Abstract: An anchor fitting assembly for attaching a full width partition, having a door opening, to the fuselage structure of an airplane for dividing a passenger area into two or more compartments. During installation of the partition, provisions are made to allow the lower attachments, of the partition to the seat tracks in the floor of the compartment, to have a certain amount of freedom of movement in both the inboard/outboard and up/down directions. This floating action in the attachment is required for absorbing fuselage deflections due to flight loads imposed on the floor beams and in some cases due to torsional deflections of the wing torque box to which the seat track is fixedly attached, in order to maintain a square door opening.

Abstract: A unitary frame having a central, annular-shaped fuselage section and a pair of outwardly opposed wing spars is fabricated from fiber-reinforced, resin matrix composites, and constitutes one of a number of similar such frames that are assembled together to form a framework of an aircraft body. Each wing spar has the general configuration of an I-beam incorporating a sine wave shear web reinforced along the upper and lower edges by flanges and lengthwise extending, tension/compression chords formed by bundles of lengthwise oriented fibers. The fuselage section has a circumferentially oriented sine wave shear web that is otherwise similar to the web of the wing spars, and has inner and outer circumferentially extending flanges that are similar to the upper and lower flanges along the wing spars. The root of each wing spar is joined to the respective side of the fuselage section by continuing the tension/compression chords into the fuselage section and by inserting a transition structure, in the form of a lightweight honeycomb core sandwiched between a pair of facing panels, at the juncture between the root of the wing spar and the fuselage section. The transition structure efficiently reacts loads developed along the tension/compression chords due to bending of the wing spar, and geometrically blends vertically oriented corrugations in the wing spar web with radially oriented corrugations in the web of the fuselage section.

Abstract: Thermal insulating apparatus for an aircraft fuselage of the type utilizing a sandwich panel construction. A foam insulation panel is provided which includes a plurality of standoffs for contacting the inwardly-facing skin of the sandwich panel. The standoffs may be arranged in a grid pattern, molded integrally with the rest of the panel, and bonded to the skin of the sandwich panel. The insulation panel may be used with or without a trim panel between it and the fuselage compartment, and in either case a sheet of metal foil may be attached to the inside face of the insulation panel. The foam may be of the self-skinning type so as to resist penetration of moisture into the foam panel and help direct condensate away from the fuselage compartment.

Abstract: This paper describes experimental studies of interior noise in a twin-engine, propeller-driven, light aircraft. An analytical model for this type of aircraft is also discussed. Results indicate that interior noise levels in this aircraft due to propeller noise can be reduced by reducing engine rpm at constant airspeed (about 3 dB), and by synchrophasing the twin engines/propellers (perhaps up to 12 dB). Ground tests show that the exterior noise pressure imposed on the fuselage consists of a complex combination of narrow-band harmonics due to propeller and engine exhaust sources. This noise is reduced by about 20-40 dB (depending on the frequency) by transmission through the sidewall to the cabin interior. The analytical model described uses modal methods and incorporates the flat-side geometrical and skin-stringer structural features of this light aircraft.

Abstract: By blending together the roll and elevation plane high-frequency solutions, a very efficient technique has been developed for the volumetric pattern analysis of antennas mounted on the fuselage of a generalized aircraft. The fuselage is simulated by an infinitely long, perfectly conducting, elliptic cylinder in cross section and a composite elliptic cylinder in profile. The wings, nose section, stabilizers, and landing-gear doors may be modeled by finite flat or bent plates. Good agreement with accurate scale model measurements has been obtained for a variety of aixborne antenna problems.

Abstract: An apparatus for handling and storing baggage or cargo within an aircraft fuselage including a fuselage door and a plurality of storage platforms with each platform consisting of a flat rectangular base and two upwardly extending side walls closely juxataposed to the shape of the fuselage. The platforms are capable of stacking one atop another when not in use adjacent the fuselage door. Each platform can move longitudinally relative to the aircraft fuselage away from and back towards the fuselage door in a telescoping sequence such that the uppermost platform will move away from said stack first and such that the lowermost platform will always return to said stack first.

Abstract: A powered aircraft has a jettisonable fuel tank releasably secured in the bottom of its fuselage. A valve is arranged to shut off fuel flow from the tank upon releasing of the tank from the fuselage, whereupon a parachute connected to the tank is released to slow the descent of the tank. Additionally, a reserve fuel tank in the fuselage is normally connected to the jettisonable fuel tank, and the valve is so arranged that fuel flow communication is normally maintained between the jettisonable fuel tank and the aircraft engine while fuel is prevented from flowing from the reserve tank to the engine. However, when the jettisonable fuel tank is released from the fuselage, the valve shuts off the flow of fuel from the jettisonable fuel tank and establishes open communication between the reserve tank and the engine to permit continued operation of the aircraft under power of the engine.

