Multimodal aircraft recovery system
A multi-modal aircraft recovery system is disclosed. In various embodiments, the system includes a first aircraft recovery parachute having a first set of physical attributes optimized for a first set of conditions and a second aircraft recovery parachute having a second set of physical attributes optimized for a second set of conditions different from the first.
1. A multimodal recovery system for an aircraft comprising:
a first aircraft recovery parachute having a first set of physical attributes optimized for a first set of conditions, wherein the first set of conditions includes an aircraft speed above a speed threshold and an aircraft altitude above an altitude threshold;
a second aircraft recovery parachute having a second set of physical attributes optimized for a second set of conditions, wherein:
the second set of physical attributes includes a larger canopy size compared with a canopy size attribute of the first set of physical attributes, and
the second set of conditions includes an aircraft speed below the speed threshold and an aircraft altitude below the altitude threshold; and
a deployment controller configured to:
determine whether the first set of conditions is present in the aircraft; and
in response to a determination that the first set of conditions is present in the aircraft:
trigger the first aircraft recovery parachute; and
after the first aircraft recovery parachute has been triggered:
determine that the first aircraft recovery parachute has been compromised, wherein the compromised first aircraft recovery parachute has been ripped; and
in response to a determination that the first aircraft recovery parachute has been compromised:
fly the aircraft in a nose up configuration; and
trigger the second aircraft recovery parachute while navigating the aircraft to a new position.
2. The system of claim 1 , wherein the first parachute and the second parachute are attached to or stored on the aircraft.
3. The system of claim 1 , wherein the first parachute and the second parachute are attached to or stored on a multicopter.
4. The system of claim 1 , wherein the first parachute and the second parachute are deployed based on one or more determined conditions.
5. The system of claim 4 , wherein the one or more determined conditions comprise one or more of the following: an altitude, a global positioning system data, a speed, an acceleration, or a directionality.
6. The system of claim 4 , wherein the one or more determined conditions are determined based on sensor data collected by a sensor on an aircraft.
7. The system of claim 1 , wherein the first set of physical attributes comprises a greater robustness, being heavier, or being able to withstand a larger load compared with the second set of physical attributes.
8. The system of claim 1 , wherein the second set of physical attributes comprises being faster to deploy, or being lighter compared with the first set of physical attributes.
9. The system of claim 1 , wherein the first parachute or the second parachute has multiple possible states of deployment.
10. The system of claim 1 , wherein the first parachute or the second parachute has the ability to be deployed with a riser ring.
11. The system of claim 1 , wherein one or more additional parachutes are deployed.
12. The system of claim 1 , wherein the first and second parachutes are deployed simultaneously.
13. The system of claim 1 , wherein the first parachute or the second parachute are deployed mechanically.
14. The system of claim 1 , wherein the first parachute or the second parachute are deployed based on a pilot indication.
15. The system of claim 1 , wherein the first parachute or the second parachute are deployed automatically.
16. The system of claim 1 , wherein the first aircraft recovery parachute and the second aircraft recovery parachute are stored in a fuselage of the aircraft.
17. The system of claim 1 , further comprising a sensor configured to detect a health of a structural component of the aircraft, wherein the deployment controller is communicatively coupled to the sensor and configured to trigger at least one of: the first aircraft recovery parachute and the second aircraft recovery parachute in response to a health of the structural component of the aircraft being below a threshold.
18. The system of claim 1 , further comprising a sensor configured to detect a health of an electrical component of the aircraft, wherein the deployment controller is communicatively coupled to the sensor and configured to trigger at least one of: the first aircraft recovery parachute and the second aircraft recovery parachute in response to a health of the electrical component of the aircraft being below a threshold.
19. The system of claim 1 , wherein triggering the second aircraft recovery parachute includes causing the second aircraft recovery parachute to at least partially inflate.
20. A method, comprising:
detecting, by a deployment controller, a first set of conditions being present in an aircraft, wherein the first set of conditions includes an aircraft speed above a speed threshold and an aircraft altitude above an altitude threshold;
detecting, by the deployment controller, a second set of conditions being present in the aircraft, wherein the second set of conditions includes an aircraft speed below the speed threshold and an aircraft altitude below the altitude threshold;
determining, by the deployment controller, whether the first set of conditions is present in the aircraft; and
in response to a determination that the first set of conditions is present in the aircraft:
triggering, by the deployment controller, a first aircraft recovery parachute, wherein the first aircraft recovery parachute has a first set of physical attributes optimized for the first set of conditions; and
after the first aircraft recovery parachute has been triggered:
determining that the first aircraft recovery parachute has been compromised, wherein the compromised first aircraft recovery parachute has been ripped;
in response to a determination that the second set of conditions is present in the aircraft or the first aircraft recovery parachute has been compromised, compromised:
flying the aircraft in a nose up configuration; and
triggering, by the deployment controller, a second aircraft recovery parachute, parachute while navigating the aircraft to a new position,
wherein the second aircraft recovery parachute has a second set of physical attributes optimized for the second set of conditions, wherein the second set of physical attributes includes a larger canopy size compared with a canopy size attribute of the first set of physical attributes.