Simulation of Saturn V S-II stage propellant feedline dynamics

Buchanan, H. J.; Jarvinen, W. A.; Kiefling, L.; Ryan, R. S.

doi:10.2514/3.30182

Cited by 7 publications

(2 citation statements)

References 2 publications

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“…Introduction P OGO vibration has been suffered by most of powerful liquid rocket vehicles, such as the Titan 2 [1], the Diamond B [2], and the Saturn 5 [3]. Its potential threats on payload and pilot safety attracted researchers' attention since it is first encountered on Titan 2 in 1960s [4], and promoted extensive studies to understand and mitigate it especially from the massive Saturn 5 for the manned Apollo program [3,[5][6][7][8].…”

mentioning

confidence: 99%

Parameter Study on Pogo Stability of Liquid Rockets

Zhao¹,

Ren²,

Yu³

et al. 2011

Journal of Spacecraft and Rockets

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Nomenclature A s= cross-sectional area of suction line, m 2 A th = nozzle throat area, m 2 C f = thrust coefficient, dimensionless g = standard gravitational acceleration, m=s 2 h s = height of propellant in suction line, m h t = height of propellant in tank, m I s = inertance of propellant in suction line, s 2 =m 2 K = effective stiffness of accumulator which is defined as K a K p =K a K p , 1=m 2 K a = stiffness of the accumulator, 1=m 2 K p = stiffness of pump cavitation, 1=m 2 k = the ratio between effective stiffness and stiffness of accumulator defined as K =K a , dimensionless L = length, m M s = modal mass of structure mode, kg i, j, n = index, dimensionless m 1 = pump gain, dimensionless N = number of thrust chambers, dimensionless p = oscillatory pressure, Pa R c = linearalized combustion resistance for propulsion flow perturbation, s=m 2 w = weight displacement of flow, N = mass flow gain factor of a pump, s = the propulsion modal damping coefficient, dimensionless = dimensionless mass flow gain factor of a pump defined as , dimensionless = couple strength between the structure mode and the propulsion system, dimensionless = frequency ratio between the propulsion mode and the structure mode, dimensionless = the structure damping ratio, dimensionless = density of the propellant, kg=m 3 ' = structural mode gain, dimensionless = circular natural frequency of the structure mode, 1=s ! = circular natural frequency of the propulsion mode, 1=sSubscripts c = combustion chamber p = pump s = suction line t = tank

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mentioning

confidence: 99%

Parameter Study on Pogo Stability of Liquid Rockets

Zhao¹,

Ren²,

Yu³

et al. 2011

Journal of Spacecraft and Rockets

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“…1. This was first experienced with the TitanII rockets in the 1960s, and recently in other powerful liquid-propellant rockets such as the Saturn V in the USA, 3) the Diamond B in France, 4) the H-IIA in Japan, 5) and the CZ-2F in China. 6) The amplitude of coupling vibration which is formed from the Pogo phenomenon can result in excessive harm to the rocket structure and astronauts.…”

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confidence: 99%

Modeling and Stability Analysis of Pogo Vibration in Liquid-Propellant Rockets with a Two-Propellant System

Tang

Li²,

Wang³

et al. 2017

Trans. Japan Soc. Aero. S Sci.

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Considering the coupling interaction between oxidant system and fuel system in liquid-propellant rockets, the modeling and stability problem of Pogo vibration in liquid-propellant rockets with a two-propellant system are investigated. Firstly, the differential equations of the two-propellant equivalent system are derived through the physical characteristics and coupling mechanism of the basic elements in a propulsion system based on reasonable assumptions and simplification. Next, the dynamic equations of the Pogo analysis model are established by coupling a longitudinal structure mode and the two-propellant equivalent equations using the dimensionless methods. It is indicated that the simplified system contains 10 dimensionless parameters expressed by the combination of all physical factors. Furthermore, the critical parameter equation of this system is then explicitly formulated using Hurwitz criterion based on the characteristic equation of the Pogo analysis model. Moreover, the numerical solutions of the boundary surface of this system stability are extensively studied. The results show the effects of dimensionless and original parameters on Pogo stability. Finally, the correctness of the simplified Pogo stability analysis is confirmed using the simulation results of a certain type of Long March rocket.

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Pressure Stiffened Modal Correlation of a Cylindrical Pressure Vessel

Jewell

Yunis

2019

Topics in Modal Analysis &Amp; Testing, Volume 8

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Simulation of Saturn V S-II stage propellant feedline dynamics

Cited by 7 publications

References 2 publications

Parameter Study on Pogo Stability of Liquid Rockets

Parameter Study on Pogo Stability of Liquid Rockets

Modeling and Stability Analysis of Pogo Vibration in Liquid-Propellant Rockets with a Two-Propellant System

Pressure Stiffened Modal Correlation of a Cylindrical Pressure Vessel

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