Techniques to deploy a parachute are disclosed. In various embodiments, a first projectile is configured to be propelled in a first direction, causing the parachute to be deployed. A second projectile configured to be propelled in a second direction is coupled to a line tethered to the parachute in such a way that a force in a direction opposite the first direction is applied to the line of the parachute when the second projectile is propelled in the second direction.

An automated aircraft recovery system is disclosed. In various embodiments, the system includes an interface configured to receive sensor data; and a control mechanism configured to: perform automatically a recovery action that is determined based at least in part on the sensor data. In various embodiments, the control mechanism may determine an expected state of an aircraft, determine whether a state of the aircraft matches the expected state, and in the event the state of the aircraft does not match the expected state, perform the recovery action.

An aerial vehicle safety apparatus includes a safety mechanism, a drive mechanism, an ejection mechanism, and a control mechanism. The safety mechanism is used for securing safety of at least one of an aerial vehicle and an object outside the aerial vehicle. The drive mechanism includes at least one drive unit serving as a drive source of the safety mechanism. The ejection mechanism ejects the drive mechanism together with the safety mechanism. The control mechanism controls operations of the drive mechanism for the drive mechanism to drive the safety mechanism after the ejection mechanism starts ejection of the safety mechanism.

An aerial vehicle safety apparatus includes a safety mechanism, a drive mechanism, an ejection mechanism, and a control mechanism. The safety mechanism is used for securing safety of at least one of an aerial vehicle and an object outside the aerial vehicle. The drive mechanism includes at least one drive unit serving as a drive source of the safety mechanism. The ejection mechanism ejects the drive mechanism together with the safety mechanism. The control mechanism controls operations of the drive mechanism for the drive mechanism to drive the safety mechanism after the ejection mechanism starts ejection of the safety mechanism.

A drogue parachute assembly may comprise a canopy housing and a mortar. The mortar may include an inner mortar tube and an outer mortar tube configured to telescope relative to the inner mortar tube. The canopy housing may be coupled to the outer mortar tube. A guide plate may be configured to contact an interface surface of the canopy housing and pivot the mortar about a pivot joint.

A drogue bridle separation assembly may comprise a housing and a pyrotechnic fastener. The housing may define a riser channel and a fastener opening. The pyrotechnic fastener may be configured to extend through the fastener opening and the riser channel. The pyrotechnic fastener includes a charge configured to undergo an exothermic reaction in response to an electrical signal.

Provided are an aerial vehicle safety apparatus capable of smoothly and quickly expanding an expandable object such as a parachute at time of expansion with a simple configuration, and a method of accommodating the expandable object in the aerial vehicle safety apparatus.

An aerial vehicle safety apparatus 100 includes a piston member 10, a cylinder 14 that accommodates the piston member 10 and is provided with a hole 13 through which the piston member 10 protrudes outward at time of operation, a push-up member 15 that is pushed up in one direction by the piston member 10, an expandable object 16 that is pushed up while being supported by the push-up member 15, a gas generator 17 as a power source that moves the piston member 10 in the cylinder 14, and a first member 18 and a second member 21 that serve as a cylindrical container that accommodates the piston member 10, the cylinder 14, the push-up member 15, the expandable object 16, and the gas generator 17. The expandable object 16 is stored in the container so as to form a plurality of layers in a radial direction.

There is provided a safety apparatus including a push-up member in which an ejected object is hardly displaced even during transportation, and an aerial vehicle including the safety apparatus. A safety apparatus 100 includes a cylinder 14 that accommodates a piston member 10 and is provided with a bore 13 through which the piston member 10 protrudes to the outside (upward in FIG. 1) during operation, a push-up member 15 that is pushed up in one direction by the piston member 10, an ejected object 16 that is pushed up while being supported by the push-up member 15, a gas generator 17 as a power source that moves the piston member 10 in the cylinder 14, a container 18 that has a bottomed cylindrical shape and accommodates the piston member 10, the cylinder 14, the push-up member 15, the ejected object 16, and the gas generator 17, and a lid 21 that closes an opening end of the container 18. A movement preventing member 27 that prevents the ejected object 16 from moving in a circumferential direction of a bottomed cylindrical portion 19 is provided on an upper surface of a support 20 of the push-up member 15.

A drogue bridle attachment assembly may comprise a housing, a lock pin, jackscrew gear pin, and a drive gear pin. The housing may define a bridle opening. The lock pin may be configured to translate into the bridle opening. The jackscrew gear pin may include a threaded portion and a gear portion. The threaded portion may engage a threaded opening in the lock pin. The drive gear pin may include a drive gear portion intermeshed with the gear portion of the jackscrew gear pin.

An automated aircraft recovery system is disclosed. In various embodiments, the system includes an interface configured to receive sensor data; and a control mechanism configured to: perform automatically a recovery action that is determined based at least in part on the sensor data. In various embodiments, the control mechanism may determine an expected state of an aircraft, determine whether a state of the aircraft matches the expected state, and in the event the state of the aircraft does not match the expected state, perform the recovery action.