抗直通短路的高可靠性電源拓?fù)浼翱刂品绞降难芯?/H1>
發(fā)布時(shí)間：2018-06-08 21:43
本文選題：航天電源 + 抗直通短路 ； 參考：《燕山大學(xué)》2015年碩士論文
【摘要】：航天電源在航天器中扮演著不可替代的作用,由于空間環(huán)境的特殊性以及電源的不可維修性,給航天電源的研制帶來(lái)很大的難度。隨著航天技術(shù)不斷發(fā)展,航天器在適用于高壓輸入、大功率、高可靠、高精度等方面對(duì)電源的研制提出了更高的要求。本文在此背景下,研究設(shè)計(jì)了抗橋臂直通的高可靠拓?fù)浣Y(jié)構(gòu)以及新型磁反饋技術(shù)。本文首先對(duì)抗直通功率變換基本單元P-Cell和N-Cell進(jìn)行分析,并根據(jù)功率流重構(gòu)的思想,構(gòu)成具有抗橋臂直通的高可靠拓?fù)浣Y(jié)構(gòu),通過(guò)對(duì)不同拓?fù)浣Y(jié)構(gòu)特性的對(duì)比分析,確定半橋推挽結(jié)構(gòu)作為變換器的主拓?fù)洳⑸钊胙芯苛酥魍負(fù)涞墓ぷ髟怼４_定主控芯片為T(mén)I公司的PWM斬波控制芯片UC3825。電源工作模式為恒壓模式,采用峰值電流控制方式,以及射極跟隨型斜坡補(bǔ)償電路消除次諧波振蕩,同時(shí)設(shè)計(jì)了浪涌抑制電路,共模抑制電路,隔離驅(qū)動(dòng)電路。為消除一次側(cè)與二次側(cè)交叉耦合的影響,原副邊要進(jìn)行電氣隔離,本文通過(guò)磁反饋實(shí)現(xiàn)輸出電壓的調(diào)節(jié),本文研究了三種磁反饋方案,對(duì)不同結(jié)構(gòu)進(jìn)行對(duì)比分析,采用了正激磁反饋方式,完成磁反饋等效小信號(hào)模型以及硬件設(shè)計(jì)。完成電源整體方案設(shè)計(jì),硬件參數(shù)設(shè)計(jì)和器件的選取,并對(duì)主功率級(jí)電路進(jìn)行小信號(hào)建模,研究設(shè)計(jì)峰值電流控制模式下系統(tǒng)的小信號(hào)模型,設(shè)計(jì)電壓外環(huán)調(diào)節(jié)器,對(duì)整個(gè)系統(tǒng)的穩(wěn)定性進(jìn)行仿真和分析。完成實(shí)驗(yàn)樣機(jī)的制作、調(diào)試,測(cè)試其工作指標(biāo)。實(shí)驗(yàn)樣機(jī)的測(cè)試結(jié)果滿(mǎn)足模塊電源預(yù)期設(shè)計(jì)的穩(wěn)態(tài)和動(dòng)態(tài)指標(biāo)。額定輸入下,半載效率達(dá)到89.8%,滿(mǎn)載效率為88.7%。本文給出了主要的實(shí)驗(yàn)波形并進(jìn)行了分析,驗(yàn)證了主電路和反饋控制設(shè)計(jì)方案的可行性,為航天電源技術(shù)提供了技術(shù)參考。
[Abstract]:Space power plays an irreplaceable role in spacecraft. Because of the particularity of space environment and the maintainability of power supply, it is very difficult to develop space power source. With the continuous development of spaceflight technology, the spacecraft has put forward higher requirements for the development of power supply in the aspects of high voltage input, high power, high reliability and high precision. In this context, a high reliable topology and a new magnetic feedback technique are designed. In this paper, first of all, P-Cell and N-Cell, the basic units of direct power transformation, are analyzed. According to the idea of power flow reconstruction, a highly reliable topology with resistance to the straight through of the bridge arm is constructed. The characteristics of different topology structures are compared and analyzed. The half-bridge push-pull structure is determined as the main topology of the converter and the working principle of the main topology is studied. Determine that the main control chip is TI PWM chopper control chip UC3825. The mode of power supply is constant voltage mode, which adopts peak current control mode and emitter follower slope compensation circuit to eliminate subharmonic oscillation. At the same time, surge suppression circuit, common-mode suppression circuit and isolation drive circuit are designed. In order to eliminate the influence of cross coupling between primary side and secondary side, the primary and secondary sides should be electrically isolated. In this paper, the output voltage is adjusted by magnetic feedback. In this paper, three magnetic feedback schemes are studied, and the different structures are compared and analyzed. The equivalent small signal model of magnetic feedback and hardware design are completed by positive excitation feedback. Complete the overall scheme design of power supply, hardware parameter design and device selection, and model the main power level circuit with small signal, study and design the small signal model of the system under the peak current control mode, design the voltage outer loop regulator. The stability of the whole system is simulated and analyzed. Complete the manufacture, debugging and testing of the experimental prototype. The test results of the experimental prototype meet the steady and dynamic indexes of the expected design of the module power supply. Under rated input, the half load efficiency is 89. 8 and the full load efficiency is 88. 7. In this paper, the main experimental waveforms are given and analyzed, and the feasibility of the main circuit and the feedback control scheme is verified, which provides a technical reference for the aerospace power supply technology.
