Abstract: The invention is directed to a method and arrangement for providing safe vertical landing of airplanes, which are not provided with VTOL equipment or which are hindered with respect to their actual flight capabilities, as well as for providing extrinsically supported zero-run takeoff of airplanes. An airplane equipped with lower takeup means is coupled in flight to upper takeup means carried by a rotary wing aircraft flying above the airplane. The rotary wing aircraft generates the propulsion necessary to transport the airplane and the lifting force and sets it down vertically. Zero-run takeoff is initiated by lifting the airplane and accelerating it into its direction of flight by the rotary wing aircraft. When sufficient height, speed against wind and self-propulsion are gained, the airplane releases the connection to the upper takeup means and flies without assistance.

Abstract: This invention uses magnetic levitation in combination with magnetic propulsion (MAGLEV) to accelerate an aircraft of spacecraft--or both crafts as a coupled unit--from standstill along a guideway to the highest possible launch velocity. The acceleration along the guideway is fuel efficient. The craft(s) are brought to launch velocity without using on board fuel. The computer controlled acceleration along the guideway could avoid high g forces to prevent damage to fragile payloads. The guideway may be sectionalized and of any shape. One section, for instance, may be circular to permit a long magnetically accelerated run with a relatively short length guideway. Very heavy crafts and payloads can be launched with superconducting levitation magnets in the guideway which form strong repulsive force fields with superconducting magnets in the MAGLEV vehicle. In another embodiment, the invention includes attraction magnets for the levitation.

Abstract: An aerial load-lifting system including a lighter-than-air unit, such as a blimp, below which is suspended a powered heavier-than-air unit, such as a helicopter, for example. The latter unit produces thrust which can be directed vertically, up or down, or tilted for translational motion in any direction. The units are connected by a flexible tension member such as a cable. The upper, lighter-than-air unit is sufficiently high above the lower, heavier-than-air unit to permit the heavier-than-air-unit to freely control and maneuver itself and the payload suspended below it with minimal restraint from the lighter-than-air units.

Abstract: A composite VTOL vehicle comprising a VTOL carrier with outboard mounted engines and an aircraft which is lifted off and retrieved by the carrier.

Abstract: A kit for converting a motorcycle to an aircraft or airborne vehicle includes a glider type parachute with fore and aft lines for connecting to and supporting a motorcycle, in a balanced position, with a propeller system including counter rotating propellers mounted on a pair of concentric shafts and driven by rollers drivingly engaging the rear drive wheel of the motorcycle. Directional control by means of control lines attached to the rear of teeter bars suspended below the wing and connected by directional control lines to outriggers attached to the front wheel structure of the motorcycle.

Abstract: A turbojet aircraft has a fuselage pod in which all fuel is stored for engines also linked to the pod. The pod and engines can be jettisoned in flight to improve aircraft performance in the event of a forced landing.

Abstract: An aerospike is adapted to be attached to the front nose of an aerodynamically asymmetric space vehicle system, such as the external tank and orbiter of the space shuttle. The aerospike basically comprises a tapered elongated portion having a first end which is adapted to be attached to the nose of the space vehicle, and a second free end terminating in a substantially rounded disc-like tip member. Use of the spike reduces aerodynamic heating and drag during ascent of the space vehicle into its orbital position, provides an attachment point for tether operations and for propellant recovery, and permits transportion of an external tank into its orbit.

Abstract: The invention is an improved method and device for utilizing the principles of lift achieved through the dynamic physics of the airfoil. In the case of the present invention, the airfoil utilized is a parafoil. The parafoil of the present invention is a multi-layered or multi-tiered arrangement to provide an improved directly vertical lift without the less efficient angular lift of the common parafoil horizontal dispersement of lifting power. The present parafoil vertical lift mechanism consists of a plurality of parafoils assembled in a multi-layered vertical configuration, a plurality of positioning stabilization rods to maintain the basic vertical spacing of the plurality of parafoils for an immediate ballooning effect at the start for take-off, a lifting frame suitably affixed to the assembled plurality of parafoils, a plurality of stabilization tether lines, at least one counter-drag tie line, and a load connector for suitably removably affixing the load to be lifted to the lifting frame.

