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| Failed brain fart. | Testing the first server sky thinsat arrays may be challenging - they don't belong in a common orbit, they won't last long below 1000 km altitude due to ram drag. It would be nice to deploy the first tests at M288, but that will require a custom launch. |
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| Testing the first server sky thinsat arrays may be challenging - they don't belong in a common orbit, they won't last long below 2000 km altitude due to ram drag. It would be nice to deploy the first tests at M288, but that will require a custom launch. | Instead, let's dispense as a co-payload from a GTO transfer orbit. We will test in a highly inclined orbit, in three steps: .1) ''Deploy:'' use a cold gas thruster to slightly lower apogee and significantly raise perigee. This will be the orbit for our experiment. The inclination of this orbit will be a function of launch latitude, and the ascending node will be on the equatorial plane. .2) ''Dispense'' approximately 100 thinsats near apogee. The subsequent fate of the dispenser is undefined; perhaps we can use it later for collision experiments. .3) ''Experiment:'' the thinsats maneuver into arrays and begin the test. The perigee drag is high enough that the apogee will decay significantly with each orbit. Thinsats will orient for minimum drag, but because they are curved the drag will be significant. .4) ''Deorbit:'' if damage has not set the thinsats tumbling, lock the optical thrusters to produce a rapid yaw tumble. This will greatly increase perigee drag. .5) ''Reentry:" after apogee decays to perigee, the orbit will rapidly spiral in. When tumbling thinsats reach ISS altitude, they will reenter one or two orbits later. |
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| But there's a trick. | The starting GTO transfer orbit will have a perigee radius of $$ r_{P-GTO} $$ (perhaps 7000 km) and an apogee radius of $$ r_{A-GTO} $$ (perhaps 42,100 km ) one or two orbits after release from the GTO upper stage. Using these numbers and the gravitational coefficient $$ \mu $$, we can compute the perigee and apogee velocities $$ v_{P-GTO} $$ and $$ p_{A-GTO} $$, the semimajor axis $$ a $$, the eccentricity $$ \eps $$, and the characteristic velocity $ v_0 $. |
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| Thinsats can be tested in a highly elliptical orbit above LEO and below GEO. Deploying them as hitchhikers from a GTO bound upper stage would work - except that the perigee of the GTO orbit would be too low. | Computing the experimental orbits will require numerical integration, with estimated perturbations telling us how difficult it will be to keep arrays together. We can approximate all thinsats in an array in one trajectory in two regimes: (1) highly elliptical, dominated by perigee drag on a thinsat oriented for minimum drag, and (2) a spiral, with decay increasing rapidly as thermospheric density increases exponentially and the thinsats tumble. It may be possible to arrange and observe a collision between one or two thinsats and the heavier and slow-orbit-decay dispenser, which will still be in a high velocity, high eccentricity orbit. |
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| What if we used a tether? Ivan Bekey proposed sending shuttle back from the space station by lowering it on a tether, first. The combined two-mass-and-a-string system would orbit around the center of gravity, with shuttle pulled down and ISS pulled up by tides. ISS moves up, going faster than natural orbital velocity, and shuttle is slower. When the tether is released (twang!) the ISS orbit rises, and shuttle reenters with somewhat less velocity than it would otherwise. Spool the tether back into ISS, and do the same thing for the next visit. This could significantly reduce the amount of propellant needed to raise orbit. |
Gas density will low during quiet sun periods around 2016, and maximum about 5 years later in 2021. If possible, we should schedule the test so that all probably-disabled thinsats will reenter during that solar maximum. |
