Launching Patents (Class 244/63)
-
Patent number: 8091461Abstract: A system includes a support structure having a compressed air tank therein, a pneumatic launch assembly coupled to the support structure, and an inflatable bladder disposed around at least a portion of a region defined by the support structure and the pneumatic launch assembly. The angle of the pneumatic launch assembly with respect to the support structure is adjustable. The pneumatic launch assembly comprises a launch tube, a compressed air manifold contained within the launch tube and in fluid connection with the compressed air tank, the compressed air manifold having an air outlet, a telescoping guide rod connected to the compressed air manifold, and a shuttle slidably coupled to the telescoping guide rod and at least partially disposed over the air outlet. The system may include a collapsible stabilizing weight coupled to the support structure, as well as communications and control circuitry within the launch tube.Type: GrantFiled: December 16, 2008Date of Patent: January 10, 2012Assignee: The United States of America as represented by the Secretary of the NavyInventors: James G. Buescher, Christopher D. Mailey, Ryan M. Stenson, Daniel A. Sura
-
Publication number: 20120001020Abstract: An unmanned aerial vehicle (UAV) launch tube that comprises a tethered sabot configured to engage a UAV within a launcher volume defined by an inner wall, the tethered sabot dimensioned to provide a pressure seal at the inner wall and tethered to the inner wall, and wherein the tethered sabot is hollow having an open end oriented toward a high pressure volume and a tether attached within a hollow of the sabot and attached to the inner wall retaining the high pressure volume or attach to the inner base wall. A system comprising a communication node and a launcher comprising an unmanned aerial vehicle (UAV) in a pre-launch state configured to receive and respond to command inputs from the communication node.Type: ApplicationFiled: September 15, 2011Publication date: January 5, 2012Inventors: Carlos Thomas Miralles, Guan H. Su, Oleksandr Andryukov, John McNeil
-
Publication number: 20110315817Abstract: An unmanned aerial vehicle (UAV) launch tube that comprises a tethered sabot configured to engage a UAV within a launcher volume defined by an inner wall, the tethered sabot dimensioned to provide a pressure seal at the inner wall and tethered to the inner wall, and wherein the tethered sabot is hollow having an open end oriented toward a high pressure volume and a tether attached within a hollow of the sabot and attached to the inner wall retaining the high pressure volume or attach to the inner base wall. A system comprising a communication node and a launcher comprising an unmanned aerial vehicle (UAV) in a pre-launch state configured to receive and respond to command inputs from the communication node.Type: ApplicationFiled: September 9, 2011Publication date: December 29, 2011Inventors: Carlos Thomas Miralles, Guan H. Su, Oleksandr Andryukov, John McNeil
-
Patent number: 8056461Abstract: Methods and apparatus for marine deployment according to various aspects of the present invention may operate in conjunction with a floatable housing adapted to be deployed by a marine vehicle. The floatable housing may be adapted to be launched from a marine vehicle and rise to the surface. Assets, such as an unmanned aerial vehicle, may be deployed from the surfaced floatable housing.Type: GrantFiled: September 18, 2008Date of Patent: November 15, 2011Assignee: Raytheon CompanyInventors: David E. Bossert, Jeffrey N. Zerbe, Ray Sampson
-
Publication number: 20110268816Abstract: A method for oxygenating a fluid, the method including launching a sub-orbital lower-level apparatus to a predetermined altitude greater than 20,000 feet above sea level. The method also includes, at the predetermined altitude, actuating a fluid capture mechanism sealingly configured to collect and store an atmospheric fluid. In addition, returning the a sub-orbital lower-level apparatus to an altitude less than 20,000 feet, and introducing at least a portion of the atmospheric fluid to an oxygenation process to mix the captured atmospheric fluid with another fluid.Type: ApplicationFiled: April 30, 2010Publication date: November 3, 2011Inventor: John Michael DeBoer
-
Patent number: 8028952Abstract: A system to launch and recover an Unmanned Aerial Vehicle (UAV) aircraft has a pole member attached to a deck of a ship. An arm member is attached to the pole member and extends away from the pole member in an approximately horizontal direction. The arm member is able to move rotationally and vertically on the pole member. An attachment mechanism is attached to a distal end of the arm member for holding and capturing the UAV aircraft. Momentum of the UAV aircraft causes the arm member to move rotationally around and vertically on the pole member when the UAV aircraft is coupled to the attachment mechanism.Type: GrantFiled: March 31, 2008Date of Patent: October 4, 2011Assignee: The Boeing CompanyInventor: James M. Urnes, Sr.
