GRACE-FO2
here : viewtopic.php?p=138785#p138785
![Hi! :hi:](./images/smilies/smile_hand.gif)
There is still need to work with this model... smoothing some parts... but this work for 2 or 3 hours... I will start that tomorrow in evening after my work...
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THE ORIGINAL MAKER's TIMELINE of TRAJECTORY:
Eris Explorer
2015 - Launched aboard a Delta IV-Heavy
2018 - Flyby of Jupiter (40,000 km)
2021 - Flyby of Saturn (377,000 km)
2029 - Flyby of Neptune (30,000 km)
2057 - Flyby of Eris (3,000 km)
Now I don't need to take 3 hours to reach Eris!
DaveBowman2001 wrote:Hmm...I have a question regarding the Eris Explorer: since it's an entirely fictional spacecraft, how would its trajectory will be projected?? Is it going to follow the trajectory its original maker has plotted in Orbiter??Code: Select all
THE ORIGINAL MAKER's TIMELINE of TRAJECTORY:
Eris Explorer
2015 - Launched aboard a Delta IV-Heavy
2018 - Flyby of Jupiter (40,000 km)
2021 - Flyby of Saturn (377,000 km)
2029 - Flyby of Neptune (30,000 km)
2057 - Flyby of Eris (3,000 km)
DaveBowman2001 wrote:FUN FACT:
There's an Orbiter video on YouTube depicting the spacecraft's flight to Eris (made by Rseferino Orbiter Filmmaker)
gironde wrote:Hello,
I found this satellite of NASA: ACE or Advanced Composition Explorer. It was launched on 25-08-1997 by NASA to study the Sun. ...
This is exactly what I explained last month in Lissajou's orbits at point L1.
the position file xyz provides the satellite positions during the defined period. In Celestia the assembly of all these points gives a curve around the Earth. If you accelerate the time with the panel7 (LUT5) you will see that the set starts to turn and that ACE follows this curve well but without ever moving away from L1 and without ever joining L2 even if the drawn curve passes by L2 which was there at another time. L1, L2, Ace, Moon, Earth continue to rotate relative to each other.
I know it's not the orbit but the curve of its positions. I tried to triturate the code to represent the orbit of ACE around the point L1 but without reaching it because the positions are given from the Earth and not from L1.
Maybe Toutatis will be able to improve the orbit code or the xyz file to change the point of origin. Knowing the position of the Earth, the position of L1, the position of ACE with respect to the Earth (the file xyz) can not we determine the position of ACE with respect to L1?
I found on https://en.wikibooks.org/wiki/Celestia/Trajectories#SpiceOrbit, a method using a Lua module to build a Lissajou orbit but without understanding much, advice to amateurs.
Technical characteristics [edit | change the code]
The NOAA POES satellites have a launch mass of 2,232 kg which includes 756 kg of propellant. The satellite includes a Star 37XFP apogee engine to circularize the orbit after separation from its launcher with a 42 kN solid propellant engine running for 51 seconds. Once in its final orbit the mass of the satellite is only 1,479 kg. The NOAA POES satellites are largely modified compared to the previous generation. To meet the energy needs of the instruments, solar panels provide 45% additional energy. All the equipment has been resized to cope with the increased capacity of this generation. The structure is reinforced to support the weight of the AMSU instrument. The three-axis stabilized platform uses a combination of Sun and Earth sensors to maintain orientation with an accuracy of 0.2 °. Orientation changes are made using reaction wheels and cold gas thrusters. The parallelepiped-shaped satellite body is 4.18 m long with a diameter of 1.88 m (overall length 7.4 m). A single wing 6,14 m long and 2,73 m wide. door solar panels that provide at least 833 Watts. The data collected is stored on 5 tape recorders with a unit capacity of 0.9 gigabits. From NOAA-17 part of the tape recorders is replaced by flash memory mass memories with a capacity of 2.7 gigabits1.