Abstract: This disclosure relates generally to the field of unmanned aircraft systems (UAS), specifically to launch, fly and land unmanned aerial vehicles (UAV). This disclosure describes a system comprised of a UAV, a portable launch pad, a telescoping landing net and an integrated RFID system. This system provides a unique combination of UAV performance and payload capabilities with integrated Radio Frequency Identification Device (RFID) electronic systems capable of withstanding extreme weather conditions including high winds in remote locations.

Abstract: A system for launching an unmanned aerial vehicle (UAV) payload includes a launch tube, liquid rocket, and launch control assembly. The rocket is positioned in the launch tube and contains the UAV payload. A booster assembly may include a canister partially filled with liquid. A gas cylinder is filled with compressed gas. The liquid is pre-pressurized by the gas or mixed with the gas right before launch such that, upon launch, liquid and gaseous thrust stages launch the rocket to a threshold altitude. The UAV payload deploys after reaching the threshold altitude. Optional stability tubes may be connected to the launch tube, which may be buoyant for water-based operations. An optional tether may be connected to the liquid rocket for arresting its flight prior to reaching apogee. The UAV payload is not launched directly by the gas/liquid mix. A method of launching the UAV payload is also disclosed.

Abstract: A UAV attachment assembly, used with a UAV launch assembly comprising a frame and a launch driver, comprises a base, a UAV support, a biasing element, a coupler, and a retainer. The base is operably coupled to the launch driver. The UAV support is mounted to the base and is placeable in vertically collapsed and vertically extended orientations. The biasing element biases the UAV support towards the collapsed orientation. The coupler releasably couples the UAV support to a UAV when the UAV support is in the extended orientation, the UAV support being free of the UAV when in the collapsed orientation. The retainer maintains the UAV support in the vertically extended orientation prior to launch and releases the UAV support at launch so that the biasing element can cause the UAV support to move towards the collapsed orientation and to disengage from the UAV.

Abstract: A method, system and a floating unit. The floating unit includes a propeller, a frame, a propeller motor that is configured to rotate the propeller about a first axis; wherein the propeller motor is coupled to the frame, a movable steering element; a controller, for controlling at least one of the propeller motor and the movable steering unit to affect at least one of a location and an orientation of the floating unit; and an interfacing module for coupling a payload to the floating unit and for receiving power from a connecting element that couples the floating unit to a ground unit; wherein the power received by the power interface is utilized to power the propeller motor and the controller.

Abstract: Various embodiments of the present disclosure provide an apparatus configured to automatically retrieve, service, and launch an aircraft. For retrieval, the aircraft drops a weighted cable, and pulls it at low relative speed into a broad aperture of the apparatus. In certain instances, the cable is dragged along guiding surfaces of the apparatus into and through a slot until its free end is captured. The aircraft becomes anchored to the apparatus, and is pulled downward by the cable into a receptacle. Guiding surfaces of the receptacle adjust the position and orientation of a probe on the aircraft, directing the probe to mate with a docking fixture of the apparatus. Once mated, the aircraft is automatically shut down and serviced. When desired, the aircraft is automatically started and tested in preparation for launch, and then released into free flight. A full ground-handling cycle is thus accomplished with a simple, economical apparatus.

Abstract: 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.

Abstract: An aircraft capable of thrust-borne flight can be automatically retrieved, serviced, and launched using equipment suitable for use on a small vessel, or at a base with similarly limited space or irregular motion. For retrieval, the aircraft drops a tether, and pulls the tether at low relative speed into contact with a horizontal guide. The tether is pulled across the guide until the guide is captured by a hook or other end effector. The tether length is then adjusted as necessary, and the aircraft swings on the guide to hang in an inverted position. Translation of the tether along the guide then brings the aircraft to a docking carriage, in which the aircraft parks for servicing. For launch the carriage is swung upright, the end effector is released from the guide, and the aircraft thrusts into free flight. A full ground-handling cycle can thus be accomplished automatically with simple and economical apparatus.

