| タイトル | Briefing notes on propulsion stability codes ADMIT, NYQUIST, and SSFREQ |
| 本文（外部サイト） | http://hdl.handle.net/2060/19930003686 |
| 著者（英） | Armstrong, W. C. |
| 著者所属（英） | Alabama Univ. |
| 発行日 | 1992-03-01 |
| 言語 | eng |
| 内容記述 | The piping in a liquid rocket can assume complex configurations due to multiple tanks, multiple engines, and structures that piping must go around. The capability to handle some of these complex configurations have been incorporated into the Low Frequency Code (ADMIT), the Nyquist Code (NYQUIST), and the Intermediate Frequency code (SSFREQ). The capability to modify the input on line has been implemented. The configurations allowed include multiple tanks, multiple engines, and the splitting of a pipe into unequal segments going to different (or the same) engines. Straight pipes, bends, inline accumulators, tuned stubs, Helmholtz resonators, parallel resonators, and pumps are the types of piping that may be used. The three codes require the computation of admittance looking toward the tank. Therefore, they all have a number of similar routines for reading in the tank, piping, and engine descriptions. They also have similar routines for computing the admittance looking toward the tank. ADMIT uses only one type of feedline, either a LOX or FUEL line. NYQUIST can use no feedlines, one feedline (either LOX or FUEL), or two feedlines (both LOX and FUEL). SSFREQ requires both feedlines to be present (LOX and FUEL). The common features of the three codes are discussed first, with two sample runs described. Then each of the three codes are discussed along with the sample runs. Several on-line variations are suggested for the second sample run. Input descriptions and the input for the sample runs are given in the appendices. |
| NASA分類 | SPACECRAFT PROPULSION AND POWER |
| レポートNO | 93N12874
NASA-CR-184449
NAS 1.26:184449 |
| 権利 | No Copyright |
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