Abstract: Modifications to a jet aircraft of the type having aft fuselage-mounted engine nacelles overlapping trailing edge portions of the aircraft's wings, wherein a channel area defined by the fuselage, wing, pylon and attached nacelle is shaped to prevent air flowing therethrough from forming a shock wave during flight operation in the transonic regime, resulting in significant drag reduction as compared to an unmodified jet aircraft of a similar type. Further modifications to the jet aircraft's wings provide additional lift while significantly reducing drag as compared to a similar, unmodified aircraft. The present invention is particularly adaptable for use with Gates Learjet type aircraft, especially Models 23, 24, 25 and other models having similar nacelle, pylon and inboard wing arrangements.

Abstract: Aircraft engine exhaust is mixed with air and fuel and recombusted. Air is drawn into the secondary combustion chamber from suction surfaces on wings. Exhaust of the secondary combustion chamber is blown over wing and fuselage surfaces.

Abstract: A high efficiency vertical tail unit is combined with a variable wing geory for large angles of attack, primarily for all-wing aircraft such as delta-type craft. The vertical tail unit is hinged for adjustment about an axis substantially parallel to the longitudinal axis of the fuselage. The outer wing portions are connected, at an angle, with a vertical tail unit which is directed vertically downward in its normal position. The assembly comprising an outer wing portion and a vertical tail unit is rotatable about the parallel axis whereby three different wing types may be realized in the same craft.

Abstract: Abstract In the context of the transmission of airborne noise into an aircraft fuselage, a mathematical model is presented for the effects of internal cavity resonances on sound transmission into a thin cylindrical shell. The “noise reduction” of the cylinder is defined and computed, with and without including the effects of internal cavity resonances. As would be expected, the noise reduction in the absence of cavity resonances follows the same qualitative pattern as does transmission loss. Numerical results show that cavity resonances lead to wide fluctuations and a general decrease of noise reduction, especially at cavity resonances. Modest internal absorption is shown to greatly reduce the effect of cavity resonances. The effects of external airflow, internal cabin pressurization, and different acoustical properties inside and outside the cylinder are also included and briefly examined.

Abstract: A numerical method has been developed to compute transonic flows about realistic wing-fuselage configurations. The finite difference scheme employs an improved small disturbance flow equation. A unique grid embedding technique, which was heretofore applied to airfoils and wings, has been extended to include the treatment of both body and wing-body shapes. The resulting high-density mesh is shown to be a valuable asset in resolving details of the three-dimensional flow. A mathematical modeling system is used to process arbitrary fuselage geometries for body boundary conditions. Correlations with experimental data for simple isolated bodies, an isolated fuselage, and wing-fuselage combinations are included.

Abstract: Static force data obtained at the NASA Ames Research Center 12 foot Pressure Tunnel are presented in plotted form for a 1/7 scale, single-engine, low-wing general aviation airplane model. The configurations tested included the basic airplane, various airfoil shapes, tail designs, fuselage strakes and fuselage modifications as well as airplane components. The test conditions included an angle-of-attack and sideslip range of -8 to 90 and -10 to 30 degrees, respectively, at a Mach number of 0.2 for Reynolds numbers of 288,000 and 3,450,000. The data are presented without analysis.

Abstract: In the context of the transmission of airborne noise into an aircraft fuselage, a mathematical model is presented for the transmission of airborne noise into a stiffened cylindrical shell. The stiffeners are longitudinal stringers and are modeled as discrete structural elements. The numerical cases examined were typical of a narrow-bodied jet transport fuselage. The stringers appeared to raise the cylinder transmission loss in the mass-controlled region, although they produced dips at the stringer resonances. The ring-frequency dip in transmission loss, which is characteristic of monocoque shells, was found to still be present. There appeared to be a small increase in transmission loss as the number of stringers was increased. The effect of high damping was also investigated.

Abstract: Two different studies are presented involving a transport category aircraft with an oblique or asymmetricall y swept wing. The first study concerns itself with the effect on flutter of changes in certain of the aircraft structural and inertial parameters. The second portion examines the subcritical damping characteristics of a flexible oblique-wing aircraft. For this purpose, a recent version of the NASTRAN computer code is used. A comparison is made between the flutter speeds found using the traditional k analysis and the results found from computation of subcritical response using the/?-/t or "British" flutter method.

Abstract: Aerodynamic characteristics obtained in a spinning flow environment utilizing a rotary balance located spin tunnel are presented in plotted form for a 1/5 scale single-engine low-wing general aviation airplane model. The configurations tested include the basic airplane, various airfoil shapes, tail designs, fuselage strakes and modifications as well as airplane components. Data are presented for pitch and roll angle ranges of 30 to 90 degrees and 10 to -10 degrees, respectively, and clockwise and counter-clockwise rotations covering an Omega b/2V range from 0 to .9. The data are presented without analysis.

Abstract: A recoverable remotely piloted vehicle (RPV) having: a deflectable canard/elevator placed very close to the nose tip; a constant (cross) section fuselage; wings mounted low and well aft on the fuselage; elevons; a centrally positioned weapons/payload bay, with doors, located internal of the upper portion of the fuselage; and, inflatable landing skids. The weapon/payload is dropped from the RVP, while the RVP is in flight in an inverted position.

