Abstract: An ejection seat may comprise a seatback, a headrest located at an upper end of the seatback, and a pitot tube rotatably coupled to the headrest. A pitot restraint assembly may be operably coupled to the pitot tube. The pitot restraint assembly may be configured to translate between a restrained state and a released state. The pitot tube may rotate from a stowed position to a deployed position in response to the pitot restraint assembly translating to the released state.

Abstract: A parachute structure includes two canopies. A primary canopy has a central air vent. The primary canopy is attached to an object by primary suspension lines for reducing the velocity of descent of the object. A secondary canopy captures air that exits from the central air vent of the primary canopy. The secondary canopy is attached to the object by control lines. Control of the direction and rate of descent of the parachute is accomplished by adjusting the length of the control lines by way of actuators to alter the distance between the secondary canopy and the primary canopy. Symmetrical changes in the length of suspension lines alter the velocity of descent of the object while asymmetric change steer of the object. In some embodiments, liquid jets ejected from the object increase deceleration and change direction and exterior air bags are deployed to cushion the object from damage.

Abstract: Systems and methods to cut a closing loop to deploy a parachute. The system includes a cutter with a body with a cutter opening that extends through the body and a blade that is movable across the cutter opening. Processing circuitry is configured to signal the cutter to move the blade across the cutter opening. A mount includes a base, a retainer with a channel sized to receive the cutter, and a mount opening that extends through the mount and across the channel. The cutter is configured to fit within the channel with the cutter opening aligned with the mount opening to form a through-opening such that the closing loop extends through the cutter and the mount.

Abstract: To improve safety during a fall of a flying apparatus, a flying apparatus (1) according to a representative embodiment of the present application includes a body unit (2), a lift-force generating part (3) that is connected to the body unit and generates a lift force, a flight control part (14) that controls the lift-force generating part, an abnormality detecting part (15) that detects an abnormality during flight, a parachute device (4) including a parachute (41, 41A) and a parachute accommodating part (42) that accommodates the parachute, and a fall control part (16) that ejects the parachute from the parachute accommodating part according to the detection of the abnormality by the abnormality detecting part.

Abstract: 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.

Abstract: A method for passive aerial cord release mechanisms and an aerial cord release mechanism for an aerial vehicle (AV). A method includes determining a retracting force to be applied to a winch of an aerial vehicle (AV), wherein the determined retracting force is a force required to retract a cord to be coiled around the winch within the AV, and the cord is temporarily coupled to the winch, such that an external force exceeding a predetermined threshold causes decoupling between the cord and the winch.

Abstract: A method of supporting off-wing maintenance of an engine of a specific aircraft includes accessing flight data for a plurality of aircraft including measurements of properties from sensors or avionic systems, and maintenance data that indicates past maintenance or off-wing maintenance of a corresponding engine of each aircraft. A machine learning model is built to predict a life expectancy of the engine of the specific aircraft, measured to future off-wing maintenance of the engine, using a machine learning algorithm, and a set of features produced from selected properties. The machine learning model is built further using a training set produced from the set of features, the flight data including measurements of the selected properties, and the maintenance data. The machine learning model is then output for deployment to predict and thereby produce a prediction of the life expectancy of the engine of the specific aircraft from distinct flight data.

Abstract: Disclosed is a technique for landing a drone using a parachute. The technique includes a parachute deployment system (PDS) that can deploy a parachute installed in a drone and land the drone safely. The parachute may be deployed automatically, e.g., in response to a variety of failures such as a free fall, or manually from a base unit operated by a remote user. For example, the PDS can determine the failure of the drone based on data obtained from an accelerometer, a gyroscope, a magnetometer and a barometer of the drone and automatically deploy the parachute if any failure is determined. In another example, the remote user can “kill” the drone, that is, cut off the power supply to the drone and deploy the parachute by activating an onboard “kill” switch from the base unit.

Abstract: A parachute assembly may comprise a canopy and a plurality of suspension lines coupled to the canopy. Each of the suspension lines may include an elastomeric insert coupled between a first portion of the suspension line and a second portion of the suspension line. At least a portion of the elastomer insert may be located within an internal volume of the suspension line.

