91results about "Parachutes testing apparatus" patented technology

A person can safely descend from a burning high-rise building or the like using an inflatable flying body that has a hollow conical form in an inflated deployed condition, but is deflated and folded into a backpack form in a stowed condition. The flying body includes an upper stabilizing ring, a lower nose structure with a pneumatic damping body, spoke struts extending conically therebetween, a cover skin covering the abovementioned inflatable components to form the conical outer surface and provide aerodynamic braking drag, and gas generators to inflate the inflatable components. A person straps on the apparatus in the stowed backpack form and pulls a handle to actuate the gas generators for inflating the apparatus, whereby the expanding apparatus ejects the person from the building and then orients itself in a nose-down attitude during the descent. The pneumatic damping body damps and dissipates the landing impact energy.

An airbag configuration for braking the landing impact of flying payloads has a central airbag (17) and at least one torus ring (11, 12, 13) surrounding the central airbag. A payload (L) is attachable on the central airbag (17). A stabilizing device (19) is provided which extends from the lowermost portion of the at least one torus ring (11, 12, 13) to the central airbag (17). The central airbag provides primarily vertical braking of the landing impact while the torus ring provides primarily horizontal braking of the landing impact.

There is provided an Unmanned Air Vehicle (UAV) including an engine and an airframe, including means for performing a deep stall maneouvre; at least one inflatable sleeve connected or connectable to the airframe, and means for inflating the sleeve during flight, wherein the inflated sleeve extends along the lower side of the airframe so as to protect same during deep stall landing. A method for operating an Unmanned Air Vehicle (UAV), including an engine and an airframe is also provided.

An improved rappelling system for raising or lowering a person or an object to or from a stationary or moving elevated point includes at least one cable for supporting a person or an object, a motor attached to the elevated point and coupled to the cable so that the motor propels the cable up or down and thereby raises or lower the person or object, respectively, a controller/processor for controlling the motion of the motor and at least one sensor attached to the elevated point and coupled to the controller/processor. The sensor measures the distance of the elevated point from a target area located at a lower point than the elevated point and continuously sends a feedback signal to the controller/processor. The feedback signal is used to calculate and adjust in real-time motor control parameters that determine speed and landing location of the person or object relative to the target area. The system also includes a display attached to the elevated point and displaying the measured distance and the motor control parameters in real-time.

A parachute release system is configured to releasably couple a parachute to a payload. A parachute release mechanism is coupled to a suspension strap routed through a strap sleeve. The parachute release mechanism is configured to provide near-simultaneous separation of the suspension straps from the payload via operation of a rotatable hinge pin. The strap sleeve reduces the possibility of the suspension strap becoming entangled with the payload. With this system and method, larger payloads may be supported and/or the mass of the parachute release system may be reduced.

An Unmanned Aerial Vehicle (UAV) system that couples the speed and responsiveness of a shoulder-launched rocket with the stable, slow-moving aerial platform of a parafoil is disclosed. The unique use of an over-damped rocket automatically positions the parafoil upwind of its target and overcomes the inherent inability of the parafoil to make headway in adverse wind conditions. This marriage of a rocket and a parafoil creates a valuable new synergy that allows the rocket to very quickly position a payload at altitude and defeat any adverse winds, while the parafoil provides an inexpensive and easy-to-fly vehicle for reconnaissance or accurately placing a payload on a target. The system is suitable for aerial videography, thermal imagery, target designation, sensor placement or precision munitions delivery; and can perform these functions at a small fraction of the cost of any other UAV. Unlike other UAV's, no flying skills are required of the operator. The system is so simple to use that no special training is required even for flying at night, and the intrinsic stability of the parafoil eliminates the need for avionic control systems.

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.

A cost-effective pack adapted to be distributed from an aircraft in the event of a natural, military, political, or other disaster includes an outer package, at least one item in the outer package for aerial delivery, and at least one aerodynamic component formed on the outer package and methods and systems for making the pack.

An air drop device that includes a frame defining a through-hole and that supports a substantially vertical axle, substantially central to the through-hole. A blade assembly is rotatably mounted to the substantially vertical axle. Also, at least three tethers are connected to the frame and are adapted to be connected to the load. In addition, a set of tether length adjust devices, each located on a different one of said tethers, are capable to take-up some of the tether to reduce the length of said tether.

An emergency safety jacket equipped with a rear ejecting parachute to protect an operator against forward accidental impact when riding a motorcycle-type vehicle is herein disclosed. The safety jacket comprises a back-mounted parachute being manually activated and ejected rearward using a propelling device, thereby removing the operator off the rear of the vehicle. The safety jacket also comprises a padded long-sleeve design with an outer shell which provides enhancements to protect the operator from impact, abrasion, and fire. The emergency safety jacket is specifically envisioned for use with motorcycle and scooter type vehicles.