【學(xué)位授予單位】：燕山大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2015
【分類(lèi)號(hào)】：V442
【參考文獻(xiàn)】
相關(guān)期刊論文 前6條
1 王建岡;阮新波;陳軍艷;;航空用大功率模塊電源的設(shè)計(jì)及關(guān)鍵技術(shù)應(yīng)用研究[J];電工技術(shù)學(xué)報(bào);2005年12期
2 張乾;王衛(wèi)國(guó);;星載開(kāi)關(guān)電源浪涌電流抑制電路研究[J];電子技術(shù)應(yīng)用;2008年12期
3 張興,馬先奎,張崇巍;推挽式DC/DC開(kāi)關(guān)電源的設(shè)計(jì)與校正[J];合肥工業(yè)大學(xué)學(xué)報(bào)(自然科學(xué)版);2000年06期
4 李斌;王衛(wèi)國(guó);劉克承;;推挽DC-DC變換器建模與控制設(shè)計(jì)[J];現(xiàn)代電子技術(shù);2011年24期
5 馮彥君;華更新;劉淑芬;;航天電子抗輻射研究綜述[J];宇航學(xué)報(bào);2007年05期
6 雷衛(wèi)軍;李言俊;;星上DC/DC變換器國(guó)內(nèi)外研究現(xiàn)狀[J];宇航學(xué)報(bào);2007年06期
，
本文編號(hào)：1997265
本文鏈接：http://sikaile.net/kejilunwen/hangkongsky/1997265.html
本文選題：航天電源 + 抗直通短路 ； 參考：《燕山大學(xué)》2015年碩士論文
【摘要】：航天電源在航天器中扮演著不可替代的作用,由于空間環(huán)境的特殊性以及電源的不可維修性,給航天電源的研制帶來(lái)很大的難度。隨著航天技術(shù)不斷發(fā)展,航天器在適用于高壓輸入、大功率、高可靠、高精度等方面對(duì)電源的研制提出了更高的要求。本文在此背景下,研究設(shè)計(jì)了抗橋臂直通的高可靠拓?fù)浣Y(jié)構(gòu)以及新型磁反饋技術(shù)。本文首先對(duì)抗直通功率變換基本單元P-Cell和N-Cell進(jìn)行分析,并根據(jù)功率流重構(gòu)的思想,構(gòu)成具有抗橋臂直通的高可靠拓?fù)浣Y(jié)構(gòu),通過(guò)對(duì)不同拓?fù)浣Y(jié)構(gòu)特性的對(duì)比分析,確定半橋推挽結(jié)構(gòu)作為變換器的主拓?fù)洳⑸钊胙芯苛酥魍負(fù)涞墓ぷ髟怼４_定主控芯片為T(mén)I公司的PWM斬波控制芯片UC3825。電源工作模式為恒壓模式,采用峰值電流控制方式,以及射極跟隨型斜坡補(bǔ)償電路消除次諧波振蕩,同時(shí)設(shè)計(jì)了浪涌抑制電路,共模抑制電路,隔離驅(qū)動(dòng)電路。為消除一次側(cè)與二次側(cè)交叉耦合的影響,原副邊要進(jìn)行電氣隔離,本文通過(guò)磁反饋實(shí)現(xiàn)輸出電壓的調(diào)節(jié),本文研究了三種磁反饋方案,對(duì)不同結(jié)構(gòu)進(jìn)行對(duì)比分析,采用了正激磁反饋方式,完成磁反饋等效小信號(hào)模型以及硬件設(shè)計(jì)。完成電源整體方案設(shè)計(jì),硬件參數(shù)設(shè)計(jì)和器件的選取,并對(duì)主功率級(jí)電路進(jìn)行小信號(hào)建模,研究設(shè)計(jì)峰值電流控制模式下系統(tǒng)的小信號(hào)模型,設(shè)計(jì)電壓外環(huán)調(diào)節(jié)器,對(duì)整個(gè)系統(tǒng)的穩(wěn)定性進(jìn)行仿真和分析。完成實(shí)驗(yàn)樣機(jī)的制作、調(diào)試,測(cè)試其工作指標(biāo)。實(shí)驗(yàn)樣機(jī)的測(cè)試結(jié)果滿(mǎn)足模塊電源預(yù)期設(shè)計(jì)的穩(wěn)態(tài)和動(dòng)態(tài)指標(biāo)。額定輸入下,半載效率達(dá)到89.8%,滿(mǎn)載效率為88.7%。本文給出了主要的實(shí)驗(yàn)波形并進(jìn)行了分析,驗(yàn)證了主電路和反饋控制設(shè)計(jì)方案的可行性,為航天電源技術(shù)提供了技術(shù)參考。
[Abstract]:Space power plays an irreplaceable role in spacecraft. Because of the particularity of space environment and the maintainability of power supply, it is very difficult to develop space power source. With the continuous development of spaceflight technology, the spacecraft has put forward higher requirements for the development of power supply in the aspects of high voltage input, high power, high reliability and high precision. In this context, a high reliable topology and a new magnetic feedback technique are designed. In this paper, first of all, P-Cell and N-Cell, the basic units of direct power transformation, are analyzed. According to the idea of power flow reconstruction, a highly reliable topology with resistance to the straight through of the bridge arm is