KNOWN Corporation

KnownX MPTMission report

Written {{written_utc}} UTC with KnownX MPT {{version}}

Produced on a trial licence.

This mission uses values that differ from the real-world defaults. {{realism_note}}

Mission time

Start date	{{start_utc}} UTCNone set. The mission runs on elapsed time only.
Elapsed when written	{{elapsed}}
Mission clock when written	{{now_utc}} UTC

Models in use

Point-mass gravity	On
Integrator	{{integrator}}
Earth gravity field	{{gravity_field}}
Earth zonal harmonics (J2, J3, J4)	{{zonal}}
Further forces	{{further_forces}}
Atmospheric drag	{{drag}}
Sun and Moon gravity	{{sun_moon}}
Validation status of this run	{{validation}}

Spacecraft

Name	Around	Altitude, km	Speed, m/s	Mass, kg
{{name}}	{{parent}}	{{altitude}}	{{speed}}	{{mass}}

Name

Around

Altitude, km

Speed, m/s

Mass, kg

Orbit of	Perigee, km	Apogee, km	Period, min	Eccentricity	Inclination, deg	RAAN, deg	Arg. perigee, deg
{{name}}	{{perigee}}	{{apogee}}	{{period}}	{{eccentricity}}	{{inclination}}	{{raan}}	{{arg_perigee}}
{{name}}	Not on a closed orbit at this moment.

Orbit of

Perigee, km

Apogee, km

Period, min

Eccentricity

Inclination, deg

RAAN, deg

Arg. perigee, deg

Not on a closed orbit at this moment.

Altitudes are above the parent body's reference radius. Orbit values are the orbit each spacecraft is on at the moment the report was written, as if only the parent's point-mass gravity acted; J2, drag and thrust make them drift. Angles are against the parent's equator and the inertial X axis.

No spacecraft in this mission.

Started from a TLE

Spacecraft Satellite Element set

{{craft}} {{satellite}} {{line1}} {{line2}}

Spacecraft	Satellite	Element set
{{craft}}	{{satellite}}	`{{line1}} {{line2}}`

Altitude over the recorded run, {{chart_body}}

{{{altitude_chart}}}

From the telemetry recorded in this run. Altitude is above the parent body's reference radius.

Propellant, {{controlled}}

Propellant capacity	{{propellant_capacity}} kg
Propellant remaining	{{propellant_remaining}} kg
Propellant used, from full	{{propellant_used}} kg
Speed change so far (delta-v)	{{delta_v}} m/s
Dry mass	{{dry_mass}} kg
Specific impulse	{{isp}} s

Delta-v is from the rocket equation, using the propellant used and the specific impulse above.

Mission sequence

Time	Step	What it does	Status
{{time}}	{{label}}	{{detail}}	{{status}}

Time

Step

What it does

Status

No scripted steps. The spacecraft was flown by hand or left to coast.

Closest approach

Between	{{conj_between}}
Miss distance	{{conj_miss}} km
Time of closest approach	{{conj_tca}}
Relative speed then	{{conj_speed}} m/s
Searched ahead	{{conj_horizon}} hours
Planned burns included	{{conj_burns}}

Miss distance only. A probability of collision needs position uncertainty for both objects, which this model does not carry.

How far to trust this

Point-mass gravity and Earth's J2 are validated against reference solutions. J3 and J4, drag, propulsion, Sun and Moon gravity and the closest-approach search are implemented and tested but not yet backed by a validation gate. A mission started from a TLE is no more accurate than the TLE, which is good to about a kilometre at its epoch and worse with every day after it. This report is not for a safety-critical decision.

{{mission}}