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| Well, it might not ''really'' work because that would jerk ISS around, and subject it to "milligravity" that it isn't designed for. And the released tether will get frisky, might break something or even puncture a hole. | == Computing the Experimental orbit == |
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| But a tether between the GTO stage and a server sky experiment package? We want to reenter the GTO stage, and raise experimental perigee. Doesn't have to be much. | === The initial orbit === |
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| Let's assume the experiment weighs 50 kg and is at the top of the tether, and the empty stage weighs 450 kg and is at the bottom. They are connected by a tether length L, and turning at rate $ \omega $, highest at perigee, lowest at apogee where they will separate. The tidal force in orbit is $ 3 {\omega}^2 \Delta r $, and balances around the center of mass. The experiment is going 0.9 \times L \times \omega $ faster than the center of the GTO orbit. | Starting with $$ r_{A-GTO} $$ and $$ r_{P-GTO} $$, we can compute the semimajor axis $$ a $$ and other parameters: |
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| || apogee || perigee || || 42164 || 6700 || km radius GTO || |
$ \large a ~ = ~ 0.5 * ( r_{A-GTO} + r_{P-GTO} ) ~ ~ ~ ~ ~ ~ ~ $ semimajor axis $ \large \eps ~ = ~ ( r_{A-GTO} - r_{P-GTO} ) / ( r_{A-GTO} + r_{P-GTO} ~ ~ ~ ~ ~ $ eccentricity $ \large T ~ = ~ 2\pi \sqrt{ a^3/\mu } ~ ~ ~ ~ ~ $ orbital period (sidereal) $ \large v_0 ~ = ~ \sqrt{ \mu / ( a (1 - {\eps}^2) ) } ~ ~ ~ ~ $ characteristic velocity $ \large v_a ~ = ~ v_0 / ( 1 + {\eps} ) ~ ~ ~ ~ ~ $ apogee velocity $ \large v_p ~ = ~ v_0 / ( 1 - {\eps} ) ~ ~ ~ ~ ~ $ perigee velocity For the first approximation, ignore $$ J_2 $$ and other complexities in the gravitational field, but include them in the numerical model. They will cause the elliptical orbit to precess towards the east. === Atmospheric Drag === The atmosphere becomes exponentially thinner with altitude until it is as low as the density of interplanetary space. The density can be approximated by $ \large \rho ( r ) ~ = ~ {\rho}_0 \exp{ - ( r - r_0 ) / L } $ where $$ {\rho}_0 $$ is the density at altitude $$ r_0 $$ , a function of temperature, solar activity, and longitude, which vary with time. $$ L $$ is the lapse rate ( a distance ), which is the distance over which the atmosphere density decays by a factor of e = 2.718 . |
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| Oops. DOESNT WORK, because the apogee omega is so small. We have nothing to spin the pair with, either | MORE LATER \\ If that level drag occurs within 50 kilometers above perigee ($ r_1 $ =7050 km), then the orbital angle is computed from: $ \large r_1 = a \Large { {1-e^2} \over { 1 + e \cos(\theta) } } $ $ \large \cos(\theta) = { { \Large { { a ~ (1-e^2) } \over { r_1 } } - 1 } \over e } $ $ \large \cos(\theta) = { { \Large { { 24582 ~ (1-0.7152^2) } \over 7050 } - 1 } \over 0.7152 } = $ 0.183 radians The seconds per radian is $ r_p / v_p $ = 7000 / 9.88 = 708.3 s / radian, so the time spent in the high drag region is 2 * 0.183 * 708.3 = 260 seconds, and the velocity lost for the first pass is about 40 m/s, 9880 to 9840 m/s. For the second pass, the velocity and drag will be smaller, but apogee will drop significantly and more time will be spent in the drag zone. After about 50 orbits, the orbit decays sufficiently that a thinsat will start a fast spiral to burnup, lasting less than a day. If the thinsat loses control, it will decay in perhaps 10 orbits. The experiment will stay in orbit for perhaps 2 weeks. This would be a good first test for the first maneuverable thinsat, if we can hitch a 5 gram ride on a GTO transfer vehicle. However, this is far too much drag and buffeting to keep an array assembled by light pressure intact. === 24 GHz instead of 70 GHz === The 1.25 cm amateur radio band extends from 24.0 GHz to 24.05 GHz, and is barely used. This is near the [[PathAttenuation | 23 GHz water peak]], perhaps .18 dB/km at 