constructed. The characteristics of different topology structures are compared and analyzed. The half-bridge push-pull structure is determined as the main topology of the converter and the working principle of the main topology is studied. Determine that the main control chip is TI PWM chopper control chip UC3825. The mode of power supply is constant voltage mode, which adopts peak current control mode and emitter follower slope compensation circuit to eliminate subharmonic oscillation. At the same time, surge suppression circuit, common-mode suppression circuit and isolation drive circuit are designed. In order to eliminate the influence of cross coupling between primary side and secondary side, the primary and secondary sides should be electrically isolated. In this paper, the output voltage is adjusted by magnetic feedback. In this paper, three magnetic feedback schemes are studied, and the different structures are compared and analyzed. The equivalent small signal model of magnetic feedback and hardware design are completed by positive excitation feedback. Complete the overall scheme design of power supply, hardware parameter design and device selection, and model the main power level circuit with small signal, study and design the small signal model of the system under the peak current control mode, design the voltage outer loop regulator. The stability of the whole system is simulated and analyzed. Complete the manufacture, debugging and testing of the experimental prototype. The test results of the experimental prototype meet the steady and dynamic indexes of the expected design of the module power supply. Under rated input, the half load efficiency is 89. 8 and the full load efficiency is 88. 7. In this paper, the main experimental waveforms are given and analyzed, and the feasibility of the main circuit and the feedback control scheme is verified, which provides a technical reference for the aerospace power supply technology.
【學(xué)位授予單位】：燕山大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2015
【分類(lèi)號(hào)】：V442
【參考文獻(xiàn)】
相關(guān)期刊論文 前6條
1 王建岡;阮新波;陳軍艷;;航空用大功率模塊電源的設(shè)計(jì)及關(guān)鍵技術(shù)應(yīng)用研究[J];電工技術(shù)學(xué)報(bào);2005年12期
2 張乾;王衛(wèi)國(guó);;星載開(kāi)關(guān)電源浪涌電流抑制電路研究[J];電子技術(shù)應(yīng)用;2008年12期
3 張興,馬先奎,張崇巍;推挽式DC/DC開(kāi)關(guān)電源的設(shè)計(jì)與校正[J];合肥工業(yè)大學(xué)學(xué)報(bào)(自然科學(xué)版);2000年06期
4 李斌;王衛(wèi)國(guó);劉克承;;推挽DC-DC變換器建模與控制設(shè)計(jì)[J];現(xiàn)代電子技術(shù);2011年24期
5 馮彥君;華更新;劉淑芬;;航天電子抗輻射研究綜述[J];宇航學(xué)報(bào);2007年05期
6 雷衛(wèi)軍;李言俊;;星上DC/DC變換器國(guó)內(nèi)外研究現(xiàn)狀[J];宇航學(xué)報(bào);2007年06期
，本文編號(hào)：1997265
本文鏈接：http://sikaile.net/kejilunwen/hangkongsky/1997265.html
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