Abstract: An impact detection system provides a means of sensing, monitoring and recording impact events on an impact surface using at least one sensor that is incorporated into the impact surface. The sensor(s) can be integral with, attached to or located behind various types of impact surface including various types of garments that can be worn by an individual or on composite materials such as an aircraft fuselage for example. The impact detection system includes a portable impact detection device electrically connected to the sensor(s) and is used to detect ballistic or non-ballistic type impacts on the impact surface. The portable impact detection device processes the impact data detected by the sensor(s) and stores the data for analysis at a later time or outputs the data to a third party system for review and/or analysis.

Abstract: Purpose – The paper aims to develop a robot that climbs on non‐ferrous surfaces, e.g. aircraft wings and fuselages, carrying a heavy payload up to 18 kg including scanning arm and various equipments, for non‐destructive testing (NDT).Design/methodology/approach – This robot in the study uses vacuum suction cups for adhesion, and two pairs of pneumatic cylinders to drive itself, moving in two directions in stepping gait. A rotation mechanism in the centre is used to correct the off‐course deviations by ± 5 degrees. Multiple universal joints are used to make every single suction cup, every robot foot and the whole structure flexible to negotiate with varying surface curvatures presented in different parts of aircraft. This flexible structure is also rigid once the robot is stuck on the surface to enable the NDT inspection being carried out reliably.Findings – The paper finds that the walking speed is limited by the cylinder stroke, time for generating vacuum and changing legs. Although most NDT inspection i...

Abstract: The work demonstrates the benefits of using digital methods for the development and optimization of large assembly manufacturing networks. Although an aircraft assembly has been used for this work, the methods and advantages of digital manufacturing techniques, which are demonstrated here, are equally applicable to any large assembly process, such as those used in the automotive, railway, and shipbuilding industries. The introduction of manufacturability into the design arena using advanced computer aided methods means that manufacturing engineers can operate more directly in assembly planning and concurrent engineering design. Network analyses carried out on the final assembly operations for a regional jet fuselage section using a methodical, step by step approach, shows that the process efficiency for workers carrying out fitting operations can be more than doubled when compared to existing shop floor performance figures. The more efficient use of operator time results in a simulated 19% improvement in financial efficiency, as the actual working hours required for assembly are reduced to below budgeted levels. The simulation predicts that these results can be achieved with one final assembly station. With two stations currently in use for the fuselage section, this means that a significant financial saving is possible in tooling expenditure.

Abstract: Purpose – This paper aims to describe the development and testing of a system for the automated assembly of aircraft fuselage panels.Design/methodology/approach – The system described in this paper uses a low‐cost industrial robot and laser stripe sensor to assemble stringers on to a fuselage panel prior to riveting. The method uses a combination of measurement and best fit placement algorithms to optimally locate parts relative to existing features.Findings – The paper demonstrates that with a combination of metrology and mathematical processing standard industrial robots can be used to assemble aero‐structure subassemblies. The paper also demonstrates that the system can work within the tolerances required within the aerospace industry.Originality/value – The paper introduces techniques for compensating for the inherent distortion that occurs in airframe components during manufacture. This is an enabling technology that will significantly increase the number of possible applications for industrial robot...

Abstract: The present invention is an unmanned air vehicle designed for reconnaissance, surveillance, data acquisition, and general research. The air vehicle is a monoplane that consists of several pieces that can easily be assembled using a minimal amount of tools. The air vehicle consists of a forward and aft fuselage section, two identical horizontal stabilizers, and four identical wing sections. The aircraft can fly with all four wing sections, or with just two wing sections (the short wing configuration). Each of the four wing sections of the air vehicle can be interchanged with any of the other wing sections for the purpose of minimizing assembly time and spare parts.

Abstract: Automated Fiber Placement (AFP) equipment has been developed capable of laying fiber in excess of 2000 inches per minute on full-size, complex parts. Two such high-speed machines will be installed for production of a nose section for a large twin-aisle commercial aircraft fuselage at Spirit AeroSystems in Wichita, Kansas along with a rotator for the fuselage mandrel. The problem of cutting and adding on the fly at these speeds requires thorough re-evaluation of all aspects of the technology, including the mechanical, controls, servos systems, and programming systems. Factors to be considered for high speed cut and add on the fly are discussed.

