mirror of
https://github.com/OpenSpace/OpenSpace.git
synced 2026-01-05 19:19:39 -06:00
153 lines
7.4 KiB
Plaintext
153 lines
7.4 KiB
Plaintext
*******************************************************************************
|
|
Revised: Mar 27, 2018 Tesla Roadster (spacecraft) -143205
|
|
(solution #10)
|
|
|
|
Tesla Roadster (AKA: Starman, 2018-017A)
|
|
|
|
NOTE:
|
|
|
|
Visibility:
|
|
20th magnitude until Feb 20,
|
|
22nd magnitude through mid-April
|
|
Brighter than 26th magnitude into mid-June
|
|
|
|
2018-Mar-01: Radial non-gravitational acceleration A1 estimated from data
|
|
(nominally solar radiation pressure)
|
|
2018-Mar-27: Two reporting sites (J04 & K93) extend data arc one month.
|
|
A1 estimate of s10 is reduced 1.2-sigma compared to s9.
|
|
|
|
LAUNCHED:
|
|
2018-Feb-06 20:45 UTC by Falcon Heavy (FH-1) from Kennedy Space Center, USA
|
|
(launchpad 39A)
|
|
|
|
BACKGROUND:
|
|
Dummy payload from the first launch of SpaceX Falcon Heavy launch vehicle.
|
|
Consists of a standard Tesla Roadster automobile and a spacesuit-wearing
|
|
mannequin nicknamed "Starman".
|
|
|
|
Also includes a Hot Wheels toy model Roadster on the car's dash with a
|
|
mini-Starman inside. A data storage device placed inside the car contains
|
|
a copy of Isaac Asimov's "Foundation" novels. A plaque on the attachment
|
|
fitting between the Falcon Heavy upper stage and the Tesla is etched with
|
|
the names of more than 6,000 SpaceX employees.
|
|
|
|
After orbiting the Earth for 5 hours, a third burn by the second stage was
|
|
completed at approximately 02:30 UTC Feb 7, placing the dummy payload in a
|
|
heliocentric orbit having a perihelion of 0.99 au and aphelion ~1.67 au.
|
|
|
|
The object stack consists of a Merlin 1D Vacuum second stage with Extended
|
|
Nozzle, Payload Attachment Fitting, and Tesla Roadster on mount.
|
|
|
|
Roadster mass: ~1250 kg (with batteries), ~800 kg (without ESS/batteries)
|
|
|
|
TRAJECTORY:
|
|
This trajectory is based on JPL solution #10, a fit to 364 ground-based
|
|
optical astrometric measurements spanning 2018 Feb 8.2 to March 19.1
|
|
|
|
Trajectory name Start (TDB) Stop (TDB)
|
|
-------------------------------- ----------------- -----------------
|
|
tesla_s10 2018-Feb-07 03:00 2090-Jan-01 00:00
|
|
|
|
Encounter predictions for s10 (w/radial 1/r^2 non-gravitational acceleration)
|
|
|
|
Date (TDB) Body CA Dist MinDist MaxDist Vrel TCA3Sg Nsigs P_i/p
|
|
----------------- ----- ------- ------- ------- ------ ------ ------ ------
|
|
2018 Feb 08.09690 Moon .000936 .000936 .000936 3.961 0.41 47509. 0.000
|
|
2020 Oct 07.26768 Mars .049530 .048923 .050242 8.150 27.40 6.63E5 0.000
|
|
2035 Apr 22.35934 Mars .015504 .004378 .027978 8.219 170.47 31247. 0.000
|
|
2047 Jan 11.89023 Earth .031919 .031716 .032123 4.493 249.70 78398. 0.000
|
|
2050 Mar 19.52949 Earth .119113 .113778 .124369 7.397 538.54 2.61E5 0.000
|
|
2052 Sep 05.15606 Mars .176363 .172469 .180319 5.738 2185.5 8.68E5 0.000
|
|
2067 Apr 15.90202 Mars .043270 .025712 .061471 7.192 1115.0 42565. 0.000
|
|
2084 Sep 17.92284 Mars .116962 .093449 .141170 9.753 787.45 6.55E5 0.000
|
|
2085 Jan 01.96490 Earth .083063 .049368 .112186 6.224 5208.9 1.00E5 0.000
|
|
2088 Mar 09.95754 Earth .049146 .033491 .063322 5.106 4505.2 1.17E5 0.000
|
|
|
|
Date = Nominal encounter time (Barycentric Dynamical Time)
|
|
CA_Dist = Highest probability close approach distance to body, au
|
|
MinDist = 3-sigma minimum encounter distance, au
|
|
MaxDist = 3-sigma maximum encounter distance, au
|
|
Vrel = Relative velocity at nominal encounter time, km/s
|
|
TCA3Sg = 3-sigma uncertainty in close encounter time, minutes
|
|
Nsigs = Number of sigmas to encounter body at nominal encounter time
|
|
P_i/p = Linearized probability of impact
|
|
|
|
NOTE:
|
|
How to obtain optional statistical uncertainty output & generate an SPK file:
|
|
|
|
Since this is a spacecraft and not part of the asteroid and comet database
|
|
which normally holds orbit covariance data, some functions like statistical
|
|
output and SPK file generation aren't automatically available for this object.
