| 引用本文: | 徐秋坪,王中原,常思江.控制速度方向的弹道修正导引方法.[J].国防科技大学学报,2016,38(4):143-152.[点击复制] |
| XU Qiuping,WANG Zhongyuan,CHANG Sijiang.Ballistic correction guidance law based on the control of velocity direction[J].Journal of National University of Defense Technology,2016,38(4):143-152[点击复制] |
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| 控制速度方向的弹道修正导引方法 |
| 徐秋坪, 王中原, 常思江 |
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(南京理工大学 能源与动力工程学院， 江苏 南京 210094)
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| 摘要: |
| 由于制导炮弹由身管武器发射，其飞行控制能力和导引信息量有限，故基于预测落点位置偏差量来修正速度方向并在控制时间内连续分配导引指令的思想提出一种新的三维末制导方法。根据非线性弹道方程组的级数解预测弹丸落点位置，得到落点与目标的偏差，并提出两种通过此偏差解算当前速度方向修正量的方法。取剩余飞行时间为修正时间，通过将速度方向修正量分配到整个剩余导引段建立加速度修正公式，从而减小导引指令饱和的可能性。通过连续地预测落点和分配加速度指令来实时地导引飞行。仿真结果表明：该导引方法简单可行，精度高，对控制能力要求较低，且具备较好的制导效果和毁伤效果，可为该体制制导炮弹的应用提供参考依据。 |
| 关键词: 制导炮弹 导引方法 弹道修正 落点预测 剩余飞行时间 |
| DOI：10.11887/j.cn.201604023 |
| 投稿日期：2015-04-15 |
| 基金项目:国家自然科学基金资助项目（11402117）；中国博士后基金资助项目（2013M541676） |
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| Ballistic correction guidance law based on the control of velocity direction |
| XU Qiuping, WANG Zhongyuan, CHANG Sijiang |
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(School of Energy and Power Engineering, Nanjing University of Science and Technology, Nanjing 210094, China)
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| Abstract: |
| Taking the limited control authority and guidance information of a gun-launched guided projectile into account, a novel three-dimension terminal guidance law based on the combination of the correction of the velocity direction via impact point prediction and continuous distribution of acceleration command was proposed. The deviations between the impact point of the projectile and the target were predicted on the basis of the series solutions of the nonlinear ballistic equations. According to the deviations, two methods to calculate the direction angle corrections of the current speed were addressed. The remaining flight time was designed as the correction time. The acceleration correction formulas were established through sharing the direction angle corrections of the current speed into the whole remaining guided flight to reduce the possibility of command saturation. By predicting the impact point and distributing the acceleration corrections continuously, the trajectory was shaped in real time. The simulation results show that the proposed guidance law is feasible and effective, and provides the performances of high precision with little requirements of control authority, and has great guidance and damage effects, which can provide reference for the application of the guided projectile. |
| Keywords: guided projectile guidance law trajectory correction impact point prediction remaining flight time |
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