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우주선 시뮬레이션
R2026a우주선의 운동 및 동특성을 모델링, 시뮬레이션 및 시각화
Aerospace Blockset > Spacecraft 하위 라이브러리에 있는 우주선 블록을 사용하여 우주선의 동특성을 모델링, 시뮬레이션 및 시각화하십시오.
블록
 | Attitude Dynamics | 하나 이상의 우주선의 모델 자세 동역학 (R2023a 이후) |
 | Attitude Profile (Nadir Pointing) | Calculate shortest quaternion rotation |
 | Cartesian State Vectors to Keplerian Orbital Elements | Calculate Keplerian orbital elements from orbital state vectors in equatorial coordinate system of celestial bodies (R2026a 이후) |
 | CubeSat Vehicle Earth (Nadir) Pointing | Model CubeSat vehicle whose primary alignment vector points towards center of Earth |
 | Keplerian Orbital Elements to Cartesian State Vectors | Calculate orbital state vectors in equatorial coordinate system of celestial bodies from Keplerian orbital elements (R2026a 이후) |
 | Line of Sight Access | Determine line of sight (LOS) access between one or more source positions and one or more target positions (R2024b 이후) |
 | Orbit Propagator Kepler (unperturbed) | Propagate orbit of one or more spacecraft using Kepler universal variable formulation |
 | Orbit Propagator Numerical (high precision) | Propagate orbit of one or more spacecraft using Kepler universal variable formulation |
 | Spacecraft Dynamics | Model dynamics of one or more spacecraft |
도움말 항목
추천 예제
Compute and visualize access intervals between the Apollo Command and Service module and a rover on the lunar surface. The module's orbit is modeled using Reference Trajectory #2 from the NASA report Variations of the Lunar Orbital Parameters of the Apollo CSM-Module [2]. This is a lunar orbit studied by NASA for the Apollo program. The example uses:
