def get_deltaV_losses(aim_altitude: float) -> float:
    """Estimates the losses due to various sources, including atmospheric drag,
    using a very simplified equation.
    The result is the amount of Delta V (ie: the velocity) lost during ascent of the rocket.

    Args:
        aim_altitude (float): The altitude of the perigee/injection in km

    Returns:
        float: the velocity lost during ascent in m/s
    """
    return (2.452e-3) * aim_altitude ** 2 + 1.051 * aim_altitude + 1387.50