Abstract: An aerial cargo container is described that includes a cargo box with a plurality of hinged rotor blades having a stowed position against the sides of the box and a deployed position extending outwardly from the box, and a deceleration and orientation assembly to slow the descent of the container and align the longitudinal axis of the container with the relative wind direction, thereby minimizing damage to the blades upon opening. The assembly includes a drogue chute, a blade retainer to secure the blades in the stowed position, and a folded metering cord attached between the drogue chute and the box, and a segment securing the blade retainer, whereby the cord segments unfold sequentially upon exertion of a force to slow and orient the container, prior to release of the blade retainer to permit movement of the blades to their deployed positions.

Abstract: The present invention 10 discloses an emergency low altitude parachute having a parachute canopy 28 that inflates by the introduction of compressed gas. A compressed gas canister 30 is located within the housing of the inflatable portion of the device and is activated by an activation ring 24. The device is stored within a carrying case 16 prior to use. When the low altitude emergency parachute 14 is removed from its storage case, the user 12 attaches the attachment harness 32 to their body. A helmet 22 with breathing apparatus is supplied. Once the user 12 is harnessed in, the device is held in the front of the body and an activation ring 24 is provided as means of activating the compressed gas canister 30. Once activated the parachute pontoons fill with the gas rapidly, expanding them and unfolding the parachute canopy 28. The device 10 is then released through the threshold 26 of the escape route.

Abstract: An automated quick release mechanism for a three ring release includes a pneumatic or hydraulic cylinder with a hardened metal pin. The pin engages a string loop of the three ring release. An internal spring holds the pin in an extended position. A controller external to the automated quick release mechanism provides a gas or fluid pressure to withdraw the pin and disengage the string loop.

Abstract: A system is provided for slowing the speed of a product released into the air from an aircraft. A flexible material wrapped about a product includes a tethered portion thereof that is collapsible against the product prior to release thereof from the aircraft. The tethered portion expands to form an air drag device after the product is released from the aircraft.

Abstract: A rescue system for rescuing persons by air, particularly from tall buildings or airplanes, has a receptacle with at least one parachute or paraglider. A harness for the parachute or paraglider is connected to the receptacle. The receptacle is constructed as a closable package with a substantially cuboid or suitcase-like shape and also has an opening mechanism. The harness for the parachute or paraglider is disposed inside the closed receptacle.

Abstract: An air drop container assembly for providing an improved air-drop container for the military and emergency operations. The air drop container assembly includes a container having a top wall, a bottom wall, side walls, and a plurality of compartments disposed therein; and also includes a parachute assembly including a cover being removably disposed upon the top wall of the container and also including a parachute member being removably attached to the container; and further includes a cargo protection assembly being disposed in the container; and also includes a weight assembly also being disposed in the container for providing the container with proper flight orientation as the container is falling through air.

Abstract: A short-haul escape system includes an elongated line for detachable suspension from a support member on an airborne vehicle, a load-carrying receptacle attached to an end of the line, a container attachable to the airborne vehicle in proximity to the support member thereon and releasably stowing a parachute such that the parachute can be pulled from the container, and a flexible strap attached to the parachute stowed in the container and extending from the container and secured to the short-haul line such that upon detaching the line from the support member of the airborne vehicle, which will cause the line and receptacle to fall away from the airborne vehicle, the flexible strap will pull the parachute from the container so that the parachute can inflate and slow the fall of the line and receptacle to a soft landing.

Abstract: A flying drone includes a flight control computer, a parachute system with a parachute, a power supply system, a propulsion system, and an actuating drive system, without any of these systems being redundantly duplicated. To prevent uncontrolled crashing of the drone due to a critical error of any subsystem, signals or data are supplied from the power supply system, the propulsion system, and the actuating drive system, to an error detection or recognition device, which detects defined errors or error combinations in the provided signals or data and then supplies a deployment signal to the parachute system, which responsively generates a control signal that triggers an ejection mechanism to eject the parachute.

Abstract: A short-haul escape system includes an elongated line for detachable suspension from a support member on an airborne vehicle, a load-carrying receptacle attached to an end of the line, a container attachable to the airborne vehicle in proximity to the support member thereon and releasably stowing a parachute such that the parachute can be pulled from the container, and a flexible strap attached to the parachute stowed in the container and extending from the container and secured to the short-haul line such that upon detaching the line from the support member of the airborne vehicle, which will cause the line and receptacle to fall away from the airborne vehicle, the flexible strap will pull the parachute from the container so that the parachute can inflate and slow the fall of the line and receptacle to a soft landing.