-
Patent number: 8028953Abstract: Providing an accelerating device capable of safely and efficiently accelerating an aircraft even if the aircraft is a high-speed and heavyweight one. The accelerating device has a support base for supporting an aircraft so that it does not go backward or levitate and does not pitch; a guide way placed along a predetermined route; guide means for guiding the support base along the guide way; and drive means for driving the support base along the guide way.Type: GrantFiled: October 6, 2006Date of Patent: October 4, 2011Assignee: Central Japan Railway CompanyInventors: Shiro Hosaka, Masatada Yamamoto, Satoshi Matsuda, Akio Yamanaka, Toshihiko Takeo
-
Patent number: 8028521Abstract: The invention relates to a catapult drive for an object to be accelerated, preferably the car of a fairground ride, wherein the object is accelerated by means of a driving element. The movement of the driving element is produced by a flexible drive and a hydraulic cylinder via which all movements of the driving element can be controlled. The invention also relates to a control system for suitably controlling the inventive catapult drive.Type: GrantFiled: February 27, 2006Date of Patent: October 4, 2011Assignee: Bosch Rexroth AGInventors: Sander Leonard Boeijen, Marten Fluks, Maarten Rik Leo Kuijpers
-
Publication number: 20110204180Abstract: An apparatus for the take-off, landing and taxiing of an aircraft without undercarriage system or with retracted undercarriage, wherein the apparatus comprises a ground-based undercarriage, the speed of which can be matched to the speed of the aircraft when landing, the ground-based undercarriage (10) is releaseably connected to a slide system, which can be driven in a direction of movement, the ground-based undercarriage (10) has at least two coupling means, which enable interfaces of the aircraft (4) on the ground-based undercarriage (10) to be coupled, the ground-based undercarriage (10) can be moved along the slide system transversally to the direction of movement of the slide system to match the ground-based undercarriage (10) to the position of the aircraft (4).Type: ApplicationFiled: April 30, 2009Publication date: August 25, 2011Inventor: Jan Binnebesel
-
Patent number: 7988088Abstract: An air transport vehicle of the present invention comprises a tubular body, said body comprising an upper half and a lower half. The upper half is positioned above the lower half and connected thereto. A central bore is formed between the upper half and the lower half. The bore extends longitudinally from the nose end of the vehicle to the tail end of the vehicle. The vehicle also comprises at least one propulsion device, preferably positioned inside the bore. The vehicle further comprises at least one bulkhead. The bulkhead connects the upper half to the lower half, and extending longitudinally inside the bore, thus dividing the bore into parallel subsections. In preferred embodiments, the upper half and the lower half comprise cavities, used among other things, for cargo and passenger transport.Type: GrantFiled: June 5, 2008Date of Patent: August 2, 2011Inventor: Alexandr Konstantinovskiy
-
Publication number: 20110168838Abstract: An unmanned aerial surveillance and reconnaissance system are disclosed wherein an unmanned aerial vehicle is launchable from a launch tube, for instance, the bore of an existing weapons system mounted on a mobile vehicle, such as a weapon barrel of a tank or armored combat vehicle and which the launch may be remotely initiated from the protected armored compartment of the mobile vehicle.Type: ApplicationFiled: April 21, 2010Publication date: July 14, 2011Applicant: Irvine Sensors CorporationInventors: William Hornback, Michael Holly
-
Publication number: 20110147515Abstract: An unmanned aerial vehicle including a controller operating in a search mode of operation where a receiver of an acquisition sensor searches for a target and causes flight control surfaces to guide the vehicle in a downward spiral path, a terminal mode of operation where the acquisition sensor detects a target and causes flight control surfaces to direct the vehicle toward the target, and an activation mode of operation where a trigger sensor detects a target within a predetermined distance to the vehicle and the controller activates a responder.Type: ApplicationFiled: December 17, 2009Publication date: June 23, 2011Inventors: Gerald Miller, James Stewart
-
Publication number: 20110147516Abstract: A cold-launch device, including a high-energy gas resource, a gas cylinder, a control valve, a gas-liquid mixing cylinder having a cylinder body, the high-energy gas resource is connected to the gas cylinder whereby supplying energy thereto, and the gas cylinder is connected to an terminal of the gas-liquid mixing cylinder via the control valve and a connecting pipe.Type: ApplicationFiled: February 28, 2011Publication date: June 23, 2011Inventors: Xuanzhe HU, Zhenhua HU, Aiwu HU
-
