Measurements and calculations of detonation propulsion performance in helium

Previously obtained results are extended to helium ambient gas to help in the assessment of performance in the atmospheres of the major planets. Measurements confirm benefits derived form detonating propellant over conventional chemical rocket propulsion. Benefits however, are reduced at high pressures in low molecular weight gas. Numerical calculations by means of a monodimensional hydrodynamic code follow the different trends obtained experimentally for high and low molecular weight gas and also offer new insights on the time behavior of the process.