Attached rocket parachute deployment system
A parachute deployment system is disclosed. In various embodiments, a parachute is tethered to an aircraft. A self-propelled projectile is tethered to the parachute. The self-propelled projectile is configured to be launched in a trajectory away from the aircraft. Once launched, the self-propelled projectile pulls the parachute taut in one dimension.
1. A parachute deployment system, comprising:
a parachute tethered to an aircraft;
a hollow outer container removably coupled to the aircraft and configured to hold a projectile; and
the projectile tethered to the parachute and configured to be launched through an opening of the hollow outer container and, wherein the projectile includes a base configured to interlock with the hollow outer container to tow the hollow outer container when the projectile separates from the parachute.
2. The system of claim 1 , wherein the projectile pulls the parachute taut in a direction away from the aircraft.
3. The system of claim 1 , wherein the projectile tensions suspension lines of the parachute.
4. The system of claim 1 , wherein the projectile is tethered at an end of the parachute opposite from the aircraft.
5. The system of claim 1 , wherein a trajectory of the projectile includes a component in a direction opposite from a direction the aircraft is traveling.
6. The system of claim 1 , wherein the parachute is packed inside a container.
7. The system of claim 6 , wherein at least one of: a tether attaching the projectile to the parachute and a tether attaching the parachute to the aircraft traverses the container.
8. The system of claim 6 , wherein the container is tethered to the aircraft.
9. The system of claim 6 , wherein the container is configured to open when the container is a predetermined distance above the aircraft.
10. The system of claim 9 , wherein the predetermined distance is equal to a length of a tether connecting the container to the aircraft.
11. The system of claim 6 , wherein the container is configured to open.
12. The system of claim 1 , wherein the projectile is configured to detach from the parachute.
13. The system of claim 1 , wherein a base of the projectile is wider than a nose of the projectile.
14. The system of claim 1 , wherein the projectile comprises a hollow outer cylindrical component.
15. The system of claim 14 , wherein an end of the cylindrical component has an opening smaller than a base of the projectile.
16. The system of claim 15 , wherein an end of the cylindrical component opposite the end of the cylindrical component that has an opening smaller than a base of the projectile is tethered to the parachute.
17. The system of claim 15 , wherein the projectile is configured to deploy through the opening at the end of the cylindrical component.
18. The system of claim 17 , wherein the base of the projectile is inside the cylindrical component and a nose of the projectile protrudes outside of the cylindrical component during deployment.
19. The system of claim 1 , wherein the projectile is surrounded with an insulating material.
20. The system of claim 1 , wherein the projectile is placed within a fiberglass capsule.