ORBITAL VISUALIZER J2000 ECI WGS84

▼ ⏱️ Mission Clock & Simulation

Current Sim Time (UTC)

2025/01/01 00:00:00

Epoch (yyyy/mm/dd hh:mm:ss UTC)

☀ Jun 21 Decl: +23.4° RA: 90°

Playback

Auto-loop at end of timeframe

Simulation Timeframe

Duration days

Sun Position / Season

Day of Year

Sun Dec: +23.4°

Animate Sun position (1 day/sec)

Options

Auto-rotate camera Earth rotation (GMST) 3D Satellite Models

▼ 🛰️ Orbital Elements PROGRADE

Presets

Semi-Major Axis (a) km

Eccentricity (e)

Inclination (i) °

RAAN (Ω) °

Arg. of Periapsis (ω) °

True Anomaly (ν) °

J2 Perturbations (RAAN/ω drift)

Derived Values

Perigee:622 km

Apogee:622 km

Period:98.3 min

Altitude:622 km

Ω̇:0 °/day

ω̇:0 °/day

Sun:☀ Sunlit

▼ 🧭 AOCS / Attitude Control

Mode: Nadir-Lock

Presets

Custom Two-Axis Pointing

Primary axis fully aligns to target. Secondary constrains the clocking (rotation about primary).

① Aligned Axis (Primary)

Body Axis

Points To

② Constrained Axis (Clocking)

Body Axis

Towards

+X Ram / Forward

+Y Port / Cross-track

+Z Zenith / Out

Show Body Axes on Satellite

▼ 👁️ Sensor Suite1

Half-Angle FOV °

Cone Opacity %

Show Sub-Nadir Points on Globe Show 3D Coverage Heatmap

Swath:0 km

Footprint:0 km²

▼ 📡 Ground Stations0

Min Elevation Mask °

▼ 🎯 Collection Targets0

0 targets 0 collected

Next Pass

Avg Revisit

▼ 📡 LOS / Visibility Analysis

Show visible links Show blocked (below horizon) Show access elevation rings

Min Elevation Mask °

Contact Prediction

Timeframe: 5 days — set in Mission Clock panel

Show day/night background

Live Contact Status

▼ ⏱️ Operations Pattern

Timeline Window min

T-0 +90 min

☀ Sun

Sunlit

Eclipse

Contact

Sunlit Time

--%

Eclipse Time

--%

Total Contact

-- min

Next Contact

▼ 📶 Link Budget (Omni)

Transmitter (Satellite)

Frequency MHz

Tx Power W

Sat Antenna Gain dBi

Line Loss dB

Path

Slant Range-- km

Free Space Loss-- dB

Atmospheric Loss-- dB

Pointing Loss0.5 dB

Receiver (Ground)

GS Antenna Diameter m

System Noise Temp K

Rx Antenna Gain-- dBi

G/T-- dB/K

Data Link

Data Rate Mbps

Required Eb/N0 dB

EIRP -- dBW

C/N0 -- dB-Hz

Eb/N0 -- dB

Link Margin -- dB

▼ ✨ Walker Constellation

i:t/p/f = 30°:24/6/1

Total Satellites (t)

Orbital Planes (p)

Phasing Factor (f)

Sats/Plane

60°

RAAN Spacing

15°

Phase Offset

▼ 🔄 Revisit Analysis

Max Scale (minutes)

0 min 60 min 120+ min

Avg:-- min

Max:-- min

▼ 🚀 Orbital Maneuvers

Spacecraft Properties

Dry Mass kg

Propellant Mass kg

Specific Impulse (Isp) s

Total Mass120 kg

Max ΔV-- m/s

In-Plane Maneuvers

Altitude Change (Hohmann)

Target Altitude km

ΔV₁ (raise/lower)-- m/s

ΔV₂ (circularize)-- m/s

Total ΔV-- m/s

Transfer Time-- min

Propellant Required-- kg

Out-of-Plane Maneuvers

Plane Change

Target Inclination °

Target RAAN °

Inclination Change-- °

RAAN Change-- °

Total Plane Change-- °

ΔV Required-- m/s

Propellant Required-- kg

⚠ Plane changes are fuel-expensive. Best performed at nodes.

Combined Maneuver

In-Plane ΔV-- m/s

Out-of-Plane ΔV-- m/s

Total ΔV-- m/s

Total Propellant-- kg

Remaining Propellant-- kg

ΔV Budget

Used: 0 m/s Planned: 0 m/s Remaining: -- m/s

▼ 📥 Export Results

Select sheets to include in the Excel workbook.

Mission Configuration Ground Stations Collection Targets Visibility / Contact Analysis Operations Pattern Link Budget Revisit Statistics

3D ECI Frame — Primary

AOCS: Nadir

Drag to rotate • Scroll to zoom • Space to pause • F: Free cam • T: Track sat