下挂式空射系统机箭分离阶段离散阵风响应分析
|
摘要
下挂式空射系统机箭分离阶段运载火箭处于无动力飞行阶段,高空阵风会对其运动轨迹产生较严重的干扰。为研究下挂式空中发射运载火箭机箭分离阶段系统的离散阵风响应,引入"网格速度"思想来计入阵风的影响,采用有限体积法求解非定常Euler和N-S方程,对机箭分离过程进行了动网格仿真分析。通过模块化方式搭建了机箭系统离散阵风响应仿真平台,平台由火箭状态及网格更新模块、力与力矩CFD解算模块、飞行状态参数求解模块和离散阵风干扰模块组成。仿真计算了机箭系统穿越1-cos离散阵风区的动态响应,并与无阵风条件下机箭分离气动特性进行了对比分析,结果表明无阵风条件下机箭分离后机箭系统可以较好地满足火箭的点火要求;在遭遇离散阵风后,机箭系统稳定性被破坏,可能导致发射失败,这对于机箭系统的控制率设计提出了更高的要求。
The rocket is in unpowered flight at the separation phase of missile and rocket of air launch system and the trajectory is prone to interference from the upper level gust.In order to research the responses of discrete gust of air launch system at separation phase,the influence of gust is simulated by using the grid velocity method,the finite volume method is used to solve unsteady Euler and N-S equation,and the separation process is calculated by using CFD dynamic grid.The simulation platform is built by the modular method,including update module of rocket's status and grid,CFD calculation module of force and moment,solution of flight status parameters and discrete gust interference module.The separation process under 1-cos gust disturbance is calculated by using the simulation platform,and the aerodynamic characteristics of the rocket and the carrier with or without gust disturbance are compared and analyzed.The results show that the air launch system can satisfy the requirement of rocket ignition after the separation of missile and rocket in the absence of gusts.After a discrete gust of wind,stability of the air launch system is de-stroyed after encountering discrete gust and may cause launch to fail,raising a higher requirement for the design of the control rate.
The rocket is in unpowered flight at the separation phase of missile and rocket of air launch system and the trajectory is prone to interference from the upper level gust.In order to research the responses of discrete gust of air launch system at separation phase,the influence of gust is simulated by using the grid velocity method,the finite volume method is used to solve unsteady Euler and N-S equation,and the separation process is calculated by using CFD dynamic grid.The simulation platform is built by the modular method,including update module of rocket's status and grid,CFD calculation module of force and moment,solution of flight status parameters and discrete gust interference module.The separation process under 1-cos gust disturbance is calculated by using the simulation platform,and the aerodynamic characteristics of the rocket and the carrier with or without gust disturbance are compared and analyzed.The results show that the air launch system can satisfy the requirement of rocket ignition after the separation of missile and rocket in the absence of gusts.After a discrete gust of wind,stability of the air launch system is de-stroyed after encountering discrete gust and may cause launch to fail,raising a higher requirement for the design of the control rate.
引文
[1]SCHADE C,MOSIER M.The Pegasus Launch Vehicle New Capabilities and the Future[Z].AIAA-94-1172.