Abstract: An improved auto-plane has been invented which has been adapted for air travel and road travel using a Pusher type design. The present invention auto-plane has two main wings which are cut approximately parallel to an imaginary fuselage centerline at about two-thirds the distance in from the wing's outer tip to the imaginary centerline, one of the two main wings being hinged along its cut and above its top surface at a height sufficient to allow both of the two wings to be folded inward 180.degree. with one resting atop the other. The auto-plane includes a rear stabilizer system which can be retracted forward to reduce the overall length for road use, a Pusher type propeller, and a Pusher type aviation engine which is located within the fuselage to drive the propeller. Landing wheels are located on the underside of the fuselage in an aviation landing relationship, e.g. tricycle, and aviation controls are located within the fuselage to control the aviation engine, propeller and elevons and rudders.

Abstract: An aerial load-lifting system comprised of a lighter-than-air unit, such as a blimp, below which is suspended a powered heavier-than-air unit, such as a helicopter, for example. The latter unit produces thrust which can be directed vertically, up or down, or tilted for translational motion in any direction. The units are connected by a flexible tension member such as a cable. The upper, lighter-than-air unit is sufficiently high above the lower, heavier-than-air unit to permit the heavier than-air-unit to freely control and maneuver itself and the payload suspended below it with minimal restraint from the lighter-than-air units.

Abstract: An airship with provisions for vectored thrust provided by a plurality of controllable pitch rotor thrust producing units attached to the elongated aerostat hull spaced from and on opposite sides of the center of overall mass of the airship. The pitch control systems for the rotors of all thrust units include collective and cyclic pitch controls of the main, horizontally rotating lifting rotors and the control systems are interconnected to be operable by a master control which establishes both similar and differential pitch settings of the rotors of selected thrust units in a manner to establish vectored thrust in directions which establish the required amounts of vertical lift, propulsion thrust, trim and control forces to control all flight aspects of the airship.

Abstract: Air, Land and Sea vehicle is convertible between aircraft form, road vehicle form and boat form. The conversion between aircraft form and road vehicle forms having (4) four tires as an automobile as well as a roadable vehicle structure that are movable outwardly for highway usage, and inwardly into stored position for the aircraft form or boat form, and having storage for the wing and tail assemblies which has a foldable section for this purpose. For conversion between aircraft form and boat forms, the apparatus has a retractable or extendable water propeller as propelling means in the water, and parts arranged for steering. The wings and tail assemblies are moved inwardly into stored position including auto and aero tires moved inwardly into their water-leak-proof compartments.

Abstract: A rolling vehicle having a generally spherical cage-like body with a diametrical axle on which a pod is suspended within the cage structure. The pod contains a propulsion unit which provides thrust for driving the vehicle in a particular direction and also carries aerodynamic lift and control surfaces. When the vehicle is rolling, the lifting surfaces reduce the bearing load of the vehicle on the supporting surface and the control surfaces provide directional control. Outrigger stabilizing wheels on the ends of the axle provide basic stability and can be made of buoyant material for operation on water.

Abstract: This invention provides a system for launching aircraft into free flight regime regardless of runway conditions, wherein a sled of the self-powered air cushion vehicle type is configured in plan form so as to accept in temporarily locked relation thereupon and in combination therewith an airplane in such manner that a successful take-off run in mutually aerodynamically compatible regime may be accomplished in spite of surface problems with the runway. Upon attainment of airborne speed, under control of the pilot the aircraft lifts off the sled into full free flight; and thus is airborne albeit the runway is at the time unusable by conventional wheel-geared aircraft; for example, as the result of a previous bombing attack on the runway by enemy aircraft. The sled incorporates self-propelling and directional guidance means for retrieval/reuse purposes, as well as a take-off abort control system.

Abstract: A three stage rocket vehicle (11) having a large forward propellant tank (12) and a small aft propellant tank (13) axially aligned. Secured to the rear end of the aft propellant tank (13) is an engine mount structure (14) carrying rocket engines (15). Offset and secured to the propellant tanks (12,13) is a payload structure (18). The propellants from the large forward tank (12) are fed into the aft propellant tank (13) and the rocket engines (15) are fed propellants from the aft propellant tank (13). This arrangement enables the vehicle to parallel stage its use of engines and components.