The invention is a flight kit that can be retrofitted to existing navy sonobuoys. The invention gives sonobuoys the capability of self-deployment, allowing them to be sent to a location remotely without the use of manned aircraft or recoverable unmanned air vehicles. This capability is advantageous in instances where it is desired to place a sonobuoy in an area hostile or hazardous to manned aircraft. The invention is an attachment of a GPS navigation and control system, wings, control surfaces, and a propulsion system, onto a naval size-A sonobuoy, using the sonobuoy as the central structural load-bearing component of the assembly. The invention navigates from a launch point on a ship to a designated position, where the sonobuoy separates from the invention, using the wings' aerodynamic forces to mechanically assist in separating the sonobuoy from the flight kit. The sonobuoy and the flight kit enter the water separately to ensure no interference with the sonobuoy.

An aerial distribution system and method for deploying items is disclosed. The system includes a bulk shipping container comprised of a single piece of corrugated plastic, cut and folded into a closable box, a plurality of deployment boxes within the bulk shipping container, each deployment box containing at least one item, a plurality of tethers, each tether coupling a deployment box to the bulk shipping container, and a freefall retarding device coupled to the bulk shipping container.

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. According to the invention the second attachment means of the improved steering unit comprise at least one upper fixed attachment point, a left moveable attachment point, a right moveable attachment point, and steering actuator means for varying the distance between the upper fixed attachment point and the left moveable attachment point and for varying the distance between the upper fixed attachment point and the right moveable attachment point.

A water-impact release mechanism has a hub with a first sleeve coupled thereto. The first sleeve has a plurality of circumferentially distributed holes therein. A spring assembly, coupled to the hub, extends into the first sleeve. In a relaxed state, the spring assembly obstructs the holes while, in a compressed state, the spring assembly does not obstruct the holes. A second sleeve, concentric with the first sleeve, is elastically coupled to the hub and biased away therefrom. The second sleeve has an inwardly-facing annular groove. A ball resides in each of the holes and is large enough to extend beyond the confines of its hole. When the bias of the second sleeve is overcome, the annular groove aligns with the holes in the first sleeve thereby allowing the radial outward movement of the balls. A plate, coupled to the second sleeve, extends radially outward therefrom to define a water-impact surface. Water-impact forces impinging on the plate cause the bias of the second sleeve to be overcome such that the second sleeve abuts the hub.

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.

Devices, methods, and systems for slowing the descent of an object in flight such as a baseball using a parachute are presented. A parachute assembly includes a canopy attached to a plurality of suspension lines converging downwardly to a corresponding number of attachment points on the surface of a ball. The attachment points are substantially equidistantly spaced apart along a line of substantially equal latitude. In one embodiment, each attachment point defines an opening to an interior channel extending to a central chamber. Each suspension line is inserted into an interior channel, through the central chamber, and out of the ball through a common shaft, where the lines are fastened together in a bundle and then withdrawn until the bundle lies in the central chamber, retaining the lines inside the ball.

A parachute system has a canopy, suspension lines that extend from the canopy skirt to a confluence point, and a center line that is attached to and between the apex of the canopy and the confluence point. A single reefing line cutter is attached to the center line and is activated after a predetermined amount of time has elapsed. A first reefing line extends through a first group of reefing rings wherein one end of the first reefing line is attached to the single reefing line cutter and the opposite end is attached to the canopy skirt at a first predetermined location. A second reefing line extends through a second group of reefing rings that is opposite the first group of reefing rings. The second reefing line has one end attached to the single reefing line cutter and an opposite end attached to the canopy skirt at a second predetermined location that is across from the first predetermined location. The canopy opens to an initial circumference that is determined by the summation of the lengths of the first and second reefing lines. When the reefing line cutter is activated, the reefing line cutter releases the first and second reefing lines so as to allow full inflation of the canopy.

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.

The invention discloses a testing device for measuring parachute opening characteristics of a parachute model in a high-speed wind tunnel. The testing device comprises a parachute model supporting device, a balance, a rotor and a parachute opening device. When airflow in a high-speed wind tunnel test section reaches the specified flow field condition, a rotating shaft of a stepper motor drives a screw rod to rotate, a nut on the screw rod moves backward and pulls out a parachute bay blocking cap and the parachute model from a parachute bay, the parachute model is opened under the action of high velocity airflow, and in the parachute opening process, a high-speed wind tunnel data collecting system continuously collects the measuring value of the balance. According to the testing device formeasuring the parachute opening characteristics of the parachute model in the high-speed wind tunnel, the parachute opening mode is safe, and parachute opening power basically does not disturb the balance and does not damage the balance; and a rod-type strain balance with an inverted-conical-shaped front cone is adopted as the balance, and accidents of damaging to the balance and the high-speed wind tunnel due to the fact that the balance is disengaged from the parachute model supporting device are prevented.

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.