|
|
|
|
However, such optional extended output is possible with some extra steps.
|
|
|
|
To propagate statistical uncertainties for this object, the full statistical
|
|
orbit solution (given below) can be manually input back into Horizons as a
|
|
"user-defined object" using the telnet or e-mail interfaces (not possible
|
|
with the browser interface).
|
|
|
|
To do this and activate statistical or SPK file output ...
|
|
|
|
Using the telnet interface (command-line "telnet ssd.jpl.nasa.gov 6775"),
|
|
enter ";" to drop into user-input mode then cut-and-paste each line shown
|
|
below, one at a time. The lines of numbers after SRC must be in the order
|
|
shown.
|
|
|
|
For SPK file generation, only the first four lines need be input: the
|
|
EPOCH, orbital element lines starting with "EC" and "OM", and the
|
|
non-gravitational acceleration model (line starting with "A1").
|
|
|
|
SRC lines are needed only for (optional) statistical output and the
|
|
H & G values only for (optional) visual magnitude output.
|
|
|
|
EPOCH= 2458164.5
|
|
EC= .2585469914787243 QR= .9860596231806226 TP= 2458153.620483722645
|
|
OM= 317.3549094214575 W = 177.3203028023227 IN= 1.088451292866039
|
|
EST=A1 A1= 2.960683526738534E-9 R0= 1. ALN= 1. NM= 2. NK= 0.
|
|
SRC= -2.057839421666802E-7 7.966781900129693E-9 -1.720426606925749E-9
|
|
-4.722542923190676E-7 2.197679131968537E-9 -1.230413802372471E-6
|
|
-2.500290306870021E-7 -3.361070889248183E-9 -1.765963020682463E-5
|
|
-3.047907547965759E-7 -4.640202045440381E-7 -4.271481116360573E-9
|
|
2.657789409005983E-5 1.726818074599357E-6 -1.359673746135991E-6
|
|
-2.478836748687631E-5 -2.309863204867099E-8 -.0002351644867403515
|
|
-1.875169281895894E-6 -2.063647245529267E-6 -1.670539551586607E-6
|
|
-4.019207817588603E-6 -3.128134469402375E-9 -3.034540373576942E-5
|
|
1.733661692209129E-7 -7.052327854535979E-7 -2.650181216776434E-7
|
|
-1.310976135791957E-10
|
|
H= 25.289 G= 0.15
|
|
|
|
When done, press a blank return to exit input mode.
|
|
|
|
Enter "J" at the prompt to indicate heliocentric J2000 ecliptic data has
|
|
been supplied. Then at the next prompt, input an arbitrary name
|
|
(i.e., Roadster).
|
|
|
|
Horizons will then proceed as usual, but with statistical output and SPK
|
|
file generation now available as options.
|
|
|
|
A basic and identical tracking ephemeris can be produced without doing any
|
|
of this, but statistical uncertainty quantities requested will be marked
|
|
"n.a.", meaning not available, and SPK generation won't be an option.
|
|
|
|
NOTE: long-term predictions
|
|
Over time, trajectory prediction errors could increase more rapidly than
|
|
the formal statistics indicate due to unmodeled thermal re-radiation or
|
|
outgassing accelerations that are not currently characterized but may exist.
|
|
*******************************************************************************
|
|
|
|
|
|
# E. Lon DXY DZ Observatory Name
|
|
--- -------- ------- ------- ----------------
|
|
L20 18.3207 +308014 +293859 AG_Sarajevo Observatory, Sarajevo
|
|
L21 27.4213 +307050 +294814 Ostrov Observatory, Constanta
|
|
L22 27.6695 +295446 +306365 Barlad Observatory
|
|
L23 27.8319 +299346 +302574 Schela
|
|
L24 27.9289 +383214 -186499 Gauteng
|
|
L25 14.4374 +255033 +340528 Smolecin
|
|
L26 11.8102 +316937 +284229 Sanderphil Urban Obs., Civitavecchia
|
|
L27 5.6470 +307222 +294693 29PREMOTE Obs., Dauban {Soulier]
|
|
L28 15.4634 +323190 +277274 ISON-Castelgrande Observatory
|
|
L29 18.0169 +391400 -168725 Drebach-South Observatory, Windhoek
|
|
Multiple matching stations found.
|
|
|