Abstract: Lift for an aircraft is provided by forming a longitudinal lifting duct therethrough, said lifting duct having a substantially planar roof and a longitudinally cambered floor. When the aircraft is driven forwardly, a stream of air enters and passes through the lifting duct and the contouring of the floor of the lifting duct give rise to a pressure gradient in the air stream which result in a higher pressure on the roof of the lifting duct than on the floor thereof so that the pressure difference provides lift for the aircraft.

Abstract: An ultralightweight aircraft including a principal longitudinally disposed load-carrying member and a wing structure supported by the load-carrying member and positioned in a horizontal plane spaced a distance below or above the horizontal plane of the load-carrying member. A housing is attached to and depends from the load-carrying member, an operator's station is disposed within the housing, the wing structure is attached to the housing and a landing gear system connected to a lower surface of the housing. A rudder and elevator assembly is mounted on the load-carrying member aft of the wing structure. A propeller is mounted on the load-carrying member between the wing structure and the rudder and elevator assembly for rotation about a longitudinal centerline of the load-carrying member. An engine is directly mounted on the load-carrying member, and a belt system drivingly connects the output of the engine to the propeller.

Abstract: Improved ultralight aircraft constructed with a tubular keel extending over the length of the aircraft from forward of its wing to the tail thereof. The aircraft includes a cantilever engine mount which is carried on a pair of mounting plates extending longitudinally from the forward end of the tubular keel. The propeller shaft, driven by the engine through a speed reduction arrangement, is supported in a bearing disposed on the engine mount. The aircraft includes a cage assembly for the operator's seat and has upright tubular rails and a pair of longitudinally extending side rails mounted on a shock absorbing landing gear. The landing gear has a nose wheel and a pair of laterally spaced rear wheels. The rear wheels are carried on the outer ends of a pair of longitudinally spaced, transversely extending tubular members.

Abstract: A ducted propeller aircraft from which visibility is excellent and which is capable of operating quietly and efficiently has a propeller shroud which serves as a primary load path to pass bending and torsional stresses to which the mainplane is subject in use between the portions of the mainplane either side of the shroud, the shroud defining a duct which is unimpinged upon by any portion of the turbulent airflow emanating from the mainplane.

Abstract: A wingless aircraft having a power channel with two parallel ducts afixed to the top of the fuselage. A jet engine or other drive mechanism is positioned within each duct. No air flow is permitted between any part of the lower surface of the power channel and the fuselage. Each duct contains a number of variable-pitch airfoils that are independently adjustable. This independence of adjustment between variable-pitch airfoils within a single duct and the ability to adjust the variable-pitch airfoils in one duct as a group independently of those in another duct provides horizontal stability and compensates for undesired yawing. The lift is controlled to somewhat by adjustment of the variable-pitch airfoils and the angle of attack, and to an even greater extent in cooperation with adjustable auxiliary wing panels mounted above openings in the upper surface of each duct above one of the variable-pitch airfoils. The auxiliary wing panels nest in openings above the airfoils when not in use.

Abstract: A sound reducing combined low mid-wing and horizontal stabilizer airplane with near longitudinal center line thrust twin engines having intensified aileron, elevator and rudder control. Small jet engines rigidly attached to the ailerons intensify attitude control for low speed manuevers.

Abstract: A parafoil for supporting a flying machine, which parafoil has a forwardly extending central section open at the front to scoop in air during flight, and wings attached to the rear of the central section and which receive air into the interior thereof either directly or from the central section, said wings being divided into compartments of equalized pressure, and restraining elements attached to the parafoil central section in front of the parafoil wings and to the outer ends of the parafoil wings, thereby in flight to hold down the front of the parafoil central section and hold down the parafoil wings in an inverted U-shape.

Abstract: An ultralight aircraft has a single stick three-axis aerodynamic control, twin engined power control, wing- and tail-mounted ailerons, an inverted V-tail and wide span wings with upturned tips.

