diff --git a/core/aerospace/spacecraft/spacecraft.py b/core/aerospace/spacecraft/spacecraft.py
new file mode 100644
index 0000000..0838db4
--- /dev/null
+++ b/core/aerospace/spacecraft/spacecraft.py
@@ -0,0 +1,38 @@
+import numpy as np
+from scipy.integrate import odeint
+from scipy.optimize import minimize
+
+class Spacecraft:
+    def __init__(self, mass, thrust, specific_impulse):
+        self.mass = mass
+        self.thrust = thrust
+        self.specific_impulse = specific_impulse
+
+    def dynamics(self, state, t):
+        # Define the dynamics of the spacecraft
+        x, y, z, vx, vy, vz = state
+        ax, ay, az = self.thrust / self.mass
+        return [vx, vy, vz, ax, ay, az]
+
+    def trajectory(self, initial_state, time_of_flight):
+        # Simulate the trajectory of the spacecraft
+        solution = odeint(self.dynamics, initial_state, time_of_flight)
+        return solution
+
+    def optimize_trajectory(self, initial_state, time_of_flight, target_state):
+        # Optimize the trajectory to reach a target state
+        def objective(thrust_vector):
+            solution = odeint(self.dynamics, initial_state, time_of_flight, args=(thrust_vector,))
+            return np.linalg.norm(solution[-1] - target_state)
+
+        result = minimize(objective, self.thrust)
+        return result.x
+
+# Example usage:
+spacecraft = Spacecraft(mass=1000, thrust=100, specific_impulse=300)
+initial_state = [0, 0, 0, 0, 0, 0]
+time_of_flight = np.linspace(0, 100, 1000)
+target_state = [100, 100, 100, 0, 0, 0]
+
+trajectory = spacecraft.trajectory(initial_state, time_of_flight)
+optimized_thrust = spacecraft.optimize_trajectory(initial_state, time_of_flight, target_state)