عنوان مقاله :
بهينه سازي هدايت فاز مياني يك پرتابه با استفاده از الگوريتم حركت توده ذرات
عنوان به زبان ديگر :
MIDCOURSE GUIDANCE A PROJECTILE OPTIMIZATION USING PARTICLE SWARM ALGORITHM
پديد آورندگان :
زردشتي، رضا دانشگاه صنعتي مالك اشتر - مجتمع دانشگاهي هوافضا , علي الهي، مصطفي دانشگاه صنعتي مالك اشتر - مجتمع دانشگاهي هوافضا
كليدواژه :
طراحي هدايت بهينه , فاز مياني , افزايش دقت , الگوريتم حركت توده ذرات , تلاش كنترلي , زاويه ديد , زاويه مسير پرواز
چكيده فارسي :
در اين مقاله، ﺑﻪ ﻣﺴﺌﻠﻪ ﻫﺪاﯾﺖ در ﻓﺎز ﻣﯿﺎﻧﯽ ﭘﺮواز ﯾﮏ ﭘﺮﺗﺎﺑﻪ ﺑﺎ ﻫﺪف ﺗﺎﻣﯿﻦ اﻟﺰاﻣﺎت و ﻣﺤﺪودﯾﺘﻬﺎي ورود ﺑﻪ ﻓﺎز آﺷﺴـﯿﺎﻧﻪ ﯾـﺎﺑﯽ آن ﭘﺮداﺧﺘـﻪ ﺷـﺪه
،اﺳﺖ. اﯾﻦ اﻟﺰاﻣﺎت و ﻣﺤﺪودﯾﺘﻬﺎ ﻣﻌﻤﻮﻻ ﺑﺮاي ﺳﯿﺴﺘﻤﻬﺎي ارزانﻗﯿﻤﺖ ﮐﻪ ﻣﻠﺰم ﺑﻪ اﻓﺰاﯾﺶ ﺑﺮد ﺧﻮد ﺷﺪهاﻧﺪ ﺑﻮﺟﻮد ﻣـﯽ آﯾـﺪ و ﺷـﺎﻣﻞ ﻣﯿـﺪان دﯾـﺪ
زاوﯾﻪ ﺗﻘﺪم )زاوﯾﻪ دﯾﺪ( و زاوﯾﻪ ﭘﺮوازي )زاوﯾﻪ ﺑﺮﺧﻮرد( ﭘﺮﺗﺎﺑﻪ در ﮐﻨﺎر ﻣﯿﺰان ﺗﻼش ﮐﻨﺘﺮﻟﯽ ﺣﺎﺻﻠﻪ در ﻓﺎز ﻣﯿﺎﻧﯽ اﺳﺖ. ﺑﺪﯾﻬﯽ اﺳـﺖ ﮐـﻪ درﺻـﻮرت
ﺗﺤﻘﻖ اﻟﺰاﻣﺎت ﻣﺰﺑﻮر، ﻣﯿﺰان ﻣﻮﻓﻘﯿﺖ ﻣﺎﻣﻮرﯾﺖ ﭘﺮﺗﺎﺑﻪ اﻓﺰاﯾﺶ ﻣﯽﯾﺎﺑﺪ. ﻟﺬا ﺑﺎ ﺗﻮﺟﻪ ﺑﻪ اﻫﻤﯿﺖ ﻣﺴـﺌﻠﻪ و ﻋﻠﯿـﺮﻏﻢ ﮐﺎرﻫـﺎي ﻣﺘﻨـﻮع و ﭘﺮاﮐﻨـﺪه اي ﮐـﻪ
ﻋﻤﻠﮑـﺮد ﻣﺘﺸـﮑﻞ از ﻣﻌﯿـﺎر ﺗـﻼش ﮐﻨﺘﺮﻟـﯽ و ﺗﺎﮐﻨﻮن اﻧﺠﺎم ﺷﺪه، در اﯾﻦ ﺗﺤﻘﯿﻖ، اﺑﺘﺪا ﻣﺴﺌﻠﻪ ﺑﻬﯿﻨﻪ ﺳﺎزي ﻫﺪاﯾﺖ ﻓﺎز ﻣﯿﺎﻧﯽ ﭘﺮﺗﺎﺑﻪ ﺑﺮاﺳـﺎس ﺗـﺎﺑﻊ
ﻫﻤﭽﻨﯿﻦ ﻣﻘﺎدﯾﺮ ﻧﻬﺎﯾﯽ زاوﯾﻪ ﺗﻘﺪم و زاوﯾﻪ ﭘﺮوازي در ﻓﺎز ﻣﯿﺎﻧﯽ ﺑﻌﻨﻮان ﺗﻮاﺑﻊ ﺟﺮﯾﻤﻪ ﺗﻌﺮﯾﻒ ﺷﺪه اﺳﺖ. ﺳﭙﺲ ﺑﺎ اﺳﺘﻔﺎده از اﻟﮕﻮرﯾﺘﻢ ﺑﻬﯿﻨـﻪ ﺳـﺎزي
ﺗﻮده ذرات، ﻓﺮاﻣﯿﻦ ﺷﺘﺎب ﺑﻬﯿﻨﻪ ﺗﻮﻟﯿﺪ ﺷﺪه اﺳﺖ. ﻧﺘﺎﯾﺞ ﺣﺎﺻﻞ از ﺷﺒﯿﻪ ﺳـﺎزي ﮐـﻪ ﺑـﺎ روش دﯾﮕـﺮ ﻣﻘﺎﯾﺴـﻪ ﮔﺮدﯾـﺪه، ﻧﺸـﺎن از ﻋﻤﻠﮑـﺮد ﻣﻨﺎﺳـﺐ
.اﻟﮕﻮرﯾﺘﻢ ﻣﺮﺑﻮﻃﻪ و ﻗﺎﺑﻠﯿﺖ آن ﺑﺮاي ﺣﻞ ﻣﺪﻟﻬﺎي ﭘﯿﭽﯿﺪه ﺗﺮ دارد
چكيده لاتين :
In this paper, the problem of guidance in the mid-course of a projectile’s flight has been addressed to meet the requirements and limitations of the homing phase. These requirements and constraints are usually for low cost systems that are required to increase their range, including the angle of priority (angle of view) and the flight path angle (the angle of impact) of the projectile along with the amount of control effort obtained in the mid-course. Obviously, if these requirements are met, the success of the projectile mission will increase. Therefore, considering the importance of the problem and despite the various and scattered works that have been done so far, in this research, first the mid-course guidance optimization problem of the projectile based on a performance function consisting of the control effort criterion, and also the final values of view angle and flight angle in the mid-course is defined as the penalty functions, respectively. Then, using the particle swarm optimization algorithm, optimal acceleration commands are generated. The simulation results compared with other methods show the proper functioning of the algorithm and its ability to solve more complex models.
عنوان نشريه :
مهندسي هوانوردي
