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    Could Comet C/2013 A1 impact Mars in 2014?

    I think "Sun Center". RPOS/RVEL means position/velocity relative to reference - Sun but not SSB, Earth but not Earth-Moon barycenter.
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    Asteroid 2012 DA14 Flight Path

    "I'll be back" ;)
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    Asteroid 2012 DA14 Flight Path

    No, HORIZONS uses right-handed coordinate system, Orbiter uses left-handed one. Need to swap Y and Z coordinates for correct conversion. BEGIN_ENVIRONMENT System Sol Date MJD 56329 END_ENVIRONMENT BEGIN_CAMERA TARGET Asteroid 2012 DA14 MODE Extern POS 43.93 -109.04 -10.91...
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    The rocket equation vs. braking distance

    It's simplification ( x = \frac{1}{2}\Delta V\cdot\ T_{burn} ) . To find the exact solution we need to solve few differential equations: (1) \frac{d \vec x(t)}{dt} = \vec v(t) Reactive motion: (2) m(t)\frac{d \vec v(t)}{dt}-\vec u_e\frac{dm(t)}{dt}=0 \Rightarrow (3) \vec v(t)=- \vec u_e...
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    Scenario Deltaglider on Curiosity Trajectory

    16:25 UTC? But real maneuver started at T+0:31 (15:33UTC) and finished at T+0:39 (15:41 UTC). Excellent time fit! :) ---------- Post added at 10:29 PM ---------- Previous post was at 08:33 PM ---------- Yes. I get dV >3900 m/s with plane change too BEGIN_DESC Contains the latest simulation...
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    Scenario Deltaglider on Curiosity Trajectory

    Inclination of parking orbit - 28.9, eject hyperbola - 34.8 http://www.youtube.com/watch?feature=player_detailpage&v=GizNSAyhypg#t=154s http://www.youtube.com/watch?feature=player_detailpage&v=GizNSAyhypg#t=816s
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    Scenario Deltaglider on Curiosity Trajectory

    You can get correct eject trajectory for MSL from HORIZONS system http://ssd.jpl.nasa.gov/?horizons http://orbiter-forum.com/showthread.php?p=317913&postcount=190
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    Updates Mars Science Laboratory (Curiosity)

    Just for fun, Orbiter MJD/RPOS/RVEL from HORIZONS state vectors for MSL: BEGIN_ENVIRONMENT System Sol Date MJD 55891.661261574 END_ENVIRONMENT BEGIN_SHIPS MSL:DeltaGlider STATUS Orbiting Earth RPOS 5.578081991138332E+06 -6.906871560268437E+06 2.695492584292812E+06 RVEL...
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    Updates Mars Science Laboratory (Curiosity)

    Landing in 253 days, 7 hours, 53 minutes. http://mars.jpl.nasa.gov/msl/ Countdown to Landing: 252 days, 1 hours, 53 minutes Something wrong.
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    Flight Question Need help with TransX

    BTW, IMFD does very simple work while we searching launch window for optimal transfer. We choose eject time and intercept time - so IMFD have position and velocity of initial point (planet), position and velocity of target point. All math - it's to find elliptical orbit through this 2 points...
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    Rotation slowdown

    Yes, but killing 200 deg/s rotation for 2 days by gravity gradient torque at Moon orbit - it's little unbelievable.
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    Rotation slowdown

    Can someone explain why rotation of DG in this scenario slowdowns in Orbiter and stops after few days (at x1000)? Orbiter v111105, all realism and perturbation check-boxes switched on. Is it real physical effect or bug of the Orbiter? BEGIN_DESC Contains the latest simulation state. END_DESC...
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    General Question Lunar space station orbit

    "Nonspherical gravity sources" does not simulate mascons. And the option does not affect on orbit around Moon (no JCoeff in Moon.cfg).
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    General Question Returning to Earth using TransX

    Can you post the scenario?
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    Challenge moon to mars

    dgatsoulis No. It's not a fault at all. The problem is not in parameters of Orbiter. With all (realistic or not) parameters TransX makes (in my hands) huge error in calculation of single-burn trajectory from Moon to Mars. As I said, "it's difficult for me to calculate precise and optimal burn...
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    Challenge moon to mars

    For example, I find in TransX this solution: MJD 52007.654, prograde velocity 1614 m/s, Cl. App. (rough) ~1.5M Scenario: BEGIN_DESC Contains the latest simulation state. END_DESC BEGIN_ENVIRONMENT System Sol Date MJD 52007.6519094714 END_ENVIRONMENT BEGIN_FOCUS Ship 1 END_FOCUS...
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    Challenge moon to mars

    I tried April 6-8 too. The idea was to look solution near this configurations (for saving maximum energy): May configuration just looked better ;). But I faulted with DV every time.
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    Challenge moon to mars

    I think, there is good simple single-burn solution at May, 5-7. Something like this: But it's difficult for me to calculate precise and optimal burn using TransX or IMFD :(
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    Can't access JPL Horizons state vectors for Deep Impact impactor

    Latest version for Orbiter2010 here: http://orbiter-forum.com/showthread.php?t=1387 BTW. Mayby, for Deep Impact its really better to take di_finalenc_nav_v3_to06048.bsp as Horizons do, but not di_finalenc_nav_v3.bsp as I did. ftp://naif.jpl.nasa.gov/pub/naif/DEEPIMPACT/kernels/spk/aareadme.txt...
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    Can't access JPL Horizons state vectors for Deep Impact impactor

    SPICE library http://naif.pds.nasa.gov/ , kernels from ftp://naif.jpl.nasa.gov/pub/naif/DEEPIMPACT/kernels/spk and a very simple program: #include <stdio.h> #include <string.h> #include "SpiceUsr.h" int main(int argc, char* argv[]) { const SpiceInt body_id=-70; const SpiceInt...
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