Relevant bibliographies by topics / Flight mechanic

Academic literature on the topic 'Flight mechanic'

Author: Grafiati
Published: 14 March 2023

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Journal articles on the topic "Flight mechanic"

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Manzanera, R. A. Jiménez, and H. Smith. "Flight in nature I: Take-off in animal flyers." Aeronautical Journal 119, no. 1213 (March 2015): 257–80. http://dx.doi.org/10.1017/s0001924000010472.

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AbstractIn this review paper, several take-off techniques of different species of animal flyers and gliders, both extinct and extant, are analysed. The methods they use vary according to animal group and size. Smaller animals, such as insects, rely on the use of transient aerodynamic techniques or the use of stored elastic energy. Medium-size flyers such as birds, bats, and other mammal gliders initiate flight by a jump which involves leg and wing movement coordination. The largest animals to fly, the extinct pterosaurs, are believed to have used a combination of aerodynamic and mechanic techniques in order to become airborne. The information presented here can be used as a resource for novel biomimetic unmanned aircraft design.
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Köthe, Alexander, and Robert Luckner. "Applying Eigenstructure Assignment to Inner-Loop Flight Control Laws for a Multibody Aircraft." CEAS Aeronautical Journal 13, no. 1 (December 21, 2021): 33–43. http://dx.doi.org/10.1007/s13272-021-00549-z.

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AbstractUnmanned aircraft used as high-altitude platform system has been studied in research and industry as alternative technologies to satellites. Regarding actual operation and flight performance of such systems, multibody aircraft seems to be a promising aircraft configuration. In terms of flight dynamics, this aircraft strongly differs from classical rigid-body and flexible aircraft, because a strong interference between flight mechanic and formation modes occurs. For unmanned operation in the stratosphere, flight control laws are required. While control theory generally provides a number of approaches, the specific flight physics characteristics can be only partially considered. This paper addresses a flight control law approach based on a physically exact target model of the multibody aircraft dynamics rather than conventionally considering the system dynamics only. In the target model, hypothetical spring and damping elements at the joints are included into the equations of motion to transfer the configuration of a highly flexible multibody aircraft into one similar to a classical rigid-body aircraft. The differences between both types of aircraft are reflected in the eigenvalues and eigenvectors. Using the eigenstructure assignment, the desired damping and stiffness are established by the inner-loop flight control law. In contrast to other methods, this procedure allows a straightforward control law design for a multibody aircraft based on a physical reference model.
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Lin, Yide. "The Development and Challenges of More Electric Aircraft." Highlights in Science, Engineering and Technology 27 (December 27, 2022): 814–19. http://dx.doi.org/10.54097/hset.v27i.3850.

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The development of electrical and electronic engineering makes the replacement of conventional hydraulic, mechanic, and pneumatic system into electrical system become much more possible. That means the secondary power of aircraft will be dominated by electricity, rather than hydraulic oil or bleed air from the engine. The Boeing 787 and Airbus A380 has applied these technologies significantly and their fuel consumption and noise level during flight are also get improved by comparison with their counterpart which has traditional hydraulic and pneumatic system. On the other side, the mass application of electrical driven components on board will lead to various new challenges to aircraft design when concerning the weight and flight safety due to the characteristics of those components. In this paper, technologies implemented, and challenges will be introduced through reviewing literatures. The benefit and drawbacks will be concluded by comparing electrical and hydraulic and pneumatic system.
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Li, He, Gang Zou, Lin Li, and Dehui Yu. "Helicopter Training Simulator Measurement and Control System Based on Computer Simulation Technology." Journal of Physics: Conference Series 2143, no. 1 (December 1, 2021): 012011. http://dx.doi.org/10.1088/1742-6596/2143/1/012011.

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Abstract With the development of computer software technology and simulation technology, simulation training has been widely used. Helicopter training simulation has become an important part of helicopter training, and its status is becoming more and more important. On the one hand, the air mechanic is responsible for the maintenance and organization of the helicopter during the flight, and on the other hand is responsible for the starting and stopping of the helicopter engine, the operation of related equipment, and the handling of emergencies during the flight. The simulation training has the characteristics of high training efficiency, convenient maintenance and low training cost. It will become an important means for helicopter air mechanics to troubleshoot and deal with special situations. This paper aims to study the helicopter training simulator measurement and control system based on computer software technology. Based on the analysis of the advantages of the simulator instead of the actual installation for training, the helicopter training simulator function and the simulator subsystem, the actual installation simulation instrument and signal are designed. The indicator light, the graphic instrument and the control signal are arranged in the circuit, and then the simulation experiment is carried out on the design. The experimental results show that the design can more accurately simulate the indication of the antenna elevation angle table, which meets the requirements of this article.
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Ristantya, Alfandira Rossa, Bina Kurniawan, and Ida Wahyuni. "HUBUNGAN ANTARA KARAKTERISTIK PEKERJA DAN PENGAWASAN TERHADAP PERILAKU TIDAK AMAN PADA TEKNISI PERAWATAN HANGAR PESAWAT PT X." Jurnal Kesehatan Masyarakat (Undip) 10, no. 3 (May 5, 2022): 267–72. http://dx.doi.org/10.14710/jkm.v10i3.30875.