Abstract: A man-portable unmanned aerial system launcher (UAS) launcher includes a rail assembly having an internal track and a carriage assembly having a base configured to translate within the internal track. The carriage assembly also includes a cradle configured to support a UAS and a bracket configured to support the cradle above the base. The UAS launcher includes a launch control system configured to secure the carriage assembly in the launch-ready position until the launch control system receives a launch signal. The UAS launcher also includes one or more elastic members configured to engage the carriage assembly and the rail assembly. Once the carriage assembly is translated to the launch-ready position, strain is applied to the carriage assembly by the one or more elastic members. Release of the carriage assembly enables force generated by strain of the elastic members to propel the carriage assembly toward a launch position.

Abstract: A system for use in monitoring, measuring, computing and displaying the volumes of internal liquid and gas within a telescopic aircraft landing gear strut. Pressure sensors and temperature sensors and motion sensors are mounted in relation to each of the landing gear struts to monitor, measure and record the impact movement and rates of internal landing gear strut fluids; experienced by landing gear struts, as the aircraft landing gear initially come into contact with the ground. The computer of this system measures the compression experienced by each landing gear strut and determines if the landing gear strut is improperly serviced with either excess or deficient volumes of hydraulic oil and nitrogen gas. Additional features include automating the inspections required to aircraft landing gear, prior to flight, during flight and during landing events.

Abstract: A furling system adapted for use with an air cushion landing system (ACLS) coupled to a hull of an airship is disclosed. The furling system includes a deployable cover having two lateral edges. The cover is configured to cover at least a first portion of the ACLS when the cover is deployed. The furling system also includes a fairing that has an inlet and is coupled to the hull of the airship. The furling system also includes a pair of cables each coupled to at least one point along respective lateral edges of the cover. The pair of cables is configured to selectably draw the cover into the fairing through the inlet when the pair of cables is activated in a first direction, thereby stowing the cover and exposing the ACLS.

Abstract: A stunt kite is attached to three lines that are attached to a single handle. Moving the handle will change the angle of the kite by pulling on the desired line or lines. By changing the angle of the kite, the user can direct the wind that is pushing on its sail, causing the kite to go off on a different direction. By doing this, the user is able to perform controlled aerial, ground, underwater and partially submerged stunts.

Abstract: A vehicle and method for enabling propulsive flight from suborbital altitudes and velocities directly to far space, or beyond Low Earth Orbit (LEO), preferably without requiring injection into or refueling in LEO. The vehicle is preferably reusable and can withstand re-entry speeds and temperatures higher than those that are typical for LEO vehicles. The vehicle preferably lands horizontally, for example on a runway. The vehicle forms the upper stage of a booster vehicle system which can be launched either from the ground or from a subsonic air platform. The vehicle may optionally be used for LEO missions.

Abstract: A vehicle includes a first sub-vehicle, and a second sub-vehicle which is repeatably moveable between coupled and uncoupled conditions with the first sub-vehicle. The first and second sub-vehicles each include a landing system and propulsion system. The first and second sub-vehicles are in the coupled condition during take-off. The first and second sub-vehicles are separately flyable in the uncoupled condition. Both vehicles are launched horizontally, by a ramp, or vertically, using atmospheric lift to achieve atmospheric flight, orbital, or sub-orbital launch.

Abstract: A UAV attachment assembly, used with a UAV launch assembly comprising a frame and a launch driver, comprises a base, a UAV support, a biasing element, a coupler, and a retainer. The base is operably coupled to the launch driver. The UAV support is mounted to the base and is placeable in vertically collapsed and vertically extended orientations. The biasing element biases the UAV support towards the collapsed orientation. The coupler releasably couples the UAV support to a UAV when the UAV support is in the extended orientation, the UAV support being free of the UAV when in the collapsed orientation. The retainer maintains the UAV support in the vertically extended orientation prior to launch and releases the UAV support at launch so that the biasing element can cause the UAV support to move towards the collapsed orientation and to disengage from the UAV.

Abstract: An aircraft comprising a fuselage, a vessel associated with the fuselage, a propulsion system associated with the fuselage, and a lift system. The vessel is capable of storing a pressurized gas compressed to a density that allows the aircraft to operate under water. The lift system is capable of providing the aircraft lift to fly in air.

Abstract: 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 releasably 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).

