A safety link assembly for use with an aerial delivery apparatus, the assembly comprising a main body, an ejectable connector, a retaining mechanism comprising a retaining lever rotatably mounted on a rotary axis on the main body and rotatable between a first retaining position, and a second releasing position, and a securing mechanism comprising a securing member moveable between a first securing position, and a second non-securing position, wherein the distance from the first region of the retaining lever to the rotary axis is less than the distance from the second region of the retaining lever to the rotary axis. Methods of performing an aerial delivery from an aircraft are also included.

A parachute separation device is employed to releasably secure a male link body attached to a parachute riser to a female base assembly attached to a harness. The link body has a pair of shoulders which are secured to rotatably biased lock pins. A slide assembly is displaced to rotate a pair of arms which cause the lock pins to rotate to eject the link body from the base assembly. The arms have a concave recess with an offset distal end. The arms are preferably identical but axially offset. The arms are configured to allow the force exerted on the slide assembly required to release the link body to approximately 15 lbs or less.

A parachute separation device is employed to releasably secure a male link body attached to a parachute riser to a female base assembly attached to a harness. The link body has a pair of shoulders which are secured to rotatably biased lock pins. A slide assembly is displaced to rotate a pair of arms which cause the lock pins to rotate to eject the link body from the base assembly. The arms have a concave recess with an offset distal end. The arms are preferably identical but axially offset. The arms are configured to allow the force exerted on the slide assembly required to release the link body to approximately 15 lbs or less.

An article of manufacture, a force reduction release mechanism and system for selectively maintaining and releasing components under tensile tension, the release mechanism offering mechanical gain such that the force required to activate a release between the components is a mere fraction of the heavy tensile tension force. Other aspects of the invention include novel cargo parachute system utilizing the release mechanism and a parachute stabilization arrangement utilizing at least one releasable stabilization anchor.

An emergency landing apparatus for an aircraft and a method of operating the emergency landing apparatus is provided. The emergency landing apparatus comprises: one or more rocket motors arranged to eject efflux in order to provide upwards thrust to control descent of the aircraft during emergency landing of the aircraft; and control circuitry configured to: cause the one or more rocket motors to eject efflux and provide upwards thrust to control descent of the aircraft during emergency landing of the aircraft; and cause redirection of the efflux ejected by the one or more rocket motors, during the emergency landing of the aircraft, in order to reduce the upwards thrust provided by the one or more rocket motors.

A stored energy release comprises an actuatable member slidably received within a housing. The actuatable member has an extended orientation wherein a portion of the actuatable member extends outwardly from the housing and a retracted orientation wherein the actuatable member resides within the housing. A biasing member is located between the actuatable member and the housing biases the actuatable member to the retracted orientation. A shaft is within the housing with the actuatable member configured for sliding movement along the shaft. A retaining member is located between the actuatable member and the shaft. The retaining member maintains the actuatable member in the extended orientation whereby potential energy is stored within the biasing member. A piezoelectric element selectively engages the retaining member to disable the retaining member and release the stored potential energy within the biasing member to place the actuatable member in the retracted orientation.

A stored energy release comprises an actuatable member slidably received within a housing. The actuatable member has an extended orientation wherein a portion of the actuatable member extends outwardly from the housing and a retracted orientation wherein the actuatable member resides within the housing. A biasing member is located between the actuatable member and the housing biases the actuatable member to the retracted orientation. A shaft is within the housing with the actuatable member configured for sliding movement along the shaft. A retaining member is located between the actuatable member and the shaft. The retaining member maintains the actuatable member in the extended orientation whereby potential energy is stored within the biasing member. A piezoelectric element selectively engages the retaining member to disable the retaining member and release the stored potential energy within the biasing member to place the actuatable member in the retracted orientation.

A ring release system is configured to releasably couple a parachute to a payload. The ring release system may comprise a series of release rings affixed to a riser. At least one release ring comprises a removable pin, permitting installation of the release ring after associated components have been stitched together, improving the reliability and manufacturability of the ring release system.

Aspects described herein relate to an apparatus, system, and method for the airborne launch of inflatable, lighter-than-air devices from aircraft. In some instances, a container comprising a drag parachute and a main parachute assembly may be deployed from an aircraft. Drag forces on the container may cause the drag parachute to be expelled from the container. Drag forces on the drag parachute may cause the main parachute assembly to be expelled from the container. The main parachute assembly may include a canopy with an opening and a release channel connecting the opening with the container. The container may further include a balloon inflation mechanism, which may be used to inflate one or more balloon envelopes. The one or more balloon envelopes, after being inflated, may be configured to be released from the container, traverse the release channel, and exit the main parachute assembly through the opening.

Aspects described herein relate to an apparatus, system, and method for the airborne launch of inflatable, lighter-than-air devices from aircraft. In some instances, a container comprising a drag parachute and a main parachute assembly may be deployed from an aircraft. Drag forces on the container may cause the drag parachute to be expelled from the container. Drag forces on the drag parachute may cause the main parachute assembly to be expelled from the container. The main parachute assembly may include a canopy with an opening and a release channel connecting the opening with the container. The container may further include a balloon inflation mechanism, which may be used to inflate one or more balloon envelopes. The one or more balloon envelopes, after being inflated, may be configured to be released from the container, traverse the release channel, and exit the main parachute assembly through the opening.