Patent number: 7963481Abstract: A method and a device for supporting the take-off rotation of an aircraft, which aircraft comprises on each side of the aircraft at least two main landing gear units, arranged one behind the other, which main landing gear units comprising wheels. For supporting the take-off rotation, in at least one rear pair of the main landing gear units the distance between the wheels of these rear main landing gear units, which wheels roll on the ground, and the fuselage, may actively be reduced.Type: GrantFiled: June 13, 2006Date of Patent: June 21, 2011Assignee: Airbus Deutschland GmbHInventors: André Anger, Wolfram Schöne
-
Publication number: 20110133024Abstract: For retrieval of a hovering aircraft, a cable, bar, or similar fixture is suspended in an approximately horizontal orientation across the retrieval area between two well-separated supports. The aircraft slowly flies into this fixture, which then slides along the aircraft in a direction approximately parallel with the aircraft's thrust line. This leads to the aircraft becoming fastened to the fixture by an interceptor or aircraft capturer, which in alternative embodiments are respectively on the aircraft or the fixture or both. Thrust is then reduced, and the aircraft comes to rest hanging from the fixture for subsequent removal. Retrieval is thus accomplished with simple and economical apparatus, light and unobtrusive elements on the aircraft, low risk of damage, and only moderate piloting accuracy.Type: ApplicationFiled: February 10, 2011Publication date: June 9, 2011Inventors: Brian T. McGeer, Andreas H. van Flotow, Corydon C. Roeseler
-
Patent number: 7954755Abstract: A method of launching a catapult, a catapult and a locking device for a catapult. The catapult comprises a carriage for fastening an aircraft. The carriage can be provided with a high acceleration by directing a launching force generated by a launching device thereto. The carriage can be held at a launching position by means of the locking device. The catapult further comprises a takeoff damper that generates a damping force having a direction opposite relative to the launching force. Accordingly, the takeoff damper restricts the acceleration of the carriage at the initial launching moments.Type: GrantFiled: May 11, 2009Date of Patent: June 7, 2011Assignee: Robonic Ltd OyInventor: Pentti Lipponen
-
Patent number: 7946241Abstract: Methods and apparatus for marine deployment according to various aspects of the present invention may operate in conjunction with a floatable housing adapted to be deployed by a marine vehicle. The floatable housing may be adapted to be launched from a marine vehicle and rise to the surface. Assets, such as an unmanned aerial vehicle, may be deployed from the surfaced floatable housing.Type: GrantFiled: September 18, 2008Date of Patent: May 24, 2011Assignee: Raytheon CompanyInventors: Ray Sampson, David E. Bossert, Jeffrey N. Zerbe
-
Publication number: 20110073707Abstract: Methods and apparatus for marine deployment according to various aspects of the present invention may operate in conjunction with a floatable housing adapted to be deployed by a marine vehicle. The floatable housing may be adapted to be launched from a marine vehicle and rise to the surface. Assets, such as an unmanned aerial vehicle, may be deployed from the surfaced floatable housing.Type: ApplicationFiled: September 18, 2008Publication date: March 31, 2011Inventors: DAVID E. BOSSERT, Jeffrey N. Zerbe, Ray Sampson
-
Patent number: 7913948Abstract: The high-altitude balloon has a skin made of nearly evacuated electrostatically inflated cells which provide thermal insulation to minimize heat loss from the gas in the balloon, while transmitting heat from the sun to heat the gas. The lower surface of the balloon is reflective to microwave or laser beams. A stable array of the balloons is maintained at a high altitude and is used to facilitate communications in a world-wide communications system. Ascent of the balloon is well controlled and weight is minimized by starting with lighter-than-air gases in liquid form, releasing a lifting gas into the craft, and then using the empty containers to store the remaining gas when the balloon is aloft.Type: GrantFiled: October 7, 2008Date of Patent: March 29, 2011Inventor: David R. Porter
-
Publication number: 20110062281Abstract: The present disclosure relates to a launch system for air vehicles. More specifically, the present disclosure relates to launching unmanned air vehicles (UAVs) that are unable to be launched by hand. The present disclosure provides a system for launching a winged vehicle, including: a projectile launching device; and a device for converting projectile momentum into acceleration of a winged vehicle.Type: ApplicationFiled: May 13, 2009Publication date: March 17, 2011Applicant: BAE SYSTEMS plcInventors: Christopher Colin Anthony Woolley, Kevin William Beggs, Ryan Andrew Bakewell, Richard Desmond Joseph Axford, John Wainwright
-
