secondly, through establishing the small-signal model, the voltage loop and the current loop are designed . the effect of the loop parameters, varieties of frequency and rms to the system are analyzed 通過逆變系統(tǒng)的小信號建模,設(shè)計(jì)了閉環(huán)參數(shù),并詳細(xì)分析閉環(huán)參數(shù)、頻率和電壓變化對系統(tǒng)的影響,前后級阻抗的匹配關(guān)系。
at first, it introduces the method of loop parameters, including gain of phase detecting, gain of loop filter and frequency sensitivity, then simulations are done under different structures and parameters . according to the results of simulation, loop structure is decided 在此章中,首先是詳細(xì)地討論了環(huán)路中各個參數(shù)的計(jì)算;接著是對各種參數(shù)和結(jié)構(gòu)進(jìn)行了性能仿真,并由此決定了環(huán)路的結(jié)構(gòu)。
by using the correction approach of vary-transfer function for designing parameter of closed-loop in the area of power electronics, the system could work reliably under wide range input voltage conditions . compared with the design method of closed-loop parameter, the advantages of the correction approach of vary-transfer function were highlighted and testified by simulation and experimental results 為了使系統(tǒng)能夠在寬電壓輸入范圍內(nèi)穩(wěn)定正常工作,本文實(shí)現(xiàn)了提出的變傳遞函數(shù)系統(tǒng)校正方法在電力電子閉環(huán)參數(shù)設(shè)計(jì)中的應(yīng)用,并與閉環(huán)參數(shù)設(shè)計(jì)方法進(jìn)行了比較,指出了該方法的優(yōu)點(diǎn),并通過仿真和實(shí)驗(yàn)驗(yàn)證了該方法的正確性。
it can be deduced from the characteristics of ilpll circuit that injection-locking bandwidth is not only related to the injection-locking bandwidth without feedback loop, but also related to the characteristics of frequency mixing, loop gain and the change of the loop phase . thus, the needed bandwidth can be obtained by adjusting the loop parameters . and the phase noise characteristics are mainly determined by loop transmission factor 由ilpll電路特性的推導(dǎo)得出:注入鎖定帶寬不僅跟開環(huán)時(shí)的注鎖帶寬有關(guān),而且與混頻特性、環(huán)路增益以及環(huán)路相位變化相關(guān)聯(lián),可以通過調(diào)節(jié)環(huán)路的參數(shù)得到所需帶寬;相噪特性主要由環(huán)路傳輸因子決定,可以通過調(diào)節(jié)環(huán)路濾波得到比開環(huán)注入鎖定相噪更優(yōu)的特性。
lastly, establish the rigid-body spaceship attitude kinematics and dynamics equations, and primarily design the spaceship attitude law including limit loop parameters and two kind switch curves . analyze the astronaut ’ s disturbance moments . put the disturbance moments of typical astronaut ’ s push-off act as the input datas of the control system simulation, and analyze the response of the attitude control system after disturbed 最后,建立剛體飛船姿態(tài)運(yùn)動學(xué)及動力學(xué)方程,并對飛船姿態(tài)控制律進(jìn)行了初步的設(shè)計(jì),包括極限環(huán)參數(shù)的設(shè)計(jì)和兩類典型的開關(guān)曲線的設(shè)計(jì);對航天員擾動力矩進(jìn)行了分析;以典型的航天員推離動作對飛船的擾動力矩作為控制系統(tǒng)仿真的輸入?yún)?shù),分析姿態(tài)控制系統(tǒng)受到擾動后的響應(yīng)。