Abstract: A pitot tube restraint system is disclosed herein. The pitot tube restrain system includes an outer shaft, a pitot tube coupled to a first end of the outer shaft and extending outward from the outer shaft, a torsion spring disposed around the outer shaft, a stop pad coupled to the first end of the outer shaft, a base disposed adjacent the second end of the outer shaft, an inner shaft having disposed through the outer shaft, a first end of the inner shaft rotationally coupled to the stop pad and a second end of the inner shaft rotationally coupled to the base, a pawl disposed around the inner shaft and adjacent the second end of the outer shaft, the pawl configured to engage the second end of the outer shaft to prevent the pitot tube from rotating in a first direction, and a pawl spring disposed around the inner shaft.

Abstract: A rope severing device for cutting a rope after a continued compressive force is disclosed. The rope severing device includes a housing having a base and a top and the top is movably mounted to the base such that the top can move axially with respect to the base. A blade is positioned at least partially within the housing and fixedly mounted with respect to the base. In some embodiments, an elastic member is positioned inside the housing in contact with the base and a damper is attached to the base to dampen relative movement of the top and the base. Upon application of a compressive force to the housing, the top moves toward the base and the blade is at least partially exposed through an opening in the top to sever a rope attached to the rope severing device.

Abstract: A multi-satellite system includes a first satellite and a second satellite configured to be separated in a predetermined distance between the satellites after being launched into space, and a tether including an optical fiber having first and second ends, wherein the first end is connected to the first satellite and the second end is connected to the second satellite, wherein a length of the tether is greater than the predetermined distance. In this case, the first satellite includes an optical transceiver connected to the first end of the optical fiber to provide a communications link to the second satellite, a spool containing partial winding of the tether, and a free space optical transceiver to provide a first communications link to a first distant satellite.

Abstract: A programmable electronic initiation device that monitors flight parameters to accurately initiate parachute disreefing or disconnect. Tracking elapsed time commencing with a startup trigger and directly measuring atmospheric conditions; temperature and pressure are used for altitude or speed calculations in addition to monitoring the acceleration sensor and liquid contact sensor for impact sensing. The device is user programmable via a software application for initiation based upon elapsed time, altitude, speed, and/or upon landing. The device may also be separated into a sensing module and an actuating module, and linked wirelessly to allow control of one or multiple actuating modules by one sensing module.

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: In one form of the invention, a deployment control for releasing a rocket recovery device such as a parachute includes an electrical heating element extensible along a heat-severable reach of an elongate retainer capable of being wrapped closely about the recovery device to retain the recovery device in a compact form until the reach is severed as the result of electricity being supplied to the heating element to thereby release and deploy the recovery device. In other forms, an apparatus for cutting a heat meltable retainer to release and deploy a rocket recovery device includes a heating element extending along at least a short reach of the retainer, and a control device for supplying electricity to the heating element for heat severing the retainer reach.

Abstract: An automatic activation device for a parachute has a pressure input for inputting a pressure value and is provided for operating in selectable working configurations according to which a reference pressure is determined either on the basis of the input pressure value or on the basis of a QNH value. Preferably the device can also operate in another selectable working configuration, where a preset time and a reference fall down speed are used.

Abstract: An ejection delay system, apparatus and/or method including an electronic ejection delay system having an ignition device; a power source connected to the ignition device; and, a flight parameter sensor switch electrically connected to the power source to initiate the provision of power from the power source to the ignition device; the electronic ejection delay system being disposed in some implementations in a housing system including a housing; a forward closure for closing the top end of the housing; and, an aft closure for closing the aft end of the housing. Also disclosed is a method for ejecting a rocket recovery system in flight; including sensing a parameter associated with flight; and, initiating deployment of a recovery system.

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: 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 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: A parachute control system is actuated primarily by drogue parachute drag force. Drag force is used as a proxy for vehicle airspeed. The control system uses altitude and force sensors combined with a chronograph to determine the state of a deployed drogue parachute. It then compares the sensed condition with a condition defined by preset altitude, force, and time values. Once both altitude and drogue parachute drag force are below certain maximum values and within pre-determined time windows, an event trigger signal is generated.

Abstract: The present invention is directed to a parachute reefing system having a flexible ring section. The flexible ring section has a circumference. The reefing system includes a plurality of equidistantly spaced loops attached to the flexible ring section and a plurality of link members wherein each link member is attached to a corresponding loop and sized to allow at least one suspension line to pass therethrough. The reefing system also has a cross-connecting section comprising pair of intersecting members that are attached to the flexible ring section. The intersecting members are attached to each other at an intersection point that is coincident with the center of flexible ring section. The reefing system has a position cord having a first end attached to the intersection point and a second end opposite the first end. A yoke is attached to the second end of the position cord and has a vertex and at least two legs that extend from the vertex. Each leg extends from the vertex to a distal end.

