A parachute canopy release assembly includes a frame assembly with first and second upstanding members. A latching member has a pivot end and a latch end, the pivot end pivotally coupled to a bottom portion of the first upstanding member. A riser bar has a pivot end and latch engaging end, the pivot end of the riser bar pivotally coupled to a top portion of the second upstanding member, the latch engaging end retained by the latch end of the latching member in the locked state. A release linkage assembly includes a lock member configured to transition from a first state to a second state, retain the latching member in a first position in the first, locked state and retain the latching member in a second position in the second, unlocked state.

A parachute canopy release assembly includes a frame assembly with first and second upstanding members. A latching member has a pivot end and a latch end, the pivot end pivotally coupled to a bottom portion of the first upstanding member. A riser bar has a pivot end and latch engaging end, the pivot end of the riser bar pivotally coupled to a top portion of the second upstanding member, the latch engaging end retained by the latch end of the latching member in the locked state. A release linkage assembly includes a lock member configured to transition from a first state to a second state, retain the latching member in a first position in the first, locked state and retain the latching member in a second position in the second, unlocked state.

A fluid activated parachute release apparatus includes a liquid sensor component moveably coupled to a cam member including a cavity; a disk configured to engage the cavity of the cam member; and a fork member releasable from the disk responsive to rotation of the cam member.

The present invention provides 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. The invention also provides methods of performing an aerial delivery from an aircraft.

A pressure activated release system and method are disclosed for deployment of surface, aerial and subsea payloads. The system and method include a payload release switch that is activated, without human intervention, by a pressure differential. The system and method also includes a payload release mechanism having an unreleased configuration at pressures below a specified pressure. The release mechanism has a released configuration at pressures above the specified pressure. The switch causes the release mechanism to move from the unreleased configuration to the released configuration.

Systems and methods for aerially delivering cargo into a body of water while avoiding parachute entrapment and entanglement are described. The system includes a parachute having a canopy and suspension lines. The system further includes a weight coupled to a first end of the suspension lines and a ring that is configured to float in the body of water. The weight is coupled to the cargo, and the ring is disposed between the weight and the canopy with the suspension lines passing through the center of the ring.

A riser release system controllably lands a descending flight vehicle having a parafoil or canopy. The system has control lines and riser lines attached to the parafoil or canopy. The other end of the riser lines are attached to an upper portion of a release structure; a lower portion of the release structure is connected to the payload; and a coupling mechanisms releasably couples the upper and lower portions. When the upper and lower portions are decoupled, a distance control device controls and limits the distance of separation between the two portions, and a rate control device controls the rate of separation. Separation causes the riser lines to increase the distance between the payload and canopy, further causing the canopy to flare and decrease the rate of descent of the flight vehicle.

A riser release system controllably lands a descending flight vehicle having a parafoil or canopy. The system has control lines and riser lines attached to the parafoil or canopy. The other end of the riser lines are attached to an upper portion of a release structure; a lower portion of the release structure is connected to the payload; and a coupling mechanisms releasably couples the upper and lower portions. When the upper and lower portions are decoupled, a distance control device controls and limits the distance of separation between the two portions, and a rate control device controls the rate of separation. Separation causes the riser lines to increase the distance between the payload and canopy, further causing the canopy to flare and decrease the rate of descent of the flight vehicle.

A ring release system is configured to releasably couple a parachute to a payload. The ring release system may comprise an upper release ring, an intermediate release ring with a partially and/or completely flattened end, and a lower release ring having a J-shape. When activated, the release rings cascadingly separate to release the parachute from the payload. With these systems and related methods, larger payloads may be supported, the mass and size of the ring release system may be reduced as compared to prior systems, and various failure modes may be eliminated.

A ring release system is configured to releasably couple a parachute to a payload. The ring release system may comprise an upper release ring, an intermediate release ring with a partially and/or completely flattened end, and a lower release ring having a J-shape. When activated, the release rings cascadingly separate to release the parachute from the payload. With these systems and related methods, larger payloads may be supported, the mass and size of the ring release system may be reduced as compared to prior systems, and various failure modes may be eliminated.