首页> 美国政府科技报告 >Design of injectors and ablative thrust chambers for a flox-propane rocket engine with a 1.2-inch throat diameter

【24h】

Design of injectors and ablative thrust chambers for a flox-propane rocket engine with a 1.2-inch throat diameter

机译：用于喉部直径为1.2英寸的flox-propane火箭发动机的喷射器和燃烧推力室的设计

获取原文

页面导航

摘要
著录项
相似文献
相关主题

摘要

Design of injectors and ablative thrust chambers for FLOX propane rocket engine with 1.2 inch throat diameter

著录项

作者
Pavli, A. J.; Peterson, D. A.; Winter, J. M.;
展开▼
作者单位

展开▼
年度 1969
页码 1-38
总页数 38
原文格式 PDF
正文语种 eng
中图分类工业技术;
关键词
ENGINEERING DRAWINGS; FLOX; INJECTORS; ROCKET ENGINES; THRUST CHAMBERS; ABLATIVE MATERIALS; PRESSURE; RATIOS; ROCKET NOZZLES; VELOCITY;

机译：工程图纸; FLOX; INJECTORs;火箭发动机;推力室; aBLaTIVE maTERIaLs;压力;比;火箭喷嘴;速度;

相似文献

外文文献
中文文献
专利

1. Dataset of the experimentally measured heat transfer in the throat region of liquid rocket engine thrust chambers [J] . Marco Pizzarelli Data in Brief . 2021,第a期

机译：液体火箭发动机推力室喉部区域的实验测量热传递的数据集
2. Overview and analysis of the experimentally measured throat heat transfer in liquid rocket engine thrust chambers [J] . Pizzarelli Marco Acta astronautica . 2021,第Jula期

机译：液体火箭发动机推力室实验测量咽喉传热分析
3. Study on the Design Criteria of the Coaxial Injector for a LOX/Hydrogen Rocket Engine: Evaluation of Design for Injectors of the LE-5 Engine and Its Derivatives [J] . Nobuyuki Yatsuyanagi Transactions of the Japan society for aeronautical and space sciences . 2007,第169期

机译：LOX /氢火箭发动机同轴喷油器的设计标准研究：LE-5发动机及其衍生物喷油器的设计评估
4. MATHEMATICAL MODEL AND EXPERIMENTAL RESULTS FOR HYBRID ROCKET ENGINE, TYPES OF INJECTORS, SCRATCHES DESIGN, THRUST CONTROL [C] . Teodor Viorel Chelaru, Florin Mingireanu, Vasile Enache, IAC;International Astronautical Congress . 2011

机译：混合火箭发动机的数学模型和实验结果，喷油器类型，划痕设计，推力控制
5. Indirect and direct methods for measuring a dynamic throat diameter in a solid rocket motor. [D] . Colbaugh, Lauren. 2015

机译：间接和直接方法，用于测量固体火箭发动机中的动态喉部直径。
6. Dataset of the experimentally measured heat transfer in the throat region of liquid rocket engine thrust chambers [O] . Marco Pizzarelli 2021

机译：实验测量的热传递的数据集在液体火箭发动机推力室的喉部区域中的热传递
7. Thermal Hydraulics Design and Analysis Methodology for a Solid-Core Nuclear Thermal Rocket Engine Thrust Chamber [O] . Wang, Ten-See, Ito, Yasushi, Canabal, Francisco, 2013

机译：实心核热火箭发动机推力室的热力学设计与分析方法
8. Design of Injectors and Ablative Thrust Chambers for a Flox-Propane Rocket Engine with a 1.2-Inch Throat Diameter [R] . Pavli, A. J., Peterson, D. A., Winter, J. M. 1969

机译：1.2英寸喉管直径的Flox-propane火箭发动机喷油器和燃烧推力腔的设计

Design of injectors and ablative thrust chambers for a flox-propane rocket engine with a 1.2-inch throat diameter

摘要

著录项

相似文献

相关主题

期刊订阅