History of U.S. Navy ramjet, scramjet, and mixed-cycle propulsion development

Waltrup, P. J.; White, Michael E.; Zarlingo, F.; Gravlin, Edward S.

doi:10.2514/6.1996-3152

Cited by 13 publications

(10 citation statements)

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“…The two main limitations of the ramjet are its inability to produce thrust at low speeds and performance drops at flight speeds above Mach 6. To overcome the problem of static thrust, most ramjets use a mixed-cycle ramjet as described by Waltrup et al [1996] to boost the vehicle to a given speed where the ramjet engine can begin to operate.…”

Section: The Ramjet Enginementioning

confidence: 99%

See 1 more Smart Citation

An Investigation of Controlled Oscillations in a Plasma Torch for Combustion Enhancement

Sanders¹,

Schetz²

2006

14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference

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Section: The Ramjet Enginementioning

confidence: 99%

“…All of the liquid hydrocarbon fuel is injected and a pilot flame is added to this small subsonic combustor to further enhance combustion. Schematic of a DCR is shown in Figure 1.4 [Waltrup et al 1996].…”

Section: The Dual Combustor Ramjetmentioning

confidence: 99%

An Investigation of Controlled Oscillations in a Plasma Torch for Combustion Enhancement

Sanders¹,

Schetz²

2006

14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference

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“…Other techniques for attaining sufficient ramjet flight velocity are provided by solid rocket propulsion systems [Waltrup et al 2002]. A series of multiple ramjet applications have conceptualized from a fundamental performance analysis perspective by LeMoyne and Mastroianni [LeMoyne 2009, LeMoyne 2011, LeMoyne 2012, LeMoyne and Mastroianni 2014a, LeMoyne and Mastroianni 2014b].…”

Section: Introductionmentioning

confidence: 99%

“…Conventional ramjet During 1909 Lake issued a patent for the concept of ramjet propulsion [Waltrup et al 2002]. On the order of four decades later flight-testing of the ramjet application was achieved by Renee Leduc during 1949 through the ramjet propelled Leduc 010, which reached preliminary flight velocity through a transport aircraft [Leduc].…”

Section: Introductionmentioning

confidence: 99%

Fundamental Architecture and Analysis of Photofission Ramjet Propulsion

LeMoyne¹,

Mastroianni²

2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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The ramjet demonstrates considerable utility for air-breathing propulsion systems. The ramjet benefits from air-breathing performance and minimal complexity in terms of moving parts. The conventional ramjet system functions based on stored chemical propellant. However, non-chemical strategies of imparting energy to the propulsive fluid, such as nuclear fission offer the advantage of increased energy density relative to chemical schemes. The concept of incorporating nuclear fission into a ramjet propulsion system has been a subject of interest from a historical perspective. Traditional fission occurs through neutrons with an appropriate kinetic energy interacting with heavy nuclei, such as uranium. However, there are many issues inherent with neutron-initiated fission. The fission reactions must be sustained by a source of neutrons with suitable kinetic energy. Neutron moderation involves the additional incorporation of various materials for modifying their respective energy kinetic levels, which can negatively impact the propulsion system in terms of both mass and system complexity. Therefore, photofission constitutes a paradigm shift relative to traditional neutron initiated nuclear fission. The proposed architecture advocates photofission derived by an ultra-intense laser as an energy source for the propulsive fluid of a ramjet. The primary physics that elucidate the phenomena of photofission are comprehensively entailed. With the foundation of the physics describing photofission presented, a fundamental analysis of the proposed photofission ramjet is incorporated. A suitable application for a photofission ramjet propulsion system would be integral with an Unmanned Autonomous Vehicle (UAV). The resulting fundamental analysis of the photofission ramjet successfully demonstrates potential feasibility for future research, development, test, and evaluation.

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“…1). Such an engine features a much more compact configuration than earlier systems having a tandem booster rocket that is jettisoned after propellant burnout (Fry 2004;Myers 1984;Waltrup et al 2002). The large difference in the chamber operating pressure between the rocket and the ramjet phase poses a major IRR development challenge, which can be solved by using a booster nozzle that is ejected after the boost phase.…”

Section: Introductionmentioning

confidence: 99%

Unified Analysis of Internal Flowfield in an Integrated Rocket Ramjet Engine. I: Transition from Rocket Booster to Ramjet Sustainer

Sung

Yang

2014

J. Aerosp. Eng.

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A comprehensive numerical analysis was conducted to study the internal flow development in an integrated rocket-ramjet (IRR) propulsion system. The study consists of two parts: transition from the rocket booster to the ramjet sustainer and combustion dynamics during ramjet operation. The physical model of concern includes the entire IRR flow path, extending from the leading edge of the inlet center body through the exhaust nozzle. The theoretical formulation is based on the Farve-averaged conservation equations of mass, momentum, energy, and species concentration in axisymmetric coordinates and accommodates finite-rate chemical kinetics and variable thermophysical properties. Turbulence closure is achieved using a low-Reynolds-number k-ɛ two-equation model. The governing equations are solved numerically by means of a finite-volume preconditioned flux-differencing scheme capable of treating a chemically reacting flow over a wide range of Mach numbers. Various important physiochemical processes involved in the transition from the booster to the sustainer phase are investigated systemically. Emphasis is placed on the flow interactions between the inlet diffuser and combustor. The effects of operation timing on the flow evolution, fuel spread, ignition, and flame development are studied.

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History of U.S. Navy ramjet, scramjet, and mixed-cycle propulsion development

Cited by 13 publications

References 0 publications

An Investigation of Controlled Oscillations in a Plasma Torch for Combustion Enhancement

An Investigation of Controlled Oscillations in a Plasma Torch for Combustion Enhancement

Fundamental Architecture and Analysis of Photofission Ramjet Propulsion

Unified Analysis of Internal Flowfield in an Integrated Rocket Ramjet Engine. I: Transition from Rocket Booster to Ramjet Sustainer

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