【摘要】：固體火箭沖壓發(fā)動(dòng)機(jī)在飛行器上越來越廣泛的運(yùn)用,促使對(duì)燃?xì)獍l(fā)生器流量調(diào)節(jié)技術(shù)的研究。隨著對(duì)整體式固體火箭沖壓發(fā)動(dòng)機(jī)的要求不斷提高,燃?xì)饬髁空{(diào)節(jié)技術(shù)及控制方法成為各國(guó)研究的熱點(diǎn)。本文圍繞變流量整體式固體火箭沖壓發(fā)動(dòng)機(jī)燃?xì)饬髁空{(diào)節(jié)技術(shù)以及發(fā)動(dòng)機(jī)控制展開相關(guān)研究工作。首先,根據(jù)執(zhí)行機(jī)構(gòu)設(shè)計(jì)指標(biāo)設(shè)計(jì)氣動(dòng)式燃?xì)饬髁繄?zhí)行機(jī)構(gòu)。建立其數(shù)學(xué)模型,對(duì)模型進(jìn)行了降階簡(jiǎn)化。對(duì)其進(jìn)行動(dòng)態(tài)響應(yīng)和靜態(tài)跟蹤測(cè)試,測(cè)試結(jié)果表明,所設(shè)計(jì)的執(zhí)行機(jī)構(gòu)的性能參數(shù)基本能夠滿足指標(biāo)要求。其次,分析燃?xì)獍l(fā)生器的工作特性,分別建立了調(diào)節(jié)系統(tǒng)的穩(wěn)態(tài)模型以及動(dòng)態(tài)模型。對(duì)模型線性化后為一個(gè)非最小相位系統(tǒng),具有逆響應(yīng)特性。并從階躍調(diào)節(jié)狀況和動(dòng)態(tài)調(diào)節(jié)狀況兩種情況對(duì)燃?xì)饬髁康哪骓憫?yīng)產(chǎn)生的原因進(jìn)行了分析,得出逆響應(yīng)是伴隨燃?xì)饬髁空{(diào)節(jié)的過程必然存在的一種現(xiàn)象。并通過系統(tǒng)仿真討論了燃速壓強(qiáng)指數(shù),燃?xì)獍l(fā)生器自由容積,初始穩(wěn)態(tài)喉道面積,噴管喉道面積變化率對(duì)絕對(duì)逆響應(yīng)量以及逆響應(yīng)持續(xù)時(shí)間的影響。然后,針對(duì)流量調(diào)節(jié)方式,討論三種不同的控制方式:噴管喉道面積控制,燃燒室壓強(qiáng)控制,考慮逆響應(yīng)現(xiàn)象的過渡過程設(shè)計(jì)。從這三個(gè)方面分別對(duì)燃?xì)獍l(fā)生器進(jìn)行了控制方法的研究和設(shè)計(jì)。在對(duì)噴管喉道面積控制時(shí),研究一種基于逆響應(yīng)限制下的控制系統(tǒng)。在要求的逆響應(yīng)限制下有效的提高了系統(tǒng)的響應(yīng)速度。針對(duì)其壓強(qiáng)系統(tǒng)特性,設(shè)計(jì)線性自抗擾控制器。在長(zhǎng)時(shí)間的工作和不同調(diào)節(jié)范圍內(nèi),能夠很好實(shí)現(xiàn)對(duì)壓強(qiáng)的快速無超調(diào)控制。以壓強(qiáng)控制系統(tǒng)為基礎(chǔ),采用了模糊微分跟蹤器作為系統(tǒng)的過渡函數(shù),在對(duì)響應(yīng)速度影響較小的情況下,有效的減小了逆響應(yīng)量的大小。對(duì)燃?xì)饬髁空{(diào)節(jié)系統(tǒng)進(jìn)行了冷調(diào)實(shí)驗(yàn)和熱調(diào)實(shí)驗(yàn)。在冷調(diào)實(shí)驗(yàn)中,驗(yàn)證了壓強(qiáng)控制系統(tǒng)的可行性。研究了控制信號(hào)變化率對(duì)逆響應(yīng)現(xiàn)象的影響。在熱調(diào)實(shí)驗(yàn)中,驗(yàn)證執(zhí)行機(jī)構(gòu)的的穩(wěn)定性,實(shí)驗(yàn)結(jié)果在一定程度上反映了燃?xì)饬髁空{(diào)節(jié)系統(tǒng)的特性。分析了機(jī)械空程對(duì)壓強(qiáng)控制系統(tǒng)的影響。最后,對(duì)變流量固體火箭沖壓發(fā)動(dòng)機(jī)進(jìn)行分析并建立數(shù)學(xué)模型。針對(duì)系統(tǒng)的變參數(shù)特性和逆響應(yīng)特性,采用廣義預(yù)測(cè)控制算法對(duì)長(zhǎng)時(shí)間工作情況下的系統(tǒng)進(jìn)行控制。仿真表明,相比與傳統(tǒng)的控制器,廣義預(yù)測(cè)控制能夠在一定程度上減小系統(tǒng)的逆響應(yīng)現(xiàn)象,降低系統(tǒng)的超調(diào)與不穩(wěn)定現(xiàn)象,提高系統(tǒng)的控制精度。
[Abstract]:Solid rocket ramjet is more and more widely used in aircraft, which promotes the research of flow regulation technology of gas generator. With the increasing demand for integral solid rocket ramjet, gas flow regulation technology and control methods have become a hot topic in many countries. This paper focuses on variable flow integral solid rocket ramjet gas flow regulation technology and engine control. Firstly, the pneumatic gas flow actuator is designed according to the design index of the actuator. The mathematical model of the model is established, and the order reduction of the model is simplified. The dynamic response and static tracking tests show that the performance parameters of the designed actuator can basically meet the requirements. Secondly, the operating