化学激光推进的研究
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摘要
激光推进是利用激光与工质相互作用产生高温高压的气团反喷以获得推力,推动空间飞行器前进的新概念推进技术。传统的激光推进走向实用,需要平均功率百MW量级的激光器。受到激光器制作技术的约束,现有激光器的平均功率最高到105W量级,远达不到实用的要求。研究中,发现一些工质在激光推进过程中存在化学能的释放,从而使推进性能得到大幅提升,我们将其定义为化学激光推进。化学激光推进过程中不仅将激光能量转化为动能,还引入了化学能,可以同时提高冲量耦合系数和比冲,从而提高推力器整体的推进性能,可降低同等推力下对激光功率的要求,且化学激光推力器的工作状态可控,为激光推进技术走向实用提供了新的思路,在空间推进中具有重要应用价值。
本文针对化学激光推进技术,进行了以下几方面的实验和数值研究：
(1)化学激光推进机理方面的研究
以化学能的释放为线索,分析化学激光推进的基本原理,将其物理过程简化为两个阶段：(1)激光与工质相互作用阶段：(2)激光作用后产生的高温高压气团在推力器中的流场演化阶段。化学能的释放既可以出现在激光作用时,也可以出现在激光作用后的高温高压气团在推力器内流场演化过程中。
化学激光推进的工质一般分为两类：(1)工质本身不含氧化剂,其在化学激光推进中的能量释放主要发生在激光作用后的高温高压气团在推力器中的流场演化过程中,需要外界提供氧气。(2)工质本身含有氧化剂,其在激光与工质相互作用时就会释放大量的化学能,这种能量释放是由工质本身提供的,不需要外界提供氧气。
在无推力器约束和有推力器约束两种条件下,分别对latm大气和latm氮气两种气体环境中的POM(聚甲醛)工质的推进性能进行了对比实验,发现在推进过程中激光烧蚀后的产物与大气环境中氧气发生了放热反应,验证了在化学激光推进中化学能释放的存在。
通过分子光谱分析,得到了激光作用于POM工质后产生的气团在真空和大气环境下的最终产物：真空中的最终产物为CH20,大气环境中的最终产物为CO2和H2O。确认了其在latm大气环境中所发生的化学反应,以及所释放的化学能。
结合高速纹影实验和Fluent数值模拟,追踪推力器约束下的POM工质在激光作用后的流场演化过程。采用有限速率化学反应模型得到的模拟结果与高速纹影实验吻合较好。结果表明,化学能释放的激烈程度与产物气团和大气中氧气的混合程度相关,混合得越充分,化学能释放得越激烈。
(2)大能量化学激光推进和推力器的研究
利用单脉冲能量为519J的TEA600型CO2激光器和自研制的掺杂A1粉的POM复合工质,几何构型优化后的直筒型化学激光推力器的冲量耦合系数和比冲分别达到113.2dyne/W和1275.4s,此时,激光能量利用率高达707%,这是目前国际上报道的最高的指标,推进中化学能的贡献超过了86%。
开展了直筒型推力器多脉冲推进的实验研究,结果表明激光重复频率为20Hz时,前一脉冲产物对后一脉冲推进性能没有明显影响,每个脉冲的推进性能只与激光的功率密度和筒径与光斑直径之比α有关。
(3)化学激光微推进的研究
由于激光微推进所用激光器的功率小(W量级),化学能的补充是提高其推进性能的关键技术,我们首先建立了精密微冲量挡板扭摆系统,对自研制的复合双基药薄膜工质进行了系统的实验和数值研究,发现随着工质厚度的增加,冲量耦合系数逐渐增加,但比冲有渐减的趋势。并得到了化学能释放和激光功率密度的关系。利用功率为1.80W的半导体激光器,25u m厚的复合双基药工质的冲量耦合系数和比冲分别达到了130.8dyne/W和493s,此时,激光能量利用率高达316%,是无化学能释放的工质的6倍以上,化学能的贡献非常明显。
Laser propulsion is a new concept technique for propulsion. It promotes the aircraft by utilizing the counterforce generated during the injection of gases with extremely high temperature and pressure which formed by interaction between high-power laser and propellant. There is a new concept of laser propulsion, called chemical laser propulsion (CLP) which can greatly enhance the propulsion performance because of the supplement of chemical energy during the propulsion process. The kinetic energy of thruster is converted by not only the laser energy, but also the chemical energy during the chemical laser propulsion process. It can also improve the momentum coupling coefficient and specific impulse, so it can greatly improve the overall propulsion performance of the thruster. It provides a new way for developing laser propulsion technology to application stage.
In the present thesis, the following researches, focused on the CLP technology, have been studied.