7.5g/m^3^ water saturation. At 10 degrees elevation and 7 km lapse rate, that is 7.3 dB attenuation; a factor of 5.3, which might be lousy for ordinary high bandwidth satellite communication, but perfectly adequate for low bandwidth telemetry. === The $20 Toy Rocket Motor Trick === Let's raise perigee just enough to make 92 each 5 gram thinsats (V = 3 array) last a couple of months - lets assume that is 922 km altitude perigee (7300 km radius). Assume a carrier that brings the total mass up to a kilogram. Start with a GTO transfer orbit with a perigee of 622 km altitude (7000 km radius), with an apogee velocity of 1640.7 m/s. The test orbit has an apogee velocity of 1692.4 m/s, for a delta V of 29.5 meters per second for one kilogram, the impulse of 30 Newton-seconds. That is similar to one Estes E9-4 model rocket engine (30 N-s, 57 grams, 2.8 seconds). Perigee velocity is 5.53 km/s. Let's assume that we are edge on as before. The average air density at 922 km altitude is about 4e-15 kg/m^3^ and that drag occurs within 100 km of perigee; a 30 degree arc, 0.52 radians, 390 seconds of drag time. The normal air density is 4e-15 kg/m^3^. The edge-on drag through perigee is $ A \rho V^3 $, or $ 0.002 * 4e-15 * 9650^3^ or 2.7e-5 N, decellerating the 5 gram thinsat by 5.4e-3 m/s^2^, or 2 m/s per orbit. Circular orbit velocity at that altitude is 7390 m/s, 2260 m/s less than our starting orbit perige, so we would get about 1000 experimental orbits before the altitude starts decaying fast. We will use three more toy rocket motors on the 500 gram carrier at apogee, after thinsat release, to bring the perigee down to 0 km altitude, for reentry. That requires 90 m/s delta V, 45 N-s impulse. Three is overkill, but means we can deorbit the whole predeployment assembly if something goes wrong. |
Hitchhiker Server Sky Test
Testing the first server sky thinsat arrays may be challenging - they don't belong in a common orbit, they won't last long below 1000 km altitude due to ram drag. It would be nice to deploy the first tests at M288, but that will require a custom launch.
Instead, let's dispense as a co-payload from a GTO transfer orbit. We will test in a highly inclined orbit, in three steps:
1) Deploy: use a cold gas thruster to slightly lower apogee and significantly raise perigee. This will be the orbit for our experiment. The inclination of this orbit will be a function of launch latitude, and the ascending node will be on the equatorial plane.
2) Dispense approximately 100 thinsats near apogee. The subsequent fate of the dispenser is undefined; perhaps we can use it later for collision experiments.
3) Experiment: the thinsats maneuver into arrays and begin the test. The perigee drag is high enough that the apogee will decay significantly with each orbit. Thinsats will orient for minimum drag, but because they are curved the drag will be significant.
4) Deorbit: if damage has not set the thinsats tumbling, lock the optical thrusters to produce a rapid yaw tumble. This will greatly increase perigee drag.
5) Reentry:" after apogee decays to perigee, the orbit will rapidly spiral in. When tumbling thinsats reach ISS altitude, they will reenter one or two orbits later.
The starting GTO transfer orbit will have a perigee radius of
Computing the experimental orbits will require numerical integration, with estimated perturbations telling us how difficult it will be to keep arrays together. We can approximate all thinsats in an array in one trajectory in two regimes: (1) highly elliptical, dominated by perigee drag on a thinsat oriented for minimum drag, and (2) a spiral, with decay increasing rapidly as thermospheric density increases exponentially and the thinsats tumble. It may be possible to arrange and observe a collision between one or two thinsats and the heavier and slow-orbit-decay dispenser, which will still be in a high velocity, high eccentricity orbit.
Gas density will low during quiet sun periods around 2016, and maximum about 5 years later in 2021. If possible, we should schedule the test so that all probably-disabled thinsats will reenter during that solar maximum.
