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Full lifetime demonstration of a Micro-Cathode-Arc thruster evolution characteristics

Chinese Journal of Aeronautics 2024年第6期37卷 38-49页

作者： Zhe ZHANG Zijing ZHAO Xiangyang LIU ningfei wang School of Aerospace Engineering Beijing Institute of TechnologyBeijing 100081China

Ground lifetime test is the most crucial experiment to assess the performance,*** flight qualification of electric propulsion,and it can bring new insights for understanding the operation *** work demonstrates a full lifetime test of 140000 cycles on a Micro-Cathode-Arc Thruster(μCAT)with 160μs charging time and 86 mJ charging energy.A four-probe resistivity measurement method is utilized to investigate variations in the conductive film thickness and resistivity throughout the thruster *** film parameters show that the lifetime of theμCAT can be divided into three *** the initial stage,the film thickness decreases by 1.2μm and the resistivity increases significantly due to the high discharge intensity and intense film ablation;In the steady stage,the change of the film thickness is within 5%,and the resistivity of the film increases slowly from 0.050Ω·mm to 0.223Ω·*** the end stage,the resistivity exponentially increases from 0.223Ω·mm to 1.176Ω·mm,with the increase accounting for 81%,ultimately resulting in the failure of the thruster open ***,the evolution of discharge parameters,and the variation of plume parameters are measured throughout the *** discharge characteristics also show significant differences in the duration of voltage and current in these three *** results of plume shape and plasma parameters are also well con-sistent with the discharge parameters and film *** results suggest that,for evaluating the steady stage lifetime of thrusters,the film thickness is the best indicator compared to the variations in resistivity and voltage-current *** the end stage,the plasma plume *** duration,and plume parameters can conveniently and clearly characterize the thruster failures and irregularity.

关键词： Electric propulsion Lifetime test Micro-Cathode-Arc Thruster(uCAT) Conductive film Discharge characteristics Plasma parameters

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Investigations of the mechanical response of dummy HTPB propellant grain under ultrahigh acceleration overload conditions using onboard flight-test measurements

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Defence Technology（防务技术） 2024年第2期32卷 473-484页

作者： Yiming Zhang ningfei wang Weihua Ma Ran wang Long Bai Yi Wu School of Aerospace Engineering Beijing Institute of TechnologyBeijing 100081China Beijing System Design Institute of Electro-mechanic Engineering Beijing 100854China Xi'an Changfeng Research Institute of Mechanism and Electricity Xi'an 710065China

In this paper,to study the mechanical responses of a solid propellant subjected to ultrahigh acceleration overload during the gun-launch process,specifically designed projectile flight tests with an onboard measurement system were *** projectiles containing dummy HTPB propellant grains were successfully recovered after the flight tests with an ultrahigh acceleration overload value of 8100 *** onboard-measured time-resolved axial displacement,contact stress and overload values were successfully obtained and *** compression tests of the dummy HTPB propellant used in the gunlaunched tests were carried out at low and intermediate strain rates to characterize the propellant's dynamic properties.A linear viscoelastic constitutive model was employed and applied in finite-element simulations of the projectile-launching *** the launch process,the dummy propellant grain exhibited large deformation due to the high acceleration overload,possibly leading to friction between the motor case and propellant *** calculated contact stress showed good agreement with the experimental results,though discrepancies in the overall displacement of the dummy propellant grain were *** dynamic mechanical response process of the dummy propellant grain was analysed in *** results can be used to estimate the structural integrity of the analysed dummy propellant grain during the gun-launch process.

关键词： Gun-launched flight test Dummy HTPB propellant Onboard measurements Utrahigh overload Mechanical response

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Numerical study on ignition start-up process of an underwater solid rocket motor across a wide depth range

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Chinese Journal of Aeronautics 2024年第10期37卷 136-157页

作者： Deyou wang Shipeng LI Ge JIN Ruyao wang Dian GUAN ningfei wang School of Aerospace Engineering Beijing Institute of TechnologyBeijing 100081China Beijing System Design Institute of Electro-mechanic Engineering Beijing 100854China