(1) The mechanism research of CLP
The physical process of CLP is divided into two stages by analysing the basic principle of CLP based on the release of chemical energy. The first one is the stage of interaction between high-power laser and propellant, and the last one is the stage of flow field evolution of gases with high temperature and pressure in thruster. The supplement of chemical energy can occur in both the first stage and the last one.The propellants of CLP are divided into energetic propellants and non-energetic propellants. In general, the supplement of a large amount of chemical energy of energetic propellant, which can release chemical energy itself without oxygen provided extra, occurs in the last stage. And that of non-energetic propellant, which needs oxygen provided extra to release chemical energy, occurs in the first stage.
The propulsion performance of the propellant has been studied both in1atm atmospheric environment and in1atm nitrogen environment under the constrained conditions by thruster and unconstrained conditions. The results show that there is an exothermic reaction in the propulsion process, occurred with oxygen contained in1atm atmospheric environment. The existence of chemical energy release in CLP has been validated.
Based on the molecular spectroscopy analysis, the the final products of the chemical reaction between gas in environment and that, which formed by interaction between high-power laser and propellant with extremely high temperature and pressure, have been ascertained. The final product in vacuum environment is CH2O. The final products with1atm atmospheric environment are CO2and H2O. The chemical reactions in1atm atmospheric environment and the chemical energy released in the reactions have been deduced.
The flow field evolution of gases with high temperature and pressure, formed by interaction between high-power laser and propellant, has been obtained by the high speed schlieren experiment and the numerical simulation using Fluent. It has given a very good agreement between simulation and experiment results. The chemical energy and the release rate of chemical energy curves have been given by numerical simulation. It shows that the release intensity of chemical energy depends on how well the product gas is mixed with oxygen in the atmosphere. The release intensity of chemical energy is greater while the gases are mixed more fully.
(2) The research of CLP with large energy and thruster
The numerical simulation of the propulsion performance of cylindrical thruster has been studied. There are two important factors affecting the propulsion performance of cylindrical nozzle thrusters:the length L of thruster and the thruster diameter to laser-spot diameter ratio α. We get the best value of L and a, which is identical with the experimental results. When we use TEA600CO2laser with the energy of519J and the best configuration of cylindrical thruster with POMAl as the propellant, the momentum coupling coefficient and specific impulse is113.2dyne/W and1275.4s, while laser energy coefficient is707%, which is the biggest value reported.
The propulsion performance of cylindrical thruster under two repeated pulses has been studied experimentally. The results show the products generated by ablation under the first pulse has no effect on the propulsion performance under the second pulse.
(3) The research of chemical laser micro-propulsion
We have designed a baffle torsion pendulum testing system, the measuring principle of which is described, and the measurement error of the system has been analyzed. The effect of the thickness of double base propellant on the propulsion performance has been stydied by using this system. The experimental results show that the momentum coupling coefficient increases with the increase of thickness, while the specific impulse decreases. The effect of laser power density on the release of chemical energy has been studied. When we use semiconductor laser with the power of1.8W and the double base propellant, which is designed ourselves, the momentum coupling coefficient and specific impulse is130.8dyne/W and493s, while laser energy coefficient is316%, which is six times better than the propellant without the release of chemical energy.
本文针对化学激光推进技术,进行了以下几方面的实验和数值研究：
(1)化学激光推进机理方面的研究
以化学能的释放为线索,分析化学激光推进的基本原理,将其物理过程简化为两个阶段：(1)激光与工质相互作用阶段：(2)激光作用后产生的高温高压气团在推力器中的流场演化阶段。化学能的释放既可以出现在激光作用时,也可以出现在激光作用后的高温高压气团在推力器内流场演化过程中。
化学激光推进的工质一般分为两类：(1)工质本身不含氧化剂,其在化学激光推进中的能量释放主要发生在激光作用后的高温高压气团在推力器中的流场演化过程中,需要外界提供氧气。(2)工质本身含有氧化剂,其在激光与工质相互作用时就会释放大量的化学能,这种能量释放是由工质本身提供的,不需要外界提供氧气。
在无推力器约束和有推力器约束两种条件下,分别对latm大气和latm氮气两种气体环境中的POM(聚甲醛)工质的推进性能进行了对比实验,发现在推进过程中激光烧蚀后的产物与大气环境中氧气发生了放热反应,验证了在化学激光推进中化学能释放的存在。
通过分子光谱分析,得到了激光作用于POM工质后产生的气团在真空和大气环境下的最终产物：真空中的最终产物为CH20,大气环境中的最终产物为CO2和H2O。确认了其在latm大气环境中所发生的化学反应,以及所释放的化学能。
结合高速纹影实验和Fluent数值模拟,追踪推力器约束下的POM工质在激光作用后的流场演化过程。采用有限速率化学反应模型得到的模拟结果与高速纹影实验吻合较好。结果表明,化学能释放的激烈程度与产物气团和大气中氧气的混合程度相关,混合得越充分,化学能释放得越激烈。
(2)大能量化学激光推进和推力器的研究
利用单脉冲能量为519J的TEA600型CO2激光器和自研制的掺杂A1粉的POM复合工质,几何构型优化后的直筒型化学激光推力器的冲量耦合系数和比冲分别达到113.2dyne/W和1275.4s,此时,激光能量利用率高达707%,这是目前国际上报道的最高的指标,推进中化学能的贡献超过了86%。
开展了直筒型推力器多脉冲推进的实验研究,结果表明激光重复频率为20Hz时,前一脉冲产物对后一脉冲推进性能没有明显影响,每个脉冲的推进性能只与激光的功率密度和筒径与光斑直径之比α有关。
(3)化学激光微推进的研究
由于激光微推进所用激光器的功率小(W量级),化学能的补充是提高其推进性能的关键技术,我们首先建立了精密微冲量挡板扭摆系统,对自研制的复合双基药薄膜工质进行了系统的实验和数值研究,发现随着工质厚度的增加,冲量耦合系数逐渐增加,但比冲有渐减的趋势。并得到了化学能释放和激光功率密度的关系。利用功率为1.80W的半导体激光器,25u m厚的复合双基药工质的冲量耦合系数和比冲分别达到了130.8dyne/W和493s,此时,激光能量利用率高达316%,是无化学能释放的工质的6倍以上,化学能的贡献非常明显。