Computing the Experimental orbit
The initial orbit
Starting with
\large a ~ = ~ 0.5 * ( r_{A-GTO} + r_{P-GTO} ) ~ ~ ~ ~ ~ ~ ~ semimajor axis
\large \eps ~ = ~ ( r_{A-GTO} - r_{P-GTO} ) / ( r_{A-GTO} + r_{P-GTO} ~ ~ ~ ~ ~ eccentricity
\large T ~ = ~ 2\pi \sqrt{ a^3/\mu } ~ ~ ~ ~ ~ orbital period (sidereal)
\large v_0 ~ = ~ \sqrt{ \mu / ( a (1 - {\eps}^2) ) } ~ ~ ~ ~ characteristic velocity
\large v_a ~ = ~ v_0 / ( 1 + {\eps} ) ~ ~ ~ ~ ~ apogee velocity
\large v_p ~ = ~ v_0 / ( 1 - {\eps} ) ~ ~ ~ ~ ~ perigee velocity
For the first approximation, ignore
Atmospheric Drag
The atmosphere becomes exponentially thinner with altitude until it is as low as the density of interplanetary space. The density can be approximated by
\large \rho ( r ) ~ = ~ {\rho}_0 \exp{ - ( r - r_0 ) / L } where
MORE LATER
\\ If that level drag occurs within 50 kilometers above perigee ( r_1 =7050 km), then the orbital angle is computed from:
\large r_1 = a \Large { {1-e^2} \over { 1 + e \cos(\theta) } }
\large \cos(\theta) = { { \Large { { a ~ (1-e^2) } \over { r_1 } } - 1 } \over e }
\large \cos(\theta) = { { \Large { { 24582 ~ (1-0.7152^2) } \over 7050 } - 1 } \over 0.7152 } = 0.183 radians
The seconds per radian is r_p / v_p = 7000 / 9.88 = 708.3 s / radian, so the time spent in the high drag region is 2 * 0.183 * 708.3 = 260 seconds, and the velocity lost for the first pass is about 40 m/s, 9880 to 9840 m/s. For the second pass, the velocity and drag will be smaller, but apogee will drop significantly and more time will be spent in the drag zone. After about 50 orbits, the orbit decays sufficiently that a thinsat will start a fast spiral to burnup, lasting less than a day. If the thinsat loses control, it will decay in perhaps 10 orbits. The experiment will stay in orbit for perhaps 2 weeks.
This would be a good first test for the first maneuverable thinsat, if we can hitch a 5 gram ride on a GTO transfer vehicle. However, this is far too much drag and buffeting to keep an array assembled by light pressure intact.
24 GHz instead of 70 GHz
The 1.25 cm amateur radio band extends from 24.0 GHz to 24.05 GHz, and is barely used. This is near the 23 GHz water peak, perhaps .18 dB/km at 7.5g/m3 water saturation. At 10 degrees elevation and 7 km lapse rate, that is 7.3 dB attenuation; a factor of 5.3, which might be lousy for ordinary high bandwidth satellite communication, but perfectly adequate for low bandwidth telemetry.
The $20 Toy Rocket Motor Trick
Let's raise perigee just enough to make 92 each 5 gram thinsats (V = 3 array) last a couple of months - lets assume that is 922 km altitude perigee (7300 km radius). Assume a carrier that brings the total mass up to a kilogram. Start with a GTO transfer orbit with a perigee of 622 km altitude (7000 km radius), with an apogee velocity of 1640.7 m/s. The test orbit has an apogee velocity of 1692.4 m/s, for a delta V of 29.5 meters per second for one kilogram, the impulse of 30 Newton-seconds.
That is similar to one Estes E9-4 model rocket engine (30 N-s, 57 grams, 2.8 seconds).
Perigee velocity is 5.53 km/s. Let's assume that we are edge on as before. The average air density at 922 km altitude is about 4e-15 kg/m3 and that drag occurs within 100 km of perigee; a 30 degree arc, 0.52 radians, 390 seconds of drag time.
The normal air density is 4e-15 kg/m3. The edge-on drag through perigee is A \rho V^3 , or $ 0.002 * 4e-15 * 96503 or 2.7e-5 N, decellerating the 5 gram thinsat by 5.4e-3 m/s2, or 2 m/s per orbit.
Circular orbit velocity at that altitude is 7390 m/s, 2260 m/s less than our starting orbit perige, so we would get about 1000 experimental orbits before the altitude starts decaying fast.
We will use three more toy rocket motors on the 500 gram carrier at apogee, after thinsat release, to bring the perigee down to 0 km altitude, for reentry. That requires 90 m/s delta V, 45 N-s impulse. Three is overkill, but means we can deorbit the whole predeployment assembly if something goes wrong.