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v0.5.0 (Day 5) - Turbomachinery Cycles, Flight Trajectory & Unified Engine Architecture

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@Callisto27A Callisto27A released this 25 Sep 17:19
· 1 commit to main since this release
v0.5.0
f215cef

?? Navronis Day 5 Release: Complete Turbomachinery Cycles, 2D Powered Ascent Simulator & Master Engine Architecture

After a one-week deep engineering sprint, Navronis Day 5 is officially launched! Day 5 marks the transition from individual component physics (combustor, injectors, cooling jacket, supersonic bell) to complete system closure and mission flight simulation.

? What's New in Day 5 (v0.5.0)

1. ?? Turbomachinery & Power Balance Cycles (cycle.py)

  • Centrifugal Pump Hydraulics: Head $H = \Delta P / (\rho g_0)$, shaft power $\dot{W}p = \dot{m} \Delta P / (\rho \eta_p)$, and impeller tip speed $u{tip}$.
  • Impeller Classification: Specific speed $N_s$ automatically classifies radial centrifugal, mixed-flow, and axial impellers.
  • Cavitation Prevention: Suction specific speed $N_{ss}$ and required Net Positive Suction Head ($NPSH_R$) inversion identities.
  • Turbine Isentropic Work: Enthalpy extraction $\Delta h_{iso} = c_p T_{in} [1 - (1/PR)^{(\gamma-1)/\gamma}]$.
  • 5 Canonical Engine Power Cycles Closed:
    1. Pressure-Fed Cycle: High-pressure inert gas tank blowdown and pressurant helium mass sizing.
    2. Gas Generator Cycle (Open): Turbopump shaft balance and exhaust dump specific impulse penalty $\Delta \text{Isp}$ (Merlin 1D / Vulcain style).
    3. Closed Expander Cycle: Regenerative cooling vapor heat extraction vs turbopump shaft power pinch-point margin (RL10 style).
    4. Staged Combustion Cycle (ORSC & FRSC): High-pressure preburner drive with zero dump loss (RD-180 & RS-25 SSME style).
    5. Full-Flow Staged Combustion (FFSC): Dual oxygen-rich and fuel-rich preburners driving separate turbopumps with gas-gas main injection (SpaceX Raptor style).

2. ?? 2D Powered Ascent Gravity Turn Flight Simulator ( rajectory.py)

  • 2D Point-Mass Dynamics: Coupled numerical integration of thrust, weight, transonic aerodynamic drag, and pitch-over dynamics:
    \frac{dv}{dt} = \frac{F - D}{m(t)} - g \sin\gamma, \quad \frac{d\gamma}{dt} = -\left(\frac{g}{v} - \frac{v}{r}\right)\cos\gamma
  • Transonic Wave Drag Curve: Continuous $C_D(M)$ modeling subsonic drag, transonic peak at Mach 1.05, and supersonic wave decay.
  • 1976 US Standard Atmosphere: Continuous density and pressure fields from sea level to 85 km.
  • Dynamic Pressure Max Q: Evaluates peak aerodynamic loading magnitude and altitude.
  • Loss Accounting: Numerical bookkeeping of gravity loss $\Delta V_{grav}$, drag loss $\Delta V_{drag}$, and orbital deficit against a 200 km circular LEO target ($7784\text{ m/s}$).

3. ??? Unified Master EngineSystem Synthesizer (system.py)

  • Connects Combustor (Day 1) + 4 Injectors (Day 2) + Regen Cooling (Day 3) + Rao Nozzle (Day 4) + Turbomachinery Balance (Day 5) + Flight Trajectory (Day 5).
  • Generates aerospace-grade specification datasheets and serialized JSON configurations.

4. ?? Automated Test Suite Expansion (100 / 100 Tests Passing)

  • Added 23 new test cases across est_cycle.py, est_trajectory.py, and est_engine_system.py.
  • Total test count expanded from 77 to 100 tests (100% pass rate, 0 failures, 0 skips) executing in 1.51s.

5. ?? Interactive Web Simulator (docs/index.html) & CLI Updates

  • Interactive UI updated with cycle selector, turbopump power gauges, and 2D flight ascent telemetry.
  • CLI enhanced with --subsystem cycle, --subsystem trajectory, and --subsystem system.

Primary Literature: Huzel & Huang (1992), Sutton & Biblarz (2016), Griffin & French (2004), NASA SP-125, SP-194, SP-8087, SP-8107, SP-8110.

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