Abstract: An adaptive guidance system (AGS) regulates the altitude and heading of a parasail to arrive at a target at a prescribed altitude. Since the altitude profile depends both on unknown wing loading, and wind magnitude and direction, the AGS estimates the glide slope and wind on the fly and provides a command to a stability augmentation system (SAS) that results in the desired glide slope and heading by performing a sequence of maneuvers and sensing the response. According to one embodiment, the SAS operates in the linear region and includes a PID controller that uses the difference between the actual heading and heading command to create an actuator output. The actuator output is limited by a position/rate limiter that imposes the physical limitations of the response time of the actuator/servos and position limits to prevent entering the nonlinear region.

Abstract: The present invention relates to a method of providing a nearly continuously updated, on-line estimate of wind magnitude and direction when in turning flight and more particularly, relates to a method that requires only a GPS receiver and y- and z-body axis mounted gyros.

Abstract: A system and method of deploying a parachute system, wherein the system functions with a timed delay or without a timed delay. The system can include a primary static line and a release-away line, wherein the primary static line is connected to a main chute and also to a soft link. The soft link can be cut by a cutter, thereby releasing the parachute system from an aircraft. Alternatively, the primary static line may contain a cable, wherein the cable features a three or more loop assembly that allows for release of the primary static line from the aircraft. The system may also utilize a three ring assembly or other mechanical actuation device. The system may include a drogue chute as well as a main chute.

Abstract: A multimodal vehicle includes a ground based vehicle with an attached high-capacity airfoil parachute for deployment. The ground based vehicle includes a drive system for use on either land, water or both. Furthermore, the ground based vehicle is sized and dimensioned for transport of multiple vehicles in a cargo plane. The high-capacity airfoil parachute allows high-altitude deployment of the multimodal vehicle. The risers to the parachute may be adjusted for powered parachute flight rather than free fall flight. The ground based vehicle may include a propeller for powered flight.

Abstract: A navigational computer design for high altitude and other similar navigational needs includes a processor, which receives as input signals from navigational and navigational related sensors such as a GPS, compass, inertial measurement unit and sensors. Processor utilizes the navigational information to provide a display to the user indicating present navigational positional information as well is providing a flight path to follow to the target. The navigational computer includes a device that enables it to operate in a peer-to-peer network with other similar navigational computers such that during use, users may track one another. Once on the ground, the navigational computer may be used to continue navigation.

Abstract: An adaptive guidance system (AGS) regulates the altitude and heading of a parasail to arrive at a target at a prescribed altitude. Since the altitude profile depends both on unknown wing loading, and wind magnitude and direction, the AGS estimates the glide slope and wind on the fly and provides a command to a stability augmentation system (SAS) that results in the desired glide slope and heading by performing a sequence of maneuvers and sensing the response. According to one embodiment, the SAS operates in the linear region and includes a PID controller that uses the difference between the actual heading and heading command to create an actuator output. The actuator output is limited by a position/rate limiter that imposes the physical limitations of the response time of the actuator/servos and position limits to prevent entering the nonlinear region.

Abstract: A sensor system and method is disclosed which is substantially non-shock sensitive, inexpensive and small enough to be incorporated into most applications. The sensor system includes a magnetometer (preferably a triaxial magnetometer) and at least one infrared sensor. In the preferred embodiment, the sensor system includes at least four infrared sensors arranged substantially orthogonal to each other in a common plane horizontal to the earth's surface. The infrared sensors generate signals that are analyzed by a processor to determine the tilt orientation of the object. Based on the tilt orientation of the object, the magnetometer is tilt compensated (preferably fully compensated). The sensor system may also include a global positioning system.

Abstract: A parachute is formed using a non-woven composite material. The non-woven composite material is formed by fusing a plurality of mono-filament fibers between thin layers of plastic. The non-woven material may be used as reinforcing tapes or as parachute lines in connection with a parachute of typical construction.

