Sleep and body rhythm disturbance amongst flight crews in long-range aviation

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Untersuchungen zu kumulativen psychischen und physiologischen Effekten des fliegenden Personals auf der Kurzstrecke

Die fliegerische Tätigkeit auf der Kurzstrecke in der zivilen Luftfahrt unterliegt arbeitsspezifischen Belastungsfaktoren, die sich in wesentlichen Punkten von denen auf der Langstrecke unterscheiden. Eine hohe Arbeitsbelastung auf der Kurzstrecke ist mit vielen Starts und Landungen am Tag verbunden. Neben der Anzahl der Flugabschnitte können auch lange Flugdienstzeiten und/oder unregelmäßige Arbeitszeiten sowie der Zeitdruck während der Einsätze auf der Kurzstrecke zur Belastung für Cockpitbesatzungsmitglieder werden und zu Ermüdungserscheinungen führen. Bisher wurden flugmedizinische und -psychologische Daten hauptsächlich auf der Langstrecke in Bezug auf die Auswirkungen der Jet-Leg Symptomatik und kaum auf der Kurzstrecke erhoben. Deshalb wurde im Rahmen des DLR- Projekts „Untersuchungen zu kumulativen psychischen und physiologischen Effekten des fliegenden Personals auf der Kurzstrecke“ eine Langzeituntersuchung zur Belastung/Beanspruchung, Ermüdung sowie Erholung des Cockpitpersonals auf der Kurzstrecke über jeweils 56 Tage durchgeführt. In Zusammenarbeit mit der Deutschen Lufthansa AG dauerte die Untersuchung zu den Auswirkungen arbeitsspezifischer Belastungsfaktoren auf die Cockpitbesatzungsmitglieder der Boeing 737-Flotte von 2003 bis 2006. ZIEL: Unter Berücksichtigung theoretisch fundierter arbeitspsychologischer Konzepte war das Ziel der Studie, kumulative und akute Effekte auf das Schlaf-Wach-Verhalten, auf die Belastung/Beanspruchung sowie auf die Müdigkeit zu identifizieren, die durch aufeinander folgende Einsätze auf der Kurzstrecke innerhalb eines Zeitraums von acht Wochen auftreten können. Hierfür wurden Daten von 29 Piloten (N=13 Kapitäne; N=16 Erste Offiziere) aufgezeichnet. Das Durchschnittsalter lag bei 33,8 ± 7,9 Jahren (Kapitäne: 42,0 ± 3,8 Jahre; Erste Offiziere: 27,4 ± 2,2 Jahre). METHODEN: Über ein Handheld PC konnten effizient Fragebögen bearbeitet und das Sleep Log sowie das Flight Log geführt werden. Die subjektive Ermüdung und Arbeitsbeanspruchung wurden durch standardisierte Fragebögen (z.B. Ermüdungsskala von Samn & Perelli (1982), NASA-TLX) operationalisiert. Im Sleep Log und im Flight Log wurden das Schlaf-Wach-Verhalten sowie flugspezifische Daten dokumentiert (z.B. Dienstbeginn, Dienstende, Flugabschnitte, Zielorte, etc.). Der Schlaf-Wach-Zyklus wurde mittels der Aktimetrie während des gesamten Messverlaufs aufgezeichnet. Die objektive Leistungsfähigkeit wurde täglich morgens und abends mit Hilfe einer computergestützten Psychomotor Vigilance Task (PVT) nach Dinges & Powell (1985) erfasst. Die Leistung in der PVT diente als Indikator für die Ermüdung eines Piloten. Zusätzliche Befragungen mit Paper-Pencil-Fragebögen sollten Aufschluss über relevante, psychosoziale Randbedingungen geben, die bei den täglichen Erhebungen nicht berücksichtigt wurden (z.B. Arbeitszufriedenheit; Essgewohnheiten; Kollegenbeziehungen). ERGEBNISSE: Unter Beachtung kumulativer Effekte wurde über die Studiendauer keine Veränderung in der Schlafqualität und im Schlafbedürfnis festgestellt. Die Müdigkeit nahm dagegen während der achtwöchigen Untersuchung zu. Die Reaktionszeit in der PVT zeigte an Flugdiensttagen eine Verschlechterung über die Zeit. Insgesamt wurden keine kritischen längerfristigen Effekte analysiert. Akute signifikante Effekte wurden bei der Ermüdung, der Gesamtbelastung und der Leistungsfähigkeit an Flugdiensttagen gefunden. Die Ermüdung als auch die Gesamtbelastung stiegen bei zunehmender Flugdienstdauer und Leganzahl und die Leistung nahm in der PVT ab. Der „time on task“ Effekt zeigte sich besonders in der Ermüdung durch die fliegerische Tätigkeit ab einer Flugdienstzeit von > 10 Stunden und > 4 Legs pro Tag. SCHLUSSFOLGERUNG: Mit diesen Ergebnissen konnte eine wissenschaftliche Datenbasis geschaffen werden aus der Empfehlungen resultieren, wie die Einsatzplanung für das Cockpitpersonal auf der Kurzstrecke unter flugmedizinischen und flugpsychologischen Gesichtspunkten optimiert werden kann. Zudem kann ein sachgerechter Beitrag im Rahmen der Diskussion zur Flugdienst- und Ruhezeitenregelung auf europäischer Ebene geleistet werden.