Abstract: A flying craft which is pushed by a surface vehicle which follows the flying craft is disclosed. The craft includes a winged body which is connected by an elongated push pole to a ground engaging propelling vehicle. The control of the winged body is accomplished by changing the vertical position of one end of the elongated push pole relative to the opposite end of the flying craft. The surface vehicle limits the angle which the pole makes relative to the surface to prevent the surface vehicle from overtaking the flying craft.

Abstract: An airplane features one basic airframe capable of carrying passengers or cargo such as intermodal containers or vehicles. It consists of a basic structure containing the cockpit, wings, engines and empennage. The cockpit and empennage portions are connected by an open, flat section (similar to a flatbed truck) on which the payload is placed. The payload thus forms and constitutes the fuselage shape and may be comprised of a passenger pod, cargo containers or outsized and vehicular equipment. Loading and unloading of such payloads is facilitated by a removable forward section to permit front end access and by laterally disposed vertical tails for aft end access.

Abstract: A flying device capable of carrying man, which contains a wing, a fuselage, and means such as cables for attaching the wing to the fuselage so that the fuselage is suspended below the wing. The fuselage contains a propulsion unit and normally does not have wings for creating a lifting force as in ordinary aircraft.

Abstract: An airship is provided utilizing a spherical balloon filled with buoyant gas such as helium at a pressure substantially greater than atmospheric so that its dimensions are substantially unaffected by changes in atmospheric pressure or temperature. The spherical balloon is rotatably mounted on a normally horizontal axle having end portions projecting from opposite sides of the balloon, and includes a rigid load supporting yoke including two arms extending upwardly from a central load supporting structure and each with an upper end suspended from the axle. The yoke arms carry engines which propel the airship in a forward direction transverse to the axle, and means are provided for rotating the balloon about the axle so that the balloon front surface moves upward relative to the centre of the balloon and provides lift due to the Magnus effect.

Abstract: An aircraft is provided utilizing a spherical balloon filled with buoyant gas such as helium at a pressure substantially greater than atmospheric so that its dimensions are substantially unaffected by changes in atmospheric pressure or temperature. The aircraft may take the form of a self-propelled and self-contained airship, or may be merely a passive device for providing lift and intended to be towed by and controlled from a helicopter. The spherical balloon is mounted on a normally horizontal axle having end portions projecting from opposite sides of the balloon, and includes a rigid load supporting yoke including two arms extending upwardly from a central load supporting structure and each with an upper end suspended from the axle.

Abstract: A combination road and air vehicle having separate engines for each craft is disclosed. The aircraft has an air frame with wings and tail elements attached to a fuselage with a tricycle landing gear attached to the air frame. A nose platform extends forward from the bottom of the fuselage. The platform is adapted to receive and support a small land vehicle. The aircraft controls are mounted on a folding stalk attached to the top side of the platform. The land vehicle has a central opening in its body through which the control stalk may be elevated to a vertical position. The aircraft and land vehicle each have its own power plant and control system.

Abstract: A substantially spherical human living module or space has a plurality of pontoons projecting from its lower hemisphere. It is preferably arranged to be self-propelled, as a vehicle, and the pontoons are preferably extensible and retractable. In a version in which wheeled landing gear is provided, a spherical human living space is provided with helicopter blades and four jet engines at the bottom of the craft, and two jet engines on the right and left sides, which swivel for direction control, for propelling the device.

Abstract: The apparatus is convertible between road vehicle and aircraft forms having wing and tail assemblies as well as propelling structure that are movable outwardly for the flying form and movable inwardly in stored position for the road vehicle form. All of the parts of the apparatus remain intact in both the road and flying forms. Storage for the wing and tail assemblies and the propelling structure is in side and end compartments, and the wing and tail assemblies have foldable sections for this purpose. The apparatus has a pair of front wheels and a pair of rear wheels, the latter wheels being movable between a narrowed rearward position for road use which allows storage of the wings in the side compartments and a forward widened position for aircraft use. The tail assembly is supported on a slide mechanism which extends downward in a forward longitudinal direction whereby the tail assembly is lowered as it is moved forwardly for storage in the rear compartment.