Abstract: A flexible linkage system for connecting an environmentally sealed apparatus such as a parachute system to an external apparatus such as a parachute harness, the system comprising an internal link and an external link. The internal link is completely within the sealing packaging and is directly attached to the sealed apparatus. The internal link has a looped end wherein the sealing packaging is sealed around the internal link and joined in the center of the loop. A portion of the sealing is cut away from the center of the loop, thereby forming a void surrounded by the loop and the sealing material. The external link comprises a loop and a connecting hardware anchored to the external link. The loop in the external link is threaded through the center of the loop in the inner link and then it is connected to the connecting hardware.

Abstract: The present invention relates to a parachute release device provided to be mounted on a parachute, which parachute is provided to be attached to an object. The device has a data processing system having a release signal output and a memory provided for storing data. The data processing system is provided for generating a release signal for opening a parachute. The device further has altitude determining device connected to said data processing system and provided for determining altitude values; and time determination means provided for determining the free fall duration as from the start of the dive. The memory is provided for storing a plurality of series of theoretical dive data, said theoretical dive data indicating for each distance value a corresponding theoretical time. The data processing system is further provided for selecting a series of theoretical dive data in function of the determined altitude values and the determined free fall duration.

Abstract: A parachute for decelerating an object is provided which includes a parachute canopy having an apex and a base and rigging lines attached to the base and attached to the object. The parachute canopy and the rigging lines are configured as a reefed pack with the parachute canopy being folded into a plurality of concentric folds one upon the other from the base to the apex across the full height of the parachute canopy. The parachute may also include a plurality of control lines associated with respective ones of the concentric folds of the parachute canopy to form therewith individual deployment zones. A control apparatus for controlling the targeted release of the folds controls line cutters to cut the respective control lines associated with the individual deployment zone to be deployed.

Abstract: A parachute assembly includes a canopy central panel of square configuration, a rectangular canopy outboard arm fixed to each side edge of the canopy central panel and extendible outwardly therefrom to form a cross configuration, each of the canopy outboard arms having two outboard corners. A suspension line is fixed to each of the outboard corners, the suspension lines being of equal length for initial deployment of the parachute assembly. A first suspension line fixed to a canopy first outboard arm at a corner thereof is extendible to cause a spinning motion and increased rate of descent of the parachute. A second suspension line fixed to a canopy second outboard arm at a corner thereof closer to the first suspension line is extendible to influence the spinning motion, rate of descent, and horizontal velocity and direction.

Abstract: A device and method of use for opening a container during descent so that objects within the container may be dispersed over a controlled ground area. The device includes a housing with a parachute canopy contained within. A sling is attached to the canopy within the housing and extends external to the housing. A cap is selectively engageable with the housing to close the housing. A spring within the housing exerts outward force on the cap. An actuation device is mounted to the cap to selectively disengage the cap from the housing. When the cap is disengaged from the housing the cap is ejected by the force of the spring. A lanyard connecting the cap to the canopy draws the canopy out of the housing for deployment. Deployment of the canopy transfers tension force through the slings to the container. The tension force imposed on the container by the slings opens the container, releasing objects held therein. The objects are released at a predetermined height.

Abstract: A mechanical dereefer comprises a frame having a housing end with a joining wall and spaced plates extending from the joining wall to define a L shaped bifurcated end. A latch is mounted between the plates for pivotal movement between a capture position, wherein a reefing line end is held, and a release position, wherein the reefing line end is released. The latch is maintained in the capture position by engagement with a latch lock slidable through an aperture in the joining wall to a projected position. The latch lock is maintained against a bias in the projected position by the engagement of an elbow link and a trigger link each pivotally mounted within the frame housing end. The trigger link may be actuated out of engagement with the elbow link either manually or by a trigger device.

Abstract: A release fitting for releasably holding at least one line to at least one item, the release fitting having a first body part, a second body part, and a third body part, the first and second body parts pivotably secured to the third body part, a bolt with a first bolt portion connected to a first portion of the first body part and a second bolt portion connected to a first portion of the second body part, at least one pin suitable for attaching thereto the at least one line, the first body part having a recess for releasably receiving an end of the pin, the bolt initially holding apart the first portion of the first body part and the first portion of the second body part to thereby maintain a second pin end in the recess, the third body part connected to the at least one item, bolt cutter apparatus for selectively cutting the bolt to release the at least one line from the pin.