Abstract: Provided herein is a canopy control system comprising a yoke, configured to be pivotably securable to a vehicle and securable to a line system of a canopy in use, such that the yoke pivots with respect to the vehicle in a first direction when the canopy is subjected to a wind force; and a control mechanism configured to apply a control force to the canopy line system to cause the canopy to oppose the wind force, such that yoke pivots with respect to the vehicle in a second direction which is opposite to the first direction.

Abstract: A delivering method using an unmanned aerial vehicle includes configuring a pre-set condition, locking a cargo, acquiring verification information about a recipient, comparing the verification information with the pre-set condition, and determining that verification is passed to unlock the cargo when the verification information is consistent with the pre-set condition.

Abstract: A cinched parachute is disclosed. In various embodiments, a cinched parachute as disclosed herein includes a canopy comprising one or more sections of canopy material, and a device integrated with the canopy that controls dimensions of the canopy material. For example, in some embodiments the device may be used to control the size of an opening atop the parachute.

Abstract: Disclosed is a control device for power kites. It consists of a tall Y-shaped structure, the base of which is connected to the center of a horizontal control bar arranged perpendicular to the structure. An articulation forms the connection between the base of the structure and the center of the horizontal control bar. The control lines for the leading edge and the control lines for the trailing edge of a power kite are attached to the front and rear pre-lines of the device. Compared to a standard kite bar, the disclosed control device makes it easier for the user to balance using very short lines.

Abstract: A system for translating a head restraint of a parachute assembly away from a head of an occupant supported by the parachute assembly may comprise a chord coupled to the head restraint and at least one of a control line configured to manipulate a canopy of the parachute assembly or a handle coupled to the control line.

Abstract: 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.

Abstract: A parachute inlet control system is configured to provide an improved inflation profile for solo and/or clustered parachutes. An inlet parachute is coupled to a main parachute via a plurality of inlet control suspension lines and/or reefing rings. The inlet control suspension lines may be passed through the reefing rings and coupled to an anchor point below the main parachute. The inlet parachute is located in the inlet area of the main parachute, and causes the inlet of the main parachute to rapidly form a desirable shape. The inlet parachute and inlet control suspension lines function as a reefing system to prevent full inflation of the main parachute until a reefing cutter has functioned. In this manner, parachute failures, such as those due to leading and/or lagging parachutes in a parachute cluster, may be reduced or eliminated.

Abstract: A parachute inlet control system is configured to provide an improved inflation profile for solo and/or clustered parachutes. An inlet parachute is coupled to a main parachute via a plurality of inlet control suspension lines and/or reefing rings. The inlet control suspension lines may be passed through the reefing rings and coupled to an anchor point below the main parachute. The inlet parachute is located in the inlet area of the main parachute, and causes the inlet of the main parachute to rapidly form a desirable shape. The inlet parachute and inlet control suspension lines function as a reefing system to prevent full inflation of the main parachute until a reefing cutter has functioned. In this manner, parachute failures, such as those due to leading and/or lagging parachutes in a parachute cluster, may be reduced or eliminated.

Abstract: A parachute deployment system is disclosed. In various embodiments, the system includes an interface configured to receive sensor information; a parachute load limiting device; and a parachute load limiting device state controller. The parachute load limiting device state controller sets a state of the parachute load limiting device to a state associated with a corresponding amount of load based at least in part on the sensor information.

Abstract: The present invention relates to a method for replacing a signal controlling an actuator in a remote-controlled flying device with another signal. A flight controller supplies control signals to a safety device, and the signal to be replaced may be a signal to be transmitted by the safety device to a speed controller of at least one motor, or to a servo unit controlling the same, or the signal to be replaced may be a signal to be transmitted from the safety device to a servo unit controlling legs, a camera rack, a camera, a stabilizing system or an electric motor of the flying device. A replacement signal is a signal stored in a memory of the safety device.

Abstract: In some embodiments, apparatuses and methods are provided herein useful to delivering climate controlled product. In some embodiments, there is provided a system for delivering climate controlled product via at least one autonomous unmanned aircraft system (UAS) that self-evaluates power sufficiency based on temperature tolerance of at least one product including: an autonomous UAS and at least one climate controlled product chamber. The UAS comprising: a control circuit, at least one rotor; a power supply, and a package coupler. The product chamber comprising: a chamber, at least one product reader, and a temperature control mechanism. The control circuit configured to: receive product identifier data; determine at least one climate threshold value; determine a confidence value of sufficient power remaining; compare whether the confidence value is within a risk threshold probability that a first mission will be completed; and initiate supply of power to the at least one rotor.