Solid rocket motors have important applications in the propulsion of trans-media vehicles and underwater launched *** this paper,the ignition start-up process of an underwater solid rocket motor across a wide depth range has been numerically studied.A novel multi-domain integrated model has been developed by combining the solid propellant ignition and combustion model with the volume of fluid multiphase *** integrated model enables the coupled simulation of the propellant combustion and gas flow inside the motor,along with the gas jet evolution in the external water *** detailed flow field developments in the combustion chamber,nozzle,and wake field are carefully *** variation rules of the internal ballistics and thrust performance are also *** effects of environmental medium and operating depth on the ignition start-up process are systematically *** results show that the influence of the operating environment on the internal ballistic characteristics is primarily reflected in the initial period after the nozzle closure *** development of the gas jet in water lags significantly compared with that in *** the water depth increases,the ignition delay time of the motor is shortened,and the morphology evolution of the gas jet is significantly compressed and ***,the necking and bulging of the jet boundary near the nozzle outlet and the consequent shock oscillations are intensified,resulting in stronger fluctuations in the wake pressure field and motor thrust.

关键词： Underwater propulsion Solid rocket motor Ignition start-up process Underwater gas jet Thrust oscillation

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A global model for evaluating discharge characteristics and performance of hollow cathodes

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Chinese Journal of Aeronautics 2024年第9期37卷 72-84页

作者： Feng TIAN Long MIAO Qimeng XIA Zhiwen WU ningfei wang Xiao HOU School of Aerospace Engineering Beijing Institute of TechnologyBeijing 100081China Chongqing Innovation Center Beijing Institute of TechnologyChongqing 404100China

Hollow cathode,with the highest plasma density,current density,and temperature,becomes one of the most important components in the electro-thruster *** the electric-propulsion thruster performance is directly related to the ionization rate,reliability,and lifetime of the hollow cathode,this paper develops a global model to study the effects of discharge current,gas flow rate,and gas species on the discharge characteristics in the insert and orifice regions of the hollow *** emitter wall temperatures of hollow cathodes predicted by the global model are compared with experimental results from NSTAR thruster neutralization cathodes,confirming the model's *** influence of hollow cathode emitter material and structure sizes on the plasma parameters in the internal regions was also *** simulation results show that there is an optimal matching relationship between the discharge current and gas flow rate to guarantee the maximum ionization *** optimal working region for the hollow cathode has been deter-mined under different energetic,regime and structural *** global model established in this paper can quickly determine the key structure and operating parameters of hollow cathode at the design stage,and provide the theoretical basis for hollow cathode design and development.

关键词： Hollow cathode Global model Electric propulsion Discharge characteristics Optimal matching relationship

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Micro-aluminum powder with bi-or tri-component alloy coating as a promising catalyst:Boosting pyrolysis and combustion of ammonium perchlorate

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Defence Technology（防务技术） 2024年第3期33卷 100-113页

作者： Chao wang Ying Liu Mingze Wu Jia Li Ying Feng Xianjin Ning Hong Li ningfei wang Baolu Shi School of Aerospace Engineering Beijing Institute of TechnologyBeijing 100081China School of Materials Science and Engineering Beijing Institute of TechnologyBeijing 100081China State Key Laboratory of Explosion Science and Technology Beijing Institute of TechnologyBeijing 100081China

A novel design of micro-aluminum(μAl)powder coated with bi-/tri-component alloy layer,such as:Ni-P and Ni-P-Cu(namely,Al@Ni-P,Al@Ni-P-Cu,respectively),as combustion catalysts,were introduced to release its huge energy inside Al-core and promote rapid pyrolysis of ammonium perchlorate(AP)at a lower temperature in aluminized *** microstructure of Al@Ni-P-Cu demonstrates that a three-layer Ni-P-Cu shell,with the thickness of~100 nm,is uniformly supported byμAl carrier(fuel unit),which has an amorphous surface with a thickness of~2.3 nm(catalytic unit).The peak temperature of AP with the addition of Al@Ni-P-Cu(3.5%)could significantly drop to 316.2℃ at high-temperature thermal decomposition,reduced by 124.3℃,in comparison to that of pure AP with 440.5℃.It illustrated that the introduction of Al@Ni-P-Cu could weaken or even eliminate the obstacle of AP pyrolysis due to its reduction of activation energy with 118.28 kJ/*** laser ignition results showed that the ignition delay time of Al@Ni-P-Cu/AP mixture with 78 ms in air is shorter than that of Al@Ni-P/AP(118 ms),decreased by 33.90%.Those astonishing breakthroughs were attributed to the synergistic effects of adequate active sites on amorphous surface and oxidation exothermic reactions(7597.7 J/g)of Al@Ni-P-Cu,resulting in accelerated mass and/or heat transfer rate to catalyze AP pyrolysis and ***,it is believed to provide an alternative Al-based combustion catalyst for propellant designer,to promote the development the propellants toward a higher energy.