Abstract: A toy assembly capable of locomotion on a solid surface and having reconfigurable component parts is disclosed. A fuselage of an airplane or rocket includes a front section configured to simulate a mobile cockpit which can be launched from the remainder of the fuselage by a spring loaded latching mechanism. Two interchangeable tail sections are provided for coupling to the fuselage. A first tail section includes a power source and a control switch to actuate an electric motor located in a center section of the fuselage. An electrical cable connects a second tail section to the first tail section whereby the toy is remotely controllable from the control switch. A multi-piece wing section is attached to either side of the fuselage. Each wing section includes a side member which, when detached from the wing provides an operable toy dart gun. The component parts of the wing sections are reconfigurable to provide other toy assemblies.

Abstract: Tilting the stabilizer at an extreme angle to the fuselage, with leading edge down, and controlling and varying engine thrust comprise a method for all-axis control of a generally conventional aircraft in ultra deep stall. The method is effective in recovery from unstable and unusual flight attributes and in landing emergencies; the aircraft may land in the ultra deep stall configuration or conventional flight may be resumed. So-called flying wing aircraft, where pitch control surfaces are incorporated with the trailing edge of the primary lift surface, are also controllable in ultra deep stall by the method of this invention.

Abstract: Acoustic data are analyzed from a series of ground tests performed on an Aero Commander propeller-driven aircraft with an array of microphones flush-mounted on one side of the fuselage. The analyses were concerned with the propeller blade passage noise during static operation at several different engine speeds and included calculations of the magnitude and phase of the blade passage tones, the amplitude stability of the tones, and the spatial phase and coherence of the tones. The results indicate that the pressure field impinging on the fuselage represents primarily aerodynamic (near field) effects in the plane of the propeller at all frequencies. Forward and aft of the propeller plane aerodynamic effects still dominate the pressure field at frequencies below 200 Hz; but at higher frequencies, the pressure field is due to acoustic propagation from an equivalent center located about 0.15 to 0.30 blade diameters inboard from the propeller hub.

Abstract: A wing pivot assembly for variable sweep wing aircraft for movably securing a wing of the aircraft to the fuselage. The wing pivot assembly has a pivot pin supported by a pair of inboard lugs secured to the fuselage of the aircraft. The wing is, in turn, movably secured to the pivot pin by bearings interposed between the pivot pin and a pair of outboard lugs. In addition an outboard shear fitting located between the wing and the pivot pin movably supports the wing and transfers shear loads to the pivot pin. An inboard shear fitting and anti-rotation device secures and transfers shear loads between the pivot pin and the fuselage. As a result of the above arrangement a multi-load path structure provides for a fail-safe pivot assembly.

Abstract: A wind tunnel test where load distributions were obtained at transonic speeds on both the canard and wing surfaces of a closely coupled wing canard configuration is reported. Detailed component and configuration arrangement studies to provide insight into the various aerodynamic interference effects for the leading edge vortex flow conditions encountered are included. Data indicate that increasing the Mach number from 0.70 to 0.95 caused the wing leading edge vortex to burst over the wing when the wing was in the presence of the high canard.

Abstract: This paper presents the design logic and optimization techniques that resulted in the Shuttle Orbiter aerodynamic configuration. Design requirements which are key configuration drivers are landing speed, payload center of gravity envelope, crossrange requirements, lateral-directional stability and control requirements, and flying qualities. Trade studies based on these requirements, subject to constraints on vehicle weight, establish wing, fuselage, and tail geometry, control surface size and geometry, and local contours and configuration details. Additional studies refine the configuration design in terms of wing aspect ratio, trailing edge sweep, twist, camber, forebody shaping, and vertical tail geometry.

Abstract: An aircraft is provided with a circular wing member which is rotatably mounted to a fuselage member. The circular wing member provides lift for horizontal flight and also provides gyroscopic stabilization of aircraft attitude. The circular wing member is substantially free of aerodynamically active flight control or propulsion members and, in a preferred embodiment, has a concentration of mass at its outer rim. The fuselage is provided with propulsion means for effecting and controlling vertical and horizontal flight. The propulsion means provides horizontal or vertical thrust along vectors which pass through the aircraft center of mass.

Abstract: A retractable fuselage mounted undercarriage comprising a leg casing mounted to pivot on a main universal joint about an axis which extends longitudinally of the aircraft, the leg casing mounting a wheel assembly which can pivot on the leg casing, a lateral deflection shock absorber and a manoeuvreing and wind bracing jack each connected to the leg casing by a joint and each connected to the fuselage by a joint, the main universal joint being mounted to pivot on the fuselage about an inclined retraction axis which does not pass through the point where the shock absorber is connected to the fuselage, so that, during lowering and retraction of the undercarriage effected by extending or retracting the manoeuvreing and wind bracing jack, the shock absorber acts as a directer bar and orientates the axis of the leg casing, which leg casing is rotated as the main universal joint pivots on the fuselage about the inclined retraction axis.