Trajectory simulations, qualitative analyses and parametric studies of a laser-launched micro-satellite using OTIS

Sean D. Knecht, Franklin B. Mead, Michael Matthew Micci, C. William Larson

Research output: Chapter in Book/Report/Conference proceedingConference contribution

4 Citations (Scopus)

Abstract

This paper will discuss Air Force Research Laboratory (AFRL) Propulsion Directorate's theoretical and computational results regarding trajectory simulations, qualitative analyses and parametric studies of a 25-cm focal diameter Laser Ramjet (X-25LR) using Optimal Trajectories by Implicit Simulation (OTIS). OTIS has been used to produce an optimized trajectory simulation of a laser ramjet's flight to Low Earth Orbit (LEO). The baseline case that has been simulated is a flight vehicle powered by a 1 MW, 10.6 μm, CO2, ground-based laser (GBL) with an initial power capture of 82%. The fuel that is used during rocket flight is Delrin® doped with energetic additives to increase the coupling coefficient and thrust by a factor of five. Additionally, a nozzle extension was considered which increased performance by 40%. The flight trajectory was separated into three phases: 1) Air-breathing ramjet flight to a specified altitude of ∼30 km and Mach number of ∼10; 2) Rocket powered flight into a trajectory with a final Mach number ∼27; and 3) Un-powered coasting flight to the final altitude of 185 km. Additional sounding rocket trajectory flights with 10-kilowatt class CO2 lasers have been assessed for a variety of laser powers. Also to be discussed in this paper are the parametric trade studies of the rocket phase comparing high thrust vs. low thrust and the effects of different-size vehicles.

Original languageEnglish (US)
Title of host publicationBEAMED ENERGY PROPULSION
Subtitle of host publicationFourth International Symposium on Beamed Energy Propulsion
Pages522-533
Number of pages12
DOIs
StatePublished - May 2 2006
EventBEAMED ENERGY PROPULSION: Fourth International Symposium on Beamed Energy Propulsion - Nara, Japan
Duration: Nov 15 2005Nov 18 2005

Publication series

NameAIP Conference Proceedings
Volume830
ISSN (Print)0094-243X
ISSN (Electronic)1551-7616

Other

OtherBEAMED ENERGY PROPULSION: Fourth International Symposium on Beamed Energy Propulsion
CountryJapan
CityNara
Period11/15/0511/18/05

Fingerprint

trajectories
flight
lasers
simulation
coasting flight
rockets
Mach number
Delrin (trademark)
high thrust
flight vehicles
rocket flight
low thrust
sounding rockets
air
low Earth orbits
breathing
propulsion
coupling coefficients
thrust
nozzles

All Science Journal Classification (ASJC) codes

  • Physics and Astronomy(all)

Cite this

Knecht, S. D., Mead, F. B., Micci, M. M., & Larson, C. W. (2006). Trajectory simulations, qualitative analyses and parametric studies of a laser-launched micro-satellite using OTIS. In BEAMED ENERGY PROPULSION: Fourth International Symposium on Beamed Energy Propulsion (pp. 522-533). (AIP Conference Proceedings; Vol. 830). https://doi.org/10.1063/1.2203295
Knecht, Sean D. ; Mead, Franklin B. ; Micci, Michael Matthew ; Larson, C. William. / Trajectory simulations, qualitative analyses and parametric studies of a laser-launched micro-satellite using OTIS. BEAMED ENERGY PROPULSION: Fourth International Symposium on Beamed Energy Propulsion. 2006. pp. 522-533 (AIP Conference Proceedings).
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abstract = "This paper will discuss Air Force Research Laboratory (AFRL) Propulsion Directorate's theoretical and computational results regarding trajectory simulations, qualitative analyses and parametric studies of a 25-cm focal diameter Laser Ramjet (X-25LR) using Optimal Trajectories by Implicit Simulation (OTIS). OTIS has been used to produce an optimized trajectory simulation of a laser ramjet's flight to Low Earth Orbit (LEO). The baseline case that has been simulated is a flight vehicle powered by a 1 MW, 10.6 μm, CO2, ground-based laser (GBL) with an initial power capture of 82{\%}. The fuel that is used during rocket flight is Delrin{\circledR} doped with energetic additives to increase the coupling coefficient and thrust by a factor of five. Additionally, a nozzle extension was considered which increased performance by 40{\%}. The flight trajectory was separated into three phases: 1) Air-breathing ramjet flight to a specified altitude of ∼30 km and Mach number of ∼10; 2) Rocket powered flight into a trajectory with a final Mach number ∼27; and 3) Un-powered coasting flight to the final altitude of 185 km. Additional sounding rocket trajectory flights with 10-kilowatt class CO2 lasers have been assessed for a variety of laser powers. Also to be discussed in this paper are the parametric trade studies of the rocket phase comparing high thrust vs. low thrust and the effects of different-size vehicles.",
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Knecht, SD, Mead, FB, Micci, MM & Larson, CW 2006, Trajectory simulations, qualitative analyses and parametric studies of a laser-launched micro-satellite using OTIS. in BEAMED ENERGY PROPULSION: Fourth International Symposium on Beamed Energy Propulsion. AIP Conference Proceedings, vol. 830, pp. 522-533, BEAMED ENERGY PROPULSION: Fourth International Symposium on Beamed Energy Propulsion, Nara, Japan, 11/15/05. https://doi.org/10.1063/1.2203295

Trajectory simulations, qualitative analyses and parametric studies of a laser-launched micro-satellite using OTIS. / Knecht, Sean D.; Mead, Franklin B.; Micci, Michael Matthew; Larson, C. William.

BEAMED ENERGY PROPULSION: Fourth International Symposium on Beamed Energy Propulsion. 2006. p. 522-533 (AIP Conference Proceedings; Vol. 830).

Research output: Chapter in Book/Report/Conference proceedingConference contribution

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Knecht SD, Mead FB, Micci MM, Larson CW. Trajectory simulations, qualitative analyses and parametric studies of a laser-launched micro-satellite using OTIS. In BEAMED ENERGY PROPULSION: Fourth International Symposium on Beamed Energy Propulsion. 2006. p. 522-533. (AIP Conference Proceedings). https://doi.org/10.1063/1.2203295