Evaluation of laser supported detonation wave thrusters for ground to orbit launch

Rollins, Chris; Bailey, Albert; Gelb, Alan; Resendes, D.; Guy, Weyl

doi:10.2514/6.1989-1914

Cited by 2 publications

(1 citation statement)

References 3 publications

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“…Most of the energy is tied up in random kinetic temperature for conversion to thrust upon expansion through a nozzle. Experimental performance values under other conditions above 15% have been reported [17] and are expected to reach as much as 40% [18]. In this regard, the performance of this thruster chamber resembles a chemical thruster in terms of thrust and specific impulse.…”

Section: Modeling Thruster Processesmentioning

confidence: 92%

Laser Propulsion for Ground Launch

Resendes¹,

Mota²,

Mendonça³

et al. 2007

Journal of Propulsion and Power

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Ground-to-orbit launch using laser propulsion requires a thermal system. A number of such thermal thruster concepts have been developed in the past. Thus far, only the laser-supported detonation thruster concept has led to a flight vehicle, the Lightcraft. It is shown via flight simulations and measurements with the Lightcraft that there are no inherent limitations for a ground-to-orbit launch vehicle using laser propulsion. A planar geometry laser-supported detonation thruster using a CO 2 laser is considered and its performance evaluated. A 10-km height flight vehicle using existing lasers is proposed. Nomenclaturespecific enthalpy of gas, height h P = Planck's constant h lsr = laser site altitude h ref = atmospheric scale height I abs = laser intensity absorbed by gas I sp = specific impulse k = absorption coefficient k B = Boltzmann's constant m = mass _ m= mass flow rate n X = number density of X P = power p = pressure q = specific heat added to gas r = radius r hot spot = vehicle hot-spot radius r lsr = laser main deflector radius T = temperature u = velocity in shock-fixed reference frame v = velocity in laboratory reference frame abs = atmospheric absorption coefficient R slant = slant range = efficiency = semivertex angle = longitude = wavelength = density = laser frequency = latitude e = Earth's rotational velocity

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Section: Modeling Thruster Processesmentioning

confidence: 92%