matlab 连接STK-526互联

%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% % 功能说明：MATLAB与STK互联 % 作者： % 版本：v1.0 % 时间：2023/7/10 %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% %% 1.初始化需要的接口函数 stkInit; % 建立连接 remMachine = stkDefaultHost; conid = stkOpen(remMachine); % 得到连接句柄（用于发送指令） % 判断场景是否存在 scen_open = stkValidScen; if scen_open == 1 rtn = questdlg('Close the current scenario?'); if ~strcmp(rtn,'Yes') stkClose(conid); return; else stkUnload('/*'); end end %% 2.建立场景、航天器和观测站 % 建立场景 disp('创建场景中......'); disp('-------------------------'); stkNewObj('/','Scenario','TestScenario'); % 设定场景时间 disp('设定场景时间......'); disp('-------------------------'); % 设定场景开始时间 % startDate = '27'; startMonth = 'Nov'; startYear = '2019'; % startHour = '00'; startMin = '00'; startSec = '00.000'; % strStartTime = strcat(startDate,32,startMonth,32,startYear,32,startHour,':',startMin,':',startSec);% 逗号之间的“32”代表“空格”之意 strStartTime = '27 Nov 2019 00:00:00.000'; % 设定场景结束时间 % stopDate = '27'; stopMonth = 'Nov'; stopYear = '2019'; % stopHour = '02'; stopMin = '00'; stopSec = '00.000'; % strEndTime = strcat(stopDate,32,stopMonth,32,stopYear,32,stopHour,':',stopMin,':',stopSec);% 逗号之间的“32”代表“空格”之意 strEndTime = '28 Nov 2019 02:00:00.000'; stkSetTimePeriod(strStartTime,strEndTime,'GREGUTC'); stkSetEpoch(strStartTime,'GREGUTC'); stkSyncEpoch; % 设定场景动画开始时间 strQuteBegTime = ['"' strStartTime '"']; % 时间写入命令是得加双引号，比较刻板 rtn = stkConnect(conid,'Animate','Scenario/TestScenario',['SetValues ' strQuteBegTime ' 10 0.1']); % 下面这个用来参考格式 % rtn = stkConnect(conid,'Animate','Scenario/TestScenario','SetValues "27 May 2019 06:14:00.000" 60 0.1'); % 设定动画时间回到起始点 rtn = stkConnect(conid,'Animate','Scenario/TestScenario','Reset'); % 建立航天器 disp('建立航天器......'); disp('-------------------------'); stkNewObj('*/','Satellite','AoXiangI'); %% 3.设定星座中各卫星的属性 %--------------------------------------------------------------% % 注意：这里的单位都是弧度(rad) % 千万别用错单位！ %--------------------------------------------------------------% disp('仿真运行中......'); disp('-------------------------'); rtn = stkConnect(conid,'Animate','Scenario/TestScenario','Start End'); d2r = pi/180; % 卫星积分起止时间、轨道历元时间、步长 t_start=0; t_stop=2*60*60; orbitEpoch=t_start; dt=10; tSimu = t_start+1:t_stop/dt; % 卫星初始轨道根数 a = 6928.137*1000; e = 0.0; i = 53.0*d2r; w = 0*pi/180; Raan = 160*pi/180; M = 0*d2r; % 设置卫星轨道属性 stkSetPropClassical('*/Satellite/AoXiangI','J2Perturbation','J2000',t_start,t_stop,dt,orbitEpoch,a,e,i,w,Raan,M); % 设置卫星姿态属性(下面写的这个是错的) Qua = [sqrt(2)/2;0;0;sqrt(2)/2]; QuaMat = repmat(Qua,1,length(tSimu)); stkSetAttitudeCBI('*/Satellite/AoXiangI','AoXiangI',tSimu,QuaMat); tic; global satPos satVel satPos = zeros(t_stop/dt,3); satVel = zeros(t_stop/dt,3); time = zeros(1,t_stop/dt); k = 1; for t = 1:dt:t_stop [satPos1,satVel1] = stkPosVelCBI('*/Satellite/AoXiangI',t); satPos(k,:) = satPos1; satVel(k,:) = satVel1; k = k+1; end toc; % 保存数据至csv中 col_str = {'sat_pos_x','sat_pos_y','sat_pos_z','sat_vel_x','sat_vel_y','sat_vel_z'}; res_table = table(satPos(:,1),satPos(:,2),satPos(:,3),satVel(:,1),satVel(:,2),satVel(:,1),'VariableNames',col_str); writetable(res_table, 'satellite_data.csv'); stkClose(conid);