Abstract: For the investigation of elastic bending of the landing gear shock absorber of an aircraft under dynamic loads upon landing and subsequent braking during roll out, an MBS-based model of the landing gear is introduced. To separate effects of the elastic bending of the main landing gear the fuselage is considered rigid. After performing a flare with subsequent landing, the aircraft is stopped by means of an antiskid system. For comparison, an analytical-numerical study of a finite-element model of the main landing gear shock strut components is done for simple static and dynamic loads considering Bernoulli's hypothesis. Simulation of a rough-landing manoeuvre reveals that vibrations due to the elastic properties of the shock absorber not only increase loads on the components but significantly affect the braking process as well.

Abstract: This paper describes the development and analysis of gain-scheduled, multi-variable Hinfin control law for the conversion of a linear parameter varying (LPV) model of a high-speed autonomous rotorcraft vehicle (HARVee), an experimental tilt-wing aircraft. Tilt-wing aircraft combine the high-speed cruise capabilities of a conventional airplane with the vertical takeoff and station keeping abilities of a helicopter by rotating their wings at the fuselage. Changing between cruise and hover flight modes in mid-air is referred to as the conversion process, or simply conversion. A nonlinear aerodynamic model was previously developed that captures the unique dynamics of the tilt-wing aircraft. An Hinfin design methodology was used to develop linear controllers along various operating points of a conversion trajectory. The development of these control systems was governed not only by performance specifications at each particular operating point, but also by the unique requirements of a gain-scheduled conversion control system. The performance of the resulting conversion closed-loop systems is analyzed in the frequency and time domains. Performance robustness with respect to variation in the location of the center of gravity (eg) has been studied.

Abstract: This paper presents a new method of wake-vortex characterization by using the 2-μm coherent Doppler lidar in airborne configuration. After modification of the scanning and data acquisition tools, the lidar system has been integrated in the DLR research aircraft Falcon 20. For wake-vortex generation a second DLR aircraft, the Advanced Technologies Testing Aircraft System equipped with a smoke generator on the portside wing, was used. Different scanning modes and flight strategies have been investigated and tested during three tryout flights. Results of vortex trajectories and circulation strengths, measured in the upper part of and above the atmospheric boundary layer, are presented. Based on the results of the tryout flights, the potential of this method for characterization of wake vortices from large transport aircraft equipped with smoke generators is estimated.

Abstract: A line system for an aircraft, in particular an airplane, having multiple assemblies, in particular multiple fuselage sections of a fuselage cell and multiple wing shells, the line system including multiple lines for transmitting power and/or information, wherein the lines are integrated on and/or in a support layer, the support layer being situated on and/or in the shell-shaped assemblies.

Abstract: Embodiments of the present invention relate a wing arrangement for an aerial vehicle configured to adjust the vehicles aspect ratio in response to flight mission parameters. The wing arrangement may include a pair of wing assemblies capable of deploying to a first winged position defining a first aspect ratio. Each wing assembly may have a forward inboard wing pivotally connected to the fuselage and an aft inboard wing pivotally connected to the carriage. The forward inboard wing and aft inboard wing of each assembly may be connected, forming a bi-plane configuration. Additionally, the each assembly may include a set of outboard wings configured to telescope from the inboard wings to an extended winged position defining a second aspect ratio greater than the first aspect ratio.

Abstract: An embodiment of an aircraft wing includes a main wing section and a variable incidence wing tip. The main wing section is adapted to connect to an aircraft fuselage at a first angle of incidence. The variable incidence wing tip is connected to the main wing section so that the variable incidence wing tip is rotatable to angles of incidence that are different from the first angle of incidence. An embodiment of a method for operating an aircraft includes generating a control signal based on an indication of a desired angle of incidence of a variable incidence wing tip, conveying the control signal to a wing tip rotation mechanism, and rotating the variable incidence wing tip in accordance with the control signal, so that the angle of incidence of the variable incidence wing tip is different from an angle of incidence of the main wing section.

