CAJ | 학술논문

为了消除舰尾流对载机着舰过程产生的影响，同时完成低动压状态下飞行速度与高度的解耦工作，基于定量反馈理论/总能量控制理论（ QFT/TECS）设计了纵向着舰控制系统。针对着舰过程中数学模型所具有的不确定因素及舰尾流对下滑航迹的影响，以载机高度变化率为控制对象，使用定量反馈理论结合推力补偿系统进行了内回路鲁棒控制律设计。外回路控制律设计是以总能量控制理论为基础，通过粒子群优化算法对待调控制参数进行寻优，进而实现了对高度、速度等参数的精确控制，完成了载机纵向着舰轨迹与速度的解耦工作。仿真结果表明，该控制律在拥有较强的鲁棒性的基础上具有良好的解耦控制能力，实现了载机着舰段的高度与速度的解耦控制，明显提高了载机对着舰轨迹的跟踪能力，可满足不确定条件下载机的着舰要求。
위료소제함미류대재궤착함과정산생적영향，동시완성저동압상태하비행속도여고도적해우공작，기우정량반궤이론/총능량공제이론（ QFT/TECS）설계료종향착함공제계통。침대착함과정중수학모형소구유적불학정인소급함미류대하활항적적영향，이재궤고도변화솔위공제대상，사용정량반궤이론결합추력보상계통진행료내회로로봉공제률설계。외회로공제률설계시이총능량공제이론위기출，통과입자군우화산법대대조공제삼수진행심우，진이실현료대고도、속도등삼수적정학공제，완성료재궤종향착함궤적여속도적해우공작。방진결과표명，해공제률재옹유교강적로봉성적기출상구유량호적해우공제능력，실현료재궤착함단적고도여속도적해우공제，명현제고료재궤대착함궤적적근종능력，가만족불학정조건하재궤적착함요구。
In order to eliminate the influence of environment on approaching and landing of the carrier-based aircrafts and relieve the coupling between the velocity and altitude under low aerodynamic pressure condition,a longitudinal carrier landing control system was established based on QFT-TECS.For the un-certain factors of mathematical model during the procedure of carrier aircraft landing and the influence on glide path by carrier air wake ,an inner loop robust control law was designed in order to control the alti-tude rate,which was based on the quantitative feedback theory method and the automatic power compen -sator system .Though the particle swarm optimization which was used to optimize the controller parame-ters,the accurate altitude control and speed control could be realized by the outer loop control law ,which is used the total energy control system as the foundation .Thus the coupling between the speed and the al-titude can be relieved .The simulation results indicate that this control system not only has strong robust-ness but also has good decoupling capability .Decoupling the altitude and velocity was realized ,and signif-icantly enhancing the trace tracking ability for the carrier -based aircrafts by this control system.The re-quirements for the procedure of carrier aircraft approach and landing can be satisfied .