CST Mach–Equilibrium Hypersonic Flight Simulation

Atomic Clock Synchronization • Earth Rotation Reference • Shockwave Stability • Wind Flow • Gravity Equilibrium • Point A to Point B Corridor Control

1. Mission Control

This conceptual simulation shows an aircraft flying from Point A to Point B while maintaining CST time synchronization, center of gravity balance, shockwave stability, thermal safety, gravity equilibrium, Earth rotation reference, and Mach-equilibrium control.

ΔT = T_aircraft − T_Earth ≈ 0
|ΔT| ≤ δt

StatusREADY

Progress0%

Distance A→B1,200 km

Altitude30.0 km

2. Live Synchronized Clock Panel

UTC Time00:00:00.000

Earth Atomic Clock00:00:00.000

Aircraft Clock00:00:00.000

CST Corrected Clock00:00:00.000

Interstellar Clock00:00:00.000

Voyager 1 Clock00:00:00.000

Voyager 2 Clock00:00:00.000

Clock Drift ΔT0.000 ms

3. Earth Motion Reference

Earth Rotation Speed at Latitude419 m/s

Earth Orbital Motion29,780 m/s

Earth Moving ReferenceACTIVE

CST / Earth Speed Ratio0.72

4. Point A → Point B Flight Corridor

POINT A
Start
Atomic Lock

POINT B
Arrival
CST Lock

Mach NumberMach 1.0

Velocity300 m/s

CST Speed Ratio0.72

Equilibrium LockSEARCHING

5. Wind Traveling Through Nose / Shock Strip Stability

Nose Flow Speed300 m/s

Shock Strip StatusFORMING

Boundary LayerATTACHED

Auto Adjustment0.00°

6. Corridor Progress

T_arrival = T_start + D_AB / V_eq
V_eq = f(T_atomic, ω_Earth, h, φ, ΔT, Q_thermal, P_shock)

7. CST Control Steps 1–4

STEP 1: Small Corridor Initialization

STEP 2: Maintain ΔT ≈ 0, Shock Stable, Pitch Stable

STEP 3: Expand Corridor Distance A → B

STEP 4: Repeat Until Mission Distance / Arrival Lock

8. Stability Calculations

Pitch Angle θ0.00°

Shock Pressure0.00

Thermal Load Q0.00

Lift / Weight1.00

CG Position50.0%

CP Position55.0%

9. New Stability Panel

Shock StabilitySTABLE

Thermal StabilitySTABLE

CG AlignmentLOCKED

Gravity Equilibrium1.000

Pressure CushionBALANCED

Aircraft Strip StabilityCENTERED

10. Center of Gravity Algorithm

CG = Σ(m_ix_i) / Σm_i
correction = K_p(CG_target − CG) + K_dd(CG)/dt

The aircraft keeps CG near the target by shifting internal trim mass, adjusting fuel balance, changing pitch slightly, aligning center of pressure with center of gravity, and keeping the shock strip attached to the nose.

11. Correction Log

System ready. Press Start to begin CST Mach-equilibrium corridor simulation.

12. Equations, Algorithms, and Mach Table

R_CST = (ω_EarthR_Earthcosφ) / V_aircraft
ΔT_velocity ≈ −(v² / 2c²)t
ΔT_gravity ≈ (gh / c²)t

Stability Condition:
|ΔT| ≤ δt
L ≈ W
P_shock ≤ P_limit
Q_thermal ≤ Q_limit
CG ≈ CG_target
CP aligned with CG
Shock strip attached to nose

Mach	Velocity m/s	CST Ratio	Control Meaning
1	300	0.72	Initial lock
3	900	2.15	Shock begins dominating
5	1500	3.58	Scramjet corridor
7	2100	5.01	Strong thermal correction
10	3000	7.16	Maximum design range

Disclaimer: This is a conceptual educational simulation using proxy equations. It is not a validated aircraft design, not CFD, not a real hypersonic guidance system, and not an official aerospace program.