[2]杜泉峰,王正平,王稳江.弹射式导弹发射时载机动力学响应研究[J].飞行力学,2008,28(2):51-54.DU Q F,WANG Z P,WANG W J.Research for Carrier-Aircraft Dynamic Response When Vertical Ejecting Missile is Launched[J].Flight Dynamics,2008,28(2):51-54.(in Chinese)
[3]杨磊,叶正寅,武洁.弹性载机对外挂物动力学响应的影响[J].气体物理,2016,1(4):1-11.YANG L,YE Z Y,WU J.Influence of Elastic Carrier to Dynamic Response of Store[J].Physics of Gases,2016,1(4):1-11.(in Chinese)
[4]廖莎莎,吴成,段继.导轨式机载导弹发射动力学模型及影响因素分析研究[J].弹箭与制导学报,2013,33(3):153-162.LIAO S S,WU C,DUAN J.Launch Dynamics Modeling and Analysis on Influencing Factors for Airborne Missile[J].Journal of Projectiles,Rockets,Missiles and Guidance,2013,33(3):153-162.(in Chinese)
[5]许晓平,祝小平,周洲,等.考虑喷流效应的机载导弹发射及气动干扰数值模拟[J].航空学报,2011.32(4):580-588.XU X P,ZHU X P,ZHOU Z,et al.Numerical Simulation of Missile Launching and Aerodynamic Interference with Plume Effects[J].Acta Aeronautica et Astronautica Sinica,2011.32(4):580-588.(in Chinese)
[6]杨秋艳,王立新.大气紊流环境下的纵向飞行参数响应分析[J].飞行力学,2009,27(1):20-23.YANG Q Y,WANG L X.Analysis of the Longitudinal Flight Parameter under Atmosphere Turbulence[J].Flight Dynamics,2009,27(1):20-23.(in Chinese)
[7]鹏程,王新民,张斯哲,等.基于LQG/LTR的飞翼飞机阵风飞机阵风减缓系统研究[J].飞行力学,2015,33(2):130-139.PENG C,WANG X M,ZHANG S Z,et al.Research on Gust Load Alleviation for Flying Wing Aircraft Based on LQG/LTR[J].Flight Dynamics,2015,33(2):130-139.(in Chinese)
[8]荆志伟,侯宗团,郭兆电.弹性飞机空投载荷设计技术[J].航空学报,2014,35(11):3037-3045.JING Z W,HOU Z T,GUO Z D.Flight Loads Design Technique for Flexible Aircraft Airdrop[J].Acta Aeronautica et Astronautica Sinica,2014,35(11):3037-3045.(in Chinese)
[9]CENKO A,PIRANIAN A,TALBOT M.Utilizing Wind Tunnel Test Data and Analysis to Determine Flight Test Envelopes For Safe Store Release[Z].AIAA-95-0328.
[10]GLEISS R,DESLANDES R M.Simulation of Missile Plumes for Aircraft Store Compatibility Assessments[Z].AIAA 2005-54.
[11]SINGH R,BAEDER J D.Direct Calculation of Three-Dimensional Indicial Lift Response Using Computational Fluid Dynamics[J].Journal of Aircraft,1997,34(4):465-471.
[12]PARAMESWARAN V,BAEDER J D.Indicial Aerodynamics in Compressible Flow-Direct Computational Fluid Dynamic Calculations[J].Journal of Aircraft,1997,34(1):131-133.
[13]詹浩,钱炜祺.翼型和机翼阵风响应的数值模拟[J].空气动力学报,2007,25(4):531-536.ZHAN H,QIAN W Q.Numerical Simulation of Gust Response for Airfoil and Wing[J].Acta Aerodynamica Sinica,2007,25(4):531-536.(in Chinese)
[14]任玉新.计算流体力学讲义[EB/OL].(2003-07-01)[2017-12-01].http://.www.docin.com/p-28135837.html.REN Y X.Computational Fluid Mechanics[EB/OL].(2003-07-01)[2017-12-01].http://www.docin.com/p-28135837.html.(in Chinese)
[15]BALLHAUS W F,GOOR JIAN P M.Computation of Unsteady Transonic Flows by the Indicial Method[J].AIAA Journal,1978,16(2):117-124.
[16]AHMAD J U,SHANKS S P,BUNING P G.Areodynamics of Powered Missile Seperation from F/A-18Aircraft[Z].AIAA-93-0766.
[17]FAA.FAR25 Airworthiness Standards:Transport Category Airplane[S].Seattle:FAA,2007.
