Spirit AeroSystems (United States)

Spirit AeroSystems is a Tier 1 Supplier to almost all major Original Equipment Manufacturers (OEMs), various startup companies, and other suppliers. As a Tier 1, Spirit needs to be able to consume and work with any and all engineering data (e.g., Computer Aided Design (CAD), Model Based Systems Engineering (MBSE) information, schedule, etc.) regardless of the toolset initially used to develop the data. Significant challenges Spirit faces are the method and content of data exchange, and the interface definition enabling the exchange of information with an OEM. Digital Transformation initiatives throughout industry seek to compress the production lifecycle by staging information as early in the lifecycle as possible. For the OEM, the interface and early data exchange are easily addressed by simply providing the suppliers with access to the OEM’s engineering design system. However, this limits the ability of the supplier to fully experience the “shift left” concept for the production lifecycle. The ability to extend the Digital Thread/Twin into the Tier 1 supply base from the OEM, allowing effective and efficient development from the program initiation is the focus of this effort. The capability starts with MBSE through detail design, manufacturing, delivery, and how to support OEM Maintenance, Repair, and Overhaul (MRO) through the life of the product.

The increased demand for cost-efficient manufacturing and metrology inspection solutions for complex-shaped components in High-Value Manufacturing (HVM) sectors requires increased production throughput and precision. This drives the integration of automated robotic solutions. However, the current manipulators utilizing traditional programming approaches demand specialized robotic programming knowledge and make it challenging to generate complex paths and adapt easily to unique specifications per component, resulting in an inflexible and cumbersome teaching process. Therefore, this body of work proposes a novel software system to realize kinesthetic guidance for path planning in real-time intervals at 250 Hz, utilizing an external off-the-shelf force–torque (FT) sensor. The proposed work is demonstrated on a 500 mm2 near-net-shaped Wire–Arc Additive Manufacturing (WAAM) complex component with embedded defects by teaching the inspection path for defect detection with a standard industrial robotic manipulator in a collaborative fashion and adaptively generating the kinematics resulting in the uniform coupling of ultrasound inspection. The utilized method proves superior in performance and speed, accelerating the programming time using online and offline approaches by an estimate of 88% to 98%. The proposed work is a unique development, retrofitting current industrial manipulators into collaborative entities, securing human job resources, and achieving flexible production.

Since the introduction of refill friction stir spot welding (RFSSW) in the early 2000s, numerous evaluations of properties, performance, and prototypes have been documented. RFSSW is a solid-state spot joining technique that is being evaluated as a rivet replacement technology for aerospace structures and fuselage fabrication. A production evaluation of overlapping wing skin assembly was completed and experimentation on stringer-stiffened curvilinear panels is underway. Weld properties were evaluated for spots produced on bare sheet as well as for sections with sealant applied. Furthermore, evaluations of the performance of repaired spots using the RFSSW process are demonstrated. Characterization of the weld interface, heat-affected zone, and complete through-thickness consolidation via computed tomography is presented.KeywordsSpot weldingAluminumAerospace

SYSTEMS in 1980 and held a wide range of technical and operational roles across different aerospace sectors including commercial aircraft, business jets and space systems. For eleven years he participated in a number of senior management roles within the company's Airbus operations. In late 1999 he left Airbus to

Kepemimpinan merupakan salah satu aspek dalam kehidupan bergereja yang penting untuk dibicarakan. Sebab, kepemimpinan berperan dalam gerak kesaksian gereja. Salah satu gagasan penting tentang kepemimpinan gereja adalah kepemimpinan hamba. Kepemimpinan hamba menegaskan prinsip bahwa seorang pemimpin adalah hamba dari Yesus Kristus. Seorang pemimpin bukan tuan yang dilayani, tetapi hamba yang melayani. Artinya, dalam perspektif Kristen, seorang pemimpin adalah seorang pelayan. Karakteristik hamba itu tampak dalam kesediaan untuk mendahulukan orang yang dilayani. Meskipun demikian, tidaklah berarti seorang pemimpin mengabaikan dirinya. Seorang pemimpin yang memiliki karakter hamba akan melayani orang lain, sama seperti yang dia inginkan terjadi bagi dirinya. Konsep kepemimpinan hamba ditulis dalam rangka memperingati 70 tahun Pdt. Emiritus Dr. I.W.J. Hendriks. Karena itu, tulisan ini ditemukan dalam buku Spirtualitas Pro-Hidup, halaman 91 -111.

This paper presents a concept for a heterogeneous unmanned team designed for autonomous persistent inspection of offshore wind turbines. This team consists of an unmanned surface vessel (USV) and an unmanned aerial system (UAS) operating cooperatively. We describe a concept of operations (CONOPS) in which the USV acts as a ground control station (gCS) for the UAS. The USV shuttles the UAS between turbines, recharges the UAS batteries, and provides a long-range data link to a remote operator. Near each turbine, the UAS is deployed from the USV, performs an inspection, and then returns to the USV so that it can transit to a different offshore wind turbine and initialize another inspection. This paper discusses the key enabling technologies required to field such a system, with focus on the problem of performing autonomous high-precision launch and landing of a UAS from a USV.

This paper describes the established process of cost model development and highlights opportunities for further improvement. Combinations of Systems Engineering tools were used within the modelling strategy in order to overcome the limitations of individual techniques. A functional modelling language was used to analyse, develop and integrate the cost model functions. The relationships between the manufacturing systems were modelled using Unified Modelling Language (UML). Furthermore, the benefits obtained by introducing changes to the cost model development process were evaluated by drawing comparisons between the two model development approaches.

In 2013-2014, a scaled cascade was designed to be tested in a 6x6 inch flow duct. This required a characterization of the 6x6 inch flow duct, calibration of the force balance used to measure forces on the scaled cascade, and attention to detail in the experimental setup to provide confidence that accurate, correct experimental test data was being acquired. A computational fluid dynamics (CFD) model of the cascade and flow duct was created to compare the experimental test results with theoretical predictions. A successful correlation would provide confidence in the CFD prediction, which is used to analyze the designs of fullscale cascades for thrust reversers. This document details the experimental design, setup, and testing that was performed on the scaled cascade and its results comparison to CFD.

CAF process combines creep and precipitation hardening which are highly dependent on time and temperature. The aging cycle relax the stresses induced during the loading phase. At the end of the process stress relaxation induces shape changes in the part but significant spring back is observed (about 70%). Usually CAF cycles for 7XXX alloys use times around 20 h and temperatures in the range of 120°C to 190°C. In the present work CAF tests were performed using the alloy 7050 in an intermediate condition named Temper to Age Forming (TAF). Using the alloy 7050-TAF resulted in significant process time reduction. From TAF temper, only 8 hours are necessary to achieve properties comparable to T74. Coupons were submitted to CAF in two levels of initial stress, 190 MPa and 290 MPa, resulting in spring back values of 70% and 60 % respectively. In addition, constant load creep tests were performed in the same stress levels and time of CAF tests to find the creep strain values. Creep tests performed under 190 MPa resulted in strain values around 0,1% after 8 h. On the other hand creep tests performed under 290 MPa failed after 7 h with creep strain values of 1,7%. Results obtained are close to that found in previous studies and it is possible to conclude that the use of alloy 7050 in TAF condition allows CAF to be done in 8 hours, since the initial stress is lower than 290 MPa.