Laser propulsion is a new concept technique for propulsion. It promotes the aircraft by utilizing the counterforce generated during the injection of gases with extremely high temperature and pressure which formed by interaction between high-power laser and propellant. There is a new concept of laser propulsion, called chemical laser propulsion (CLP) which can greatly enhance the propulsion performance because of the supplement of chemical energy during the propulsion process. The kinetic energy of thruster is converted by not only the laser energy, but also the chemical energy during the chemical laser propulsion process. It can also improve the momentum coupling coefficient and specific impulse, so it can greatly improve the overall propulsion performance of the thruster. It provides a new way for developing laser propulsion technology to application stage.
In the present thesis, the following researches, focused on the CLP technology, have been studied.
(1) The mechanism research of CLP
The physical process of CLP is divided into two stages by analysing the basic principle of CLP based on the release of chemical energy. The first one is the stage of interaction between high-power laser and propellant, and the last one is the stage of flow field evolution of gases with high temperature and pressure in thruster. The supplement of chemical energy can occur in both the first stage and the last one.The propellants of CLP are divided into energetic propellants and non-energetic propellants. In general, the supplement of a large amount of chemical energy of energetic propellant, which can release chemical energy itself without oxygen provided extra, occurs in the last stage. And that of non-energetic propellant, which needs oxygen provided extra to release chemical energy, occurs in the first stage.
The propulsion performance of the propellant has been studied both in1atm atmospheric environment and in1atm nitrogen environment under the constrained conditions by thruster and unconstrained conditions. The results show that there is an exothermic reaction in the propulsion process, occurred with oxygen contained in1atm atmospheric environment. The existence of chemical energy release in CLP has been validated.
Based on the molecular spectroscopy analysis, the the final products of the chemical reaction between gas in environment and that, which formed by interaction between high-power laser and propellant with extremely high temperature and pressure, have been ascertained. The final product in vacuum environment is CH2O. The final products with1atm atmospheric environment are CO2and H2O. The chemical reactions in1atm atmospheric environment and the chemical energy released in the reactions have been deduced.
The flow field evolution of gases with high temperature and pressure, formed by interaction between high-power laser and propellant, has been obtained by the high speed schlieren experiment and the numerical simulation using Fluent. It has given a very good agreement between simulation and experiment results. The chemical energy and the release rate of chemical energy curves have been given by numerical simulation. It shows that the release intensity of chemical energy depends on how well the product gas is mixed with oxygen in the atmosphere. The release intensity of chemical energy is greater while the gases are mixed more fully.
(2) The research of CLP with large energy and thruster
The numerical simulation of the propulsion performance of cylindrical thruster has been studied. There are two important factors affecting the propulsion performance of cylindrical nozzle thrusters:the length L of thruster and the thruster diameter to laser-spot diameter ratio α. We get the best value of L and a, which is identical with the experimental results. When we use TEA600CO2laser with the energy of519J and the best configuration of cylindrical thruster with POMAl as the propellant, the momentum coupling coefficient and specific impulse is113.2dyne/W and1275.4s, while laser energy coefficient is707%, which is the biggest value reported.
The propulsion performance of cylindrical thruster under two repeated pulses has been studied experimentally. The results show the products generated by ablation under the first pulse has no effect on the propulsion performance under the second pulse.
(3) The research of chemical laser micro-propulsion
We have designed a baffle torsion pendulum testing system, the measuring principle of which is described, and the measurement error of the system has been analyzed. The effect of the thickness of double base propellant on the propulsion performance has been stydied by using this system. The experimental results show that the momentum coupling coefficient increases with the increase of thickness, while the specific impulse decreases. The effect of laser power density on the release of chemical energy has been studied. When we use semiconductor laser with the power of1.8W and the double base propellant, which is designed ourselves, the momentum coupling coefficient and specific impulse is130.8dyne/W and493s, while laser energy coefficient is316%, which is six times better than the propellant without the release of chemical energy.
引文
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