Most recent or all developments in the field of small UAV’s seem to use Quadcopters. It’s a valued commenting that a quadcopter is a smaller amount stable than a similar regular chopper and is additionally less economical. A Quadcopter UAV’s with four propellers is always a major concern to the society when brings to its stability as its major factor. To design and analyze the use of one propeller monocopter is the main objective of this paper. Wacky Whirler technology used here to demonstrate the passage of the monocopter. It is a single propeller powered with a coreless motor which is a modern enhancement in the UAV. It is based on the All Rotating monocopter theory. In the proposed system, controller based on IOT can be used which will be helpful in monitoring and processing the microdrone status.
The certification of transport category cabin interiors requires a thorough understanding of Part 25 Transport Category aircraft cabin interior safety and crashworthiness regulations and compliance requirements. Regardless of whether it is a simple modification, a specialized completion (VIP or VVIP) or airline passenger configuration, engineers, designers, and airworthiness personnel must understand and adhere to these requirements. This two day seminar will begin with a discussion of Commercial off the Shelf (COTS) test requirements.
Despite the advantages of electronic flight bags (EFB), passenger entertainment and email access during flights, and the ability to access aircraft repair manuals electronically, computer interconnectivity throughout aviation has opened the aviation sector to cyber-attacks that could impact flights, data, and safety. This two-day seminar is intended to introduce aviation professionals to the need to implement cyber security throughout commercial aviation including the supply chain.
ARP4754A substantially revises the industry guidance for the development of aircraft and aircraft systems while taking into account the overall aircraft operating environment and functions. This development process includes validation of requirements and verification of the design implementation for certification and product assurance. ARP4754A provides the practices for showing compliance with regulations and serves to assist companies in developing and meeting its own internal standards though application of the described guidelines.
Designing derivative aircraft is a complex process with potentially large amounts of program risk. In this paper we present new technologies such as digital interface control documents, and generative design that can transform this process. Employing these types of technologies makes the process more verifiable and repeatable. The paper explains how the technologies can be adopted from the early definition of components & LRUs, to their aggregation into reusable subsystems, as well as the automation and validation processes that can be built around them to reduce the associated complexity and program risk.
Accurate and fast positioning of large aircraft component is of great importance for Automated Alignment System. The Ball joint is a widely-used mechanical device connecting the aircraft component and Automated Alignment System. However, there are some shortcomings for the device in man-machine engineering, such as the entry state of the ball-head still needs to be confirmed by the workers and then switched to the locking state manually. To solve above problems, a new positioning mechanism is present in this paper, which consists of a ball-head and a ball-socket. The new device is equipped with a monocular vision system, in which a calibrated industrial camera is used to collect the images of the ball-head. And then, the 3-D coordinate of the ball-head center is calculated by a designed algorithm, which combines the symmetry of the sphere and the principle of projection transformation, guiding the positioner to capture the ball-head.
In this study, we focus on an electric air-cycle system in an electric aircraft, where the system has an electric compressor instead of a hydraulically-operated oil-based compressor. The electric compressor consumes the power to compress the rarefied air outside and take it in the system. The air goes through the air-cycle as a working fluid to exchange the heat and work. The main purpose of the air-cycle is to adjust the temperature and pressure in a cabin. Therefore, the working fluid of the air repeats compression and expansion. The working fluid passing through the cabin absorbs heat from the passengers and avionics. After that, the air is discharged outside with higher heat level and pressure levels. This means that the discharged air has a potential energy to recover the power consumption in the electric compressor.
The relevance of innovative and functional lightweight components for aircrafts has risen significantly during the recent years. In this context, modern lightweight materials as well as cost-efficient and time-saving manufacturing technologies are required for a future aircraft production. The so called Hybrid SMC Technology and the SMC-Foam-Sandwich Technology are promising approaches for the cost-efficient and time-saving manufacturing of lightweight, geometrically complex and functional aircraft components. Both technologies have been used for the development of a new generation overhead stowage system. It is realized by sidewalls made out of enhanced SMC technologies with directly implemented metallic load introduction elements and regular sandwich structures that can be assembled by a quick-assembly principle.
Over recent decades, there has been a lot of progress toward a more electric aircraft (MEA) to reduce emissions and fuel consumption. In MEAs, many subsystems that previously used hydraulic or pneumatic power have been replaced by electrical systems with inverters and electrical machines. Therefore, MEAs reduce the weight, i.e. fuel consumption, and maintenance cost. To achieve advanced electrical systems, the weight of inverters has significant importance. In this work, a gradationally controlled voltage (GCV) inverter is proposed to reduce the weight and enhance reliability. A GCV inverter can supply gradational quasi-sinusoidal voltages combining two different voltages from a 3-phase 3-level (main) inverter and three single-phase H-bridge (sub) inverters. A dc power supply is required only for the main inverter. A main inverter with Si-IGBTs supplies the fundamental voltage by only one switching in the fundamental period.
This paper documents the potential use of reconfigurable reusable jig tooling based on the box-joint system for use in the assembly of a prototype compound helicopter wing. Due to the aircraft configuration the wing design is pinned at both ends and therefore requires a higher degree of accuracy (typically 0.2mm), over the 4m length, than conventional wings. In this paper the cost benefit of reusable tooling in a low volume prototype scenario is examined followed by the design of the jig and location features to enable accurate build and metrology documentation. A prototype 4m test jig comprising of commercially available components and bespoke machined ‘pick-ups’ is presented here. Hardware and measurement process cost modelling is documented along with results for the positional and hinge-line concentricity setting accuracy that was achieved using a laser tracking system.
The Rapid And Cost Effective Rotorcraft (RACER) is being developed by Airbus Helicopters (ABH) to demonstrate a new Vertical Take-Off and Landing configuration to fill the mobility gap between conventional helicopters and aeroplanes. RACER is a compound rotorcraft featuring wings and multiple rotors. The wing arrangement suggested by ABH is defined as a staggered bi-plane joined configuration with an upper and a lower straight wing, either side of the fuselage, connected at their outboard extent to form a triangular structure. The ASTRAL consortium, consisting of the University of Nottingham and GE Aviation Systems, are responsible for the design, manufacture and assembly of the wings. Producing an optimised strategy to assemble a joined-wing configuration for a passenger carrying rotorcraft is challenging and novel. The objective of this work concerns all aspects of assembling the joined-wing structure.