One record per aspect. The origin says what kind of thing each value is; the source says where it came from; the limit says what it cannot tell you.
Two-body orbit from published elements
TESS is placed by solving a Keplerian orbit around earth at the simulation time (a = 250,000 km, e = 0.55, period 13.7 d). Shown from 2018-04-18 onward.
Epoch2018-04-18T00:00:00Z
MethodTwo-body propagation of the stored elements by the shared orbit service; no perturbations.
LimitA two-body orbit ignores perturbations; positions drift from the true ephemeris away from the element epoch.
Bulk properties
TESS: mass 3.620 × 10^2 kg. These values are bundled with the object record and drive the rendered size.
Close-up hull model
The close-up shows a published 3D model scaled to 4 m deployed solar-array span. Distributed through NASA 3D Resources; original mission-agency credit applies.
MethodSpace Time normalises the source model to the published deployed dimension.
LimitSource-asset presentation pose; time-dependent flight attitude is not modeled.
Description and facts
The short description and the fact list are written by the Space Time authors for orientation. They are not quoted from a catalog field and carry no citation of their own.
SourceSpace Time editorial text
LimitBackground reading is linked under Further reading; it is not the source of the displayed numbers.
Space Time