Abstract: A front flying line kite depower system includes a line sheath that extends through a transverse opening in the control bar. A front flying line parting fitting is non-rotatably fixed to an upper end of the line sheath above the control bar. When a manual rotation force is imparted to the line sheath, the relative positioning of a first front flying line and a second front flying line is altered by the front flying line parting fitting to untangle any twisting above the line sheath. Within the line sheath, the second front flying line is off-set from a primary axis and orbits the first front flying line which is positioned on the primary axis to avoid any tangling during manual adjustment.

Abstract: Systems and methods for delivering packages via aerial vehicles are disclosed. The system can comprise a label that includes a parachute to enable the packages to be dropped from the aerial vehicle, yet land at the package's destination without damage. The system can include a self-adhesive backing, a plurality of parachute cords, a parachute, and a breakaway cover. The parachute cords can include a shock absorber to reduce the shock on the package of the parachute opening. The parachute and/or the breakaway cover can include graphics to provide address, velocity, or spin information for the package. The parachute cords can include a harness to separate the cords and reduce tangling of the cords and spinning of the parachute canopy with respect to the package.

Abstract: A multi-staged suspension line length parachute is provided. The parachute may comprise a canopy, a suspension line, a bundle, a bundling confluence, a traditional confluence, and a riser. The parachute may also comprise a cutter and a cutter pin puller configured to activate the cutter. The bundle may comprise a bundling line configured to secure secondary length from the suspension line. The parachute may deploy to a first length. In response to tension on the cutter pin puller, the cutter may activate to sever the bundling line in the bundle, causing the secondary length of the suspension line to release. The parachute may then deploy to a second length.

Abstract: A steerable container delivery system (“CDS”) includes a pallet configured with inflatable fins for steering a CDS cargo bundle during free fall when airdropped. The inflatable fins are inflated shortly after deployment using compressed air carried by a tank in the pallet. A flight management computer (“FMS”) continuously monitors the location of the CDS bundle using GPS technology and determines a vector to a drop location based on stored GPS measurements. The FMC continuously monitors and positions the CDS bundle over the drop location, and is able to independently rotate the fins to control the position of the CDS bundle, either by rotating the CDS bundle or laterally moving it. At the appropriate altitude, the FMC causes the main parachute to open to slow the descent of the CDS bundle for impact.

Abstract: A method and apparatus comprising a housing, a processor unit, a display, a navigation module, and a number of modules. The navigation module is configured to guide an airdrop system to a target location. The number of modules is configured to provide functions for use by a number of operators to perform a mission in addition to an airdrop.

Abstract: Embodiments described herein provide a system and method for persistent high-accuracy payload delivery utilizing a two-phase procedure during the terminal descent phase of aerial payload delivery. In the first phase a small parafoil provides aerial delivery of a payload to within a close proximity of an intended touchdown point, e.g., a target. In the second phase a target designator acquires the target and a trajectory to the target is determined. A harpoon launcher deploys a harpoon connected to the payload by an attachment line, such as a rope. A reel mechanism reels up the attachment line causing the payload to be moved to the target thus providing high accuracy touchdown payload delivery.

Abstract: A parachute can be opened automatically without requiring manual operation. In addition, the parachute is capable of staying balanced during the course of landing. The parachute comprises: a spherical canopy, an air guide member and four assistant canopies. The air guide member is a rotation symmetrical structure with respect to the central axis, each of the cylindrical members is also a rotation symmetrical structure with respect to the assistant central axis, and the assistant canopies are also symmetrically arranged with respect to the central axis, so as to maintain the parachute in a stable and balanced state when the parachute is falling.

Abstract: Systems and methods for health monitoring of complex systems are disclosed. In one embodiment, a method includes receiving a plurality of signals indicative of observation states of plurality of operating variables, performing a combined probability analysis of the plurality of signals using a diagnostic model of a monitored system to provide a health prognosis of the monitored system, and providing an indication of the health prognosis of the monitored system. In some embodiments, the monitored system may be an onboard system of an aircraft.