关键词： Micro-aluminum powder(μAl) Nano-sized alloy coating Combustion catalyst Ammonium perchlorate Pyrolysis behavior Ignition and combustion

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喷注位置对多组分燃料超燃冲压发动机燃烧的影响

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航空动力学报 2024年第5期39卷 25-35页

作者：滑远帆李世鹏王宁飞于文浩马源辰北京理工大学宇航学院北京100081 中国航天科技集团有限公司北京航天动力研究所北京100076 沈阳航空航天大学航空宇航学院沈阳110136

为研究含铝高能量密度碳氢燃料在超燃冲压发动机中的燃烧组织细节,使用离散相模型(DPM)和简化反应机理对不同燃料喷注位置下燃烧流动过程进行了数值模拟。结果表明:使用七喷注器从上壁面进行燃料喷注时,出口截面处温度场形成了以近上壁... 详细信息

为研究含铝高能量密度碳氢燃料在超燃冲压发动机中的燃烧组织细节,使用离散相模型(DPM)和简化反应机理对不同燃料喷注位置下燃烧流动过程进行了数值模拟。结果表明:使用七喷注器从上壁面进行燃料喷注时,出口截面处温度场形成了以近上壁面轴线为中心低温-升至最高温-降至较低温度的分布特征,氧浓度在中心处的含量也较低,这都将影响燃烧反应的进程。在研究工况下随着喷注器与燃烧室入口距离增大,燃料比冲呈先增大后减小的变化趋势,在研究工况中实现燃料最大比冲11092 m/s,可以通过改变燃料从上壁面喷入燃烧室的喷注位置和优化喷注器布局等提升燃烧室性能,优化后最大比冲提升了12.68%。

关键词：多组分燃料超燃冲压发动机喷注位置燃烧性能喷注布局优化

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摩擦力对空间非导电绳系释放动力学的影响

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兵工学报 2024年第4期45卷 1158-1167页

作者：梁福文苗龙田丰宋家辉白松何梓豪王宁飞北京理工大学宇航学院北京100081

当前空间非导电绳系释放过程因摩擦力数据缺乏,导致释放动力学仿真结果不能有效反映真实情况。为此,基于绳系地面释放平台,开展非导电绳系释放摩擦力测量实验,研究了系绳材料、直径、缠绕方向和释放速度对系绳释放所受摩擦力的影响,阐... 详细信息

当前空间非导电绳系释放过程因摩擦力数据缺乏,导致释放动力学仿真结果不能有效反映真实情况。为此,基于绳系地面释放平台,开展非导电绳系释放摩擦力测量实验,研究了系绳材料、直径、缠绕方向和释放速度对系绳释放所受摩擦力的影响,阐明非导电绳系释放过程影响球形效应不稳定现象的主要因素,确定非导电绳系释放摩擦力与释放条件之间的定量关系。进一步建立考虑摩擦力的绳系释放动力学模型。仿真结果表明,非导电绳系释放摩擦力对释放过程影响较大,对于500 m长的系绳,初始释放速度为2 m/s,在未考虑释放摩擦力时,绳系释放完成时间与考虑摩擦力的实际情况相差约20%。

关键词：空间绳系释放摩擦力地面实验释放速度动力学仿真

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Cooperative task assignment of multiple heterogeneous unmanned aerial vehicles using a modifed genetic algorithm with multi-type genes

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Chinese Journal of Aeronautics 2013年第5期26卷 1238-1250页

作者： Deng Qibo Yu Jianqiao wang ningfei Key Laboratory of Dynamics and Control of Flight Vehicle Ministry of EducationSchool of Aerospace EngineeringBeijing Institute of Technology

