- 公開されているTLEデータから適当に2つの衛星を選択しました
- (お手持ちのデータや時間範囲に変更すれば同様に適用可能だと思います)
- for文は不要で、vecnorm関数で相対距離と相対速度を演算しました
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読み込む軌道要素データ,iss_orbit.tle
・解析条件
startTime = datetime(2022,12,08,00,00,0);
stopTime = startTime + hours(12);
sampleTime = 5;
この時、ISSとFENGYUN 1C DEB が最も接近するとき,その時刻,直線距離,相対速度を求めなさい.
startTime = datetime(2020,6,02,8,23,0);
% stopTime = startTime + days(1);
stopTime = startTime + hours(3);
sampleTime = 5;
sc = satelliteScenario(startTime,stopTime,sampleTime);
sat = satellite(sc,"./iss_orbit.tle");
%show(sat) % 自分で再生ボタンを押してスタートさせる
%地表にfootprintを描く
groundTrack(sat,"Lead Time",12*60*60);
disp("----- start -----");
startTime_1 = datetime(2022,12,08,00,00,0);
stopTime_1 = startTime+ hours(12);
time_step_1 = seconds(5);
time_x_array = [];
distance_array = [];
velocity_array = [];
for time_x = startTime_1 : time_step_1 : stopTime_1
% disp(time_x);
[pos_1, vel_1] = states(sat(1),time_x,"CoordinateFrame","inertial");
[pos_2, vel_2] = states(sat(2),time_x,"CoordinateFrame","inertial");
distance_21 = sqrt( ...
(pos_2(1)-pos_1(1))^2 + ...
(pos_2(2)-pos_1(2))^2 + ...
(pos_2(3)-pos_1(3))^2 ...
);
rel_vel_21 = sqrt( ...
(vel_2(1)-vel_1(1))^2 + ...
(vel_2(2)-vel_1(2))^2 + ...
(vel_2(3)-vel_1(3))^2 ...
);
time_x_array = [time_x_array; time_x];
distance_array = [distance_array distance_21];
velocity_array = [velocity_array rel_vel_21];
end
% disp(size(distance_array));
[M,I] = min(distance_array);
% disp(M);
% disp(I);
disp("----- end -----");
% apple silicon m1, calc time = 3min
% disp(time_x_array(I));
% disp(distance_array(I));
% disp(velocity_array(I));
plot(time_x_array, distance_array);
X = sprintf('Time = %s, Distance(km) = %f, Relative V(km/sec) = %f \n', ...
datetime(time_x_array(I)), distance_array(I)/1000.0, velocity_array(I)/1000.0);
disp(X);
play(sc); % 自動で再生ボタンが押されてスタートする
これを利用して、軌道解説お願いします。
2 Commenti
Atsushi Ueno
il 20 Mar 2023
Spostato: Atsushi Ueno
il 21 Mar 2023
urlwrite("https://celestrak.org/NORAD/elements/stations.txt","iss_orbit.tle");
startTime = datetime(2023,3,5,22,49,45);
stopTime = startTime + minutes(3);
sampleTime = 5;
sc = satelliteScenario(startTime,stopTime,sampleTime);
sat = satellite(sc,"./iss_orbit.tle");
[pos_1, vel_1] = states(sat( 1),"CoordinateFrame","inertial");
[pos_2, vel_2] = states(sat(10),"CoordinateFrame","inertial");
distance_array = vecnorm(pos_1-pos_2, 3, 1);
velocity_array = vecnorm(vel_1-vel_2, 3, 1);
time_x_array = startTime : seconds(sampleTime) : stopTime;
[M,I] = min(distance_array);
fprintf('Time = %s, Distance(km) = %f, Relative V(km/sec) = %f \n', ...
datetime(time_x_array(I)), distance_array(I)/1000.0, velocity_array(I)/1000.0);
plot(time_x_array, distance_array);
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