characteristics of the gas generator are analyzed, and the steady-state model and the dynamic model of the regulating system are established respectively. The model is linearized as a non-minimum phase system with inverse response. The causes of the inverse response of gas flow are analyzed from the two situations of step regulation and dynamic regulation. It is concluded that the inverse response is an inevitable phenomenon in the process of gas flow regulation. The effects of burning rate pressure index, free volume of gas generator, initial steady throat area and nozzle throat area on the absolute inverse response and the inverse response duration are discussed by systematic simulation. Then, three different control methods are discussed: nozzle throat area control, combustion chamber pressure control, and transition process design considering inverse response. The control method of gas generator is studied and designed from these three aspects. In the control of nozzle throat area, a control system based on inverse response is studied. The response speed of the system is improved effectively under the restriction of the required inverse response. According to the characteristics of the pressure system, a linear ADRC controller is designed. In the long working hours and different adjustment range, it can realize the fast and no overshoot control of the pressure. Based on the pressure control system, the fuzzy differential tracker is used as the transition function of the system. In the case of less influence on the response speed, the size of the inverse response is reduced effectively. The cold regulation experiment and the heat regulation experiment are carried out on the gas flow regulation system. The feasibility of the pressure control system is verified in the cold adjustment experiment. The effect of the change rate of control signal on the inverse response is studied. The stability of the actuator is verified in the heat regulation experiment, and the experimental results reflect the characteristics of the gas flow regulation system to some extent. The influence of mechanical airspeed on pressure control system is analyzed. Finally, the variable flow solid rocket ramjet is analyzed and the mathematical model is established. The generalized predictive control (GPC) algorithm is used to control the system with long working time according to the variable parameter and inverse response characteristics of the system. The simulation results show that compared with the traditional controller, the generalized predictive control can reduce the inverse response of the system to a certain extent, reduce the overshoot and instability of the system, and improve the control accuracy of the system.
【學(xué)位授予單位】：北京理工大學(xué)
【學(xué)位級(jí)別】：博士
【學(xué)位授予年份】：2015
【分類號(hào)】：V435

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本文編號(hào)：2394354