Write in a clean editor, then format for Journal of the American Rocket Society in one click — DocuGuru applies the official AIAA template with numbered references and exports a submission-ready PDF plus the editable LaTeX source. Free to start.
Journal of the American Rocket Society is a peer-reviewed journal published by AIAA, covering Rocket and propulsion systems research, Diverse Scientific and Economic Studies, Human auditory perception and evaluation.
| Publisher | AIAA |
|---|---|
| Reference style | Numbered (AIAA) Numbered — [1], [2] in the text [1] Smith, A., Jones, B., and Lee, C., "A Representative Article Title," Journal of the American Rocket Society, Vol. 12, No. 3, 2023, pp. 45–58.
Formats any DOI in Journal of the American Rocket Society style. No sign-up. |
| Publishes research in | Rocket and propulsion systems research Diverse Scientific and Economic Studies Human auditory perception and evaluation Legal Cases and Commentary Energetic Materials and Combustion |
| ISSN | 0095-9073 |
| h-index | 19 |
| i10-index | 29 |
| Total citations | 1,778 |
| Top institutions publishing here | Jet Propulsion Laboratory |
| Journal website | arc.aiaa.org |
| You get | A submission-ready PDF and the editable LaTeX source — ready to submit. |
Citations each year’s papers have accumulated so far — the most recent years are still building up.
Existing theories are able to explain part of the observed ffects of low-frequency unstable combust ion with the issumption of a constant t ime lag between the propellants ujection and their transformation into hot gases. A discussion shows that the t i m e lag cannot be constant if the pressure oscillates, but m u…
The mass ratio or the characteristic velocity for the take-off of a space ship from the satellite orbit is computed for two cases: the radial thrust, and the circumferential thrust. The circumferential thrust is much more efficient in that the required mass ratio is much less than for the radial thrust. Both cases show, however,…
On the basis of an hypothesis that low-frequency oscillat ions (chugging) somet imes observed in l iquid propellant rocket engines , are the result of oscillatory propellant flow induced by a combust ion t ime lag, condit ions for the suppression of such oscil lations are derived. It is found that stability can be achieved…
The transfer function is defined as the fractional oscillating mass flow rate divided by the fractional sinusoidal pressure oscillation in the rocket combustion chamber. This is calculated as a function of the frequency of oscillation. For very small frequencies, the transfer function is approximately 1 with a small "lead component." For very large frequencies, the…
In Part I the problem of low-frequency combust ion in stability in monopropellant rocket motors has been analyzed under the basic assumpt ion that the t ime lag is affected by pressure variations. The same idea is applied now to the bipropellant case. It is shown that for certain relations between the parameters of the…