Abstract: A large scale parafoil apparatus which makes use of an energy attenuator positioned between the initially deployed drogue parachute and the parafoil for controlling the initial stages of deployment thereof and significantly reducing rebound to enhance the deployment of the parafoil canopy in an orderly manner with the suspension lines thereof extending from the canopy to the load retained therebelow being maintained under continual tension during canopy deployment for enhancing rapid and full deployment thereof. The energy attenuating device is a ripstitch modulator having preferably multiple ripstitch sections for gradually decreasing the force resistant to separating the drogue from the parafoil and ultimately completely separating to allow full deployment of the parafoil canopy. The parafoil canopy defines a plurality of air cells with one main air cell being deployed in the lateral central location thereof.

Abstract: A parachute device for a helicopter includes a canopy confining case having a stationary casing part, and a removable casing part mounted removably on the stationary casing part. The stationary and removable casing parts cooperatively form a compartment to receive a parachute canopy that has a release cord connected to the removable casing part, and a suspension line unit. An anchoring line has one end that extends into the canopy confining case and that is coupled to the suspension line unit of the parachute canopy. A rocket member includes a launch tube mounted on the stationary casing part externally of the compartment, and a rocket disposed in the launch tube and connected to the removable casing part. The rocket is capable of propelling from the launch tube when ignited. An ignition control line has a first end connected to the rocket member, and a second end provided with an ignition unit that is operable so as to ignite the rocket.

Abstract: Disclosed is a low-drag/high-speed pilot chute which is attached to a bridle cord, and a high-drag/low-speed pilot chute which is attached with a weak link to the bridle cord. In a low-speed deployment scenario, the high-drag pilot chute provides enough drag to deploy the canopy quickly. However, if the deployment speed is high enough, the force from the high-drag pilot chute will exceed the strength of the weak link and break it. This separates the high-drag pilot chute from the rest of the assembly. The low-drag/high-speed pilot chute then continues deploying the parachute, effectively protecting the parachute and its cargo from the ill effects of having too much pilot chute force.

Abstract: A helium actuated airplane parachute including an airplane having a rectangular compartment formed therein with an associated top opening. A flexible inelastic parachute is included having a closed hemispherical configuration with an open bottom having a peripheral edge. A plurality of strings each have a first end spacedly coupled to the peripheral edge and a second end mounted to a bottom face of the compartment. A helium gas tank is situated adjacent the compartment. The gas tank is connected to an actuator valve mounted on the bottom face of the compartment below the parachute when in a folded undeployed orientation. The actuator valve is adapted to release gas within the compartment thereby deploying the parachute.

Abstract: A parachute releasing apparatus is operable with a reserve static line for automatically releasing one riser after failure of a second riser, thus avoiding entanglement of the main parachute with the reserve parachute. First and second risers of the main parachute are releasably attached to a harness through quick releases devices for each riser. The reserve static line is connected between the first riser of the main parachute and a deployment pin of the reserve parachute. A connection is made between the first riser of the main parachute and the quick release device of the second riser for automatically releasing the second riser from the harness prior to the reserve static line deploying the reserve parachute. Thus, the main parachute is released from the harness before the reserve parachute deploys and avoids entanglement of the failed main parachute with the reserve parachute.

Abstract: An aircraft passenger extraction system having a fuselage and a tail section removably attached to the fuselage. A plurality of interconnected passenger modules are removably disposed within the fuselage. Four I-beam rails are longitudinally mounted about the inside circumference of the fuselage, and the passenger modules have four sets of wheels that slide on the rails. The tail section has four pairs of separation flaps and four extraction flaps to assist in the separation of the tail section in the event of an airborne emergency. Upon separation of the tail section of the fuselage, the interconnected passenger modules are slidingly withdrawn from the fuselage. Once the passenger modules clear the fuselage, the interconnections of each passenger module are severed in sequence, and a series of parachutes are deployed to safely float each passenger compartment to earth.

Abstract: The assistant landing device of a troubled airplane of the present invention comprises a storing chamber under the front end of the airplane, which has a freely opened door, and a strengthen network the front end of which is connected with the airplane body. When the network is expanded from the storing chamber, it will not affect the descent of the front and back landing gears. A plurality of canopy packets arranged as an array are installed on the front and back sides of the network and may be opened by controlling so that a group of canopy packets are formed on the right and left sides of the body of the airplane so that the airplane may be descended slowly. Each of the canopy packets has a large and a small canopy packets and a gas container for being quickly charged with air so that the small canopy packet may be opened.

