《飞行力学》课程实验指导(共5页).doc

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1、精选优质文档-倾情为你奉上飞行力学课程实验指导实验名称：铅垂平面飞行弹道仿真及分析课内学时：学时，课外学时：学时实验内容与要求：根据描述飞行器在铅垂平面内运动的数学模型，编制某导弹的铅垂平面无控飞行弹道仿真程序，利用计算机解算无控飞行弹道，并对初始段弹道参数的变化规律进行分析。数学模型：（2-121）推荐算法：四阶龙格库塔法。原始数据：1）初值x=0(m)y=20.0(m) J=18 q=18v=20(m/s)wz=0(rad/s)m=52.38(kg)2）攻角与马赫数范围(仅用于插值计算)攻角=010 马赫数=0.1 0.93）阻力系数表马赫数攻角()02468100.1.4177.4404

2、.5219.6603.85341.10230.2.3858.4086.4903.6290.82261.07230.3.3779.4007.4827.6218.81601.06660.4.3785.4015.4838.6234.81841.07000.5.3787.4018.4846.6249.82091.07380.6.3829.4062.4897.6310.82841.08350.7.3855.4091.4934.6363.83581.09380.8.4082.4321.5175.6621.86411.12540.9.4947.5192.6073.7571.96721.23924）升力系数表

3、马赫数攻角()02468100.1.0000.64301.47582.28703.07133.84630.2.0000.64541.48072.29423.08143.85980.3.0000.64801.48582.30143.09153.87310.4.0000.65121.49232.31073.10393.88910.5.0000.65541.50072.32273.11973.90920.6.0000.66171.51342.34093.14363.94010.7.0000.66981.53042.36613.17753.98350.8.0000.67921.55012.39503.

4、21624.03230.9.0000.69331.59352.47063.32734.17905）推力数据t(s).000.15.492.112.273.538.7825.4542.8043.6844.08P(kgf)331.2614.3505.4607.848.6543.9742.0141.0040.8040.792.22第一级工作结束时间：2.1126s，第二级工作结束时间：44.0832s 6）发动机质量秒流量t(s)0.2.12.10544.144.105100秒流量(kg/s)2.3622.3620.210590.210590.0. 7）转动惯量t(s).02.02.46.410.4

5、14.418.422.426.430.434.038.442.444.0Jy(kgms)8.357.887.867.817.787.757.737.717.707.707.697.697.697.69 8）导弹重心（起自头部）t(s).02.02.410.018.026.032.038.042.044.0XG(m).9381.9095.9091.9026.8969.8928.8907.8896.8895.88969）静稳定力矩系数马赫数攻角()02468100.10.0000 -0.0104 -0.0341 -0.0564 -0.0771 -0.09850.20.0000 -0.0104 -0

6、.0341 -0.0564 -0.0770 -0.09830.30.0000 -0.0104 -0.0341 -0.0564 -0.0769 -0.09820.40.0000 -0.0105 -0.0342 -0.0564 -0.0768 -0.09790.50.0000 -0.0104 -0.0339 -0.0560 -0.0761 -0.09690.60.0000 -0.0093 -0.0314 -0.0521 -0.0708 -0.09030.70.0000 -0.0080 -0.0286 -0.0477 -0.0650 -0.08290.80.0000 -0.0065 -0.0252

7、-0.0425 -0.0578 -0.07390.90.0000 -0.0053 -0.0229 -0.0391 -0.0538 -0.0693当导弹重心变化时的修正公式：10）阻尼力矩导数当Xg=.9381时马赫数攻角()02468100.1-0.4686 -0.4829 -0.4982 -0.5130 -0.5272 -0.54090.2-0.4707 -0.4850 -0.5003 -0.5150 -0.5292 -0.54290.3-0.4744 -0.4886 -0.5039 -0.5186 -0.5327 -0.54640.4-0.4797 -0.4939 -0.5090 -0.5

8、237 -0.5378 -0.55140.5-0.4882 -0.5022 -0.5173 -0.5318 -0.5458 -0.55930.6-0.5089 -0.5227 -0.5376 -0.5520 -0.5658 -0.57910.7-0.5366 -0.5502 -0.5649 -0.5790 -0.5927 -0.60580.8-0.5738 -0.5871 -0.6014 -0.6153 -0.6287 -0.64150.9-0.6272 -0.6407 -0.6553 -0.6694 -0.6830 -0.6960当Xg=.8896时马赫数攻角()02468100.1-0.6

9、179 -0.6384 -0.6600 -0.6805 -0.6999 -0.71820.2-0.6207 -0.6410 -0.6626 -0.6830 -0.7024 -0.72070.3-0.6253 -0.6455 -0.6670 -0.6874 -0.7067 -0.72490.4-0.6319 -0.6521 -0.6734 -0.6937 -0.7129 -0.73100.5-0.6424 -0.6624 -0.6835 -0.7036 -0.7226 -0.74060.6-0.6669 -0.6866 -0.7074 -0.7272 -0.7459 -0.76360.7-0.6

10、997 -0.7190 -0.7395 -0.7589 -0.7774 -0.79480.8-0.7435 -0.7624 -0.7824 -0.8014 -0.8194 -0.83650.9-0.8069 -0.8266 -0.8474 -0.8672 -0.8859 -0.903511）其它参数特征面积(m2)特征长度(m)毛翼展(m)音速(m/s)大气密度(kg/m3)0.02271.80.5343.131.225插值算法：气动数据插值等距双变元抛物线插值；推力、重心、转动惯量等不等距一元线性插值。推荐步长：0.0050.01s论文提交：按北京理工大学学报对学术论文的规范要求，实验结束后一周内提交不低于3000字的论文（内容包含建模、仿真及分析等），附上源程序。专心-专注-专业