Abstract: A method of controlling a ram air parachute using a variable trim platform is disclosed. In a particular embodiment, the method includes securing a front trim control line between a front portion of the variable trim platform and a guidance control unit and securing a rear trim control line between a rear portion of the variable trim platform and the guidance control unit. The method also includes securing ram air parachute suspension lines between the variable trim platform and the parachute and securing guidance unit risers between the variable trim platform and the guidance unit. An attachment point of the guidance unit risers to the variable trim platform is separate from an attachment point of the suspension lines to the platform to create a pivot point for the variable trim platform to rotate about.

Abstract: The invention relates to an unmanned air vehicle control system and method, designed such that, in one mission mode, the vehicle follows the mission route. The system comprises means (400, 450) for storing data indicating at least one auxiliary route (4000, 4001, 4002, 4003), such that each of a plurality of the mission route segments (10, 20), is assigned at least part (30, 31, 32, 33) of at least one auxiliary route. Furthermore, the system comprises route change means (53) designed for, as a response to a mission abandonment event (52), determining which part of which auxiliary route is assigned to the mission route segment where the vehicle is located, such that the vehicle can change the mission route to the corresponding auxiliary route.

Abstract: A surveillance vehicle (10) comprising a vessel (11) and a parasail (12). The vehicle (10) is loaded, in a pre-launch condition, into a mortar tube for projection therefrom towards an area of interest. In this pre-launch condition, the vessel (11) resembles a conventional mortar round and the parasail (12) is stowed within the vessel (11). Upon arrival at the area of interest, the parasail (12) is deployed from the vessel (11) and instrumentation collects survey data.

Abstract: The present invention relates to an autonomous stratosphere platform which is preferably intended to be positioned in the stratosphere, is carried by a carrying shield (1) and is controlled by a control and drive unit (3) which can use control elements (301) to control the carrying shield (1) via lines (302). A cable (5) is used to connect the control and drive unit (3) to a capsule (2) which is intended to hold a payload and the requisite electrical and electronic components for operating the autonomous stratosphere platform. A control element (8) having an anchoring shield (6) is fastened to the capsule (2), again on a cable (5). The stratosphere platform experiences uplift as a result of the wind gradient between the wind layer of the anchoring shield (6) and that of the carrying shield (1).

Abstract: A refueling system on an aircraft comprises a fuel hose coupled to the aircraft, a drogue coupled to the fuel hose, an air data computer, and a drogue canopy controller coupled to the drogue canopy. The drogue further comprises a coupling, a plurality of vanes, and a drogue canopy. The drogue canopy controller determines a selected surface area of the drogue canopy based on air speed. The drogue canopy controller is configured to modify a surface area of the drogue canopy to conform to the appropriate surface area.

Abstract: The invention relates to a steering unit for a wind propulsion system, the steering unit comprising a first fixed attachment means for securing a first end of a tractive cable the second end of which is secured to a device or a vehicle to which a tractive force shall be transferred, a second attachment means for attaching a number of tractive lines, the second end of which being secured to an aerodynamic wing element, a mechanical support frame connecting the first attachment means to the second attachment means for transferring a tractive force. The invention aims at providing such a steering unit with improved design for better maneuverability and stability.

Abstract: A reefing slider for providing improved line management and canopy deployment characteristics of a ram air inflated airfoil type canopy. During initial descent of the parachute the slider, secured by retaining elements, is held against the canopy in the upper reefing position where it mechanically restricts canopy deployment while giving the canopy time to achieve proper orientation following the drop from the launching aircraft. Upon sufficient air flow into the canopy cells, the retaining elements separate, releasing the slider and enabling full opening of the canopy.

Abstract: A parachute inlet control system is configured to provide an improved inflation profile for solo and/or clustered parachutes. An inlet parachute is coupled to a main parachute via a plurality of lacing loops and/or reefing rings. The lacing loops may be passed through the reefing rings and/or may be routed around one or more of the main parachute suspension lines. The inlet parachute is located in the inlet area of the main parachute, and causes the inlet of the main parachute to rapidly form a desirable shape. The inlet parachute and lacing loops function as a reefing means, and prevent full inflation of the main parachute until a reefing cutter has functioned. In this manner, parachute failures, such as those due to leading and/or lagging parachutes in a parachute cluster, may be reduced or eliminated.