Patent number: 7900866Abstract: A system and methods for airborne launch and recovery of aircraft. In one embodiment the system comprises a flexible tether configured to be towed behind an airborne mother ship. A drag device is secured to a distal end of the flexible tether to generate drag and maintain tension in the flexible tether. A reel associated with the mother ship anchors a proximal portion of the flexible tether and selectively lets out and takes up the flexible tether to adjust a length of the flexible tether. A capture mechanism associated with the aircraft engages the flexible tether to enable the aircraft to translate along the flexible tether. In embodiments of the present methods, a flexible tether is deployed from an airborne mother ship. An aircraft translates forward and rearward along the flexible tether. Prior to launch, the weight of the aircraft is transferred from the flexible tether to the wings. During recovery, the weight of the aircraft is transferred from the wings to the flexible tether.Type: GrantFiled: October 18, 2007Date of Patent: March 8, 2011Assignee: The Boeing CompanyInventors: Aaron J. Kutzmann, Kevin R. Lutke
-
Publication number: 20100314490Abstract: Disclosed are a wing deployment apparatus and an apparatus for launching a flying object having the same, the wing deployment apparatus including wings configured to be in a folded state and a deployed state, a driving unit connected to the wings, and configured to drive the wings to be switched from the folded state to the deployed state or vice versa, and a damper cooperative with the operation of the driving unit, and configured to damp a driving force of the driving unit from the start of the wings being moved to the completion of the movement of the wings.Type: ApplicationFiled: April 9, 2010Publication date: December 16, 2010Applicant: AGENCY FOR DEFENSE DEVELOPMENTInventors: Heon Suk HONG, Sang Hun SHIN, Woo Yong LEE
-
Publication number: 20100294879Abstract: Disclosed are a wing assembly including a wing movably accommodated in a launch tube, and a buffer unit detachably mounted to the wing to come in contact with the launch tube and configured to be separated from the wing after the wing comes out of an inner space of the launch tube, and an apparatus for launching a flying object having the same.Type: ApplicationFiled: May 13, 2010Publication date: November 25, 2010Applicant: AGENCY FOR DEFENSE DEVELOPMENTInventors: Sang Hun SHIN, Heon Suk HONG, Woo Yong LEE
-
Patent number: 7815146Abstract: A fixed sized bell rocket nozzle is lined with a layer of combustible material that is ignited during launch ignition and burns to outgas into the rocket exhaust for spatially variably confining the exhaust and perfecting an effective variably sized altitude compensating exhaust nozzle that maximizes lift during the launch of a spacecraft into orbit.Type: GrantFiled: August 29, 2001Date of Patent: October 19, 2010Assignee: The Aerospace CorporationInventors: Gary F. Hawkins, John W. Murdock
-
Patent number: 7811151Abstract: A toy airplane with foldable wings. The wings can be folded before being launched by a launcher. When the toy airplane is launched the wind pressure maintains the wings in the folded position. When the toy airplane reaches a certain reduced speed, springs of the toy plane move the wings back into an unfolded position. Movement of wings into the unfolded position closes a switch and powers a propeller of the toy plane. The propeller can be powered by a battery within the toy plane fuselage. The combination of a motorized propeller, switch and folded wings provides a toy airplane that minimizes drag during launch and allows for extended flight after launch.Type: GrantFiled: April 27, 2006Date of Patent: October 12, 2010Inventor: Steve Conrad
-
Publication number: 20100252676Abstract: One embodiment includes a launch vessel defining an elongate, linear interior extending from a bottom portion to an exit opening. The embodiment includes a ram slidably disposed in the launch vessel, the ram sealed to the vessel. The embodiment also includes one or more wedges coupled to the launch vessel along the interior proximal the exit opening, with each wedge shape sized to increasingly narrow a cross section of the interior along an exit vector extending from the bottom portion toward the exit opening. In the embodiment, the vessel is to house a charge proximal the bottom portion, the charge to propel the ram along the exit vector, with the one or more wedges sized to stop be ram inside the interior.Type: ApplicationFiled: April 2, 2009Publication date: October 7, 2010Applicant: Raytheon CompanyInventors: Jeffrey H. Koessler, Brian L. Cochran, Mark A. DeBake, Steven J. Elder
-
NON-CIRCULAR CROSS-SECTION MISSILE COMPONENTS, MISSILES INCORPORATING SAME, AND METHODS OF OPERATION
