Parachute architecture for low-altitude VTOL aircraft

1. A system to deploy a plurality of parachutes, comprising:

a plurality of parachute canopies each packed in a canister;

a plurality of rockets adapted to extract an associated canopy from the canister; and

a controller configured to:

determine that an aircraft is at least one of: in a hover mode of operation and a forward flight mode of operation;

in response to the determination that the aircraft is in the hover mode of operation, apply a hover deployment sequence including instructing the plurality of parachutes to deploy substantially simultaneously; and

in response to the determination that the aircraft is in the forward mode of operation and above a threshold airspeed, apply a forward deployment sequence including instructing the plurality of parachutes to deploy in a predefined sequence.

2. The system of claim 1 , wherein the controller is configured to instruct the rockets to deploy such that a lower vehicle system does not exceed a threshold impact velocity.

3. The system of claim 1 , wherein the system is provided behind a cockpit of a vehicle.

4. The system of claim 1 , wherein one of the plurality of canopies is a drogue parachute canopy configured to be extracted prior to the other ones of the plurality of canopies.

5. The system of claim 1 , wherein each of the plurality of canopies is connected by an independent line to a connection point behind a headrest in a cockpit of the aircraft.

6. The system of claim 5 , wherein the connection point is part of a frame of a fuselage.

7. The system of claim 1 , wherein the plurality of canisters are arranged in a triangular formation with at least one of the plurality of canisters positioned closer to a tail of the aircraft than at least two others of the canisters.

8. The system of claim 1 , wherein:

at least one of the plurality of canopies is coupled to an associated rocket via a first load path, the first load path including a tow line, at least one upper parachute line, at least one lower parachute line, and a second load path including a release line; and

at least one of the plurality of rockets is adapted to tow the associated canopy via the tow line.

9. The system of claim 8 , further comprising a lower parachute line restrainer which when released permits the at least one lower parachute line to extend to full length.

10. The system of claim 8 , further comprising a release configured to open in response to a load switching from the first load path to the second load path, wherein when the release is open, the associated canopy and the associated rocket are permitted to separate.

11. The system of claim 1 , wherein at least one of the canisters is a deployment bag with a locking stow adapted to close flaps of the deployment bag and the locking stow is configured to unlock permitting the associated canopy to separate from the deployment bag.

12. The system of claim 1 , wherein at least one of the canisters is a deployment bag including:

a lacing system adapted to maintain pressure on the deployment bag;

a pocket adapted to separate the associated canopy stored in the deployment bag from other components of in the deployment bag; and

at least one mounting grommet for attaching the deployment bag to the aircraft.

13. A method to deploy a plurality of parachutes, comprising:

receiving an indication to deploy a parachute system from a flight computer;

determining that an aircraft is at least one of: in a hover mode of operation and a forward flight mode of operation;

in response to the determination that the aircraft is in the hover mode of operation, applying a hover deployment sequence including deploying the plurality of parachutes substantially simultaneously; and

in response to the determination that the aircraft is in the forward mode of operation and above a threshold airspeed, applying a forward deployment sequence.

14. The method of claim 13 , wherein the flight computer determines the indication to deploy the parachute system based at least in part on an anticipated crash landing, hard landing, or fault.

15. The method of claim 13 , further comprising determining that the aircraft is in the hover mode of operation based at least in part on the aircraft's airspeed being below the threshold airspeed.

16. The method of claim 13 , further comprising determining that the aircraft is in the hover mode of operation based at least in part on the aircraft's forward speed or lateral speed being substantially zero.

17. The method of claim 13 , wherein the forward deployment sequence includes deploying at least one of the plurality of parachutes prior to deploying other ones of the plurality of parachutes.

18. The method of claim 17 , wherein the forward deployment sequence includes:

deploying the at least one of the plurality of parachutes;

waiting for the aircraft to stabilize; and

deploying at least one rocket associated with another one of the plurality of parachutes, wherein a trajectory of the at least one rocket is configured to clear a vertical axis and canopy under which the aircraft is hanging.

19. The method of claim 13 , wherein all canopies associated with the plurality of parachutes are fully extracted before any one is fully inflated.

20. A system to deploy a plurality of parachutes, comprising:

container means for holding a respective parachute canopy in a packed state;

deployment means for extracting an associated canopy from the container means; and

controller means for:

determining that an aircraft is at least one of: in a hover mode of operation and a forward flight mode of operation;

in response to the determination that the aircraft is in the hover mode of operation, applying a hover deployment sequence including instructing the plurality of parachutes to deploy substantially simultaneously; and

in response to the determination that the aircraft is in the forward mode of operation and above a threshold airspeed, applying a forward deployment sequence including instructing the plurality of parachutes to deploy in a predefined sequence.