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 trap system is presented for deployment of a reserve parachute. The trap system includes a trap line with a first end coupled to a main parachute and a trap attached to a surface of the container. The trap includes an outer perimeter to removably hold the trap line and an interior to removably hold the reserve bridle. A kit is also presented for converting a parachute container into an improved parachute container to deploy a reserve parachute. The kit includes an attachment to be secured to a surface of the parachute container. The attachment includes a trap line with a first end configured to be coupled to the first end of the RSL lanyard, and a trap secured to a region of the attachment, with an outer perimeter to removably hold a second end of the trap line and an interior to removably hold the reserve bridle.

A trap system is presented for deployment of a reserve parachute. The trap system includes a trap line with a first end coupled to a main parachute and a trap attached to a surface of the container. The trap includes an outer perimeter to removably hold the trap line and an interior to removably hold the reserve bridle. A kit is also presented for converting a parachute container into an improved parachute container to deploy a reserve parachute. The kit includes an attachment to be secured to a surface of the parachute container. The attachment includes a trap line with a first end configured to be coupled to the first end of the RSL lanyard, and a trap secured to a region of the attachment, with an outer perimeter to removably hold a second end of the trap line and an interior to removably hold the reserve bridle.

An inflatable head restraint system for a parachute assembly may comprise an inflatable volume configured to inflate in response to a deployment of the parachute assembly. The inflatable volume may be located between a left shoulder riser and a right shoulder riser of the parachute assembly. A conduit may be fluidly coupled to the inflatable volume.

An electronic parachute deployment system including an electronic actuator, a control module, a deployment actuator, and a release mechanism. A parachute is positioned on a payload device, such as a racecar, to slow or stop the payload upon receipt of an electronic deployment activation signal. The electronic deployment signal is verified, including determining proper voltage and source. The deployment system includes multiple redundancies including mechanical deployment redundancy, remote deployment redundancy, and power supply redundancy. The control module responsible for monitoring deployment includes indicators and sensors to indicate a status, operation, or mode relative to the operability of the payload device, relative to components of the release mechanism, and relative to the parachute deployment.

An electronic parachute deployment system including an electronic actuator, a control module, a deployment actuator, and a release mechanism. A parachute is positioned on a payload device, such as a racecar, to slow or stop the payload upon receipt of an electronic deployment activation signal. The electronic deployment signal is verified, including determining proper voltage and source. The deployment system includes multiple redundancies including mechanical deployment redundancy, remote deployment redundancy, and power supply redundancy. The control module responsible for monitoring deployment includes indicators and sensors to indicate a status, operation, or mode relative to the operability of the payload device, relative to components of the release mechanism, and relative to the parachute deployment.

A system enabling safe manned and unmanned operations at extremely high altitudes (above 70,000 feet). The system utilizes a balloon launch system and parachute and/or parafoil recovery.

A system enabling safe manned and unmanned operations at extremely high altitudes (above 70,000 feet). The system utilizes a balloon launch system and parachute and/or parafoil recovery.

A parachute assembly for decelerating an occupant of an ejection seat may comprise a left shoulder riser configured to be located over a left shoulder of the occupant upon deployment of the parachute assembly. A right shoulder riser may be configured to be located over a right shoulder of the occupant upon deployment of the parachute assembly. A head restraint, configured to be behind a head of the occupant upon deployment of the parachute assembly, may be located between the left and right shoulder risers.