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* Modified SSTO problem to be a single component rather than a group * Updated problem to use wildcard for derivative declaration * Removed anayltical derivatives. Removed cb as an option and replaced it with options for rho_ref and h_scale. Removed targets and units where not longer necessary * fixed test_upgrade_guide problem to match changes to LaunchVehicleODE * added tolerance to coloring * Modified scaling on problem * updated some docs for kaushiks SSTO case * formatting fix for pep8 Co-authored-by: Kaushik Ponnapalli <kaushik.s.ponnapalli@nasa.gov> Co-authored-by: Rob Falck <rfalck@nasa.gov>
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| Original file line number | Diff line number | Diff line change |
|---|---|---|
| @@ -1,34 +1,121 @@ | ||
| import openmdao.api as om | ||
| import numpy as np | ||
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| from .log_atmosphere_comp import LogAtmosphereComp | ||
| from .launch_vehicle_2d_eom_comp import LaunchVehicle2DEOM | ||
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| class LaunchVehicleODE(om.Group): | ||
| class LaunchVehicleODE(om.ExplicitComponent): | ||
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| def initialize(self): | ||
| self.options.declare('num_nodes', types=int, | ||
| desc='Number of nodes to be evaluated in the RHS') | ||
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| self.options.declare('central_body', values=['earth', 'moon'], default='earth', | ||
| desc='The central gravitational body for the launch vehicle.') | ||
| self.options.declare('g', types=float, default=9.80665, | ||
| desc='Gravitational acceleration, m/s**2') | ||
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| self.options.declare('rho_ref', types=float, default=1.225, | ||
| desc='Reference atmospheric density, kg/m**3') | ||
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| self.options.declare('h_scale', types=float, default=8.44E3, | ||
| desc='Reference altitude, m') | ||
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| self.options.declare('CD', types=float, default=0.5, | ||
| desc='coefficient of drag') | ||
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| self.options.declare('S', types=float, default=7.069, | ||
| desc='aerodynamic reference area (m**2)') | ||
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| def setup(self): | ||
| nn = self.options['num_nodes'] | ||
| cb = self.options['central_body'] | ||
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| if cb == 'earth': | ||
| rho_ref = 1.225 | ||
| h_scale = 8.44E3 | ||
| elif cb == 'moon': | ||
| rho_ref = 0.0 | ||
| h_scale = 1.0 | ||
| else: | ||
| raise RuntimeError('Unrecognized value for central_body: {0}'.format(cb)) | ||
| self.add_input('y', | ||
| val=np.zeros(nn), | ||
| desc='altitude', | ||
| units='m') | ||
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| self.add_input('vx', | ||
| val=np.zeros(nn), | ||
| desc='x velocity', | ||
| units='m/s') | ||
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| self.add_input('vy', | ||
| val=np.zeros(nn), | ||
| desc='y velocity', | ||
| units='m/s') | ||
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| self.add_input('m', | ||
| val=np.zeros(nn), | ||
| desc='mass', | ||
| units='kg') | ||
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| self.add_input('theta', | ||
| val=np.zeros(nn), | ||
| desc='pitch angle', | ||
| units='rad') | ||
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| self.add_input('thrust', | ||
| val=2100000 * np.ones(nn), | ||
| desc='thrust', | ||
| units='N') | ||
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| self.add_input('Isp', | ||
| val=265.2 * np.ones(nn), | ||
| desc='specific impulse', | ||
| units='s') | ||
| # Outputs | ||
| self.add_output('xdot', | ||
| val=np.zeros(nn), | ||
| desc='velocity component in x', | ||
| units='m/s') | ||
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| self.add_output('ydot', | ||
| val=np.zeros(nn), | ||
| desc='velocity component in y', | ||
| units='m/s') | ||
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| self.add_output('vxdot', | ||
| val=np.zeros(nn), | ||
| desc='x acceleration magnitude', | ||
| units='m/s**2') | ||
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| self.add_output('vydot', | ||
| val=np.zeros(nn), | ||
| desc='y acceleration magnitude', | ||
| units='m/s**2') | ||
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| self.add_output('mdot', | ||
| val=np.zeros(nn), | ||
| desc='mass rate of change', | ||
| units='kg/s') | ||
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| self.add_output('rho', | ||
| val=np.zeros(nn), | ||
| desc='density', | ||
| units='kg/m**3') | ||
|
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| # Setup partials | ||
| # Complex-step derivatives | ||
| self.declare_coloring(wrt='*', method='cs', show_sparsity=True) | ||
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| def compute(self, inputs, outputs): | ||
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| theta = inputs['theta'] | ||
| cos_theta = np.cos(theta) | ||
| sin_theta = np.sin(theta) | ||
| vx = inputs['vx'] | ||
| vy = inputs['vy'] | ||
| m = inputs['m'] | ||
| F_T = inputs['thrust'] | ||
| Isp = inputs['Isp'] | ||
| y = inputs['y'] | ||
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| self.add_subsystem('atmos', | ||
| LogAtmosphereComp(num_nodes=nn, rho_ref=rho_ref, h_scale=h_scale)) | ||
| g = self.options['g'] | ||
| rho_ref = self.options['rho_ref'] | ||
| h_scale = self.options['h_scale'] | ||
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| self.add_subsystem('eom', LaunchVehicle2DEOM(num_nodes=nn, central_body=cb)) | ||
| CDA = self.options['CD'] * self.options['S'] | ||
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| self.connect('atmos.rho', 'eom.rho') | ||
| outputs['rho'] = rho_ref * np.exp(-y / h_scale) | ||
| outputs['xdot'] = vx | ||
| outputs['ydot'] = vy | ||
| outputs['vxdot'] = (F_T * cos_theta - 0.5 * CDA * outputs['rho'] * vx**2) / m | ||
| outputs['vydot'] = (F_T * sin_theta - 0.5 * CDA * outputs['rho'] * vy**2) / m - g | ||
| outputs['mdot'] = -F_T / (g * Isp) |
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