Rocket nozzles: 75 years of research and development

被引:19
作者
Khare, Shivang [1 ]
Saha, Ujjwal K. [2 ]
机构
[1] Norwegian Univ Sci & Technol, Dept Energy & Proc Engn, N-7491 Trondheim, Norway
[2] Indian Inst Technol Guwahati, Dept Mech Engn, Gauhati 781039, India
来源
SADHANA-ACADEMY PROCEEDINGS IN ENGINEERING SCIENCES | 2021年 / 46卷 / 02期
关键词
Rocket nozzle; aerodynamics; thrust; expansion ratio; nozzle contour; shock wave; method of characteristics; efficiency; THRUST VECTOR CONTROL; FLOW SEPARATION; SIDE-LOADS; SUPERSONIC NOZZLE; SHOCK SEPARATION; CONTOUR; PERFORMANCE; TRANSITION; DESIGN; UNSTEADINESS;
D O I
10.1007/s12046-021-01584-6
中图分类号
T [工业技术];
学科分类号
08 ;
摘要
The nozzle forms a large segment of the rocket engine structure, and as a whole, the performance of a rocket largely depends upon its aerodynamic design. The principal parameters in this context are the shape of the nozzle contour and the nozzle area expansion ratio. A careful shaping of the nozzle contour can lead to a high gain in its performance. As a consequence of intensive research, the design and the shape of rocket nozzles have undergone a series of development over the last several decades. The notable among them are conical, bell, plug, expansion-deflection and dual bell nozzles, besides the recently developed multi nozzle grid. However, to the best of authors' knowledge, no article has reviewed the entire group of nozzles in a systematic and comprehensive manner. This paper aims to review and bring all such development in one single frame. The article mainly focuses on the aerodynamic aspects of all the rocket nozzles developed till date and summarizes the major findings covering their design, development, utilization, benefits and limitations. At the end, the future possibilities of development are also recommended.
引用
收藏
页数:22
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