Publication number: 20100242772Abstract: A missile component such as a rocket motor case, of an initial transverse cross-sectional shape flexible into another, different cross-section responsive to application of internal pressure from ignition of a propellant grain within the component. A missile launch assembly including at least one missile of a non-circular cross-section disposed within a segment of a partitioned circular launch tube. A multi-stage missile comprising at least a first stage and a second stage having rocket motor cases of non-circular transverse cross-section, the rocket motor case of at least one of the stages being deformable into another, different cross-section. A method of launching a missile including igniting a rocket motor of a component having a first cross-section, internally pressurizing the missile component substantially concurrently with motor ignition and flexing the component rocket motor into a second, different cross-sectional shape.Type: ApplicationFiled: March 24, 2009Publication date: September 30, 2010Inventors: Phillip R. Martineau, Christopher J. Sullivan, David W. Hull, Steven C. Sara -
Publication number: 20100123041Abstract: The launching of an unmanned projectile includes pre-packaging a barrel with a projectile, a pusher cup, and a gas generator. The gas generator generates gas to propel the projectile out of the barrel. A pressure chamber increases a pressure of the gas in the barrel. The pressure chamber comprises a front body portion connected to the gas generator; an aft body portion connected to the front body portion and the gas generator; and a vent sleeve positioned around the front body portion and adapted to provide an aperture through which the gas exits the barrel in order to control a level of gas pressure in the barrel. A triggering of the gas generator causes the pusher cup to push the projectile out of the barrel at a predetermined launch velocity in order to attain a predetermined self-propelled flight trajectory, wherein the triggering causes the pusher cup to exit the barrel.Type: ApplicationFiled: September 15, 2007Publication date: May 20, 2010Inventors: Michael L. Nair, John A. Condon
-
Patent number: 7712702Abstract: Methods and apparatuses for launching unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can be launched from an apparatus that includes a launch carriage that moves along a launch guide. The carriage can accelerate when portions of the carriage and/or the launch guide move relative to each other. A gripper carried by the launch carriage can have at least one grip portion in contact with the aircraft while the launch carriage accelerates along the launch axis. The at least one grip portion can move out of contact with the aircraft as the launch carriage decelerates, releasing the aircraft for takeoff. A brake can arrest the motion of the gripper after launch.Type: GrantFiled: November 21, 2006Date of Patent: May 11, 2010Assignee: Insitu, Inc.Inventors: Brian T. McGeer, Andreas H. von Flotow, Cory Roeseler
-
Publication number: 20100096496Abstract: An aircraft launcher includes a base frame, a first sliding frame that slides with respect to the base frame, a second sliding frame that slides with respect to the first sliding frame, an aircraft support located on the second sliding frame, and a drive apparatus adapted to slide at least one of the first sliding frame and the second sliding frame with respect to the base frame.Type: ApplicationFiled: October 20, 2009Publication date: April 22, 2010Applicant: AAI CorporationInventor: Stephen William Miller
-
Publication number: 20100051741Abstract: An unmanned air vehicle for military, land security and the like operations includes a fuselage provided with foldable wings having leading edge flaps and trailing edge ailerons which are operable during ascent from launch to control the flight pattern with the wings folded, the wings being deployed into an open unfolded position when appropriate. The vehicle is contained within a pod from which it is launched and a landing deck is provided to decelerate and arrest the vehicle upon its return to land.Type: ApplicationFiled: September 3, 2008Publication date: March 4, 2010Inventor: Anvar Ismailov
-
Patent number: 7665691Abstract: An aerial vehicle launching system includes a launch platform and a restraint system coupled to the launch platform. The restraint system has at least one passive restraint suitably adapted to indirectly restrain an aerial vehicle. The restraint system is configured to coordinate the uniform retention and release of the passive restraint in order to launch the aerial vehicle.Type: GrantFiled: February 27, 2007Date of Patent: February 23, 2010Assignee: Raytheon CompanyInventors: Patrick T. Hanzlick, Joshua J. Lange
-
Patent number: 7658347Abstract: A Micro Air-Vehicle (MAV) starting system that provides the combined functions of: packing protection of sensitive vehicle components, a mechanical starting assembly, and a launch pad. The preferred embodiment comprises a container and a container lid with the MAV clamped to the lid. Also disposed on the container lid is a starting assembly. The lid which doubles as a launching pad with the attached MAV is removed from the container, placed on the ground, the MAV is started with the starting mechanism and launched. The arrangement minimizes the physical risk to the operator, minimizes weight of the total MAV system, consumes minimum space in the operators transport system, and eliminates dependence on supply lines for battery replacement or charging.Type: GrantFiled: July 25, 2006Date of Patent: February 9, 2010Assignee: Honeywell International, Inc.Inventors: Emray R. Goossen, Glen A. Mantych, William T. Campbell