Abstract: An apparatus for supporting a parachute flight controller from a parachute comprises a bearing member, for example a pulley, a load-bearing coupling, for example a harness, connected to the bearing member and including a connector for connecting the coupling to a parachute flight controller. The coupling includes a load-bearing connector for connecting a payload thereto, and the bearing member is adapted to enable relative movement, controlled by the flight controller, between the bearing member and a support member, for example a flexible coupling line or web for supporting the bearing member connected between first and second suspension lines of a parachute. The flight controller may include one or more control lines connected to the support member or suspension lines which can be wound in or out of the flight controller to effect relative movement between the bearing member and the support member and thereby control the direction of the parachute.

Abstract: A parachute inlet control system is configured to provide an improved inflation profile for solo and/or clustered parachutes. An inlet parachute is coupled to a main parachute via a plurality of lacing loops and/or reefing rings. The lacing loops may be passed through the reefing rings and/or may be routed around one or more of the main parachute suspension lines. The inlet parachute is located in the inlet area of the main parachute, and causes the inlet of the main parachute to rapidly form a desirable shape. The inlet parachute and lacing loops function as a reefing means, and prevent full inflation of the main parachute until a reefing cutter has functioned. In this manner, parachute failures, such as those due to leading and/or lagging parachutes in a parachute cluster, may be reduced or eliminated.

Abstract: A hybrid parachute, method of deploying a parachute and method of landing a payload. The hybrid parachute utilizes a reefing system that provides for the initial deployment of a deceleration stage that is configured to withstand the stresses of high-speed and/or high altitude openings. The deceleration stage has operating characteristics similar to known high-speed parachutes. After sufficient deceleration has been achieved with the deceleration stage, reefings are released deploying one or more low-speed high drag stages of the device. The high drag stage(s) provide the landing characteristics of a low-speed parachute, including the possibility of controlled descent and landing.

Abstract: A parachute inlet control system is configured to provide an improved inflation profile for solo and/or clustered parachutes. An inlet parachute is coupled to a main parachute via a plurality of lacing loops and/or reefing rings. The lacing loops may be passed through the reefing rings and/or may be routed around one or more of the main parachute suspension lines. The inlet parachute is located in the inlet area of the main parachute, and causes the inlet of the main parachute to rapidly form a desirable shape. The inlet parachute and lacing loops function as a reefing means, and prevent full inflation of the main parachute until a reefing cutter has functioned. In this manner, parachute failures, such as those due to leading and/or lagging parachutes in a parachute cluster, may be reduced or eliminated.

Abstract: An aerial delivery system is configured to allow delivery of one or more releasable items after the system is extracted from an aircraft. One or more linear guidance devices and releasable securing mechanisms allow the aerial delivery system to deploy one or more releasable items at an appropriate time. The one or more releasable items may be deployed simultaneously, or in a staged or staggered fashion. Through use of drag or lift-producing devices, the system may be recovered and reused. The attitude and/or azimuth orientation of the system may be varied prior to, during, and/or after release of a releasable item.

Abstract: A safety pre-impact deceleration system for a variety of conveyances includes a parachute structure formed from air bags inflated with gas. Alternatively, the parachute structure includes a canopy with orifices. Air spaces in the parachute structure or orifices in the canopy have adjustable and selective dimensions to control the operational parameters of the vehicle. The system includes sensors and rapid exposure rate cameras with continuous loop recording to measure operational parameters of the vehicle and to predict possible collision. Once a collision condition is detected, audio/video images are stored on storage media. The air bags are deployed and inflated. In addition to air bags constituting the parachute structure, a plurality of air bags are provided to be deployed external the vehicle to aid in a safe landing.

Abstract: An AGU adapted for one-time use is provided for use with a parachute. The AGU has a frame made of wood, plywood or other biodegradable material to which the parachute suspension lines are secured. The frame includes an exterior wall having an access portal to a compartment within which an avionics unit is mounted so that one side of the avionics unit remains exposed and substantially flush with the exterior wall. The avionics unit is secured to the frame around the perimeter of the access portal using connecting elements that can be removed by accessing only the exterior wall of the frame so that the avionics unit can be easily removed following deployment. The AGU also includes a harness that is wrapped around at least a part of the AGU frame and which provides multiple attachment points for securing of the AGU to the parachute suspension lines as well as to a payload, eliminating the need for any harness structural attachment points on the AGU frame.

