Investigation of a Laser-Supported Directed-Energy "Air Spike" in Hypersonic Flow

Minucci, M. A. S.; Toro, Paulo; Chanes, J. B.; Ramos, Antonio G.; Pereira, A. L.; Nagamatsu, H. T.; Myrabo, Leik N.

doi:10.2514/2.3927

Cited by 10 publications

(4 citation statements)

References 3 publications

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“…Experimental classical aerothermodynamics [14][15] , experimental basic flow control using energy deposition by laser [16][17][18][19][20] , basic research in supersonic combustion (scramjet) [21][22][23] .…”

Section: B Ieav 030-m Nozzle Exit Diameter Hypersonic Shock Tunnel T2mentioning

confidence: 99%

Brazilian 14-X Hypersonic Aerospace Vehicle Project

Toro¹,

Minucci²,

Rolim³

et al. 2012

18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference

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The Brazilian 14-X Hypersonic Aerospace Vehicle, a new generation of scientific aerospace vehicle, designed at Prof. Henry T. Nagamatsu Laboratory of Aerothermodynamics and Hypersonics, at Institute for Advanced Studies (IEAv), is part of the continuing effort of the Department of Aerospace Science and Technology (DCTA), to develop a technological demonstrator using: i) waverider technology to provide lift to the aerospace vehicle, and ii) scramjet technology to provide hypersonic airbreathing propulsion system based on supersonic combustion. In consequence of the nature of the supersonic combustion engines, they are unable to produce thrust while stationary, the static thrust is zero. Accordingly, they must be accelerated to a speed such that the shock waves produced by the air intake are able to compress the atmospheric air. This velocity, called initial operation speed, is approximately four times the speed of sound, Mach 4, considering scramjet. Two-stage, unguided, rail launched, solid rocket engines will be used to accelerate the 14-X Hypersonic Aerospace Vehicle to the pre-established conditions to operate the scramjet engine, i.e., position (altitude, latitude and longitude), speed (Mach number), dynamic pressure and angle of attack. The 14-X Hypersonic Aerospace Vehicle project consists of four atmospheric flights. The first flight is planned for 14-X captive (accelerator and 14-X vehicles coupled during the entire flight) unpowered scramjet Mach number 6; the second for 14-X free (accelerator and 14-X vehicles separated after burn of 2 nd stage of accelerator vehicle) unpowered scramjet Mach number 6 flight; and the two last are planned for free hydrogen-powered scramjet Mach number 6 and Mach number 10, respectively. Pure waverider aerodynamic, scramjet power off and power on as well as 14-X stage separation will be experimentally investigated using the three Hypersonic Shock Tunnels at Prof. Henry T. Nagamatsu Laboratory of Aerothermodynamics and Hypersonics. Pressure and temperature measurements at pure waverider external upper and lower surfaces and scramjet power off and power on internal surfaces will be obtain to provide wind-tunnel data to design the full 2-m. long atmospheric flight of 14-X Hypersonic waverider scramjet Aerospace Vehicle. Non-intrusive measurements using optical diagnostic techniques have been implemented at Hypersonic Shock Tunnels, as well as in-house computational fluid dynamics have been developed for waverider, scramjet and 14-X Hypersonic Aerospace Vehicle.

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Section: B Ieav 030-m Nozzle Exit Diameter Hypersonic Shock Tunnel T2mentioning

confidence: 99%

Brazilian 14-X Hypersonic Aerospace Vehicle Project

Toro¹,

Minucci²,

Rolim³

et al. 2012

18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference

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“…e experimental results showed that the peak pressure of the bow shock and the type IV shock interference was reduced by 40% and 30%, respectively. Minucci et al [8][9][10][11] conducted a single-pulse laser drag reduction experiment in a hypersonic shock wave tunnel. e air spike structure was observed using direct photography.…”

Section: Introductionmentioning

confidence: 99%

Experimental Study on Interaction between Nanosecond Pulsed Laser and Normal Shock Wave

Shi

Wang

Huang

2021

Shock and Vibration

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Nanosecond pulsed lasers possess two remarkable advantages: a high peak power density and the ability to break down air to form plasma readily. Therefore, they have significant practical value in the drag reduction of a supersonic body. An experimental investigation is conducted on the fundamental physical phenomenon of the interaction of the pulsed laser plasma with a normal shock wave to reveal the mechanism of drag reduction. Moreover, a high-precision schlieren system is developed to measure complex wave structures with a time resolution of up to 30 ns and a spatial resolution up to 1 mm. A high-speed particle image velocimetry system is set up to measure the velocity and vorticity of the flow field quantitatively; the system has a time resolution of up to 500 ns. The characteristics of the spherical shock wave and the high-temperature and low-density region induced by the laser plasma are presented. The flow characteristics and evolution process of the laser plasma under a normal shock wave are substantially revealed. The cause of the supersonic drag reduction by the pulsed laser plasma is illustrated with numerical simulation results. The following results are obtained in this study: the initial Mach number of the shock wave induced by the laser plasma increases with the laser energy, and the shape of the wave gradually evolves from a droplet shape to a spherical shape. The propagation velocity decreases with time and is close to the sound velocity after 50 μs. The shape of the initial high-temperature and low-density region is approximately spherical; it subsequently destabilizes to form a sharp spike structure in the laser’s incident direction. Ultimately, the region evolves into a double-vortex ring structure with upper and lower symmetry; the size of this region increases with the laser energy.

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“…Among different suggestions, an interesting idea directed toward this field is the possibility of reducing the aerodynamic drag and heating of a hypersonic vehicle by adding energy to the air ahead of it. This active control of the flowfield was suggested by several authors, with different methods for its accomplishment, in which theoretical and experimental reports present the plasma generation by plasma torch [1,2], electric arcs [3,4], surface electrical discharge [5], lasers [6][7][8][9][10], and microwaves [11,12]. The use of a focused laser beam is an attractive solution to attain this goal [13,14].…”

Section: Introductionmentioning

confidence: 99%

Bow Shock Wave Mitigation by Laser-Plasma Energy Addition in Hypersonic Flow

Oliveira

Minucci²,

Myrabo³

et al. 2008

Journal of Spacecraft and Rockets

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Experimental results of bow shock wave mitigation by laser-plasma energy addition in a low-density Mach 7 hypersonic flow conducted in a shock tunnel are presented. A high-power pulsed CO 2 laser operating with 7 J of energy and 30 MW of peak power was used to generate the plasma ahead of a hemispherical model installed in the tunnel test section. The schlieren technique was used to visualize the time evolution of energy addition to the flow by laser-induced plasma and the interaction between this disturbed region and the inherent bow shock formed on the model by hypersonic flow. A complete mitigation of the bow shock profile under action of the energy addition was observed. The impact pressure on the hemispherical model measured at the stagnation point reveals the correlation between the schlieren images and the pressure reduction.

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Investigation of a Laser-Supported Directed-Energy "Air Spike" in Hypersonic Flow

Cited by 10 publications

References 3 publications

Brazilian 14-X Hypersonic Aerospace Vehicle Project

Brazilian 14-X Hypersonic Aerospace Vehicle Project

Experimental Study on Interaction between Nanosecond Pulsed Laser and Normal Shock Wave

Bow Shock Wave Mitigation by Laser-Plasma Energy Addition in Hypersonic Flow

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