Abstract: Transportation infrastructure comprises linear induction drives wherein a roadway surface is induced to simultaneously exert forward, lateral, levitation and three axis angular alignment forces on a vehicle and wherein a vehicle is capable of inducing roadway surface currents that produce said forces in said roadway surface. Comprehensive system sustains continuous traffic flow from the point of entering the infrastructure to the moment of disembarking in a parking facility. Transportation infrastructure comprises integration of air and space travel with substantially reduced cost and transit time.

Abstract: An unmanned aerial vehicle (UAV) system provides for UAV deployment and remote, unattended operation with reduced logistics requirements. The system includes a launcher that can include one or more launch tubes, each launch tube configured to house a UAV in a canister and one or more gas generators operatively connected to each canister and configured to push the UAV out of the launch tube by releasing gas into the canister. A controller for activating the gas generators can sequentially, and with a predetermined time delay, expel the UAV with a desired velocity and acceleration. The system further includes a UAV recovery device, a power supply, a security subsystem, a command and control subsystem and a communications subsystem. Command, control and communications can be provided between a remote station and the UAV.

Abstract: An air vehicle that is launched from inside a launcher, includes a release mechanism for releasing fins of the vehicle from a stowed condition to a deployed condition. The release mechanism includes a pin that is located within a cavity in the fuselage of the air vehicle. Pressurized gasses initially fill the cavity in the fuselage. The launcher includes a reduced-pressure portion such as from a muzzle brake. When the air vehicle passes into the reduced-pressure portion of the launcher, the gas pressure behind the air vehicle is reduced. This causes the pressurized gas within the cavity to drive the release mechanism backwards out of the cavity. The length of the pin may be used to control the timing of the fin deployment, the delay between the initial movement of the release mechanism out of the cavity, and when the fins are released.

Abstract: 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.

Abstract: 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.

Abstract: A device for launching unmanned missiles from an aircraft with a pallet, on which at least one container is provided to receive a missile. The container has an upper container section that has a pylon for the suspended, detachable support of the missile. The container has a lower container section that is embodied as a support area for the missile.

Abstract: A projectile and a compact carrying and launching case in combination. The projectile includes foldable wings which when unfolded resemble a plane. The compact carrying and launching case includes a two piece housing that is pivotally attached to each other about a hinge/launching mechanism. When closed, the two piece housing encloses the plane in its folded position. When opened, the hinge/launching mechanism can be pulled to a cocked position and then released forcibly moves the projectile such that it releases from the launching mechanism and is capable of flying.

Abstract: A canister system for a folding aircraft may include a canister housing and a launch mechanism powered by one or more compression springs. A hand-operated drive mechanism may rotate a plurality of threaded rods to drive the launch mechanism from a released position to a cocked position, in which mechanical energy is stored in the springs. A latch mechanism may capture the launch mechanism in the cocked position. The canister may include a housing for receiving and storing the aircraft when the launch mechanism is in the cocked position. A trigger mechanism may release the latch mechanism, permitting the energy stored in the compressed springs to drive the launch mechanism toward the released position and propel the aircraft from the housing at launch velocity.

Abstract: A rocket launch system (1) includes a tubular rocket launcher carriage (2) with electromotive cableway traction drives (26) conveyed beneath a two axis pivot (63) anchored to the earth, elevated into a co-axial transfer tube (124, 143) leading to three primary tether cables (27) whose weight is offset by balloons (164). The carriage is conveyed to a docking station (166) supported into the stratosphere by a pair of secondary cables (184) suspended under an attachment frame (162) for tensioning balloons. The carriage is engaged by a carriage end gripper (196) guided by two secondary and two tertiary cables (186) and lifted by a lower hoist (198) guided by the secondary cables. This lower hoist is supported by an upper hoist (168) suspended from the tensioning balloons attachment frame.

Abstract: 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.

Abstract: A launch vehicle comprising a casing, a solid propellant, a channel, a geometric feature, and a suppression structure. The solid propellant is located within the casing. The channel is through the solid propellant, and the geometric feature is in the channel. The suppression structure is located around a centerline for the channel and located upstream in a flow path from the geometric feature.