-
Patent number: 7644891Abstract: Systems and methods for releasing a spacecraft payload at a substantially constant velocity are disclosed. A linear actuator is used that includes a spring loaded and fluid filled chamber. The spring drives against a piston within the chamber that includes a control orifice that restricts the fluid flowing from one side of the piston to the other and results in a substantially constant damped motion of the piston. The piston drives a rod from the chamber that is attached to a capture device that holds a flange of the spacecraft payload. The capture device moves along a linear guide toward an open end. Spring loaded latches are held in a closed position by the side walls of the guide as the capture device moves. The latches release the flange as exit the open end of the guide.Type: GrantFiled: May 25, 2007Date of Patent: January 12, 2010Assignee: The Boeing CompanyInventors: Richard W. Aston, Michael Langmack, Torger J. Totusek
-
Publication number: 20090314883Abstract: An unmanned aerial vehicle (UAV) is launched and recovered using a UAV management system. The UAV is stored in a magazine and moved from the magazine during a launch operation and to the magazine during a recovery operation.Type: ApplicationFiled: May 12, 2008Publication date: December 24, 2009Inventors: Paul E. Arlton, David J. Arlton
-
Publication number: 20090314882Abstract: A Micro Air-Vehicle (MAV) starting system that provides the combined functions of: packing protection of sensitive vehicle components, a mechanical starting assembly, and a launch pad. The preferred embodiment comprises a container and a container lid with the MAV clamped to the lid. Also disposed on the container lid is a starting assembly. The lid which doubles as a launching pad with the attached MAV is removed from the container, placed on the ground, the MAV is started with the starting mechanism and launched. The arrangement minimizes the physical risk to the operator, minimizes weight of the total MAV system, consumes minimum space in the operators transport system, and eliminates dependence on supply lines for battery replacement or charging.Type: ApplicationFiled: July 25, 2006Publication date: December 24, 2009Inventors: Emray R. Goossen, Glen A. Mantych, William T. Campbell
-
Publication number: 20090302150Abstract: An air transport vehicle of the present invention comprises a tubular body, said body comprising an upper half and a lower half. The upper half is positioned above the lower half and connected thereto. A central bore is formed between the upper half and the lower half. The bore extends longitudinally from the nose end of the vehicle to the tail end of the vehicle. The vehicle also comprises at least one propulsion device, preferably positioned inside the bore. The vehicle further comprises at least one bulkhead. The bulkhead connects the upper half to the lower half, and extending longitudinally inside the bore, thus dividing the bore into parallel subsections. In preferred embodiments, the upper half and the lower half comprise cavities, used among other things, for cargo and passenger transport.Type: ApplicationFiled: June 5, 2008Publication date: December 10, 2009Inventor: Alexandr KONSTANTINOVSKIY
-
Publication number: 20090250550Abstract: A method of launching a catapult, a catapult and a locking device for a catapult. The catapult comprises a carriage for fastening an aircraft. The carriage can be provided with a high acceleration by directing a launching force generated by a launching device thereto. The carriage can be held at a launching position by means of the locking device. The catapult further comprises a takeoff damper that generates a damping force having a direction opposite relative to the launching force. Accordingly, the takeoff damper restricts the acceleration of the carriage at the initial launching moments.Type: ApplicationFiled: May 11, 2009Publication date: October 8, 2009Inventor: Pentti LIPPONEN
-
Publication number: 20090242693Abstract: A system to launch and recover an Unmanned Aerial Vehicle (UAV) aircraft has a pole member attached to a deck of a ship. An arm member is attached to the pole member and extends away from the pole member in an approximately horizontal direction. The arm member is able to move rotationally and vertically on the pole member. An attachment mechanism is attached to a distal end of the arm member for holding and capturing the UAV aircraft. Momentum of the UAV aircraft causes the arm member to move rotationally around and vertically on the pole member when the UAV aircraft is coupled to the attachment mechanism.Type: ApplicationFiled: March 31, 2008Publication date: October 1, 2009Inventor: James M. Urnes, SR.
