Experiments were performed with a 2‐D, repetitively‐pulsed (RP) laser Lightcraft model in hypersonic flow conditions. The main objective was the feasibility analysis for impulse generation with repetitively‐pulsed air‐breathing laser Lightcraft engines at hypersonic speeds. The future application of interest for this basic research endeavor is the laser launch of pico‐, nano‐, and micro‐satellites (i.e., 0.1–100 kg payloads) into Low‐Earth‐Orbit, at low‐cost and on‐demand. The laser propulsion experiments employed a Hypersonic Shock Tunnel integrated with twin gigawatt pulsed Lumonics 620‐TEA CO 2 lasers (∼ 1 μs pulses), to produce the required test conditions. This hypersonic campaign was carried out at nominal Mach numbers ranging from 6 to 10. Time‐dependent surface pressure distributions were recorded together with Schlieren movies of the flow field structure resulting from laser energy deposition. Results indicated laser‐induced pressure increases of 0.7–0.9 bar with laser pulse energies of ∼ 170 J, on off‐shroud induced breakdown condition, and Mach number of 7.


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    Titel :

    2‐D Air‐Breathing Lightcraft Engine Experiments in Hypersonic Conditions


    Beteiligte:

    Kongress:

    BEAMED ENERGY PROPULSION: Seventh International Symposium ; 2011 ; Ludwigsburg, (Germany)


    Erschienen in:

    AIP Conference Proceedings ; 1402 , 1 ; 174-186


    Erscheinungsdatum :

    10.11.2011


    Format / Umfang :

    13 pages





    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch



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