Saturday, August 19, 2017
There are rumors that there will be an eclipse next week. How do we know this is so? We can start with HORIZONS data for the daily noon positions of the Sun and Moon in geocentric equatorial coordinates for the year 2017. Next we convert RA and DEC into the spherical angles φ and θ in radians to determine the angular separation of the Sun and Moon.
The first plot is Δφ and the jags occur because Δφ is always increasing and we only need to know the relative angular distance between them and when it crosses the line Δφ=0. The second plot tells us when Δθ=0. But for an eclipse to occur both conditions need to be satisfied at approximately the same time. So we look through our table of Δφ and Δθ for nearly simultaneous crossings. The occurs twice in 2017 on or about Feb 2 and Aug 21.
The eclipse on Feb 26th has already occurred so we'll focus on the Aug 21 eclipse candidate. Another plot gives us a better picture of when both Δφ and Δθ cross the horizontal axis.
It's difficult to tell exactly when the Sun and Moon will be closest together since they are moving at different rates but a calculation indicates the minimum separation is just under half a degree. The directions of the Sun and Moon are eS and eM respectively.
This looks promising since the Moon's paralax, the shift in angle for moving from the subsolar position on the Earth surface to the Earth's limb, is about 0.0179 rad and adding the apparent angular radius of the Moon, 0.0043 rad, and the angular size of the Sun, 0.0047 rad, we get a maximum allowable separation of 0.0268 rad. Adding a box to indicate these bounds to a plot of Δθ vs. Δφ indicates that there will indeed be an eclipse at this time.
The point on the curve closest to the origin is towards the end of the eclipse which would explain the relatively later time.
Sunday, August 13, 2017
I redid the series of fits for the Sun's apparent position this time in the plane of the Ecliptic. The primary motion is of course a Keplerian ellipse. The horizontal and vertical axes are the major and minor axes and at the beginning of the year the Sun in near perigee on the right and moves upwards. The units are AU.
The Keplerian elements for the fit are as follows.
The residuals of this fit form a rose curve which appears to be due to solar pulls and torques acting on the Moon's orbit. Again the units are AU.
The residuals of the second fit are down to μAUs and more random in appearance. There's an odd step in the direction of increasing perigee at the end of the year. Could the Earth be slowing down and spending more time at perihelion? What effect would that have on global warming?
Fits can produce some deviations when all the error isn't accounted for.
Wednesday, August 9, 2017
I was preparing for the solar eclipse later this month, doing a fit of the Sun's relative position from the center of the Earth, and the fit didn't turn out as I expected. A linear least squares fit of the Sun's position for the functions indicated resulted in the following relative differences between the fit and the calculated positions.
The sinusoidal function is mainly due to the Moon's pull on the Earth but there appears to be another component present. How can one explain the displacement of mean error from zero? It turns out there are some Chebyshev polynomials present.
This polynomial series generates a displacement of the following form given in AU.
After subtracting this and the displacement due to the pull of the Moon the following error remains.
The error can be measured in micro AU (μAU). For comparison the Earth moves about the Sun at a mean rate of 2π/365.24=0.0172AU/day=12μAU/min. It probably wouldn't hurt to get accurate measurements of the start and end eclipse times.
Essentially the same error or perhaps correction is present in both MICA and HORIZONS data for the Sun's position relative to the Earth.
Wednesday, August 2, 2017
One can study various modes of light sail operation to see how it will perform. The parasitic reduction of perigee seems to be associated with acceleration in the direction of sunlight and requires more energy for insertion into a higher circular orbit. The following mode of operation prefers acceleration in the direction of sunlight. The attitude of the sail is directed as follows.
The relative change in the apogee of the sail increases with time but the perigee also decreases even if a small 10 second step is used in the calculation.
Again, more Δv is required to put the light sail into a circular orbit than for a ballistic transfer orbit. More time would be required to compensate for the loses when the Δv is in the proper direction orbit insertion.
If nature favors some modes of light sail operation over others the preferred mode would make the desired orbital changes in the least possible time. It may require a little R & D to determine the optimal solution. The rate of the gain in altitude at apogee is greatest for α=0 when the light sail moves in the direction of sunlight. If the drop in perigee isn't compensated for light sail won't climb out of the Earth's gravity well before it encounters atmospheric drag. So one will have to do the climb stepping from one circular orbit to a higher one.
Tuesday, August 1, 2017
Since the light sail's orbit appeared to show signs of a deteriorating perigee I tried playing with the attitude of the sail relative to the direction of sunlight to get relatively more angular acceleration. In the figure below the direction on sunlight is to the left. The light sail's acceleration is along its normal n which is at an angle α relative to the horizontal axis. The changes to the equations of motion are also shown.
The angle of the sail was set to α=π/2-θ when it was above the x-axis and moving away from the Sun and α=π/2 when it was below in order to restrict the acceleration some. The behavior was sensitive to the size of the step so Δt was set to 10 seconds. This gave better results for the behavior of Δr=r-r0.
It still drifts away from a ballistic object in the original circular orbit due to changes in the eccentricity and the period of the orbit.
Changing the step size resulted in a closer match of the light sail's Δv's with the transfer orbit Δv's for insertion into the higher circular orbit.
So it appears that a light sail can make changes to a transfer orbit. Unfortunate, the apogee is on the sunward half of the orbit and one can't use sunlight to accelerate towards the sun to go into a higher circular orbit. This is where an auxiliary propulsion system would be needed if one wanted to do orbit changes. A flyby mission would not require orbit insertion.
Supplemental (Aug 1): After the passage of half a year the sunlight will be in the opposite direction (to the right in the first figure) and the Δv will be directed properly for insertion into the higher circular orbit. It may be possible for a light sail to slowly work its way out of a gravity well.
Monday, July 31, 2017
One can compare the energy change in LightSail 2's orbit that with that required to go into a transfer orbit. After a number of revolutions however the perigee of the light sail starts to drop. This loss of energy has to be compensated for if one desires to go into a circular orbit at the light sail's apogee.
In the plot above the blue curve indicates the velocity change Δv required to go from a point of the light sail's orbit into a circular orbit. The solid red line is the total Δv required to go from the original circular orbit into a circular orbit at the apogee of the transfer orbit. The dashed red line indicates just the Δv required to go from the apogee of the transfer orbit into a circular orbit. Initially the orbit injection Δv's of the light sail match up with the Δv's for the transfer orbit. After about six revolutions more Δv is required to compensate for the drop in perigee. The implication appears to be that the orbit of the light sail needs to be periodically corrected to a circular orbit to keep the light sail from becoming parasitic. The major deficiency of the light sail is that the direction of its thrust is limited. It's lack of angular acceleration requires an auxiliary propulsion system for some orbit changes.
Supplemental (Aug 1): The deviations in the Δv's for the light sail when going to the higher circular orbit are affected by the step size. Here the step size was Δt=60 seconds. Compare next blog.
Sunday, July 30, 2017
One can compute LightSail 2's gain in energy over time and estimate the average rate at which it will gain energy.
This average rate appears to be linear and allows one to estimate how long it would take for the light sail to acquire enough energy to escape from the Earth's gravity well. The answer is 6.4 years.
The model used was overly simplified neglecting the Earth's shadow and didn't take into account the need to raise the height of perigee to avoid atmospheric drag. As the Earth moves about the Sun in its orbit the direction of sunlight will slowly change.