System and method for determining earth-fixed trajectory launching from within a specified area
View Patent ↗Determining a launch window from anywhere within a specified area to avoid or minimize close approaches between a launch vehicle and orbiting space objects. A method and apparatus is disclosed for minimizing close approaches, or conjunctions between spacecraft being launched from anywhere within a specified area and other objects in space during the launch and early deployment phase of their lifetime, by defining a launch window, utilizing and identifying launch window blackout times to avoid close approaches of launch trajectories from anywhere within an area with remaining objects in space as noted in a space object catalog.
1. A method for performing area conjunction analysis comprising:
establishing by a launch processor a reference trajectory associated with a plurality of potential launch sites for a space vehicle within a particular area;
creating by the launch processor an area range threshold associated with the reference trajectory, wherein the area range threshold encompasses all range thresholds for all potential launch sites within the particular area;
evaluating by the launch processor a secondary trajectory associated with an object in space;
calculating by the launch processor a conjunction time interval between the points on the reference trajectory and a secondary trajectory associated with the space object; and
establishing by the launch processor a conservative blackout interval for the reference trajectory based upon the range threshold and its conjunction with the secondary trajectory for all potential launch sites within the particular area.
2. The method of claim 1 , wherein establishing a reference trajectory comprises the launch processor executing instructions causing the processor to sample the reference trajectory at different points in mission elapsed time (MET).
3. The method of claim 1 , wherein creating an area range threshold comprises the launch processor executing instructions causing the launch processor to:
determine a maximum dispersion distance;
add a maximum dispersion distance to a range threshold for an individual launch vehicle; and
add a safety factor distance to the sum of the maximum dispersion distance and the individual range threshold.
4. The method of claim 1 , wherein evaluating a secondary trajectory associated with an object in space comprises sampling by the launch processor the location of the space object in the secondary trajectory at multiple points in time during a mission elapsed time period.
5. The method of claim 1 further comprising calculating by the launch processor conjunction intervals based upon the area range falling below a threshold.
6. The method of claim 1 , wherein establishing a reference trajectory comprises establishing a plurality of reference trajectories associated with sampled potential launch locations in the particular area.
7. The method of claim 6 further comprising establishing by the launch processor a primary trajectory surface at a given MET.
8. The method of claim 7 further comprising sampling by the launch processor the secondary trajectory and determine a minimum range to the primary trajectory surface.
9. The method of claim 8 further comprising creating by the launch processor an additional blackout interval based upon the conjunction of the sampled secondary trajectory with the primary trajectory surface.