Abstract: A setting mechanism for a triggering device employs a knob fixed to a rotating part of the triggering device. The knob carries a selector lever that is pivotable to radially project from the knob in angularly spaced directions. Arcuate walls surround the knob to define gaps corresponding to alternative rotational periods for the knob. The selector is pivoted to travel in one or the other gap. The selected rotational period may correspond to a predetermined time.

Abstract: A hydraulic mechanism is positioned within the drogue bridle of a parachute system. The hydraulic link is slowly moved by tension on the drogue bridle to operate a release. The release operates to release the drogue chute and to deploy the main chute. The movement of the hydraulic link provides a time delay between deployment of the drogue chute and the main chute to allow the load to stabilize before deployment of the main chute.

Abstract: A system for providing an interface between a launch vehicle and a payload of the launch vehicle includes payload integration points of the launch vehicle that remain unchanged relative to different payload configurations, such that a payload is configurable apart from the launch vehicle. The system makes it possible to de-couple payload installation and launch vehicle turnaround operations. Payloads can be configured off-line from launch vehicle processing, thus making it possible to accommodate unique payloads while reducing wear and tear on the launch vehicle.

Abstract: An experiment system with six different re-entry experiment locations for testing high temperature re-entry materials, creating new thermal protection systems, proving innovative new concepts for spacecraft exterior surfaces and the incremental development of next generation aerospace materials. A commercial transportation system to and from orbit provides a 24-hour return cycle for the experiments on a surface actually re-entering the earth's atmosphere. Now using existing doors, hatches and other points on the reusable launch vehicle's exterior, the actual re-entry environment is experienced by test specimens with quick turn around for a wide variety of different re-entry temperatures ranges for broad testing and development purposes. The reusable launch vehicle launches, remains in orbit for 24 hours and returns to provide an actual test environment for the exterior experiment system.

Abstract: A drinking straw for consuming a beverage is prepared by: a) melt-extruding a polymeric material in the shape of a continuous tubular conduit suitable for preparing a plurality of drinking straws; b) cooling said continuous tubular conduit to a temperature below the softening point of the polymer; c) flattening the tubular conduit so as to collapse its structure into a substantially planar form, thereby constricting the central longitudinal cavity and reducing the volume of the continuous tubular conduit; d) cutting a length from the continuous conduit of suitable length for making the straw; and e) dilating the length cut from the conduit so as to restore the cross-sectional area of the central cavity and reconstitute the tubular structure of the straw. Advantages of the invention include minimizing storage space and shipping bulk, as well as reducing the need for packaging materials.

Abstract: The present invention relates to multi-segment air bag tether panels and to a pattern-wise arrangement of such tether segments in relation to air bag panels on a fabric blank. In one embodiment, the tether panel is comprised of two or more tether segments that are cut in substantial alignment with the warp or the fill of the fabric blank. The tether panels are then connected to one another along their tether-attachment ends to form a functional tether system. This multiple-segment construction decreases the amount of fabric that is used in the manufacture of the air bag and tethers, while providing sufficient elongation for the tether system to be functional.

Abstract: An elliptical satellite system which carries out communication. The satellite orbits a height above the earth less than that necessary for geosynchronous orbits. When the satellite is near the apogee portion of its orbit, its velocity approximates the rotational velocity of the earth, and during that period it appears to hover over the earth. Each ground station on the earth always communicates a satellite within a predetermined position of its apogee, and hence that satellite appears to the ground station to hover over the earth. The satellite hence does not communicate with any earth station when it is outside of that apogee portion. During the times when the satellite is outside the apogee portion, its communication is therefore shut off to prevent.any possibility of interfering with geosynchronous satellites. During this time, the power supply on the satellite is also used to charge a battery on the satellite.

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: 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 tether (FIG. 6) having the special technical feature of multiple primary load-bearing lines (601,603) and normally slack secondary lines (605, 603). These primary and secondary lines are connected together with knotless, slipless interconnections so the tether maintains high strength and some of the lines can be cut without failure of the tether when it is operated near the ultimate failure load of the material from which it is constructed. This tether can safely carry (FIG. 31) load hundreds of times longer than prior art tethers in harsh environments where a single-line tether experiences a substantial risk of failure. The specific industrial applications of an electrodynamic tether system to deorbit satellites and a low Earth orbit to lunar surface tether transport system are all part of the general innovative concept of the invention.

Abstract: A method for automatic resetting of a timer according to the exit time when an item starts descending from a flying object. The resetting is based on a number of altitude values, which are continuously measured by performing air pressure measurements or position measurements. Furthermore, a microprocessor based apparatus implementing said method is described. The timer can be used for activating an external mechanical or electrical apparatus e.g. a canopy or an audible warning device.

Abstract: The present invention relates to a parachute release device comprising a data processing and acceleration determining means connected to said data processing system and provided for determining an acceleration parameter indicating the acceleration of a falling object to which the parachute is attached, said data processing system being provided for calculating from said acceleration parameter and a jump duration time an instant speed and an instant height value, and for generating a release signal for opening said parachute when said instant height value reaches an opening height value.