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Unsafe behavior is a failure to apply work rules and procedures, resulting in work accidents. Work accidents in the aviation are not spared from work accidents that can be experienced by technicians when carrying out aircraft maintenance and repairs. The development of the aviation industry in Indonesia is not proportional to the availability of the number of flight technician workers, resulting in an increase of work-related accidents experienced by flight technicians. Therefore, an approach is needed to determine the behavior of technicians that cause work accidents. This study aims to analyze the relationship between worker characteristics (knowledge, attitude, and working period) and supervision with unsafe behavior in PT X hangar maintenance technicians. This research is quantitative research with cross-sectional study design. The sample in this study were mechanic technicians shift I totaling 120 people who were obtained by random sampling. Data in this study were collected by using a questionnaire and the results were tested using the chi square test. The results of this study indicate that there is a correlation between attitude (p-value: 0,000) on unsafe behavior in PT X aircraft maintenance technicians. Meanwhile, there was no correlation between knowledge (p-value: 0.388), work period (p-value: 0.694), supervision (p-value: 0.305) and unsafe behavior. From the results obtained, hopefully management can add topics to safety briefings and improve the safety information media.
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Bai, Bo, Ziyang Zhao, Kai Yuan, Rongxin Tang, Xiaohua Deng, Mingyang Mao, Jiawei Xiong, and Kaili Wang. "Characteristics of EHF Wave Propagation in Hypersonic Plasma Sheaths Magnetized by Dipole Magnetic Fields." Applied Sciences 12, no. 6 (March 18, 2022): 3105. http://dx.doi.org/10.3390/app12063105.

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Communication blackout is always a serious threat to the flight tasks of modern hypersonic vehicles moving in near space. EHF communication is considered as a potential solution to the blackout problem. Nevertheless, EHF waves suffer from severe attenuation in hypersonic plasma sheaths. An external magnetic field could mitigate EHF wave attenuation in hypersonic plasma sheaths. Dipole magnetic fields, generated by coils, are feasible in realistic scenarios. In the present study, a model for EHF wave propagation in hypersonic plasma sheaths magnetized by dipole magnetic fields that are generated with coils is developed. The dissipation caused by the inhomogeneity of dipole magnetic fields and the magnetic field component of electromagnetic waves are compared with the dissipation yielded by the collision between electrons and neutral particles. The results show that collision is still the main dissipation mechanic for EHF waves. The study also found that, in the blunt-coned plasma sheath, the mitigation effect of a dipole magnetic field is weaker than that of a uniform magnetic field. The mechanics which yield the difference is analyzed. In addition, the relation between the characteristics of EHF waves and the coil parameters is investigated. Suggestions for the coil parameters and the operation frequencies of the EHF communication systems are made based on the investigation.
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Gao, Xinglong, Qingbin Zhang, and Qiangang Tang. "Fluid-Structure Interaction Analysis of Parachute Finite Mass Inflation." International Journal of Aerospace Engineering 2016 (2016): 1–8. http://dx.doi.org/10.1155/2016/1438727.

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Parachute inflation is coupled with sophisticated fluid-structure interaction (FSI) and flight mechanic behaviors in a finite mass situation. During opening, the canopy often experiences the largest deformation and loading. To predict the opening phase of a parachute, a computational FSI model for the inflation of a parachute, with slots on its canopy fabric, is developed using the arbitrary Lagrangian-Euler coupling penalty method. In a finite mass situation, the fluid around the parachute typically has an unsteady flow; therefore, a more complex opening phase and FSI dynamics of a parachute are investigated. Navier-Stokes (N-S) equations for uncompressible flow are solved using an explicit central difference method. The three-dimensional visualization of canopy deformation as well as the evolution of dropping velocity and overload is obtained and compared with the experimental results. This technique could be further applied in the airdrop test of a parachute for true prediction of the inflation characteristics.
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Calvert, B. J. "Aircrew and Automation." Journal of Navigation 38, no. 1 (January 1, 1985): 1–18. http://dx.doi.org/10.1017/s0373463300038121.

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On 18 June, 1914 Lawrence, son of Elmer Sperry (founder of the Sperry Gyroscope Company) flew over a crowd assembled at Argenteuil, near Paris (Fig. 1). His aircraft was a Curtiss C2 flying boat and the purpose of the flight was to demonstrate the Sperry Gyroscopic Stabilizer in a competition organized by the Aero Club of France. It was a dramatic demonstration. On the first pass over the crowd Lawrence Sperry stood up and held both hands in the air whilst his mechanic, Emile Cachin, walked out on the wing and stood holding one of the struts. The lateral stability of the aeroplane was undisturbed, but the spectators were able to see the ailerons move to compensate for the engineer's weight. This performance was repeated several times and Sperry also demonstrated the automatic ‘volplaning’ function of the system which caused the aircraft to dive and regain speed in the event of an approach to the stall. The company was awarded a prize of 50000 francs as winner of the competition.
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Cipolla, Vittorio, Davide Zanetti, Karim Abu Salem, Vincenzo Binante, and Giuseppe Palaia. "A Parametric Approach for Conceptual Integration and Performance Studies of Liquid Hydrogen Short–Medium Range Aircraft." Applied Sciences 12, no. 14 (July 6, 2022): 6857. http://dx.doi.org/10.3390/app12146857.

