QIU Xiao-jie 1,LIN Xing-chen 1,WANG Quan-sheng 2,HU Wen-fei 1,WANG Qin 1.Research of Speed Overshoot Control Technology in High Altitude for Missile Engine Control Systems[J].航空发动机,2018,44(3):31-35 |
Research of Speed Overshoot Control Technology in High Altitude for Missile Engine Control Systems |
DOI: |
Key Words:PI Control similarity principle speed overshoot parameter correction aeroengine |
Author Name | Affiliation | E-mail | QIU Xiao-jie 1,LIN Xing-chen 1,WANG Quan-sheng 2,HU Wen-fei 1,WANG Qin 1 | 1. AECC Aero Engine Control System Institute,Wu' Xi Jiangsu,214063,China
2. Office of PLA Air Force Representative,Yang Zhou Jiangsu,225000,China) | 65909677@qq.com |
|
Hits: 1336 |
Download times: 0 |
Abstract:In order to solve engine speed overshoot problem caused by controller parameter on the ground unsuitable for altitude tests,
which is result from similarity principle can't be carried to PI controller parameter in real time because of lacking for missile engine control
systems. A method of speed overshoot control for missile engine under lacking of engine inlet parameter measurement was designed. P1 is
constructed based on P3 and PI controller parameter is corrected. Through full digital simulation, semi-physical simulation test, and altitude
simulation test and altitude flyight test, its availability was proved. |
View Full Text View/Add Comment Download reader |
|
|
|