A one-time flare mechanism system for use with an aerial payload system is describe which uses minimal actuation force to produce a reliable flare with minimal shock to the payload, parafoil and rigging.

A one-time flare mechanism system for use with an aerial payload system is describe which uses minimal actuation force to produce a reliable flare with minimal shock to the payload, parafoil and rigging.

In an example, a system is described. The system comprises an unmanned aerial vehicle (UAV) having a UAV control system to control flight of the UAV. The system also comprises a steerable parachute system for parachute-assisted landing. The steerable parachute system comprises (i) a deployable parachute having steerable parachute cables, (ii) steering actuators, each steering actuator coupled to, and movable to adjust, a respective steerable parachute cable, (iii) a steerable parachute controller, and (iv) one or more parachute system sensors communicatively coupled to the steerable parachute controller and configured to detect physical characteristics of a reachable landing zone for the UAV. The steerable parachute controller is configured to (i) select a safe landing location within the reachable landing zone based on the physical characteristics and (ii) control movement of the steering actuators to steer the parachute to land the UAV at the safe landing location.

In an example, a system is described. The system comprises an unmanned aerial vehicle (UAV) having a UAV control system to control flight of the UAV. The system also comprises a steerable parachute system for parachute-assisted landing. The steerable parachute system comprises (i) a deployable parachute having steerable parachute cables, (ii) steering actuators, each steering actuator coupled to, and movable to adjust, a respective steerable parachute cable, (iii) a steerable parachute controller, and (iv) one or more parachute system sensors communicatively coupled to the steerable parachute controller and configured to detect physical characteristics of a reachable landing zone for the UAV. The steerable parachute controller is configured to (i) select a safe landing location within the reachable landing zone based on the physical characteristics and (ii) control movement of the steering actuators to steer the parachute to land the UAV at the safe landing location.

Methods of reducing wing type parachute opening shock during a parachute drop, and parachute systems with reduced opening shocks are disclosed, the opening force reduction is achieved by dynamic braking, i.e. dynamically adjusting the canopy control lines during the inflation stage of the canopy. Typically, the control lines are set to zero brake length when the parachute canopy is released from the deployment bag, and are at least shortened during the inflation stage, optionally all the way to full brake. Optionally the control lines are also lengthened prior to completion of the canopy inflation. Other features and parachute systems are also disclosed.

Methods of reducing wing type parachute opening shock during a parachute drop, and parachute systems with reduced opening shocks are disclosed, the opening force reduction is achieved by dynamic braking, i.e. dynamically adjusting the canopy control lines during the inflation stage of the canopy. Typically, the control lines are set to zero brake length when the parachute canopy is released from the deployment bag, and are at least shortened during the inflation stage, optionally all the way to full brake. Optionally the control lines are also lengthened prior to completion of the canopy inflation. Other features and parachute systems are also disclosed.

A suspension line assembly for a parachute may comprise a first set of suspension lines bound together to form a first riser, and a second set of suspension lines bound together to form a second riser. A confluence may be formed by the first set of suspension line and the second set of suspension line. The confluence may comprise interior confluence suspension lines and exterior confluence suspension lines that alternate circumferentially along a perimeter of a parachute canopy.

Devices and methods of a pod that deploys from an aircraft or vehicle and descends to safely land. The pod is configured to be attached to an aircraft or vehicle. The pod includes walls that extend around and form a contained interior space that houses one or more travelers or cargo containers. During flight of the aircraft or vehicle, the pod deploys from the aircraft or vehicle while at an elevation above ground. A landing location is determined for the pod. While the pod is descending, the pod is steered towards and lands at the landing location.

Devices and methods of a pod that deploys from an aircraft or vehicle and descends to safely land. The pod is configured to be attached to an aircraft or vehicle. The pod includes walls that extend around and form a contained interior space that houses one or more travelers or cargo containers. During flight of the aircraft or vehicle, the pod deploys from the aircraft or vehicle while at an elevation above ground. A landing location is determined for the pod. While the pod is descending, the pod is steered towards and lands at the landing location.

Provided is a landing apparatus which guides an unmanned aircraft to avoid obstacles and lands the unmanned aircraft at a low-risk spot. The landing apparatus has a dangerous object position detecting device, a movement target spot calculating device, and a parachute control device. The dangerous object position detecting device detects the position of a dangerous object that is present in the vicinity of the unmanned aircraft attempting to land using a parachute. Based on the position of the dangerous object, the movement target spot calculating device calculates a movement target spot to which the unmanned aircraft should move at each instance in order to avoid colliding with the dangerous object and landing on a dangerous site. The parachute control device controls the parachute so that the unmanned aircraft moves to the movement target spot calculated by the movement target spot calculating device.