diff --git a/rocketpy/rocket/aero_surface.py b/rocketpy/rocket/aero_surface.py
index c5d154f3e..27f87cd5c 100644
--- a/rocketpy/rocket/aero_surface.py
+++ b/rocketpy/rocket/aero_surface.py
@@ -1978,8 +1978,9 @@ def __init__(
             brakes drag coefficient will be used for the entire rocket instead.
             Default is False.
         deployment_level : float, optional
-            Current deployment level, ranging from 0 to 1. Deployment level is the
-            fraction of the total airbrake area that is Deployment. Default is 0.
+            Initial deployment level, ranging from 0 to 1. Deployment level is
+            the fraction of the total airbrake area that is Deployment. Default
+            is 0.
         name : str, optional
             Name of the air brakes. Default is "AirBrakes".
 
@@ -1997,6 +1998,7 @@ def __init__(
         self.reference_area = reference_area
         self.clamp = clamp
         self.override_rocket_drag = override_rocket_drag
+        self.initial_deployment_level = deployment_level
         self.deployment_level = deployment_level
         self.prints = _AirBrakesPrints(self)
         self.plots = _AirBrakesPlots(self)
@@ -2023,6 +2025,12 @@ def deployment_level(self, value):
                 )
         self._deployment_level = value
 
+    def _reset(self):
+        """Resets the air brakes to their initial state. This is ran at the
+        beginning of each simulation to ensure the air brakes are in the correct
+        state."""
+        self.deployment_level = self.initial_deployment_level
+
     def evaluate_center_of_pressure(self):
         """Evaluates the center of pressure of the aerodynamic surface in local
         coordinates.