55 lines
1.8 KiB
Rust
55 lines
1.8 KiB
Rust
//! The propagated state of a satellite.
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use apsis_math::Vec3;
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/// The position and velocity of a satellite in the True Equator Mean Equinox
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/// frame.
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///
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/// Position is in kilometers and velocity is in kilometers per second. The
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/// frame is the one the model defines, with its first axis toward the mean
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/// equinox, its third axis along the true equator pole, and the second
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/// completing a right-handed set.
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///
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/// 真赤道平春分点系中卫星的位置与速度。
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///
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/// 位置单位为千米，速度单位为千米每秒。该系是模型所定义者：第一轴指向平春分点，
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/// 第三轴沿真赤道极，第二轴构成右手系。
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#[derive(Debug, Clone, Copy, PartialEq)]
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pub struct State {
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/// Position, in kilometers.
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///
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/// 位置，单位为千米。
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pub position: Vec3,
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/// Velocity, in kilometers per second.
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///
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/// 速度，单位为千米每秒。
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pub velocity: Vec3,
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/// The propagated semi-major axis, in kilometers.
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///
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/// This is the semi-major axis after the secular drag term has been
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/// applied, so it differs from the value implied by the mean motion in
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/// the element set.
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///
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/// 传播所得的半长轴，单位为千米。
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///
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/// 这是施加长期阻力项之后的半长轴，故与根数集中平运动所隐含的值不同。
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pub semi_major_axis: f64,
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}
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impl State {
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/// Returns the distance from the center of the Earth, in kilometers.
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///
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/// 返回到地心的距离，单位为千米。
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pub fn altitude_radius(self) -> f64 {
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self.position.norm()
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}
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/// Returns the speed relative to the Earth's center, in kilometers per
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/// second.
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///
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/// 返回相对地心的速率，单位为千米每秒。
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pub fn speed(self) -> f64 {
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self.velocity.norm()
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}
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}
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