AEON ORBIT

Mission Change & Recovery Environment · V0.2

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Engineering workflow

Change → consequence → recovery → decision

Start from a validated mission baseline. Introduce a real engineering change, trace its multidisciplinary blast radius, generate constrained recovery options, then preserve the selected solution as a new reproducible baseline.

01
Baseline
02
Change
03
Impact
04
Recover
05
Compare
06
Baseline

Current engineering baseline

Deterministic first-order mission model. Click any margin for its calculation basis.

VALID
RequirementMeasuredThresholdMarginStatus

Engineering history

Every baseline is immutable; new work creates a new state.

Open change set

No change is active. Introduce a change to see how ORBIT responds.

NONE
Baseline is stable. Use Introduce change to create an engineering delta.

Engineering blast radius

Explainable dependency propagation — no hidden AI scoring.

NOT ANALYZED
Run impact analysis after introducing a change.

Recover mission

Lock what must not change. ORBIT searches only within the remaining design freedom.

WAITING
No recovery study generated.
Mission memory

Baseline archive

Preserve what the team believed, calculated and decided at each engineering state. Historical baselines remain read-only and reproducible.

Mission timeline

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Calculation model

Transparent by design

V0.2 is intentionally a first-order early-phase model. Every displayed engineering result is derived from explicit parameters and deterministic equations. The tool should explain a result before asking anyone to trust it.

Active mission parameters

Edit the baseline model directly. Changes here are treated as engineering model edits, not as an open supplier change set.

Equations & assumptions

Scope boundaries for this prototype.

Orbit: circular Earth orbit using μ = 398600.4418 km³/s² and Earth radius 6378.137 km. Eclipse uses a zero-beta cylindrical-shadow approximation.
Power: generated orbital energy = solar EOL power × sunlight duration × 0.88 conversion efficiency. Average electrical load is bus + effective payload load.
Battery: usable delivered energy = capacity × selected depth of discharge × 0.92 discharge efficiency.
RF: free-space path loss plus explicit user losses, antenna gains, receiver noise figure, data rate and required Eb/N0.
Not modeled in V0.2: detailed thermal, radiation, ADCS authority, drag lifetime, structural modes, component reliability, launch interface control, regulatory/licensing, detailed pass scheduling or cost models. These belong in later validated modules or external tools.
AEON App Experiments

Why ORBIT exists

AEON ORBIT explores a specific systems-engineering question: when a spacecraft mission changes, can software make the consequences and viable recovery paths immediately understandable without becoming another opaque optimization black box?

Product thesis

The core workflow is not “design me a satellite.” It is “this validated design changed — what broke, why, and what are the smallest feasible ways to recover it?”

Professional intent

ORBIT is positioned as an early-phase change-intelligence and recovery environment. High-fidelity mission tools remain authoritative for their specialist domains; ORBIT is designed to sit across disciplines and preserve engineering reasoning.

Prototype status

This V0.2 is suitable as an interactive concept demonstrator and engineering workflow prototype. It is not certified flight software and should not be used as the sole basis for safety-critical or mission-critical decisions.

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