Abstract: A lightweight, man carrying aircraft including a skeletal fuselage assembly in combination with a primary arc-shaped lifting airfoil having variable camber, incidence angle, and pitching moment and a secondary stabilizing airfoil of a tubular, ring-like configuration. The arc-shaped primary airfoil is superior to traditional low speed airfoil forms due to its high aerodynamic efficiency, inherent design simplicity and strength. The ring-tail assembly, offering marginal aerodynamic lift, contributes significantly to the in-flight stability and safety of the aircraft. Both airfoil members are independently controllable and constructed of a fabric or like skin material which is fitted over a wing assembly and tensioned into an operable airfoil form by the aerodynamic forces of the air during flight. Typically, the wing assemblies are supported and maintained by a lightweight, tubular fuselage structure to which is affixed the propulsion system, control mechanisms and ground support assemblies.

Abstract: A cruciform wing structure for a solar powered aircraft is disclosed. Solar cells 28 are mounted on horizontal wing surfaces 20, 22. Wing surfaces 24, 26 with spanwise axis perpendicular to surfaces 20, 22 maintain these surfaces normal to the sun's rays by allowing aircraft to be flown in a controlled pattern at a large bank angle.The solar airplane may be of conventional design with respect to fuselage, propeller and tail, or may be constructed around a core 70 and driven by propeller mechanisms 75, 76, 77, and 78 attached near the tips of the airfoils.

Abstract: A tandem wing aircraft having two wings of similar area wherein a lower first wing is located at the forward end of the fuselage attached directly to fuselage structure. A second higher wing is located at the aft end of the fuselage but is aerodynamically separated from the fuselage structure by strut structure. Pitch control is achieved by increasing or decreasing the lift on either wing; but downward acting load is not required. The two wings are preferably vertically separated by 25% to 50% of the span of the wings. Control redundancy for flight safety is achieved because of availability and location of control surfaces. Higher aspect ratio wings can be used because of inherently reduced bending moments on the wing; and overall aircraft gross weight is reduced due to structural and aerodynamic efficiency.

Abstract: In a lightweight aircraft having a principal longitudinal load-carrying member, a wing structure mounted on the load-carrying member, a tail rudder and elevator assembly mounted on the load-carrying member, a propeller mounted on the load-carrying member for rotation about the member's longitudinal center line, an engine mounted on the load-carrying member, and means drivingly connecting the engine to the propeller.

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: A landing gear for ultralight aircraft includes a main landing gear assembly disposed in a position relative to the longitudinal axis of the aircraft to permit either tail wheel type landing or tricycle landing operations with the assembly including an arched axle wherein the arch provides a spring for the landing gear as well as provides clearance to enable foot launching of the aircraft. A nose wheel strut assembly is linked to and extends forward of the main wheel landing gear assembly and includes a resilient tension link member.

Abstract: A ducted propeller aircraft from which visibility is excellent and which is capable of operating quietly and efficiently has a propeller shroud which serves as a primary load path to pass bending and torsional stresses to which the mainplane is subject in use between the portions of the mainplane either side of the shroud, the shroud defining a duct which is unimpinged upon by any portion of the turbulent airflow emanating from the mainplane.

Abstract: A glider formed from a multi-sided tube open at its ends is disclosed. The body and lifting surfaces of the glider comprise a multi-sided tube including a top wall of planar configuration; a pair of opposed upper side walls of planar configuration integral with the top wall extending downward and outward a distance; a pair of opposed vertical side walls of planar configuration integral with the upper side walls; a pair of opposed lower side walls of planar configuration integral with the side walls extending downward and inward to a point inward of a vertical extension of the top wall and upper side wall intersections; a bottom wall extending between lower end walls and integral therewith enclosing the structure. The bottom wall includes a pair of upward extending planar sections meeting at a midpoint between lower end walls to form a ridge.