Workshop on Integrated Crew Resource Management (CRM) /

"May 1992."

The third man : a history of the airline crew complement controversy, 1947-1981 /

Includes index.

Aviation operations handbook.

"February 1991."

Multi-objective mission flight planning in civil unmanned aerial systems

Unmanned Aerial Vehicles (UAVs) are emerging as an ideal platform for a wide range of civil applications such as disaster monitoring, atmospheric observation and outback delivery. However, the operation of UAVs is currently restricted to specially segregated regions of airspace outside of the National Airspace System (NAS). Mission Flight Planning (MFP) is an integral part of UAV operation that addresses some of the requirements (such as safety and the rules of the air) of integrating UAVs in the NAS. Automated MFP is a key enabler for a number of UAV operating scenarios as it aids in increasing the level of onboard autonomy. For example, onboard MFP is required to ensure continued conformance with the NAS integration requirements when there is an outage in the communications link. MFP is a motion planning task concerned with finding a path between a designated start waypoint and goal waypoint. This path is described with a sequence of 4 Dimensional (4D) waypoints (three spatial and one time dimension) or equivalently with a sequence of trajectory segments (or tracks). It is necessary to consider the time dimension as the UAV operates in a dynamic environment. Existing methods for generic motion planning, UAV motion planning and general vehicle motion planning cannot adequately address the requirements of MFP. The flight plan needs to optimise for multiple decision objectives including mission safety objectives, the rules of the air and mission efficiency objectives. Online (in-flight) replanning capability is needed as the UAV operates in a large, dynamic and uncertain outdoor environment. This thesis derives a multi-objective 4D search algorithm entitled Multi- Step A* (MSA*) based on the seminal A* search algorithm. MSA* is proven to find the optimal (least cost) path given a variable successor operator (which enables arbitrary track angle and track velocity resolution). Furthermore, it is shown to be of comparable complexity to multi-objective, vector neighbourhood based A* (Vector A*, an extension of A*). A variable successor operator enables the imposition of a multi-resolution lattice structure on the search space (which results in fewer search nodes). Unlike cell decomposition based methods, soundness is guaranteed with multi-resolution MSA*. MSA* is demonstrated through Monte Carlo simulations to be computationally efficient. It is shown that multi-resolution, lattice based MSA* finds paths of equivalent cost (less than 0.5% difference) to Vector A* (the benchmark) in a third of the computation time (on average). This is the first contribution of the research. The second contribution is the discovery of the additive consistency property for planning with multiple decision objectives. Additive consistency ensures that the planner is not biased (which results in a suboptimal path) by ensuring that the cost of traversing a track using one step equals that of traversing the same track using multiple steps. MSA* mitigates uncertainty through online replanning, Multi-Criteria Decision Making (MCDM) and tolerance. Each trajectory segment is modeled with a cell sequence that completely encloses the trajectory segment. The tolerance, measured as the minimum distance between the track and cell boundaries, is the third major contribution. Even though MSA* is demonstrated for UAV MFP, it is extensible to other 4D vehicle motion planning applications. Finally, the research proposes a self-scheduling replanning architecture for MFP. This architecture replicates the decision strategies of human experts to meet the time constraints of online replanning. Based on a feedback loop, the proposed architecture switches between fast, near-optimal planning and optimal planning to minimise the need for hold manoeuvres. The derived MFP framework is original and shown, through extensive verification and validation, to satisfy the requirements of UAV MFP. As MFP is an enabling factor for operation of UAVs in the NAS, the presented work is both original and significant.

Vibration isolation for autonomous helicopter flight

The mechanisms of helicopter flight create a unique, high-vibration environment which can play havoc with the accurate operation of on-board sensors. Vibration isolation of electronic sensors from structural borne oscillations is paramount to their reliable and accurate use. Effective isolation is achieved by realising a trade-off between the properties of the suspended instrument package, and the isolation mechanism. This is made more difficult as the weight and size of the sensors and computing hardware decreases with advances in technology. This paper presents a history of the design, challenges, constraints and construction of an integrated isolated vision and sensor platform and landing gear for the CSIRO autonomous X-Cell helicopter. The results of isolation performance and in-flight tests of the platform in autonomous flight are presented.