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 deceleration device for a submunition unit ejectable from a spin stabilized carrier projectile includes a deployable deceleration element. The deceleration element is packaged in textile package including an essentially circular disc, at least three straps connected and arranged radially to the disc, with each strap having a free end and provided with a loop and a closing line received through the loops for pulling the loops together to close the package about the deceleration element. An activation line is connected to the closing line and held by the textile package for releasing the closing line for allowing the package to open for deployment of the deceleration element after the activation line is released from the package by being stretched in a controlled manner.

Abstract: A submunition unit provided with a rotary parachute (3) as the sole parachute. The parachute, after release, initially is unable to be fully deployed due to reef loops (16) provided on the rigging lines (15) and held by a releasable holding device arrangement (4, 5, 6) and therefore acts as a deceleration and stabilization parachute at high flight velocities. The reef loops (16) are released after a predetermined period of time to permit the rigging lines (15) to fully extend and parachute (3) to become fully deployed or opened.

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 electro ballistic escape sequencing system is actuated only by the seat initiators. Current entering the system by any other means will see only open circuits. A pressure sensitive switch is provided in each circuit subject to outside interference and is normally in the open position. When ejection is required, pressure from one of the seat initiators activates the thermal battery and closes all circuits required for ejection.

Abstract: A parachute deployment actuator incorporating an aneroid with a relatively long strike results in a significant diminution in the degree of precision with which the associated parts have to be made. A spring is provided externally of the aneroid in such relationship as to augment the natural spring force tending to expand the aneroid, such spring operating not only to keep the aneroid off its internal stop at sea level but also to cause the overall system to have a desired spring rate. A variable lever system inter-relates a preprinted scale and associated altitude cam with the aneroid in such relationship that the parachute actuator will release the chute very near a pre-set altitude.

Abstract: A tether line is connected between a rocket launched flare and the canopy of a supporting parachute to cause the parachute to collapse and fall to the earth along with the burned out flare upon release of the single support cable.

Abstract: A dual redundant pitot-static sensing system for use in a system for deplng a parachute during ejection of an occupant from a disabled aircraft includes a pair of pressure-sensitive check valves to store peak dynamic airstream pressure for obviating difficulties experienced when the pitots are blocked by airborne debris.

Abstract: An electronic system for selecting the proper mode sequence for deploying a ecovery parachute from an aircraft ejection seat. The system senses altitude, airspeed, and sink rate; and compares these to predetermined reference signals. The system also incorporates logic circuits and time delay circuits. The logic circuits are arranged to select one of four time delays depending on the status of the various parameters relative to the reference signals.

Abstract: An aircraft ejection seat system which incorporates means for permitting deployment of a main parachute at the end of a delay after ejection and a mode selector mechanism operable to permit such deployment at a shorter predetermined time after ejection if ejection takes place at low speed and low altitude. The mode selector mechanism incorporates a piston slidable along a bore to operate a firing pin to fire a cartridge and thus initiate the earlier deployment of the parachute. Means for sensing barometric pressure, air speed, and deceleration are arranged, if the sensed value indicates the longer delay period is required, to project respective plungers transversely into the bore to prevent the piston from striking the firing pin. A further plunger remains projected into the bore unless auxiliary sensing means positively senses low speed and altitude.

Abstract: A parachute deployment sequencer includes two sequencer systems in electromagnetic shielding housings. Each housing contains two bellows connected to pitot tubes, a third bellows for measuring ambient pressure and three switch contact sets connected in series, each contact set being operated by one of the bellows. Each housing also contains a battery actuated by seat ejection and a deployment firing circuit with a series switch circuit in between. After ejection, deployment is initiated when all three switches are closed.

Abstract: In a time-delayed device for opening a parachute, a spring-loaded cable is coupled to a cylindrical translational gear for conjoint movement. When the cable is released from a cocked position and spring-driven to a release position at which it opens the parachute, the translational gear is driven past the input gear of a gear train. As it moves, the translational gear engages and rotates the input gear along and through an effective gear engagement length which may be selectively varied by rotating the translational gear with respect to the input gear. An adjustable escapement contacts the gear train output gear and retards rotation of the input gear, and thus retards the rate of movement of both the translational gear and the cable, during engagement between the input gear and the translational gear through the selected effective engagement length.

Abstract: An automatic line release system for severing parachute suspension lines at a pre-set time in order to evaluate parachute performance under controlled conditions. The line release system utilizes an electronic timer and switching circuit to energize strands of wire ("burn" wire) wrapped about the desired suspension lines at a point near the riser connector links to burn through the lines and thereby release them.

Abstract: A release mechanism for use with an air-dropped store having a timed firing echanism which can be set for different time intervals. Action is initiated by a plurality of dynamic pressure sensing fins which, upon actuation, first unlock an inertia locking arm and then the fins impart a rotation to the store which rotation, in turn, causes the locking arm to pivot and initiate a timer. The timer, in turn, initiates separation of the release mechanism from the store.