Abstract: A parachute release mechanism is provided which is compact, lightweight, and free from external wire harnesses. The release mechanism includes a passage connected between a source of pressurized gas and a piston chamber having a piston disposed therein. A shear pin is disposed in an opening in the piston and in the piston chamber. Activation of the source of pressurized gas causes the piston to move forward shearing the shear pin and either deploying or releasing a parachute.

Abstract: An emergency soft-landing system (10) for use on a rotor-type aircraft such as a helicopter (70). The system (10) includes at least one parachute-containing structure (12) that houses at least one parachute (50). The structure (12) is designed to be selectivelly attached to various locations on the helicopter's lower surface (76), the sides (82), and to the landing gear struts (85). The parachute (50) is deployed from the structure (12) when an out-of-control landing is unavoidable or an extreme emergency exists. The system (10) can be designed so that the parachute-containing structure (12) operates in combination with an airbag (60). An airbag can be attached to the helicopter's lower surface (76) near the rear end (78), and front end (80), and to the center of the helicopter between the landing gear (84). The parachute(s) (50) and airbag(s) (60) are designed to be manually deployed by a helicopter crew member or automatically by a dynamic responsive switch (34).

Abstract: An air-chute safety system (10) for an aircraft (12) having a fuselage (14) with a cockpit (16) and a tail end (18), and a pair of wings (20) with engines (22). The system (10) comprises a plurality of drag parachutes (24) stored in and deployed from the tail end (18) of the fuselage (14), in conjunction with an aerodynamic braking apparatus in the aircraft (12), which will shut down the engines (22) during an emergency when in flight, so that the aircraft (12) will slow down. A plurality of top parachutes (26) are provided. A structure (28) is for storing each of the top parachutes (26) in vertical spaced apart relationships below a top surface (30) of the fuselage (14) between the cockpit (16) and tail end (18) thereof.

Abstract: The present invention relates to an emergency landing auxiliary apparatus of an aircraft using a parachute, whereby a rapid accident crash of an aircraft can be avoided through releasing the chute set inside an apparatus accepting room 11 and the landing distance of the aircraft can be reduced in case of an emergency landing. Therefore, the present invention is effective in decreasing a possible loss of lives and the damage of the aircraft itself.

Abstract: A pressure dependent parachute release device having a primary storage volume, a check valve between the primary storage volume and a secondary storage volume, a pressure operable valve, the outlet of which is connected to the inlet of a flow restrictor, with the outlet of the flow restrictor being connected to a pressure operated actuator. The inlet of the check valve and a primary port of the pressure operable valve are in fluid communication with the primary storage volume, and a secondary port of the pressure operable valve and the outlet of the check valve are in fluid communication with the secondary storage volume. The pressure operable valve is first set to a primary position, blocking communication from the secondary storage volume to the outlet. A pressure differential between the primary and secondary storage volumes shifts the valve to a secondary position allowing fluid communication between the secondary storage volume and the pressure operated actuator via the flow restrictor.

Abstract: A system and method for aerial cargo delivery is disclosed that uses a linkless towplate having an eccentric cam and a pin. The cargo flexible tension member is isolated from the force of a deployed drogue parachute by a frictional holding force generated by the eccentric cam and the pin. A system and method for aerial cargo delivery is also disclosed that uses a towplate with a link assembly. The towplate has two cylinders that hold the cargo flexible tension member and the drogue parachute flexible tension member.

Abstract: A stabilizing in-flight parachute system for an airplane comprising a retractable canopy built into a top portion of a fuselage of the airplane. A parachute is under the canopy, while a framework is attached to the parachute. A device is for winding and unwinding the parachute on the framework. A facility is for retracting the canopy and exposing the parachute. A mechanism is for accelerating deployment of the parachute out from the fuselage of the airplane, when the canopy is retracted.

Abstract: A reference point device and method for aiding in the training of free falling parachutists or skydivers. The reference point device indicates relative position and velocity to the skydiver during free fall, and is structured to be first tossed from an airplane followed immediately by the skydiver jumping, or released from the hands of the skydiver shortly after jumping from an airplane, wherein the reference device achieves and maintains the approximate terminal velocity of the free falling skydiver. The reference device falls in a stable manner, enabling the skydiver to have a close proximity visual point of reference to determine or gauge his or her relative directional movement and speed of fall, and this so that the skydiver may practice movement and speed control during free falling prior to opening his or her parachute.