Abstract: A floor to fuselage attachment structure incorporates a truss having an upper angled attachment (10) engaging the floor proximate an edge and extending at an angle upward from the floor (14) edge to attach to the fuselage (16). Additionally, the truss includes a lower angled attachment engaging the floor proximate the edge and extending at an angle downward to attach to the fuselage. The upper and lower angled attachments support the floor with the edge spaced from the fuselage and further have a plurality of apertures (18) for providing airflow between a first volume above the floor and a second volume below the floor.

Abstract: An architectural archway for an aircraft. The archways can be positioned individually, or in pairs or other sets along the length of an aircraft fuselage. The archways are used to run or connect various transport elements, such as electrical wiring, water lines, and environmental control system conduits, between the upper crown, lower bay and passenger cabin of the aircraft. The invention simplifies installation complexity and eliminates the installation and variability associated with running transport elements between the various sections of the aircraft.

Abstract: A structuring construction (10) for an aircraft fuselage comprises an outer skin (12) as well as a plurality of formers (14) extending at a spacing side by side crosswise to the longitudinal direction of the fuselage. According to the invention, at least a partial number of the formers comprise a main former portion (18) which is channel-like in cross section and the channel edges of which are adjacent to the outer skin (12). In a preferred development the channel space of the main former portion (18) serves to accommodate at least one supply air line which may be formed, for example, by a separate pipe line (28).

Abstract: This paper describes the development and analysis of gain-scheduled, multi-variable Hinfin control law for the conversion of a linear parameter varying (LPV) model of a high-speed autonomous rotorcraft vehicle (HARVee), an experimental tilt-wing aircraft. Tilt-wing aircraft combine the high-speed cruise capabilities of a conventional airplane with the vertical takeoff and station keeping abilities of a helicopter by rotating their wings at the fuselage. Changing between cruise and hover flight modes in mid-air is referred to as the conversion process, or simply conversion. A nonlinear aerodynamic model was previously developed that captures the unique dynamics of the tilt-wing aircraft. An Hinfin design methodology was used to develop linear controllers along various operating points of a conversion trajectory. The development of these control systems was governed not only by performance specifications at each particular operating point, but also by the unique requirements of a gain-scheduled conversion control system. The performance of the resulting conversion closed-loop systems is analyzed in the frequency and time domains. Performance robustness with respect to variation in the location of the center of gravity (eg) has been studied.

Abstract: The present invention pertains to a specially designed insulating mat (1) for the sound insulation of an aircraft fuselage structure that is composed of frames (4) and stringers (3) extending transverse to the frames (4), to a specially designed fastening means (8) for fastening an insulating mat (1) on an aircraft fuselage structure such that acoustic bridges are prevented, and to an insulating kit (1, 8) that comprises at least one inventive insulating mat (1) as well as at least one inventive fastening means (8). The insulating mat (1) features a multitude of fastening clips (17) that are fixed on a first surface of the insulating mat (1) and laterally protrude over the border of the insulating mat (1).

Abstract: Over the last 50 years, commercial aviation has been mainly based what is currently called the conventional layout, characterized by a slender fuselage mated to a high aspect ratio wing, with aft-tail planes and pod-mounted engines under the wing. However, it seems that this primary configuration is approaching an asymptote in its productivity and performance characteristics. One of the most promising configurations for the future is the flying wing in its distinct arrangements: blended-wing-body, C-wing, tail-less aircraft, etc. These layouts might provide significant fuel savings and, hence, a decrease in pollution. This configuration would also reduce noise in take-off and landing. All this explains the great deal of activity carried out by the aircraft industry and by numerous investigators to perform feasibility and conceptual design studies of this aircraft layout to gain better knowledge of its main characteristics: productivity, airport compatibility, passenger acceptance, internal architecture, emergency evacuation, etc. The present paper discusses the main features of flying wings, their advantages over conventional competitors, and some key operational issues, such as evacuation and vortex wake intensity.

Abstract: .Method and apparatus for fabricating a fuselage section by the automatic deposition of fibre tapes impregnated with resin on an outer surface of a mandrel composed of radially retrectable sectors.