[18]符文星,尚妮妮,常晓飞,等.离散阵风幅值计算的方法研究[J].西北工业大学学报,2014,32(5):822-827.FU W X,SHANG N N,CHANG X F,et al.A New Method for Calculating Magnitude of Wind Gust[J].Journal of Northwestern Polytechnical University,2014,32(5):822-827.(in Chinese)
[2]杜泉峰,王正平,王稳江.弹射式导弹发射时载机动力学响应研究[J].飞行力学,2008,28(2):51-54.DU Q F,WANG Z P,WANG W J.Research for Carrier-Aircraft Dynamic Response When Vertical Ejecting Missile is Launched[J].Flight Dynamics,2008,28(2):51-54.(in Chinese)
[3]杨磊,叶正寅,武洁.弹性载机对外挂物动力学响应的影响[J].气体物理,2016,1(4):1-11.YANG L,YE Z Y,WU J.Influence of Elastic Carrier to Dynamic Response of Store[J].Physics of Gases,2016,1(4):1-11.(in Chinese)
[4]廖莎莎,吴成,段继.导轨式机载导弹发射动力学模型及影响因素分析研究[J].弹箭与制导学报,2013,33(3):153-162.LIAO S S,WU C,DUAN J.Launch Dynamics Modeling and Analysis on Influencing Factors for Airborne Missile[J].Journal of Projectiles,Rockets,Missiles and Guidance,2013,33(3):153-162.(in Chinese)
[5]许晓平,祝小平,周洲,等.考虑喷流效应的机载导弹发射及气动干扰数值模拟[J].航空学报,2011.32(4):580-588.XU X P,ZHU X P,ZHOU Z,et al.Numerical Simulation of Missile Launching and Aerodynamic Interference with Plume Effects[J].Acta Aeronautica et Astronautica Sinica,2011.32(4):580-588.(in Chinese)
[6]杨秋艳,王立新.大气紊流环境下的纵向飞行参数响应分析[J].飞行力学,2009,27(1):20-23.YANG Q Y,WANG L X.Analysis of the Longitudinal Flight Parameter under Atmosphere Turbulence[J].Flight Dynamics,2009,27(1):20-23.(in Chinese)
[7]鹏程,王新民,张斯哲,等.基于LQG/LTR的飞翼飞机阵风飞机阵风减缓系统研究[J].飞行力学,2015,33(2):130-139.PENG C,WANG X M,ZHANG S Z,et al.Research on Gust Load Alleviation for Flying Wing Aircraft Based on LQG/LTR[J].Flight Dynamics,2015,33(2):130-139.(in Chinese)
[8]荆志伟,侯宗团,郭兆电.弹性飞机空投载荷设计技术[J].航空学报,2014,35(11):3037-3045.JING Z W,HOU Z T,GUO Z D.Flight Loads Design Technique for Flexible Aircraft Airdrop[J].Acta Aeronautica et Astronautica Sinica,2014,35(11):3037-3045.(in Chinese)
[9]CENKO A,PIRANIAN A,TALBOT M.Utilizing Wind Tunnel Test Data and Analysis to Determine Flight Test Envelopes For Safe Store Release[Z].AIAA-95-0328.
[10]GLEISS R,DESLANDES R M.Simulation of Missile Plumes for Aircraft Store Compatibility Assessments[Z].AIAA 2005-54.
[11]SINGH R,BAEDER J D.Direct Calculation of Three-Dimensional Indicial Lift Response Using Computational Fluid Dynamics[J].Journal of Aircraft,1997,34(4):465-471.
[12]PARAMESWARAN V,BAEDER J D.Indicial Aerodynamics in Compressible Flow-Direct Computational Fluid Dynamic Calculations[J].Journal of Aircraft,1997,34(1):131-133.
[13]詹浩,钱炜祺.翼型和机翼阵风响应的数值模拟[J].空气动力学报,2007,25(4):531-536.ZHAN H,QIAN W Q.Numerical Simulation of Gust Response for Airfoil and Wing[J].Acta Aerodynamica Sinica,2007,25(4):531-536.(in Chinese)
[14]任玉新.计算流体力学讲义[EB/OL].(2003-07-01)[2017-12-01].http://.www.docin.com/p-28135837.html.REN Y X.Computational Fluid Mechanics[EB/OL].(2003-07-01)[2017-12-01].http://www.docin.com/p-28135837.html.(in Chinese)
[15]BALLHAUS W F,GOOR JIAN P M.Computation of Unsteady Transonic Flows by the Indicial Method[J].AIAA Journal,1978,16(2):117-124.
[16]AHMAD J U,SHANKS S P,BUNING P G.Areodynamics of Powered Missile Seperation from F/A-18Aircraft[Z].AIAA-93-0766.
[17]FAA.FAR25 Airworthiness Standards:Transport Category Airplane[S].Seattle:FAA,2007.
[18]符文星,尚妮妮,常晓飞,等.离散阵风幅值计算的方法研究[J].西北工业大学学报,2014,32(5):822-827.FU W X,SHANG N N,CHANG X F,et al.A New Method for Calculating Magnitude of Wind Gust[J].Journal of Northwestern Polytechnical University,2014,32(5):822-827.(in Chinese)