The task assignment problem of multiple heterogeneous unmanned aerial vehicles （UAVs）, concerned with cooperative decision making and control, is studied in this paper. The heterogeneous vehicles have different operational capabilities and kinematic constraints, and carry limited resources （e.g., weapons） onboard. They are designated to perform multiple consecutive tasks cooperatively on multiple ground targets. The problem becomes much more complicated because of these terms of heterogeneity. In order to tackle the challenge, we modify the former genetic algorithm with multi-type genes to stochastically search a best solution. Genes of chromo- somes are different, and they are assorted into several types according to the tasks that must be performed on targets. Different types of genes are processed specifically in the improved genetic operators including initialization, crossover, and mutation. We also present a mirror representation of vehicles to deal with the limited resource constraint. Feasible chromosomes that vehicles could perform tasks using their limited resources under the assignment are created and evolved by genetic operators. The effect of the proposed algorithm is demonstrated in numerical simulations. The results show that it effectively provides good feasible solutions and finds an optimal one.

关键词： Cooperative control Genetic algorithm Heterogeneous unmanned aerial vehicles Multi-type genes Task assignment

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空心阴极羽流等离子体放电不稳定性二维仿真模型

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兵工学报 2024年第4期45卷 1208-1218页

作者：田丰苗龙梁福文宋家辉何梓豪武志文王宁飞北京理工大学宇航学院北京100081

空心阴极放电过程中空间电势振荡会影响其工作性能,振荡过程产生的高能离子会对阴极孔产生溅射腐蚀,进而严重影响空心阴极的使用寿命。建立由质点网格(Particle-in-Cell,PIC)模型、振荡幅值模型与等效电路模型组成的一体化耦合模型来计... 详细信息

空心阴极放电过程中空间电势振荡会影响其工作性能,振荡过程产生的高能离子会对阴极孔产生溅射腐蚀,进而严重影响空心阴极的使用寿命。建立由质点网格(Particle-in-Cell,PIC)模型、振荡幅值模型与等效电路模型组成的一体化耦合模型来计算空心阴极放电过程电势振荡特性。采用PIC模型计算不同放电电流、放电电压及气体流量下羽流等离子体放电特性,获得羽流的电势、等离子数密度、电场强度和电子温度等时均参数的空间分布。基于等离子体聚集与耗散理论,建立电势振荡幅值模型,根据计算得到的时均参数来预估空间电势振荡幅值。将等离子体时均参数以及电势幅值振荡参数作为输入参数,代入到空心阴极放电等效电路模型中,从而得到相应工况下的电势振荡波形图。通过和实验结果对比发现,所建立的一体化耦合模型能较好地预估空心阴极羽流等离子体电势振荡特性,研究成果可用于指导空心阴极稳定放电,提升空心阴极在轨工作时限。

关键词：空心阴极质点网格模型电势振荡等效电路模型等离子体聚集与耗散

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入口流场不均匀性对固体火箭发动机大膨胀比喷管内流场的影响

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固体火箭技术 2024年第4期47卷 547-556页

作者：高惊涛孙宏权李新艳王宁飞北京理工大学宇航学院北京100081

在高机动飞行过程中,固体火箭发动机承受长时间的小过载会导致喷管入口处燃气方向改变,而药柱空间非均匀燃烧又会导致燃气密度分布不均匀,从而影响喷管入口处质量通量分布。二者均会造成入口燃气流动非均匀性,这是引起喷管流场不均匀性... 详细信息

在高机动飞行过程中,固体火箭发动机承受长时间的小过载会导致喷管入口处燃气方向改变,而药柱空间非均匀燃烧又会导致燃气密度分布不均匀,从而影响喷管入口处质量通量分布。二者均会造成入口燃气流动非均匀性,这是引起喷管流场不均匀性的主要原因之一,直接影响发动机性能。以膨胀比为100的固体火箭发动机喷管为研究对象,改变入口处质量通量分布规律与入射方向,结合计算流体力学软件研究入口流场不均匀性对喷管内流场的影响规律。结果表明:当喷管入口质量通量呈抛物面分布时,入口的不均匀性对喷管内流场影响较小,在喷管喉部位置不均匀效应基本消除;由俯仰过载导致燃气非垂直入射时,喷管入口位置流场周向不均匀性高达23%;随着燃气充分膨胀,不均匀效应减弱,在喷管扩张比达到92.8时,流场基本均匀,但是在有限扩张比条件下由入射角度导致的流场不均匀效应无法完全消除。

关键词：固体火箭发动机喷管大膨胀比流动不均匀内流场

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