Abstract: The invention concerns an ultra-rapid air vehicle together with a method of aerial locomotion by means of an ultra-rapid air vehicle, where the air vehicle is propelled by a system of motors formed of turbojets (TB1, TB2), ramjets (ST1, ST2) and a rocket motor which can be made streamlined to reduce the drag of the base during the cruise phase, and where the vehicle has a gothic delta wing (A) fitted with moving fins (a1, a2) at both outer ends of the trailing edge of the delta wing (A).

Abstract: 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.

Abstract: 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.

Abstract: A system and method for assessing the risk of conjunction of a rocket body with orbiting and non-orbiting platforms. Two-body orbital dynamics are used to initially determine the kinematic access for a ballistic vehicle. The access may be represented in two ways: as a volume relative to its launcher and also as a geographical footprint relative to a target position that encompasses all possible launcher locations.

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

Abstract: 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.

Abstract: 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.

Abstract: A system for launching an unmanned aerial vehicle (UAV) payload includes a launch tube, liquid rocket, and launch control assembly. The rocket is positioned in the launch tube and contains the UAV payload. A booster assembly may include a canister partially filled with liquid. A gas cylinder is filled with compressed gas. The liquid is pre-pressurized by the gas or mixed with the gas right before launch such that, upon launch, liquid and gaseous thrust stages launch the rocket to a threshold altitude. The UAV payload deploys after reaching the threshold altitude. Optional stability tubes may be connected to the launch tube, which may be buoyant for water-based operations. An optional tether may be connected to the liquid rocket for arresting its flight prior to reaching apogee. The UAV payload is not launched directly by the gas/liquid mix. A method of launching the UAV payload is also disclosed.

Abstract: A lighter than air (LTA) balloon and payload for the LTA balloon are stored on or in an underwater launcher. The launcher provides a source for a supply of a lighter than air gas, which is operatively connected to the LTA balloon until release. On deployment, the lighter than air gas is generated. The LTA balloon is deployed by activating the launcher to fill the LTA balloon and then releases the LTA balloon.

Abstract: A transforming unmanned aerial-to-ground vehicle assembly comprising: an aerodynamic flying assembly comprising an unmanned aerial vehicle integrated with an unmanned ground vehicle, a power unit shared by the unmanned aerial vehicle and the unmanned ground vehicle, vehicle controls shared by the unmanned aerial vehicle and the unmanned ground vehicle, a disengagement mechanism to separate the unmanned ground vehicle from the unmanned aerial vehicle, one or more manipulator arms located on either the unmanned aerial vehicle or the unmanned ground vehicle, and landing gear.

Abstract: Embodiments of a submersible transport and launch canister are provided for use by a diver in the deployment of an airborne object. In one embodiment, the submersible transport and launch canister includes a pressure vessel having an open end portion and a storage cavity configured to receive the airborne object therein. A diver-actuated cap is movable between an open position and a closed position in which the diver-actuated cap sealingly engages the open end portion. A propellant device is fluidly coupled to the storage cavity and is configured to propel the airborne object from the storage cavity and through the open end portion when the propellant device is actuated by the diver.

Abstract: Embodiments of a method for deploying an airborne object are provided utilizing a submersible transport and launch canister of the type that includes a pressure vessel in which the airborne object is stored and a cap which sealingly engages the pressure vessel. In one embodiment, the method includes the steps of positioning an end portion of the pressure vessel above the surface level of a body of water, opening the cap, and launching the airborne object from the pressure vessel while in the body of water.

Abstract: An aircraft is configured for flight in an atmosphere having a low density. The aircraft includes a fuselage, a pair of wings, and a rear stabilizer. The pair of wings extends from the fuselage in opposition to one another. The rear stabilizer extends from the fuselage in spaced relationship to the pair of wings. The fuselage, the wings, and the rear stabilizer each present an upper surface opposing a lower surface. The upper and lower surfaces have X, Y, and Z coordinates that are configured for flight in an atmosphere having low density.

Abstract: 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.