Abstract: An aircraft, either rigid-wing or a collapsible hang-glider, is provided which is a bi-plane of apparent annular-wing construction in plan view, but the wing tips of an anhedral foreplane are separated from and above the wing tips of a dihedral aftplane. In a hang-glider construction the wing tips of the foreplane may be supported above the wing tips of the aftplane by struts, the trailing edges of the foreplane wing tips being supported by the struts above the leading edges of the aftplane wings. Also in the hang-glider, the geometry of the fore and aftplanes can be varied by moving their points of connection to the keel therealong.

Abstract: There is disclosed an airplane having an inflatable type air cushion confining undercarriage thereunder wherein the airplane wing structures comprise three-dimensionally enlarged inner wing components merging aerodynamically with the airplane fuselage. The under surfaces of the inner wing components and the fuselage cooperate to provide a downwardly convex broad base structure which is oval-shaped in planform, and a toroidal configured inflatable trunk is attached to the perimeter of the base structure for circumscribing the air cushion cavity under the airplane. Thus, an enlarged width and length air cushion type undercarriage is provided to give the airplane improved stability characteristics when operating in air cushion, ground, or water supported mode. When the trunk system is deflated the elastic sheet material thereof retracts snugly against the slightly convex bottom surface of the base structure.

Abstract: A glider formed from a multi-sided tube open at its ends is disclosed. The body and lifting surfaces of the glider comprise a multi-sided tube including a top wall of planar configuration; a pair of opposed upper side walls of planar configuration integral with the top wall extending downward and outward a distance; a pair of opposed vertical side walls of planar configuration integral with the upper side walls; a pair of opposed lower side walls of planar configuration integral with the side walls extending downward and inward to a point inward of a vertical extension of the top wall and upper side wall intersections; a bottom wall extending between lower end walls and integral therewith enclosing the structure. The bottom wall includes a pair of upward extending planar sections meeting at a mid point between lower end walls to form a ridge.

Abstract: A foot-launched and foot-landed hang glider is powered by an internal combustion two-cycle engine drivingly connected through a reduction-drive unit to a large relatively slow-moving propeller. A reduction mount, so referred to because it couples the reduction-drive unit closely to the engine, allows the engine to rotate a large propeller relatively slowly, thus providing more thrust at near-stalling flight conditions. The hang glider, thus powered, also obviates the necessity of being launched from the edge of a precipice and permits flight which is not predicated on the fortuitous selection of favorable air currents.

Abstract: A self propelled kite having a frame including a nose piece, a stringer backwardly extending from the nose piece, and two spars attached to the nose piece equidistant and outwardly diverging in an upward inclination from the stringer. A substantially V-shaped fairing is connected between the spars and beneath the stringer. A propeller driven by a small internal combustion engine is the prime mover, being located above the fairing and mounted to the stringer. The kite may also have a rudder with rudder control mounted above the stringer and rearward to the propeller. The kite may also contain landing struts, air intake ports for unassisted take off, and cargo carrying apparatus.

Abstract: An airplane includes a wing having the configuration of an equilateral triangle and covered with a flexible membrane which is provided with free trailing edges. The wing is secured by pivot brackets to the top of supports placed at the center of gravity of the airplane body as to pivot right and left alternatively to obtain a self-balancing of flight like the action of a flying kite, such that it is safe and easy to control the airplane during takeoff, landing and sustained flight while increasing the lifting force.

Abstract: The vehicle is constructed from a flat disc recessed in a slot in a thin, pencil-like fuselage having aft and front propulsion engines and mounted for rotating about the center of the disc and about an axis extending transversely to the disc and to the direction of extension of the fuselage.

Abstract: An aircraft has two concentric wings of substantially equal diameters, the wings being connected to each other and stayed by an elongated central corridor which is located beneath a central engine duct disposed in the plane of the upper wing.