-
Patent number: 7594624Abstract: A flying vehicle-launching apparatus and method for launching a winged flying vehicle by accelerating the vehicle in a predetermined direction includes a flying vehicle-supporting platform, a guide device, and a driving device. The flying vehicle-supporting platform supports the winged flying vehicle so that it can lift off therefrom. The guide device supports the flying vehicle-supporting platform across two or more separated and parallel guide ways and guides the flying vehicle-supporting platform along the guide ways. In the flying vehicle-launching method, a propulsive engine of the winged flying vehicle is started after initiating acceleration with a flying vehicle-accelerating device. The winged flying vehicle is released from the flying vehicle-accelerating device in a predetermined angle of attack that is positive to a direction of acceleration after reaching a predetermined velocity.Type: GrantFiled: June 15, 2007Date of Patent: September 29, 2009Assignee: Central Japan Railway CompanyInventor: Masatada Yamamoto
-
Publication number: 20090224097Abstract: The present invention relates to a system for landing UAV's. The system comprises a slingshot structure that includes arm based structure and an axis means installed along the arm of the structure and wherein it enables the arm to move around it in addition, the system comprises base means connecting the axis means to a platform at which the system is installable. The system also include a controlled pulling and braking means that connects between the arm of the structure and the platform upon which the system is installable and a stretchable elastic means installed in a stretched manner at a gap formed between two arms and set to connect with a landing UAV. At the landing phase, the controlled pulling and braking means of the system, essentially breaks the motion of the arm based structure that is propelled to revolve around the system's axis means, from a time that the UAV forms contact with the elastic means and with it propels the structure to move around the axis means.Type: ApplicationFiled: February 2, 2009Publication date: September 10, 2009Inventor: Amnon Kariv
-
Publication number: 20090224094Abstract: A system is disclosed whereby a sensor, communication device, or other payload may be lofted to an operational altitude and maintained over an area of interest for some time by a relatively inexpensive and disposable buoyant aircraft, then returned intact to its point of origin or another desired location by a reusable but also relatively inexpensive non-buoyant aircraft. Automatic unpiloted control is used for all stages of flight, including ascent, loiter, return, and landing Specialized equipment can be provided to simplify launch procedures, reducing the number of personnel required to operate the system.Type: ApplicationFiled: February 26, 2009Publication date: September 10, 2009Inventor: Timothy T. Lachenmeier
-
Publication number: 20090212157Abstract: A flying micro-rotorcraft unit is provided for remote tactical and operational missions. The unit includes an elongated body having an upper and a lower end. The body defines a vertical axis. The unit further includes a navigation module including means for determining a global position of the elongated body during flight of the unit. Rotor means of the unit is coupled to the upper end of the elongated body for generating a thrust force that acts in a direction parallel to the vertical axis to lift the elongated body into the air. The rotor means is located between the elongated body and the navigation module.Type: ApplicationFiled: December 26, 2006Publication date: August 27, 2009Inventors: Paul E. Arlton, David J. Arlton
-
Patent number: 7562843Abstract: A method of launching a catapult, a catapult and a locking device for a catapult. The catapult comprises a carriage (4) for fastening an aircraft (5). The carriage (4) can be provided with a high acceleration by directing a launching force (F1) generated by a launching device thereto. The carriage (4) can be held at a launching position (6) by means of the locking device (9). The catapult further comprises a takeoff damper (34) that generates a damping force (F2) having a direction opposite relative to the launching force. Accordingly, the takeoff damper (34) restricts the acceleration of the carriage (4) at the initial launching moments.Type: GrantFiled: November 11, 2004Date of Patent: July 21, 2009Assignee: Robonic Ltd OyInventor: Pentti Lipponen
-
