|Table of Contents|

The Controlling Technology of Changeable-depth Missile Launch Power(PDF)

《南京理工大学学报》(自然科学版)[ISSN:1005-9830/CN:32-1397/N]

Issue:
2003年02期
Page:
127-131
Research Field:
Publishing date:

Info

Title:
The Controlling Technology of Changeable-depth Missile Launch Power
Author(s):
LiYue ZhouRurong ①
Institute of Pilotless Aircraft,① School of Mechanical and Electrical Engineering, Nanjing University of Aeronautics and Astronautics,Nangjing 210016
Keywords:
missiles chang eable-depth launch nozzles aerat ion area interior trajectory
PACS:
TJ765
DOI:
-
Abstract:
The scheme to cont rol launch pow er is int roduced for chang eable-depth launch of missile. It is to change the aerat ion area at the nozzle throat of high-pressure chamber in launcher. The range of the aeration area corresponding to the launch depth rang e is solved throug h the design and the solution of interior trajectory. The inf luence of the aerat ion area on the movement of missile and interior trajectory capability of launcher is analy zed. T he results indicate that the gas pow er of missile launcher has been cont rolled effect ively through changing the aeration area at the nozzle throat. Thereby the chang eable-depth launch of missile has been realized in theory.

References:

1 倪火才. 变深度发射和能量可调发射动力系统[ J] . 舰载武器, 1998( 1) : 16~ 25.
2 倪火才. 潜地弹道导弹水下发射系统的发展[ J] . 舰载武器, 1994( 4) : 1~ 10.
3 徐温干. 固体火箭发动机推力大小调节技术的发展[ J] . 推力技术, 1994( 1) : 39~ 44.
4 李悦. 潜射导弹变深度弹射研究) ) ) 燃气动力系统的弹射动力可调性探索[ D] . 南京: 南京理工大学, 1996.
5 袁曾凤. 火箭导弹弹射内弹道学[M] . 北京: 北京工业出版社, 1987. 49~ 120.

Memo

Memo:
-
Last Update: 2013-03-17