Abstract: Improvements in and relating to aircraft structures. The aircraft comprises a narrow delta planform fuselage with two small-span shoulder type wings in tandem and cascade. The shape of the fuselage and its relationship with the wings result in an aircraft capable of exploiting more efficiently, than conventional aircrafts, the potential energy carried by the aircraft and to comply more accurately with the first degree of universal flexibility as does the atmospheric environment than do conventional aircrafts.

Abstract: A short coupled airplane with variable wing lift comprising a fuselage that is free of the conventional tail assembly and has a wing structure comprising a plurality of short span wing segments spaced apart longitudinally of the fuselage with the forwardmost wing section being located forwardly of and above the level of the aircraft center of gravity, and the rearwardmost wing section being located rearwardly of, and below the level of the aircraft center of gravity. The wing sections at their projecting ends on either side of the airplane are connected by vertical airfoils each equipped with a rudder. The wing sections along their trailing edges are each equipped, on either side of the fuselage, with full span, vertically swingable members that combine the functions of flaps and elevators (and are thus called eleflaps). The eleflaps and rudders are respectively moved in unison to elevate, lower, and steer the aircraft.

Abstract: Disclosed is a staggered channel wing-type aircraft comprising a reverse staggard lower and upper wing which relates to aircraft of the type generally described as a short takeoff and landing vehicle (STOL) and more particularly to an improved version thereof having superior low speed handling characteristics in both takeoff and landing and an economical high speed cruise configuration. Also having an improved gliding characteristic and easy storage because the wingspan is reduced to a minimum but keeping still rather large wing area.

Abstract: A supersonic aircraft in which the engines are disposed under the middle portion of a delta wing and the contour of the nose portion except for the front end of the fuselage is defined essentially by two arcs of different circumference, the circumferences being disposed one above the other, with the lower circumference being described by a greater radius than the radius of the upper circumference, a cabin floor at the intersection of these circumferences, the nose portion at its front end including such end being inclined downwardly for thereby decreasing the height of the aircraft and increasing the number of seats in a row, and engines under the middle portion of the wing.

Abstract: An aircraft of the Canard type in which a first airfoil is attached to an aft fin portion of the fuselage at a higher elevation than a second airfoil which is attached to the fore portion of the fuselage. The second airfoil extends outwardly and rearwardly to meet the first airfoil whereby a triangular configuration is formed in plan view and in front elevation view. The airfoils may be flexible; simple cable controls may be provided to control the aircraft so that even inexperienced pilots can easily operate the aircraft. The triangular configuration ensures a lightweight and inexpensive yet rugged and strong aircraft. The aircraft may also include a split rudder and may be hinged for folding to facilitate storage and transportation.

Abstract: An aircraft having a composite configuration comprising a conventional fuselage forebody portion which symmetrically and variformly blends into a relatively wide, substantially flat beaver-tail-like afterbody, with the afterbody having an integral pitch trimming camber and a composite pitch control device and air brake, hinged transversely thereacross and forming at least a part of its trailing edge. The beaver-tail afterbody is geometrically blended into and joined with the after portion of the conventional forebody through the medium of an intervening medial body defined by a geometric transition piece. The composite aircraft is further capable of fixedly accommodating any type of conventional wing configuration without the necessity for any adaptative, structural change or modification and also carries conventional propulsion units and control surface components.

Abstract: An aircraft designed to afford passengers an unrestricted view for "sightseeing" or other purposes. Passenger accommodation extends to the foremost part of a fuselage and is enclosed by a cabin transparency extending to cover substantially the entire field of view of passengers from a fixed position. The pilot of the aircraft is accommodated above and behind the passengers, the aircraft's powerplant also being disposed behind the passenger accommodation.

Abstract: An aircraft having a major longitudinal strength structure generally centralized in the vertical mid-plane. Shallow V-shaped wing panels are secured to the longitudinal strength structure, one at the top and one at the bottom to define a rhombic cellular configuration. Control linkages are provided, positioned and connected to act as stays between paired of upper and lower wing panels.