ENH: Implementing 3-dof-simulation

.vscode/settings.json

@@ -241,6 +241,7 @@
         "outerboundaryis",
         "overshootable",
         "planform",
+        "pointmassmotor",
         "polystyle",
         "powerseries",
         "Prandtl",

rocketpy/__init__.py

@@ -17,6 +17,7 @@
     MassBasedTank,
     MassFlowRateBasedTank,
     Motor,
+    PointMassMotor,
     SolidMotor,
     SphericalTank,
     Tank,
@@ -35,6 +36,7 @@
     LinearGenericSurface,
     NoseCone,
     Parachute,
+    PointMassRocket,
     RailButtons,
     Rocket,
     Tail,

rocketpy/motors/__init__.py

@@ -3,6 +3,7 @@
 from .hybrid_motor import HybridMotor
 from .liquid_motor import LiquidMotor
 from .motor import GenericMotor, Motor
+from .point_mass_motor import PointMassMotor
 from .solid_motor import SolidMotor
 from .tank import (
     LevelBasedTank,

rocketpy/motors/point_mass_motor.py

@@ -0,0 +1,106 @@
+from functools import cached_property
+from typing import Callable
+
+import numpy as np
+
+from rocketpy.mathutils.function import Function, funcify_method
+
+from .motor import Motor
+
+
+class PointMassMotor(Motor):
+    """Motor modeled as a point mass for 3-DOF simulations."""
+
+    def __init__(
+        self,
+        thrust_source,
+        dry_mass,
+        propellant_initial_mass,
+        burn_time=None,
+        propellant_final_mass=None,
+        reshape_thrust_curve=False,
+        interpolation_method="linear",
+    ):
+        if isinstance(thrust_source, (int, float, Callable)):
+            if propellant_initial_mass is None:
+                raise ValueError(
+                    "For constant or callable thrust, 'propellant_initial_mass' is required."
+                )
+            if burn_time is None and propellant_final_mass is None:
+                raise ValueError(
+                    "For constant or callable thrust, either 'burn_time' or "
+                    "'propellant_final_mass' must be provided."
+                )
+        elif isinstance(thrust_source, (Function, np.ndarray, str)):
+            if propellant_initial_mass is None:
+                raise ValueError(
+                    "For thrust from a Function, NumPy array, or CSV, 'propellant_initial_mass' is required."
+                )
+        else:
+            raise TypeError(
+                "Invalid 'thrust_source' type. Must be int, float, callable, str, numpy.ndarray, or Function."
+            )
+
+        self._propellant_initial_mass = propellant_initial_mass
+        self.propellant_final_mass = propellant_final_mass
+
+        super().__init__(
+            thrust_source=thrust_source,
+            dry_inertia=(0, 0, 0),
+            nozzle_radius=0,
+            center_of_dry_mass_position=0,
+            dry_mass=dry_mass,
+            nozzle_position=0,
+            burn_time=burn_time,
+            reshape_thrust_curve=reshape_thrust_curve,
+            interpolation_method=interpolation_method,
+            coordinate_system_orientation="nozzle_to_combustion_chamber",
+        )
+
+    @property
+    def propellant_initial_mass(self):
+        return self._propellant_initial_mass
+
+    @funcify_method("Time (s)", "Exhaust velocity (m/s)")
+    def exhaust_velocity(self):
+        """Assume constant exhaust velocity: total impulse / propellant mass"""
+        v_e = self.total_impulse / self.propellant_initial_mass
+        return Function(v_e).set_discrete_based_on_model(self.thrust)
+
+    @cached_property
+    def total_mass_flow_rate(self) -> Function:
+        """Mass flow rate: -thrust / exhaust_velocity"""
+        return -self.thrust / self.exhaust_velocity
+
+    @cached_property
+    def center_of_propellant_mass(self):
+        """Center of propellant mass is always zero"""
+        return Function(0.0)
+
+    # Propellant inertias: always zero, but return as Function objects
+    def _zero_inertia_func(self):
+        return Function(0.0)
+
+    @cached_property
+    def propellant_I_11(self):
+        return self._zero_inertia_func()
+
+    @cached_property
+    def propellant_I_12(self):
+        return self._zero_inertia_func()
+
+    @cached_property
+    def propellant_I_13(self):
+        return self._zero_inertia_func()
+
+    @cached_property
+    def propellant_I_22(self):
+        return self._zero_inertia_func()
+
+    @cached_property
+    def propellant_I_23(self):
+        return self._zero_inertia_func()
+
+    @cached_property
+    def propellant_I_33(self):
+        return self._zero_inertia_func()