Abstract: This invention pertains to helicopter airborne load systems and composite aircraft configurations. The composite aircraft configurations are designed to allow a fixed wing aircraft to take off and land either vertically or in a short ground run when assisted by a rotary winged aircraft such as a helicopter, and includes a maneuverable probe system used to attach two aircraft to form a composite aircraft configuration, the fixed wing aircraft embodying the use of a receptacle or attachment device cooperative with the maneuverable probe to effect the uniting of the aircraft. The helicopter systems airborne includes the use of the probe to cooperate with special external pods capable of carrying loads, fuel and instrumented devices.

Abstract: An orbit vehicle launch system including reusable turbojet propelled booster vehicles releasably connected to a reusable rocket powered orbit vehicle. The coupled orbiter-booster combination takes off horizontally and ascends to staging altitude and speed under booster power with both orbiter and booster wings providing lift. After staging, the booster vehicles fly back to earth for horizontal landing and the orbiter vehicle continues ascending to orbit.

Abstract: A vehicle for traveling in the air and on the ground is equipped with two, four, or eight propellers on vertical shafts, each driven by a rotary hydraulic motor of the radial-piston type. The motor comprises two rotors which are connected in individual hydraulic circuits supplied with fluid from different hydraulic pumps. One embodiment of the vehicle comprises an automobile with the propellers mounted in oblique air ducts or in shrouds pivotable in the travel direction. Each rotor of the hydraulic motors is coupled to the shaft unidirectionally so that in case of failure, the shaft can be driven by the other rotor. Each hydraulic pump preferably produces four equal fluid flows and comprises two rotors on a common shaft, each rotor with two separate groups of cylinders, the eccentricity of at least one of the rotors being adjustable. Both the hydraulic motor and the pump have inlet and outlet connections on the radial periphery of the housing.

Abstract: A vehicle for traveling in the air and/or on the ground is equipped with two, four, or eight propellers on vertical shafts, each driven by a rotary hydraulic motor of the radial-piston type. The motor may comprise two rotors which are connected in individual hydraulic circuits supplied with fluid from different hydraulic pumps. One embodiment of the vehicle comprises an automobile with the propellers mounted in oblique air ducts or in shrouds pivotable in the travel direction. Each rotor of the hydraulic motors is coupled to the shaft unidirectionally so that in case of failure, the shaft can be driven by the other rotor. Each hydraulic pump preferably produces four equal fluid flows and comprises two rotors on a common shaft, each rotor with two separate groups of cylinders, the eccentricity of at least one of the rotors being adjustable. Both the hydraulic motor and the pump have inlet and outlet connections on the radial periphery of the housing.

Abstract: A land-, air- and water-vehicle comprising a rolling, floatable and steerable fuselage, the roof-hinged doors of which serve as its wings, and which fuselage's lateral and rear portions are extendable into an airfoil with attached fins and stabilizer, whereby wings, fuselage and stabilizer provide sufficient aerodynamic lift.

Abstract: An air lifting vehicle includes, inter alia, a main frame containing an engine, a helicopter-type rotor driven by the engine, a rear located propeller which provides torque compensation for the rotor as well as yaw control for the vehicle, and a pilot's cabin. Attached to the frame through a plurality of outwardly extending truss members is a keel structure which includes a circular truss section essentially coaxial with and positioned above the rotor and other generally triangular or rounded triangular truss sections attached fore and aft of the circular truss section. Balloon members including fore and aft generally triangular Forlanini envelope sections are secured to the keel and laced together at the center to define a circular opening or duct above the rotor. A pair of forward thrusting propellers are driven by an auxiliary engine carried in the frame and are gimbaled in the elevational plane for pitch control of the vehicle.

Abstract: A combination motorcycle and hang-glider comprising a triangular wing formed by a flexible sheet material affixed to a trifurcated frame structure which is pivotally attached to a vehicle, such as a motorcycle suspended below the wing by a plurality of truss members, whereby the wing and the vehicles are adjustably connected to each other. The frame structure includes pivotal means and means for changing the angle of attack of the wing to provide aerodynamic lift for the motorcycle.

Abstract: A balloon has an airfoil-shaped member connected to its top surface. The airfoil-shaped member has a top curved skin with a plurality of parallelly-spaced partitions which form therebetween a plurality of air passageways for air. Upon the descent or lateral movement of the balloon, the airfoil-shaped member is expanded to provide a vertical stabilization of the balloon and to afford better control of the balloon during the lateral travel thereof.