Low-cost flight control system for a small autonomous helicopter

In this paper we describe a low-cost flight control system for a small (60 class) helicopter which is part of a larger project to develop an autonomous flying vehicle. Our approach differs from that of others in not using an expensive inertial/GPS sensing system. The primary sensors for vehicle stabilization are a low-cost inertial sensor and a pair of CMOS cameras. We describe the architecture of our flight control system, the inertial and visual sensing subsystems and present some flight control results.

Reduction of environmental effects of civil aircraft through multi-objective flight plan optimisation

With rising environmental alarm, the reduction of critical aircraft emissions including carbon dioxides (CO2) and nitrogen oxides (NOx) is one of most important aeronautical problems. There can be many possible attempts to solve such problem by designing new wing/aircraft shape, new efficient engine, etc. The paper rather provides a set of acceptable flight plans as a first step besides replacing current aircrafts. The paper investigates a green aircraft design optimisation in terms of aircraft range, mission fuel weight (CO2) and NOx using advanced Evolutionary Algorithms coupled to flight optimisation system software. Two multi-objective design optimisations are conducted to find the best set of flight plans for current aircrafts considering discretised altitude and Mach numbers without designing aircraft shape and engine types. The objectives of first optimisation are to maximise range of aircraft while minimising NOx with constant mission fuel weight. The second optimisation considers minimisation of mission fuel weight and NOx with fixed aircraft range. Numerical results show that the method is able to capture a set of useful trade-offs that reduce NOx and CO2 (minimum mission fuel weight).

Flight testing of an augmented separation management system providing separation protection during failure of the central communication network

Future air traffic management concepts often involve the proposal of automated separation management algorithms that replaces human air traffic controllers. This paper proposes a new type of automated separation management algorithm (based on the satisficing approach) that utilizes inter-aircraft communication and a track file manager (or bank of Kalman filters) that is capable of resolving conflicts during periods of communication failure. The proposed separation management algorithm is tested in a range of flight scenarios involving during periods of communication failure, in both simulation and flight test (flight tests were conducted as part of the Smart Skies project). The intention of the conducted flight tests was to investigate the benefits of using inter-aircraft communication to provide an extra layer of safety protection in support air traffic management during periods of failure of the communication network. These benefits were confirmed.

Super-orbital re-entry in Australia : laboratory measurement, simulation and flight observation

There are large uncertainties in the aerothermodynamic modelling of super-orbital re-entry which impact the design of spacecraft thermal protection systems (TPS). Aspects of the thermal environment of super-orbital re-entry flows can be simulated in the laboratory using arc- and plasma jet facilities and these devices are regularly used for TPS certification work [5]. Another laboratory device which is capable of simulating certain critical features of both the aero and thermal environment of super-orbital re-entry is the expansion tube, and three such facilities have been operating at the University of Queensland in recent years[10]. Despite some success, wind tunnel tests do not achieve full simulation, however, a virtually complete physical simulation of particular re-entry conditions can be obtained from dedicated flight testing, and the Apollo era FIRE II flight experiment [2] is the premier example which still forms an important benchmark for modern simulations. Dedicated super-orbital flight testing is generally considered too expensive today, and there is a reluctance to incorporate substantial instrumentation for aerothermal diagnostics into existing missions since it may compromise primary mission objectives. An alternative approach to on-board flight measurements, with demonstrated success particularly in the ‘Stardust’ sample return mission, is remote observation of spectral emissions from the capsule and shock layer [8]. JAXA’s ‘Hayabusa’ sample return capsule provides a recent super-orbital reentry example through which we illustrate contributions in three areas: (1) physical simulation of super-orbital re-entry conditions in the laboratory; (2) computational simulation of such flows; and (3) remote acquisition of optical emissions from a super-orbital re entry event.

Optimal-stopping control for airborne collision avoidance and return-to-course flight

This paper considers an aircraft collision avoidance design problem that also incorporates design of the aircraft’s return-to-course flight. This control design problem is formulated as a non-linear optimal-stopping control problem; a formulation that does not require a prior knowledge of time taken to perform the avoidance and return-to-course manoeuvre. A dynamic programming solution to the avoidance and return-to-course problem is presented, before a Markov chain numerical approximation technique is described. Simulation results are presented that illustrate the proposed collision avoidance and return-to-course flight approach.