NeuralBlitz Aerospace Engineering
What I Do
I provide comprehensive aerospace engineering tools including aerodynamic analysis, propulsion systems, flight dynamics, orbital mechanics, and aerospace structures for aerospace applications.
When to Use Me
- Aerodynamic performance analysis
- Propulsion system design
- Aircraft performance calculations
- Orbital trajectory analysis
- Structural analysis
- Stability and control
Core Concepts
- Aerodynamics: Lift, drag, boundary layers
- Propulsion: Jet engines, rockets, efficiency
- Flight Dynamics: Equations of motion, stability
- Orbital Mechanics: Kepler's laws, Hohmann transfers
- Propulsion: Thrust, specific impulse, mass flow
- Aircraft Performance: Range, endurance, climb
- Structural Analysis: Loads, fatigue, aeroelasticity
- Avionics: Navigation, control systems
Code Examples
Aerodynamics
import numpy as np
def dynamic_pressure(q, rho, V):
return 0.5 * rho * V**2
def lift_coefficient(CL_alpha, alpha, alpha0):
return CL_alpha * (alpha - alpha0)
def induced_drag_coefficient(CL, e, AR):
return CL**2 / (np.pi * e * AR)
def drag_polar(CD0, K, CL):
return CD0 + K * CL**2
def reynolds_number(rho, V, L, mu):
return rho * V * L / mu
def mach_number(V, a):
return V / a
def skin_friction_coefficient(Re, Cf_formula='schlichting'):
if Cf_formula == 'schlichting':
return 0.455 / np.log10(Re)**2.58
return 0.074 / Re**0.2
rho = 1.225 # kg/m³
V = 250 # m/s
L = 5 # m
mu = 1.81e-5 # Pa·s
Re = reynolds_number(rho, V, L, mu)
print(f"Reynolds number: {Re:.2e}")
M = mach_number(V, 343)
print(f"Mach number: {M:.3f}")
Propulsion
def thrust_force(mdot, Ve, pe, pa, A_e):
return mdot * Ve + (pe - pa) * A_e
def specific_impulse(F, mdot, g0=9.81):
return F / (mdot * g0)
def thermal_efficiency(eta_carnet, T_t4, T_t2):
return eta_carnet * (1 - (T_t2 / T_t4)**((gamma-1)/gamma))
def propulsive_efficiency(V, Ve):
return 2 / (1 + V/Ve)
def overall_efficiency(eta_thermal, eta_propulsive):
return eta_thermal * eta_propulsive
def rocket_equation(dv, Ve):
return np.exp(dv / Ve)
def mass_ratio(m0, mf):
return m0 / mf
def Tsiolkovsky_mdv(m0, mf, Ve):
return Ve * np.log(m0 / mf)
mdot = 100 # kg/s
Ve = 3000 # m/s
pa = 101325 # Pa
pe = 50000 # Pa
A_e = 1.0 # m²
F = thrust_force(mdot, Ve, pe, pa, A_e)
Isp = specific_impulse(F, mdot)
print(f"Thrust: {F:.0f} N")
print(f"Specific impulse: {Isp:.0f} s")
Flight Dynamics
def lift_force(q, S, CL):
return q * S * CL
def drag_force(q, S, CD):
return q * S * CD
def thrust_available(eta_propulsive, P_avail, V):
return eta_propulsive * P_avail / V
def rate_of_climb(L, D, W):
return (L - D) * V / W
def minimum_drag_speed(CL_max, rho, S, W):
return np.sqrt(2 * W / (rho * S * CL_max))
def stall_speed(V_s, sqrt(CL_max_clean / CL_max_landing)):
return V_s * np.sqrt(CL_max_clean / CL_max_landing)
def turn_rate(V, load_factor, g=9.81):
return g * np.sqrt(n**2 - 1) / V
def bank_angle(turn_radius, V):
return np.arctan(V**2 / (turn_radius * g))
W = 50000 # N
V = 150 # m/s
CL, CD = 1.2, 0.05
q = 0.5 * 1.225 * V**2
S = 30 # m²
L = lift_force(q, S, CL)
D = drag_force(q, S, CD)
ROC = rate_of_climb(L, D, W)
print(f"Rate of climb: {ROC:.1f} m/s")
Orbital Mechanics
def orbital_velocity(mu, r):
return np.sqrt(mu / r)
def orbital_period(T, mu, a):
return 2 * np.pi * np.sqrt(a**3 / mu)
def vis_viva_equation(v, mu, r1, r2):
return np.sqrt(mu * (2/r1 - 1/r2))
def hohmann_transfer(r1, r2, mu):
a_transfer = (r1 + r2) / 2
dv1 = np.sqrt(mu/r1) * (np.sqrt(2*r2/(r1+r2)) - 1)
dv2 = np.sqrt(mu/r2) * (1 - np.sqrt(2*r1/(r1+r2)))
return dv1 + dv2
def escape_velocity(v_esc, mu, r):
return np.sqrt(2 * mu / r)
def orbital_eccentricity(a, e_vec, h_vec):
return e_vec / h_vec
def inclination(i, h_z, h):
return np.arccos(h_z / h)
mu_earth = 3.986e14 # m³/s²
r_earth = 6371e3 # m
V_orb = orbital_velocity(mu_earth, r_earth)
print(f"LEO orbital velocity: {V_orb:.0f} m/s")
V_esc = escape_velocity(V_orb, mu_earth, r_earth)
print(f"Escape velocity: {V_esc:.0f} m/s")
Structural Analysis
def wing_loading(W, S):
return W / S
def aspect_ratio(b, S):
return b**2 / S
def taper_ratio(cta, ctr):
return cta / ctr
def wing_torsion_constant(J, c_max, t_max):
return (1/3) * c_max**3 * t_max * (1 - 0.63*t_max/c_max)
def flutter_speed(V_f, b, omega_alpha, m_alpha):
return V_f * b * omega_alpha / (2 * m_alpha)
def gust_load_factor(V_gust, cL_alpha, rho, W_S):
return 1 + rho * V_gust * cL_alpha / (2 * W_S)
def fatigue_life(N_f, sigma_a, sigma_m):
return N_f * (sigma_a / sigma_a_ref)**(-1/b)
b = 30 # m
S = 120 # m²
AR = aspect_ratio(b, S)
print(f"Aspect ratio: {AR:.1f}")
Best Practices
- Safety Factors: Apply appropriate factors
- Certification: Follow FAR/CS requirements
- Aerodynamic Validation: Wind tunnel testing
- Structural Fatigue: Consider cyclic loads
- Mission Profile: Define all flight conditions
Common Patterns
# Aircraft sizing
def preliminary_sizing():
pass
# CFD integration
def cfd_simulation():
pass
Core Competencies
- Aerodynamic analysis
- Propulsion systems
- Flight dynamics
- Orbital mechanics
- Aerospace structures