Abstract: An aircraft fuselage structure with frames (11) running transversely with respect to the longitudinal direction of the fuselage, and main deck cross members (14) is disclosed. The aircraft fuselage structure contains premanufactured integral units (10) which each comprise at least the lower region of the fuselage frame (11) and the main deck cross member (14), the fuselage frame (11) and a region (14a) of the main deck cross member (14) that spans at least an essential part of the width of the main deck and merges on both sides into the fuselage frame (11) being premanufactured in the form of an integral component.

Abstract: According to the invention, said aircraft comprises at least one engine which has ducted propellers and is mounted on the back of the rear portion of the fuselage, the cowling being able to be oriented about the axis of said engine.

Abstract: The present invention provides a floor structure for a fuselage comprising a plurality of cross beams to which respectively at least one first strut and at least one second strut are associated for connecting the respective cross beam to the fuselage. The at least one first strut is aligned in a corresponding first direction vector and the at least second strut is aligned corresponding to a second direction vector. The projections of the first direction vector and of the second direction vector onto the longitudinal direction of the fuselage are different for absorbing a force acting in the longitudinal direction of the fuselage on the floor structure, through the first and second struts.

Abstract: Methods and systems for attaching aircraft wings to fuselages are disclosed herein. An aircraft configured in accordance with an embodiment of the invention includes a fuselage and a wing. The wing includes a right wing portion extending outwardly from a right side portion of the fuselage and a left wing portion extending outwardly from a left side portion of the fuselage. In this embodiment, the right wing portion is fixedly attached to the left wing portion by a wing center section extending through at least a portion of the fuselage. The aircraft further includes a first pivotable link structurally attaching the wing center section to the right side portion of the fuselage, and a second pivotable link structurally attaching the wing center section to the left side portion of the fuselage.

Abstract: An aerospace vessel including a fuselage, a means for causing the fuselage to fly coupled to the fuselage, and an environmental control system within the fuselage. The environmental control system includes a duct made of closed cell thermoplastic foam, such as polyvinylidene fluoride foam.

Abstract: An ornithopter having segmented, flapping wings and capable of bird-like flight. A main drive system provides flapping motion to the wings. Servo systems are provided for independently moving each wing forward and backward along a major axis of the aircraft fuselage, thereby providing a balance subsystem. A single servomechanism controls upward and downward direction of the wings thereby providing a center angle control subsystem. Two additional servo systems are provided to control a tail assembly that provides steering and other ancillary control functions. Each subsystem is controlled by a dedicated, onboard microcontroller. One embodiment of the aircraft is remotely controlled by a wireless data communication link. The aircraft may be constructed to resemble a natural bird, in both static appearance and flight characteristics. The aircraft may be scaled from model size to a full-size, passenger carrying aircraft.

Abstract: Noise is a frequently encountered problem in modern society. One of the environments where the presence of noise causes a deterioration in people’s comfort is in aircraft cabins. For modern aircraft flying at cruise conditions, the main sound source is the turbulent boundary layer around the fuselage. Especially in the mid and high frequency range (500-2000 Hz), this source significantly contributes to the sound levels in the aircraft cabin. Passive noise reduction methods can provide a suitable solution to many noise problems in this frequency range. In the present study, a new passive noise reduction method is presented, known as tube resonators. Tube resonators are well-known for their application for sound absorption. However, in the present work, this type of resonator is applied for the reduction of sound radiation and sound transmission. The aim of this work is to investigate the applicability of this new method and to develop and validate efficient models for the prediction of sound radiation by and sound transmission through panels with tube resonators. For a proper understanding of the influences of the different phenomena, different models and experiments are presented in order of increasing complexity.

Abstract: A micro aerial vehicle can be converted during flight between a fixed wing flight mode and a rotary wing flight mode. The canard design micro aerial vehicle includes a fuselage, two tiltable propellers and airfoils arranged at a forward portion of fuselage, a pair of coaxial drive shafts positioned aft of the tiltable propeller and airfoil arranged for contra-rotation, a stop rotor mechanism, and a pair of wing panels, each of the wing panels attached to one of the coaxial drive shafts. The wing panels act as contra-rotating rotor blades in the rotary wing flight mode, and act as fixed wing panels in the fixed wing mode.