Arithmos
Engine 01 / 05 · Computation · Independent
Computation held to account —
every quantity carries the derivation that produced it.
Explore more ↓DISCIPLINES COVERED
From governing equations to a bounded result
Aerodynamics & flight mechanics
Lift, drag, stability derivatives, trim states — from governing flow equations with the validity regime declared.
Thermal & TPS sizing
Aerothermal loads, stagnation heating, radiator and thermal-protection sizing with margins stated.
Structures & loads
Load paths, stress and buckling checks, factors of safety against the declared load cases.
Orbital mechanics
Transfers, rendezvous, station-keeping budgets — two-body through perturbed propagation.
Propulsion performance
Nozzle and cycle analysis, Isp and thrust budgets, propellant sizing across the mission profile.
Control & stability
Linearized models, gain and phase margins, handling-qualities checks with the model limits shown.
A WORKED RESULT
A computation you can audit
ARITHMOS reports the governing equation, the stated assumptions, the numerical result, and the range over which it holds — so the figure can be examined and reproduced, not merely accepted.
EQUATION Δv₁ = √(μ/r₁) · ( √( 2r₂ / (r₁+r₂) ) − 1 )
ASSUME two-body · impulsive burns · coplanar circular orbits
INPUT r₁ = 6 778 km (LEO 400 km) → r₂ = 42 164 km (GEO)
DERIVE aₜ = ½(r₁+r₂) = 24 471 km · v₁ = 7.669 km/s
RESULT Δv₁ = 2.397 · Δv₂ = 1.457 · Δv_total = 3.854 km/s
VALIDITY coplanar circular · errors grow with eccentricity > 0.01
VERIFIED · TRACEABLE TO FIRST PRINCIPLES
THE OTHER FOUR ENGINES
Each one self-contained
No sequence binds them. Engage whichever engine the analysis in front of you requires.
ARITHMOS · AEROSPACE INTELLIGENCE