a the ellipse has a semimajor axis a, -2a perigee to apogee-- is 2a.
椭圆轨道半长轴为,近地点到远地点。
mistakenly believe that doing elliptical motion of the satellite perigee and apogee of the orbit radius of curvature different.
错误地认为做椭圆运动的卫星在近地点和远地点的轨道曲率半径不同。
the shape and perigee of artificial satellite orbits shall continually variate due to caused by the atmospherical drag and the earth gravity.
人造地球卫星的轨道由于大气阻力和地球引力场等因素的摄动,其形状和近地点位置将不断改变。
in this paper, variations of ae-d's perigee altitudes, the corresponding atmospheric expansion and the density distributions are analyzed.
本文分析了aed极轨卫星近地点的变化及其相应的大气膨胀和密度分布情况。
if this is an ellipse around the earth, then this would be perigee and this would be apogee.
如果这是一个围绕,地球的椭圆形轨道,那么这是近地点,这是远地点。
since the average lunar perigee is 364,397 km (226,432 mi), on march 19 the moon was about 7,820 km (4,860 mi) closer to the earth.
由于月球表面距地球的平均近地点距离约为364,397km(26 432米)。19日晚的超级月亮距地球的距离在此平均值的基础上又缩短了近7820km(4860米)。
he also stressed that the upcoming maximal perigee had nothing to do with the events in japan.
他说:「月球过去接近地球时,日本并没有发生地震,所以我们不能把这些事件联系起来。日本的地震发生于月球近地点一周之前,而当时海洋也正处于低潮时期。」
seen here, the near perigee full moon still hugs the horizon, distorted by atmospheric refraction as it rises over boston, massachusetts, usa.
在上面这张照片中,这轮因大气折射而显得有些变形的超级满月,紧挨着地平线,就好像正在美国波士顿市上空冉冉升起。
if you managed to miss this perigee full moon, make a note on your calendar.
如果你真得错过了这轮近地满月,在你的日历上做个记号。
we know the period, we know where apogee is, we know where perigee is, - we know the orbital period-- anything we want to know.
知道周期,知道远地点,和近地点在哪里,知道轨道周期-,知道了想知道的一切。
you now have the ecliptic longitude of perigee of the sun for the mean summer solstice of your chosen year (and effectively for the entire year) .
你现在有黄道经度的近地点的阳光平均夏季冬至,你选择了一年(而有效地为整个一年) 。
the average full moon at perigee appears around 12 percent larger than an average non-perigee full moon. supermoons, even more so.
事实证明的确如此,于近地点观测到的满月要比非近地点观测到的大12%左右,超级月亮相对会更大一些。
now we want to know what the situation is with perigee and with apogee.
现在我们要看看,近地点和远地点的情况。
this paper offers a method which maintain orbital shape and perigee location.
本文提供一种保持轨道形状和近地点位置不变的控制方法。