Abstract: Methods and apparatus for reducing the velocity of a rider in or on an open cockpit vehicle when the rider is thrown from the vehicle are disclosed. The present invention provides a drag-reducing device such as a parachute or parawing that is affixed to the rider so that when a crash occurs, the rider is slowed down after ejection and therefore more likely to survive the crash without severe injuries. The present invention is preferably used in conjunction with a motorcycle and includes a sensor system for sensing the imminence or occurrence of a crash an/or the ejection of the rider from the vehicle. A transmitter receiver system is used to relay a signal to a deployment system that is attached to the rider as part of a system containing the drag inducing device, which rapidly deployed, thereby causing the velocity of the ejected rider to be reduced and providing the further benefit of lifting the rider away from the crash site.

Abstract: An air-launchable gliding sonobuoy store includes a canister enclosing an flatable membranous wing folded in a collapsed state with an electroacoustic system. After launching, the wing inflates and a steering mechanism controls the wing glide path by skewing the trailing edge thereof. Upon reaching the sea, the wing serves as a buoy with the electroacoustic system transducer depending therefrom.

Abstract: A parachute deployment system having a pack with an attached parachute and a detachably coupled handle. The handle is used to activate the deployment system by physically opening the pack via an internal rip cord pin in communication therewith. Further, the handle is used to pull a pilot bag, which holds the parachute, from the pack and into the air stream. The pilot bag provides sufficient drag for effectively deploying the parachute therefrom.

Abstract: A compact altitude and rate of descent instrument is combined with a visual indication device and attached directly as a self-contained unit to protective eye wear or headgear for the determination of critical altitudes while engaged in freefall skydiving without the need for head or hand movements. Such an instrument reduces potentially fatal lack of altitude awareness due to extraneous factors and allows for more complete concentration on maintaining eye contact with others when performing maneuvers in close proximity such as during freefall formation flying (relative work).

Abstract: A cover or apron interposed between a ballute and the aft cover of a submtion for delaying deployment of the ballute and preventing the ballute from contacting the aft cover during deployment.

Abstract: A shock energy absorbing device provides shock protection for the riser l employed to attach an aerodynamic deceleration device to a primary body during deployment of the system into an airstream. During deployment, for example, by dropping an unopened parachute and attached load or by rocket delivery of the unopened parachute and attached load, the parachute is made to open at a desired altitude wherupon very large shock tension forces are generated which are applied to the line. In order to protect the line from failing under these forces and to reduce the requirement for a bulky, heavy line, a shock absorber is provided in the form of a block having one or more breakable web portions formed therein and through which the riser line is threaded. Upon deployment of the system into an airstream, the shock tension forces operate to fracture some or all of the breakable web portions thereby dissipating the shock energy generated during deployment and protecting the riser line from failure.

Abstract: An object of the invention is to provide an escape apparatus which enables persons to promptly escape from an elevated place such as a building and an aircraft, and is easy to handle. An aerial floating flier such as airfoil or a parachute is folded and contained in a case, and by throwing out such a case or an aerial floating flier in folded state into the air, the aerial floating flier is spread in the air, thereby allowing to escape from a site of an accident by hanging from the aerial floating flier and descend slowly on the ground.

Abstract: An environmentally-sealed parachute deployment system for bail-out parachutes comprising a spring-loaded pilot parachute, an environmentally sealed vacuum bag, a deployment bag having one or two elastic closure loops, and a man-rated parachute. The drag force exerted by the pilot parachute tears open the environmentally sealed bag, initiating deployment of the parachute.

Abstract: A self-staging parachute apparatus including a drogue parachute and a main parachute each encapsulated in a respective packing bag with the main parachute packing bag defining a side pocket through which a specialized retention bridle extends from the suspension lines of the drogue chute directly to a load line connected to the load. The load thus utilizes a single point of attachment for both the drogue parachute and the main parachute with the retention bridle of the drogue parachute in movable engagement extending through the pocket of the main parachute deployment bag. The main parachute and drogue parachute when packed are designed to form a generally cylindrical shape which is adapted to be easily placed within cylindrical payloads such as flares or the like to facilitate deployment thereof after the rocket motor has been separated.