Patent number: 7556219Abstract: An unmanned aerial vehicle (UAV) is provided, that is cost effective to use and manufacture and that includes a low count of component parts, allowing mission planners to use the UAVs in a disposable manner. The UAV includes an airframe having a central body and wings extending from the central body, defining an interior cavity. The airframe includes an upper and a lower shell, each configured of a unitary piece of plastic. The upper and lower shells have walls among them that define a fuel tank and a payload bay in a stacked configuration. The airframe can further include a payload cover configured to enclose the payload bay and to contribute to the central body of the airframe. A launch assembly is also provided. In a first configuration, a launch assembly is provided, that includes a container for housing multiple UAVs and a deployment mechanism that initiates rapid ejection of the UAVs from the container.Type: GrantFiled: February 22, 2005Date of Patent: July 7, 2009Assignee: Swift Engineering, Inc.Inventors: Mark A. Page, Doug McLarty, Adrian Fazio, Christian Durand, Bob Emerick
-
Publication number: 20090145999Abstract: The high-altitude balloon has a skin made of nearly evacuated electrostatically inflated cells which provide thermal insulation to minimize heat loss from the gas in the balloon, while transmitting heat from the sun to heat the gas. The lower surface of the balloon is reflective to microwave or laser beams. A stable array of the balloons is maintained at a high altitude and is used to facilitate communications in a world-wide communications system. Ascent of the balloon is well controlled and weight is minimized by starting with lighter-than-air gases in liquid form, releasing a lifting gas into the craft, and then using the empty containers to store the remaining gas when the balloon is aloft.Type: ApplicationFiled: October 7, 2008Publication date: June 11, 2009Inventor: David R. Porter
-
Publication number: 20090146002Abstract: In example embodiments described herein, techniques are described for launching flying structures such as a plank wings or a gliders, canards, or any other flying structures. In some example embodiments, a rotational arrangement facilitates such launches. In operation, a rotational arrangement couples with the flying structure and is configured to allow a user to impart rotational movement to the flying structure. In imparting the rotational movement, the rotational mechanism allows an automatic variation of a radius of the associated radius of curvature.Type: ApplicationFiled: December 8, 2008Publication date: June 11, 2009Applicant: Freestyle Engineering, LLCInventor: James Michael Lovette
-
Publication number: 20090134273Abstract: An unmanned aerial vehicle (UAV) is provided, that is cost effective to use and manufacture and that includes a low count of component parts, allowing mission planners to use the UAVs in a disposable manner. The UAV includes an airframe having a central body and wings extending from the central body, defining an interior cavity. The airframe includes an upper and a lower shell, each configured of a unitary piece of plastic. The upper and lower shells have walls among them that define a fuel tank and a payload bay in a stacked configuration. The airframe can further include a payload cover configured to enclose the payload bay and to contribute to the central body of the airframe. A launch assembly is also provided. In a first configuration, a launch assembly is provided, that includes a container for housing multiple UAVs and a deployment mechanism that initiates rapid ejection of the UAVs from the container.Type: ApplicationFiled: February 22, 2005Publication date: May 28, 2009Applicant: Swift Engineering Inc.Inventors: Mark A. Page, Doug McLarty, Adrian Fazio, Christian Durand, Bob Emerick
-
Publication number: 20090134274Abstract: [PROBLEMS] Providing an accelerating device capable of safely and efficiently accelerating an aircraft even if the aircraft is a high-speed and heavyweight one. [MEANS FOR SOLVING PROBLEMS] The accelerating device has a support base for supporting an aircraft so that it does not go backward or levitate and does not pitch; a guide way placed along a predetermined route; guide means for guiding the support base along the guide way; and drive means for driving the support base along the guide way.Type: ApplicationFiled: October 6, 2006Publication date: May 28, 2009Applicant: CENTRAL JAPAN RAILWAY COMPANYInventors: Shiro Hosaka, Masatada Yamamoto, Satoshi Matsuda, Akio Yamanaka, Toshihiko Takeo
-
Patent number: 7530527Abstract: A heavier-than-air air vehicle, particularly a long endurance, solar powered, unmanned aerial vehicle (UAV) intended for “perpetual” flight within the stratosphere, is carried to its operational altitude suspended on a tether from a helium balloon. The tether is attached at or towards a tip of the UAV's wing so that it is carried in effectively a 90° banked attitude. At the desired altitude the UAV's powerplant is started and it flies on its tether in an upwardly-spiralling path relative to the balloon until a level or near level attitude is attained, when the tether is released and the UAV is permitted to assume free flight.Type: GrantFiled: May 20, 2004Date of Patent: May 12, 2009Assignee: Qinetiq LimitedInventor: Christopher Charles Kelleher