Propulsion Systems

Moss, J.B.; Stark, John

doi:10.1002/9781119971009.ch6

Cited by 2 publications

(4 citation statements)

References 19 publications

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“…Positive expulsion devices are extensively used in spacecraft secondary propulsion systems. Secondary propulsion systems are used in spacecrafts in maneuvers of reduced thrust level, such as station keeping and orbit control and attitude control (Moss and Stark, 2003). Positive expulsion devices use a pressure differential to expel propellant from its storage vessel.…”

Section: Introductionmentioning

confidence: 99%

Thermal analysis of the girth weld of an elastomeric diaphragm tank

Vincent

Carella

Cisilino

2014

Journal of Materials Processing Technology

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Section: Introductionmentioning

confidence: 99%

Thermal analysis of the girth weld of an elastomeric diaphragm tank

Vincent

Carella

Cisilino

2014

Journal of Materials Processing Technology

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“…The ratio of nozzle to core exit pressure p 3.3 /p 3.1 is a function of the selected nozzle geometry. The resulting thrust F and specific impulse I SP are given by (Moss 1995 whereṁ is the total propellant mass flow (kg s −1 ), A sect,3.3 is the cross-sectional area of the nozzle exit (m 2 ), p ambient is the ambient pressure (Pa) and g 0 is the gravitational acceleration at the surface of the earth (m s −2 ). The specific impulse allows the overall performance of a rocket-propelled vehicle to be determined via the Tsiolkovsky equation (Moss 1995) …”

Section: (A) Fundamental Performance Relations For a Baseline Mars Homentioning

confidence: 99%

“…Using the station numbering convention introduced in figure 1 and assuming steady, isentropic flow of a perfect gas, the exhaust velocity of a convergentdivergent rocket nozzle is given by (Moss 1995) …”

Section: (A) Fundamental Performance Relations For a Baseline Mars Homentioning

confidence: 99%

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A Mars hopping vehicle propelled by a radioisotope thermal rocket: thermofluid design and materials selection

2010

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Rocket-propelled vehicles capable of travelling a kilometre or more in a ballistic ‘hop’ with propellants acquired from the Martian atmosphere offer the potential for increased mobility and planetary science return compared with conventional rovers. In concept, a radioisotope heat source heats a core or ‘thermal capacitor’, which in turn heats propellant exhausted through a rocket nozzle to provide thrust. A systematic study of the thermodynamics, heat transfer and selection of core materials for a Mars hopper was undertaken. The aim was to advance the motor design and assess technical risks and feasibility. Analytical and numerical motor models were developed; the former to generate thermodynamic performance limits, an ideal hop distance and plot a materials selection chart using simple explicit relations. The numerical model assessed the effect of core configuration and geometry. A hop coefficient C hop is shown to characterize the effect of core geometry independently of core material and temperature. The target hop distance of 1 km is shown to be robust. A moderate advantage to pebble-bed cores over a core consisting of straight channels was suggested. High-performance engineering ceramics such as boron carbide offer the longest hop providing the core temperature can be increased significantly above 1200 K.

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Propulsion Systems

Cited by 2 publications

References 19 publications

Thermal analysis of the girth weld of an elastomeric diaphragm tank

Thermal analysis of the girth weld of an elastomeric diaphragm tank

A Mars hopping vehicle propelled by a radioisotope thermal rocket: thermofluid design and materials selection

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