Abstract: A non-powered pre-stage (10) with a commensurably large wing area is used to launch a variety of single-stage and multiple-stage space vehicles (20), such as conventional ballistic rockets and prospective spaceplanes, from conventional runways. This method of launch eliminates need in dedicated ground launch structures and/or dedicated long runways. The vehicle to be launched (20) is mated to this non-powered aero-assisted pre-stage (NAP) (10), with their flight directions aligned, using a lock-and-release mechanism (30). The resulting stack takes off like a conventional airplane using the propulsion of the vehicle and aerodynamic lift of the NAP. After the desired trajectory of the vehicle is achieved, the vehicle is separated from the NAP and continues its ascent. The NAP returns back to the surface for reuse or disposal. Thus, a wide variety of conventional airfields can be used for launch of ballistic and aero-assisted flight vehicles.

Abstract: Systems and methods are disclosed for autonomous or remote-controlled operation of unmanned aerial vehicles (“UAVs”). An integrated mechanical and electrical system is capable of launching, controlling, snagging, recovering, securing, parking, and servicing UAVs without human intervention at the site of the system. The illustrative embodiment comprises a boom and a container that houses the boom and UAV(s). The boom rotates about its longitudinal axis to operationally orient a plurality of faces thereof. Each face is associated with certain system operations, including but not limited to: launching a UAV, snagging a UAV from the air, and securing a UAV to the boom.

Abstract: 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.

Abstract: 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.

Abstract: Embodiments of a method for deploying an airborne object are provided utilizing a submersible transport and launch canister of the type that includes a pressure vessel in which the airborne object is stored and a cap which sealingly engages the pressure vessel. In one embodiment, the method includes the steps of positioning an end portion of the pressure vessel above the surface level of a body of water, opening the cap, and launching the airborne object from the pressure vessel while in the body of water.

Abstract: Embodiments of a submersible transport and launch canister are provided for use by a diver in the deployment of an airborne object. In one embodiment, the submersible transport and launch canister includes a pressure vessel having an open end portion and a storage cavity configured to receive the airborne object therein. A diver-actuated cap is movable between an open position and a closed position in which the diver-actuated cap sealingly engages the open end portion. A propellant device is fluidly coupled to the storage cavity and is configured to propel the airborne object from the storage cavity and through the open end portion when the propellant device is actuated by the diver.

Abstract: An on board secondary propulsion system for an aircraft provides the capability of taxiing the aircraft on the ground without using the main aircraft engine(s). The power system includes a small taxi engine mounted on or in the aircraft at a location suitable to provide a thrust sufficient only to taxi the aircraft. Such a suitable system may be provided as original equipment to an aircraft or retrofitted to existing aircraft. The on board secondary propulsion system, in addition to the taxiing function, can provide electrical power, an environmental control unit, power for the aircraft hydraulic system and an emergency power unit as desired. The system can also be used to supplement the main aircraft engines as necessary during takeoff and climb to further reduce fuel consumption, noise, engine emissions, maintenance costs and extend the life of the main aircraft engines, reduce the required takeoff distance of an aircraft when used in conjunction with the main engines and provide emergency glide support.

Abstract: An air-based vertical launch system is described by means of which ballistic missile defense can be achieved effectively from a large aircraft. A method for ensuring safe missile egress is proposed. A method for ensuring that the missile strikes the ballistic missile payload section is also proposed. Together, the air basing method employing vertical (or near-vertical) launch and semi-active laser guidance yield an affordable and operationally effective missile defense against both tactical and long-range ballistic missiles. The affordability of missile defense is enhanced by the ability of an aircraft equipped with a vertical launcher to simultaneously carry out several defensive and offensive missions and to provide other capabilities such as satellite launch at other times.

Abstract: A UAV attachment assembly, used with a UAV launch assembly comprising a frame and a launch driver, comprises a base, a UAV support, a biasing element, a coupler, and a retainer. The base is operably coupled to the launch driver. The UAV support is mounted to the base and is placeable in vertically collapsed and vertically extended orientations. The biasing element biases the UAV support towards the collapsed orientation. The coupler releasably couples the UAV support to a UAV when the UAV support is in the extended orientation, the UAV support being free of the UAV when in the collapsed orientation. The retainer maintains the UAV support in the vertically extended orientation prior to launch and releases the UAV support at launch so that the biasing element can cause the UAV support to move towards the collapsed orientation and to disengage from the UAV.