,

Rao²,

Kalyani³

et al. 2015

Current Science

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The Lyman Alpha Photometer (LAP), developed for flight on the Mars Orbiter Mission (MOM) spacecraft in 2013, is primarily designed to measure deuterium to hydrogen abundance ratio of the Martian exosphere over a 6-month period from a 263 km  71,358 km elliptical orbit around Mars. A set of ultrapure (99.999%) hydrogen and deuterium gas-filled cells comprising tungsten filaments, a 25 mm diameter collection lens and a solar-blind photomultiplier tube together with an 8 nm bandpass Lyman alpha filter are the principal electro-optical assemblies of the instrument. This article presents scientific objectives of LAP and its performance specifications along with details of instrument design. The ground characterization techniques to assess LAP operational performance are also presented. End-to-end test results and evaluation matrix of LAP were satisfactory, well within the desired specifications. The first LAP onboard operation was carried out during the cruise phase of MOM spacecraft journey to verify its functionality and all recorded on-board health parameters were satisfactory.

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Mars reconnaissance lander: Vehicle and mission design

Cited by 7 publications

References 23 publications

Correlated reliability and an application: Propulsive landing on Mars

Correlated reliability and an application: Propulsive landing on Mars

Unsteady Stream-Tube Model for Pulse Performance of Bipropellant Thrusters

Lyman Alpha Photometer: a far-ultraviolet sensor for the study of hydrogen isotope ratio in the Martian exosphere

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