rocketpy/rocket/__init__.py

@@ -14,4 +14,4 @@
 )
 from rocketpy.rocket.components import Components
 from rocketpy.rocket.parachute import Parachute
-from rocketpy.rocket.rocket import Rocket
+from rocketpy.rocket.rocket import PointMassRocket, Rocket

rocketpy/rocket/rocket.py

@@ -2052,3 +2052,112 @@ def from_dict(cls, data):
             )
 
         return rocket
+
+
+class PointMassRocket(Rocket):
+    def __init__(
+        self,
+        radius: float = 0.05,
+        mass: float = 0,
+        center_of_mass_without_motor: float = 0,
+        power_off_drag: float = 0.4,
+        power_on_drag: float = 0.4,
+    ):
+        self._center_of_mass_without_motor_pointmass = center_of_mass_without_motor
+        self._center_of_dry_mass_position = center_of_mass_without_motor
+        self._center_of_mass = center_of_mass_without_motor
+        # Dry inertias are zero for point mass
+        self._dry_I_11 = 0.0
+        self._dry_I_22 = 0.0
+        self._dry_I_33 = 0.0
+        self._dry_I_12 = 0.0
+        self._dry_I_13 = 0.0
+        self._dry_I_23 = 0.0
+
+        # Call base init with safe defaults
+        super().__init__(
+            radius=radius,
+            mass=mass,
+            inertia=(0, 0, 0),
+            power_off_drag=power_off_drag,
+            power_on_drag=power_on_drag,
+            center_of_mass_without_motor=center_of_mass_without_motor,
+        )
+
+    # ------------------------------------------------------------------
+    # Center of Mass Properties
+    # ------------------------------------------------------------------
+    @property
+    def center_of_mass_without_motor(self):
+        return self._center_of_mass_without_motor_pointmass
+
+    @center_of_mass_without_motor.setter
+    def center_of_mass_without_motor(self, value):
+        self._center_of_mass_without_motor_pointmass = value
+
+    @property
+    def center_of_dry_mass_position(self):
+        return self._center_of_dry_mass_position
+
+    @center_of_dry_mass_position.setter
+    def center_of_dry_mass_position(self, value):
+        self._center_of_dry_mass_position = value
+
+    @property
+    def center_of_mass(self):
+        return self._center_of_mass
+
+    @center_of_mass.setter
+    def center_of_mass(self, value):
+        self._center_of_mass = value
+
+    # ------------------------------------------------------------------
+    # Inertia Properties (always zero)
+    # ------------------------------------------------------------------
+    @property
+    def dry_I_11(self):
+        return 0.0
+
+    @dry_I_11.setter
+    def dry_I_11(self, value):
+        self._dry_I_11 = 0.0
+
+    @property
+    def dry_I_22(self):
+        return 0.0
+
+    @dry_I_22.setter
+    def dry_I_22(self, value):
+        self._dry_I_22 = 0.0
+
+    @property
+    def dry_I_33(self):
+        return 0.0
+
+    @dry_I_33.setter
+    def dry_I_33(self, value):
+        self._dry_I_33 = 0.0
+
+    @property
+    def dry_I_12(self):
+        return 0.0
+
+    @dry_I_12.setter
+    def dry_I_12(self, value):
+        self._dry_I_12 = 0.0
+
+    @property
+    def dry_I_13(self):
+        return 0.0
+
+    @dry_I_13.setter
+    def dry_I_13(self, value):
+        self._dry_I_13 = 0.0
+
+    @property
+    def dry_I_23(self):
+        return 0.0
+
+    @dry_I_23.setter
+    def dry_I_23(self, value):
+        self._dry_I_23 = 0.0