| タイトル | RSRM-11 (36OW011) ballistics mass properties (STS-35) |
| 本文（外部サイト） | http://hdl.handle.net/2060/19910010890 |
| 著者（英） | Hutchinson, B. J.; Gruet, L. P.; Richards, M. C. |
| 著者所属（英） | Thiokol Corp. |
| 発行日 | 1991-01-21 |
| 言語 | eng |
| 内容記述 | The propulsion performance and reconstructed mass properties data from Thiolol's RSRM-11 motors which were assigned to the STS-35 launch are contained. The Thiokol manufacturing designations for the motors were 360W011A/360W011B, which are referred to as RSRM-11A and RSRM-B, respectively. The launch of STS-35 occurred on 2 December 1990 at the Eastern Test Range (ETR). The data contained herein was input to the STS-35 Flight Evaluation Report. The SRM propellant, TP-H1148, is a composite type solid propellants, formulated of polybutediene acrylic acid, acryonitrile terpolymer binder, epoxy curing agent, ammonium perchlorate oxidizer, and aluminum powder fuel. A small amount of burning rate catalyst (iron oxide) was added to achieve the desired propellant burn rate. The propellant evaluation and raw material information for the RSRM-11 are included. The ballistic performance presented was based on the Operational Flight Instrumentation (OFI) 12.5 sample per second pressure data for the steady state and tail off portion of the pressure trace. Recent studies have shown that the transducers are affected by the measuring system at KSC and temperature gradients created by the igniter heaters. Therefore, an adjustment to the data from each transducer is made to make the initial reading match the atmospheric pressure at the time of launch. |
| NASA分類 | SPACECRAFT PROPULSION AND POWER |
| レポートNO | 91N20203
TWR-17550-10
NASA-CR-184107
NAS 1.26:184107 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/133524 |
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