Abstract: A large parachute having an inlet control parachute operable to positively expand the inlet area of a large parachute detachably secured thereto to facilitate deployment of the large parachute including a main canopy which is reefed to the outer portion of the inlet control parachute. The inlet control parachute includes an inlet control canopy with an upper vent and a plurality of longitudinally extending inlet control gore panels which are attached with respect to one another longitudinally therealong and define an inlet control skirt along the lowermost edge thereof. The inlet control parachute is designed to expand in a generally circular form and thereby positively expand and circularize the inlet area of the large parachute to minimize folding and uneven distribution of the canopy of the large parachute during deployment thereof.

Abstract: An aviator harness fitting includes a releasable member secured to a buckle member by means of a movable bolt. A pressure inlet is provided to enable translational motion of the bolt in the manner of a piston. When actuated, the bolt moves to a release position to permit separation of the releasable and buckle members.

Abstract: A parachute associated with an object unfolds faster in an airstream if the object is first accelerated in the direction of descent. This principle can be applied advantageously to a mine system combating military targets from the air because the time between starting from an ambush position in the terrain to the onset of searching movements in the air can be shortened.

Abstract: The invention concerns a releasing mechanism for a parachute which is stowed in a container held closed by a safety string against the pulling force of a preloaded spring. This safety string is fixed to a container and can be released by action of an energy storage, e.g. a detonator or a preloaded spring. The energy set free by controlled ignition or triggering can either destroy or release the safety string.

Abstract: The disclosed device comprises, in the first element, on which the second element is mounted, a peripheral housing opened outwards, a circlip engaged in said housing, comprising teeth capable of getting engaged in retaining means of the second element, and a means to bring the ends of the circlip closer together in order to retract it and to bring out the teeth of the retaining means controlled by a delay means. The disclosed device is particularly suited to the locking and unlocking of sub-munitions parachute containers.

Abstract: A parachute apparatus with a main canopy having conventional suspension lines and load carrying means with a plurality of main loops attached with respect to the panels of the main canopy. A secondary canopy is positioned within the main inlet opening of the first canopy and is adapted to intially retain the lower edge of the main canopy in a closed position. The outer surface of the secondary canopy and the inner surface of the main loop canopy are connected by way of the main loops and by way of secondary loops located on the external surface of the secondary canopy. A retaining cord extends through the secondary loops and the main loops to reef the main canopy to the secondary canopy during the initial stages of inflation. During this time the secondary canopy will inflate and provide a controlled flow of inflation air into the main chute. Once the main parachute has become partially inflated then the reefing cord is cut allowing full inflation of the larger main canopy.

Abstract: An ejectable or launchable member which possesses a storage space for a parachute. An ejectable member of the type which is under consideration herein has the dimensions of the constructional elements reduced in the periphery of a parachute cassette, so as to resultingly provide for savings in deployment weight, and at a given caliber, to be able to increase the amount of storage space which is available for the parachute.

Abstract: The deployment system includes a pilot chute and a bridle wherein the bridle is secured at one end to the forward portion of a parachute canopy. The bridle extends through a rear portion of the canopy. Prior to deployment, the deployment bag is packed such that the forward and rear portions of the canopy lie closely adjacent one another to fully extend the bridle pilot chute from the main canopy. Upon deployment, relative front-to-back opening forces of the parachute displace the front and rear portions of the parachute away from one another thereby drawing the bridle within the canopy and the pilot chute into a closely snugged location to the canopy.

Abstract: The reserve parachute is folded and disposed in a covering. A pilot chute overlies the reserve parachute outside of the covering. A disc overlies the pilot chute and bears against a compression spring maintained under compression by a single centrally positioned cord connected between the disc and a single release pin on the opposite side of the covering. The cord extends centrally through the compression spring and is connected centrally of the disc. Handling, packing and releasing of the reserve parachute and deployment of the pilot chute is thereby simplified.

Abstract: The invention provides a release device for a secondary parachute canopy intended to operate when during a descent after a main parachute canopy should have been opened by normal operation, the rate of descent exceeds a chosen value indicating some form of failure of the main canopy, comprising a negative rate diaphragm arranged to experience atmospheric pressure on a first side and a reference pressure on the opposite side, an operating member which is movable between a canopy retaining position and a canopy releasing position by movement of the diaphragm, a valve arranged to selectively open the chamber to atmospheric pressure to inhibit operation of the diaphragm, an air bleed arranged to allow air to enter the chamber during a descent to balance the atmospheric pressure on the diaphragm, and a float valve sensitive to rate of descent arranged to close the bleed when a chosen rate of descent is exceeded, thus to trap the reference pressure in the chamber and to apply operating differential pressure to the