自旋火箭弹固体火箭发动机推力偏差及初温对射程和横偏影响

推进技术 ›› 1999, Vol. 20 ›› Issue (2): 13-16.

自旋火箭弹固体火箭发动机推力偏差及初温对射程和横偏影响

刘文,张为华,周珞晶,曾庆华

国科科技大学航天技术系;国科科技大学航天技术系;国科科技大学航天技术系;国科科技大学航天技术系

发布日期:2021-08-15

EFFECT OF THRUST BIAS AND GRAIN INITIAL TEMPERATURE ON RANGE AND CROSSWISE DEVIATION OF SPINNING ROCKET

Dept.of Aerospace Technology,National Univ.of Defence Technology,Changsha,410073;Dept.of Aerospace Technology,National Univ.of Defence Technology,Changsha,410073;Dept.of Aerospace Technology,National Univ.of Defence Technology,Changsha,410073;Dept.of Aerospace Technology,National Univ.of Defence Technology,Changsha,410073

Published:2021-08-15

摘要/Abstract

摘要： 采用火箭弹６Ｄ弹道仿真软件，就推力偏斜和横移对火箭弹射程和横偏的影响规律进行了仿真计算，得到推力偏斜和横移对火箭弹射程和横偏的影响规律。此外就固体火箭发动机装药初温对发动机推力及火箭弹外弹道性能的影响，分析了装药初温对火箭弹射程的影响规律。

关键词: 火箭弹;推力偏差;射程;射弹散布分析;射表编制

Abstract: The effect of thrust direction variation and crosswise shifting on range and crosswise deviation of spinning rocket was studied using six dimensional exterior trajectory simulation software.The effort of thrust direction variation and crosswise shifting on rocket range and crosswise deviation was discussed.The effect of grain initial temperature on the range of the spinning rocket was also analyzed .

Key words: Rocket projectile;Deviation of thrust;Firing range;Projectile dispersion analysis;Firing table establishment

刘文,张为华,周珞晶,曾庆华. 自旋火箭弹固体火箭发动机推力偏差及初温对射程和横偏影响[J]. 推进技术, 1999, 20(2): 13-16.