Abstract: A system and method of guiding an aircraft is disclosed. The aircraft includes at least one non-rigidly attached sensor for providing a signal indicative of the angular rate of turn of the aircraft. The signal includes an oscillation component and an angular rate of turn component. A filter receives the signal from the sensor and attempts to remove the oscillation component found in the signal. A guidance system provides a commanded turn rate signal. A stability augmentation system receives the filtered angular rate of turn signal and the commanded turn rate signal and processes those signals to provide an actuator command signal. The actuator command signal can best be used to control an air vehicle activation device. The method involves receiving at least one signal indicative of an angular rate of turn of the aircraft from the sensor not rigidly suspended from an aircraft, wherein the signal includes an oscillation component and an angular rate of turn component.

Abstract: A release device, and in particular a release device for use in parachute systems in place of pyrotechnic cutters. The inventive systems utilize a severable structural member of low melting point, high strength polymer that is severed by introducing a heat defect. The member is typically a ultra high molecular weight polyethylene braided line and the heat defect is preferably caused a resistance heater or solid state laser diode. This inventive results in a low cost non-pyrotechnic release device with is not subject to regulatory and transportation restrictions.

Abstract: A multimodal vehicle includes a ground based vehicle with an attached high-capacity airfoil parachute for deployment. The ground based vehicle includes a drive system for use on either land, water or both. Furthermore, the ground based vehicle is sized and dimensioned for transport of multiple vehicles in a cargo plane. The high-capacity airfoil parachute allows high-altitude deployment of the multimodal vehicle. The risers to the parachute may be adjusted for powered parachute flight rather than free fall flight. The ground based vehicle may include a propeller for powered flight.

Abstract: An autonomous guided parachute system for cargo drops that divides the requirements of guidance and soft landing into separate parachutes. Said invention includes a high wing-loaded ram air parachute for guidance, a larger round parachute for soft landing, a harness/container system, flight computer, position sensors and actuation system. The system is dropped from an airplane. A predetermined period of drogue fall ensures a stable position prior to deploying the guidance parachute. The flight controller determines a heading to intersect with an area substantially above the desired target and controls the guidance parachute via pneumatic actuators connected to the parachutes steering lines to fly on that heading. At a minimum altitude prior to the system's impact with the ground the flight computer transitions the system from the fast high performance guidance parachute to a larger landing parachute by releasing the guidance parachute to static line extract and deploy the landing parachute.

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: An improved ram air canopy is disclosed having a top skin formed of a plurality of substantially rectangular top skin pieces. Each top skin piece has areas of reduced width at predetermined locations. The areas of reduced width result in a specific tension pattern of the top skin so as to reduce distortion. The increased tension pattern of the top skin better maintains the modeled desired airfoil shape of the canopy.

Abstract: An autonomous guided parachute system for cargo drops that divides the requirements of guidance and soft landing into separate parachutes. Said invention includes a high wing-loaded ram air parachute for guidance, a larger round parachute for soft landing, a harness/container system, flight computer, position sensors and actuation system. The system is dropped from an airplane. A predetermined period of drogue fall ensures a stable position prior to deploying the guidance parachute. The flight controller determines a heading to intersect with an area substantially above the desired target and controls the guidance parachute via pneumatic actuators connected to the parachutes steering lines to fly on that heading. At a minimum altitude prior to the system's impact with the ground the flight computer transitions the system from the fast high performance guidance parachute to a larger landing parachute by releasing the guidance parachute to static line extract and deploy the landing parachute.

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: An automatic controlled parachute includes a parachute canopy, a flight controller and risers connecting the canopy to the flight controller. Pneumatic actuators are connected along the risers. The flight controller operates the pneumatic actuators to control the length of the risers. The direction of flight of the parachute is controlled by the length of the risers.

Abstract: The ram air parachute has restrictions on the inlets to the cells to reduce drag during flight and to reduce opening forces. The restrictions include triangular sections blocking portions of the inlets. The triangular sections may be positioned at loaded and non-loaded ribs. Furthermore, the triangular sections are dimensioned to tension the top skin between the loaded ribs and non-loaded ribs to preserve an aerodynamic shape during flight without cross-bracing. The loaded ribs may be shortened to create a zig-zag pattern at the front edge of the bottom skin for improved deployment with reduce drag during flight.