推力中断型固体ロケット用プロペラント組成と急速減圧燃焼中断性との関係

• Material Type: 文書・図像類
• Title: 推力中断型固体ロケット用プロペラント組成と急速減圧燃焼中断性との関係
• Author/Editor: 五代, 富文; 藤原, 勉; 清水, 盛生; 種村, 利春; 伊藤, 克弥; GODAI, Tomifumi; FUJIWARA, Tsutomu; SHIMIZU, Morio; TANEMURA, Toshiharu; ITO, Katsuya
• Author Heading: 五代, 富文; 藤原, 勉; 清水, 盛生; 種村, 利春; 伊藤, 克弥; GODAI, Tomifumi; FUJIWARA, Tsutomu; SHIMIZU, Morio; TANEMURA, Toshiharu; ITO, Katsuya
• Publication, Distribution, etc.: 航空宇宙技術研究所
• Publication Date: 1976-07
• Publication Date (W3CDTF): 1976-07
• Alternative Title: Relationship between depressurization extinction and composition of fluid-controlled solid rocket propellants
• Periodical title: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-461
• No. or year of volume/issue: 461
• Volume: 461
• Pages: 22-
• ISSN (Periodical Title): ISSN : 0389-4010
• Text Language Code: jpn
• Target Audience: 一般
• Note (General): The high pressure exponent in the burning rate rule, easy extinction by rapid depressurization and high specific impulse are primary factors in the propellants of fluid-controlled solid rocket motor. The composite propellant currently employed for the fluid-controlled solid rocket and designated RS-1105 has the following formulation: blend ammonium perchlorate(AP) to potassium perchlorate(PP) at a ratio of 80 to 20, fine oxidizers with a unimodal particle size distribution, polybutadiene binder(CTPB) and restricted concentration of aluminium powder. Experimental investigation to improve the extinction characteristics of the standard propellant and clarify the mechanism of extinction by rapid depressurization, was conducted in order to study the effect of propellant composition on depressurization extinction. The composition parameters were: oxidizer type, oxidizer blend ratio, oxidizer particle size, fuel binder type, oxidizer-fuel mixture ratio and aluminium concentration. The principal measurements were the initial pressure level P, and the initial depressurization rate, (dP/dt) max. Flame luminosity measurement during pressure drop and observation of the surface structure of extinguished propellants utilizing a scanning electron microscope were also conducted. The main results obtained: (1)Extinction and nonextinction regimes were determined on the P versus(dP/dt) max plane. The slope of the straight threshold line was found to be useful as a measure of extinction characteristics. (2)The threshold depressurization rate of RS-1105 propellant at a pressure level of 290 N/cm2(30 kg/cm2) was 3400 N/cm2 sec(350 kg/cm2 sec) which was extremely below that of conventional composite propellants with AP oxidizers. (3)Partial addition of PP to AP was effective in easing combustion termination. However, further addition of PP to AP exceeding 20 percent had less influence on extinction characteristics. (4)The oxidizer blend ratio effect on depressurization extinction was due to a change in the propellant surfaces structure. (5)The extinction characteristics were not affected by the oxidizer particles size of AP propellants, although PP propellant with fine oxidizer ceased combustion much easier than the coarse PP propellant by a factor of 100. (6)AP particles on the propellant surface were consumed during slow depressurization. (7)Polyurethane propellant and fuel-rich propellant exhibited easier extinction characteristics compared with CTPB propellants and nearly stoichiometric propellants. (8)Combustion of aluminized propellants was difficult to stop by rapid pressure drop and tended to reignite automatically a few seconds after temporary extinction.; 資料番号: NALTR0461000; レポート番号: NAL TR-461
• Access Restrictions: 限定公開
• Data Provider (Database): 国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）; https://irdb.nii.ac.jp
• Original Data Provider (Database): 宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