Collision avoidance maneuvers to prevent orbital collisions between two catalogued objects are typically planned multiple days in advance. If the warning time is decreased to less than half-an-orbit in advance, the problem becomes more complex. Typically, the maneuver (assumed to be impulsive) would be placed at perigee or apogee and oriented in the direction that allows for a fuel-optimal maneuver to be performed well before the predicted collision. Instead, for rapid collision avoidance scenarios, finite burn propagation was applied to determine the thrust duration and direction required to reach a desired minimum collision probability. Determining the thrust time and direction for a wide range of orbits and spacecraft properties results in a semi-analytical solution to the collision avoidance problem anywhere in Low-Earth Orbit. The speed at which this method can be applied makes it valuable when minimal time is available to perform such a maneuver. For many spacecraft missions, even the slightest change in the orbit of the spacecraft may significantly affect its ability to perform to its required specifications. With the high volume of debris in orbit, debris-creating events could occur with no advanced notice, making rapid collision avoidance scenarios a real possibility. Care must be taken to ensure that any potential collision is avoided while minimizing the effect of the maneuver on the spacecraft's mission performance. Assuming perfect knowledge of the states of all objects and that the possible collisions occur at high relative velocities, the required thrusting time to achieve a desired collision probability is found. Varying the desired collision probability, the resulting changes in the required thrust duration time (and, thus, fuel use) can be observed, providing options for trading the fuel use and likelihood of a collision. Additionally, both of these variables contribute directly to the ability of the spacecraft to perform to the desired mission specifications. As the collision probability threshold and required burn time increase, the mission performance decreases. The level of robustness necessary in the mission specifications can be used to limit the desired collision probability threshold. This is accomplished by determining the time and fuel required to perform the collision avoidance maneuver to the desired probability level and analyzing the effect of the time spent away from the mission orbit and the quantity of fuel required to perform the maneuver on the mission performance. It was found that, for notification times less than around 20 minutes, it is best to decrease the collision probability as much as the available fuel will allow without regard for the time duration of the maneuver. As the notification time increases past 20 minutes, more emphasis can be placed on the time required to perform the entire maneuver and it was found that simultaneously minimizing the maneuver time and collision probability outweighed the slight extra fuel required for such a maneuver. Such analysis would prove significant in real-time spacecraft operations when determining an optimal collision probability threshold (typically a subjective variable) for rapid collision avoidance scenarios.