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.

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.

In an example, a recovery system is shown, the recovery system comprising: a housing; a parasail comprising a canopy coupled within the housing fastened by a releasable fastener, wherein the parasail is compressed into a compact mass and is configured to rapidly expand; primary ballistics attached to the parasail, wherein the primary ballistics are configured to launch the parachute from the housing; and a guidance system within the housing wherein the guidance system is configured to steer the parasail and guide the recovery system to a landing site.

A selection is made between single stage and multistage parachute deployment for a vehicle based at least in part on vehicle state information. In the event multistage parachute deployment is selected, a drogue parachute is deployed during a first deployment stage and afterwards, a main parachute is deployed during a second deployment stage. In the event single stage parachute deployment is selected, at least the main parachute is deployed in a single stage where in the event the drogue parachute is deployed during the single stage, the drogue and main parachute are deployed simultaneously.

A vehicle recovery system includes a harness having a hub and a plurality of cords each including opposite first and second ends. The first ends are each coupled to the hub. The second ends are each configured to be connected to a fuselage of a vehicle. A tractor rocket includes a body and a bridle. The bridle includes a first end coupled to the body and an opposite second end. A parachute includes a riser, a canopy and a plurality of suspension lines. The suspension lines each include a first end coupled the canopy and an opposite second end coupled a first end of the riser. An opposite second end of the riser is coupled to the hub. The second end of the bridle is coupled to the first end of the riser.

Provided are an ejection device with reduced weight without reducing an ejection speed of an ejected object and a flying object including the ejection device. An ejection device 100 includes a piston member 10, a cylinder 14 which accommodates the piston member 10 and is provided with a hole portion 13 for allowing the piston member 10 to project outward during operation, a push-up member 15 pushed up in one direction by the piston member 10, an ejected object 16 pushed up while being supported by the push-up member 15, and a gas generator 17 which moves the piston member 10 in the cylinder 14, and in the ejection device 100, the push-up member 15 has a support portion 20 disposed on a distal end side of the piston member 10 with a tip of the piston member 10 in a moving direction of the piston member 10 set as a reference.

An aircraft safety apparatus removably disposed on at least a portion of an aircraft, the aircraft safety apparatus including a parachute canister, including a main body to store at least one item therein, and at least one parachute disposed within at least a portion of the main body to reduce a rate of descent of the aircraft in response to extraction from the main body, and a rocket canister removably connected to at least a portion of the main body to at least partially fill at least a portion of the main body with a combustible gas, and a gas canister removably connected to at least a portion of the main body to at least partially fill at least a portion of the main body with a non-combustible gas.

A universal sequencer for an ejection seat may comprise a connector defining a plurality of pin receptacles. A controller may be electrically coupled to the connector. A tangible, non-transitory may be memory configured to communicate with the controller. The tangible, non-transitory memory has instructions stored thereon that, in response to execution by the controller, cause the controller to perform operations, which may comprise determining an ejection seat or aircraft model and determining an ejection sequence based on the ejection seat or aircraft model determination.

In an embodiment, a parachute deployment system includes a parachute coupled to a release via a first load path. The first path includes crown lines. The release is adapted to attach the parachute to a rocket via the crown lines, and disengage the parachute from the rocket if a load shifts from the first path to a second path. The system also includes a line constrainer between the release and the parachute. The crown lines pass through the line constrainer, and the line constrainer is adapted to restrict an extent to which the crown lines are able to extend away from a longitudinal axis. An example release includes a back plate configured to couple a tow line to crown lines and a soft pin. The pin is adapted to separate from the back plate in response to tensioning of the release line, causing the parachute to disengage.

An aircraft includes an airframe parachute system. The parachute system includes an activation system, an extraction system, a harness system, and a parachute assembly.