Abstract: An airplane which is universally adaptable to land on any type of flat surface, such as water, snow, ice, as well as land. The landing pods of the aircraft include a wheel with a V-shaped ski surface surrounding each wheel. Each landing pod is constructed in the shape of a hydrofoil for moving through water and creating lift. A boat is detachably securable to the underside of the fuselage of the aircraft. The boat functions as pontoons when the plane is landing and parked on water.

Abstract: An aircraft that is designed to additionally be able to travel along a railroad track so that it can get into a heart of a city, instead of terminating at an airport located some distance away from the city; the aircraft including wings which can be folded inwardly adjacent the side of the aircraft fuselage so that it requires approximately a same width of clearance as a conventional railroad train, and the railroad tracks being additionally fitted with a system of channel rails welded on top of the oid railroad track so that the airplane can travel thereupon.

Abstract: This invention relates to a method and apparatus whereby functioning airborne conventional aircraft and engine combinations may be assisted during flight in attaining above normal airspeeds and/or altitudes; for the purpose of improving their performance during flight. In the method steps, well known apparatus elements, and/or new and useful combinations thereof, are utilized to enable such aircraft to achieve flight advantages, and improved flight performance, not believed to be possible prior to this invention. According to the method, booster apparatus is used initially in acquiring altitude, forward momentum of the aircraft, rotational momentum of its rotor airfoils, and the like. Apparatus used includes oxygen booster systems. Such systems can include forward thrust rockets, rotational boosters, and apparatus for injecting a supplemental oxidizer into a gas turbine engine afterburner.

Abstract: An escape capsule integrally designed within a parent aircraft and having a fly-away capability throughout the entire speed range of the parent aircraft. The capsule utilizes segments of the leading edges of the aircraft wings to provide flight capability and stabilization to the capsule, an elevon system controlling the capsule about both its lateral and longitudinal axes, and rudder and vertical stabilizing elements for controlling the capsule about its vertical axis. A rocket is provided to supply the thrust necessary to accomplish positive separation of the capsule from the parent aircraft along a required trajectory. A thrust system, such as a turbojet or fan jet engine, is provided for sustaining the capsule in flight.

Abstract: Various modifications are disclosed of the composite aircraft, which is the subject of U.S. Pat. No. 3,856,236 by this same inventor. The control console is supported from the center of the upper rotating balloon sphere instead of its south pole to reduce the periodic motion of the console about its point of attachment to the sphere. The console is supported from the center of an inner framework through a tapered indentation in the bottom of the sphere. A lift command control system determines the angle of attack of each wing about the periphery of the sphere to provide the force required to generate movement of the sphere in a preselected direction. If the wing experiences a gust, the force reaction compels the wing to seek a different angle of attack to keep the new force in balance with the command force exerted by the control on the wing to automatically provide gust control. A pneumatic lift command control system is illustrated.

Abstract: This invention relates to marine skimmer craft that is, watercraft of the kind that is only partially immersed and skims along the surface of the water under propulsion, the craft being supported at least partly by aerodynamic force produced by suitable support structure. According to this invention the support structure comprise wings located in at least two planes: each wing consists of at least two wing panels joinable by their mutually adjacent lateral edges whereby the number of wing panels actually used may be selected in dependence upon the desired lift characteristics and the desired position of the center of gravity of the craft as a whole. As an example, two wing panels may be arranged in one plane on either side of the craft and four wing panels in another plane above its stern.

Abstract: A hovercraft capable of free flight having lifting fans driven alternatively by a gas turbine coupled to the fan shafts or by the diverted exhaust gases of jet engines impinging on circumferential turbine blades on the fans. The jet engines normally provide propulsion, but their exhaust may be directed downward to provide lift. Baffles at the various intake and discharge ports control the direction of movement of the craft and contribute to its stability. Retractable wings enhance lift during horizontal flight.

Abstract: A dual-function aircraft is disclosed having a fuselage shaped like an airfoil, a series of airfoils of shorter chord length arranged in tandem and disposed below the fuselage to provide additional aerodynamic lift, and a downwardly movable rear wall and a pivoted forward airfoil which forms a plenum chamber under the fuselage and produce a cushion of air during the ground mode. Transition from the ground effect mode to the flight mode is made in flight by simultaneously lowering the tandem of airfoils, lifting the rear wall and altering the angle of attack of the forward airfoil.