Abstract: A method for controlling the drag area growth of a parachute canopy during airborne descent with sensors attached to the payload for facilitating modification of the schedule of release of a parachute canopy reefing mechanism. A control processor is included that can receive and/or calculate a schedule for disengaging the reefing on the parachute. One or more wireless transmitters at the payload transmit the releasing signal from the payload to the reefing mechanism normally located adjacent the parachute canopy. The control processor can also be configured to receive input information from multiple sensors attached to the payload that monitor parameters such as altitude, position, load force, dynamic pressure, time and others to facilitate instantaneous recalculation of the disreefing schedule responsive to such conditions.

Abstract: A method for controlling the drag area growth of a parachute canopy during airborne descent with sensors attached to the payload for facilitating modification of the schedule of release of a parachute canopy reefing mechanism. A control processor is included that can receive and/or calculate a schedule for disengaging the reefing on the parachute. One or more wireless transmitters at the payload transmit the releasing signal from the payload to the reefing mechanism normally located adjacent the parachute canopy. The control processor can also be configured to receive input information from multiple sensors attached to the payload that monitor parameters such as altitude, position, load force, dynamic pressure, time and others to facilitate instantaneous recalculation of the disreefing schedule responsive to such conditions.

Abstract: A system collaboratively and autonomously plans and controls a team of vehicles having subsystems within an environment. The system includes a mission management component, a communication component, a payload controller component, and an automatic target recognition component. The mission management component plans and executes a mission plan of the team and plans and executes tasks of the vehicles. The communication component plans communication and networking for the team. The communication component manages quality of service for the team. The communication component directs communication subsystems for the team and for the vehicles. The payload controller component directs and executes sensor subsystems for the team and for the vehicles. The automatic target recognition component processes and fuses information from the sensor subsystems and from the vehicles for use by the mission management component.

Abstract: An apparatus for controlling the drag area growth of a parachute canopy during airborne descent with sensors attached to the payload for facilitating modification of the schedule of release of a parachute canopy reefing mechanism. A control processor is included that can receive and/or calculate a schedule for disengaging the reefing on the parachute. One or more wireless transmitters at the payload transmit the releasing signal from the payload to the reefing mechanism normally located adjacent the parachute canopy. The control processor can also be configured to receive input information from multiple sensors attached to the payload that monitor parameters such as altitude, position, load force, dynamic pressure, time and others to facilitate instantaneous recalculation of the disreefing schedule responsive to such conditions.

Abstract: A parachute inlet control system is configured to provide an improved inflation profile for solo and/or clustered parachutes. An inlet parachute is coupled to a main parachute via a plurality of lacing loops and/or reefing rings. The lacing loops may be passed through the reefing rings and/or may be routed around one or more of the main parachute suspension lines. The inlet parachute is located in the inlet area of the main parachute, and causes the inlet of the main parachute to rapidly form a desirable shape. The inlet parachute and lacing loops function as a reefing means, and prevent full inflation of the main parachute until a reefing cutter has functioned. In this manner, parachute failures, such as those due to leading and/or lagging parachutes in a parachute cluster, may be reduced or eliminated.

Abstract: A deployment brake release system for use with an airborne guidance unit (AGU) of a parachute suitable for precision cargo delivery. The parachute includes deployment brake lines secured at one end to the edge of the canopy and connected at the other end through looped ends to motor control lines. The motor control lines are, in turn, engaged with the motor of the AGU. The deployment brake release system includes at least one hook mount having a hook secured to the AGU frame. The looped ends of the deployment brake lines are engaged with the hook during rigging so that, upon deployment, opening forces are applied to the hook mount rather than the motor. After full canopy inflation, the motor, via the motor control lines, pulls on the brake line looped ends to disengage them from the hook, transferring subsequent canopy loads to the AGU motor for the remainder of the flight. A method for releasing the deployment brake lines is also disclosed.

Abstract: The present invention relates to an autonomous stratosphere platform which is preferably intended to be positioned in the stratosphere, is carried by a carrying shield (1) and is controlled by a control and drive unit (3) which can use control elements (301) to control the carrying shield (1) via lines (302). A cable (5) is used to connect the control and drive unit (3) to a capsule (2) which is intended to hold a payload and the requisite electrical and electronic components for operating the autonomous stratosphere platform. A control element (8) having an anchoring shield (6) is fastened to the capsule (2), again on a cable (5). The stratosphere platform experiences uplift as a result of the wind gradient between the wind layer of the anchoring shield (6) and that of the carrying shield (1).