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The present paper deals with the investigation, at conceptual level, of the performance of short–medium-range aircraft with hydrogen propulsion. The attention is focused on the relationship between figures of merit related to transport capability, such as passenger capacity and flight range, and the parameters which drive the design of liquid hydrogen tanks and their integration with a given aircraft geometry. The reference aircraft chosen for such purpose is a box-wing short–medium-range airplane, the object of study within a previous European research project called PARSIFAL, capable of cutting the fuel consumption per passenger-kilometre up to 22%. By adopting a retrofitting approach, non-integral pressure vessels are sized to fit into the fuselage of the reference aircraft, under the assumption that the main aerodynamic, flight mechanic, and structural characteristics are not affected. A parametric model is introduced to generate a wide variety of fuselage-tank cross-section layouts, from a single tank with the maximum diameter compatible with a catwalk corridor to multiple tanks located in the cargo deck, and an assessment workflow is implemented to perform the structural sizing of the tanks and analyse their thermodynamic behaviour during the mission. This latter is simulated with a time-marching approach that couples the fuel request from engines with the thermodynamics of the hydrogen in the tanks, which is constantly subject to evaporation and, depending on the internal pressure, vented-out in gas form. Each model is presented in detail in the paper and results are provided through sensitivity analyses to both the technologic parameters of the tanks and the geometric parameters influencing their integration. The guidelines resulting from the analyses indicate that light materials, such as the aluminium alloy AA2219 for tanks’ structures and polystyrene foam for the insulation, should be selected. Preferred values are also indicted for the aspect ratios of the vessel components, i.e., central tube and endcaps, as well as suggestions for the integration layout to be adopted depending on the desired trade-off between passenger capacity, as for the case of multiple tanks in the cargo deck, and achievable flight ranges, as for the single tank in the section.
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Grigore, Jan Cristian. "Aspects Concerning the Dynamics of the Mechanisms with Clearances." Advanced Materials Research 837 (November 2013): 411–15. http://dx.doi.org/10.4028/www.scientific.net/amr.837.411.

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The clearances in the cinematic links appear due to the long functioning. In the paper we shall make a few considerations of geometric and mechanic type about the clearances in the linkages, linkages planes with rotation joint links. We shall elaborate methods to study the influence of the clearances. Consider a rotational kinematic coupling clearance, the clearance being defined by the distance, difference between the radius of the bearing and the radius of the journal. This relationship between elements is unilateral. Journal's behaviour inside the bearing can be highlighted the value normal reaction force. The journal can have the following phases, phase contact (when there is contact between the bearing and journal, the normal reaction force is zero) flight phase (no contact between end journal bearing at this stage is normal reaction force 0). It is considered the most dangerous phase, recovery phase of flight phase where the contact is restored. In this phase occurs shocks, shocks in turn produce vibration in the mechanism leading to the destruction of the system. The clearance size is directly proportional to magnitude impact and vibration level especially high. To be reduced or even eliminated these shocks, the paper presents a solution. Crank Mechanism with clearance, mechanism considered in this paper applies a force so that maintain contact between the bearing and journal, is considered the center of gravity of the connecting rod the forces and the moment. Based on the relations obtained from equation echililibru and vector equation of the contour goes to the numerical calculation for the engine element is inserted angle value (which defines the initial position of the mechanism), one deduces the angles, which define the position of the mechanism. Any would be their source of appearance, they usually produce unwished effects during the mechanisms functioning.
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Dissertations / Theses on the topic "Flight mechanic"

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MARGUERETTAZ, PAOLO. "Development of an integrated/multidisciplinay methodology for the analysis of rotorcraft flight mechanics with external loads." Doctoral thesis, Politecnico di Torino, 2014. http://hdl.handle.net/11583/2540692.

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Helicopter is an invaluable tool in many civil applications and a fundamental asset in military operations. Two of its most appreciated capabilities, are the ability to transport external loads suspended from a cable and the possibility to carry stores rigidly mounted to the fuselage or to stub wings. Unfortunately, a suspended load adds its aerodynamics, rigid body and elastic suspen- sion dynamics to the helicopter bare airframe dynamics and less than satisfactory handling can ensue. Moreover, rigidly mounted stores must be dropped before a forced landing in order to get rid of dangerous items (e.g. fuel or explosives) and decrease weight as much as possible. In this conditions a safe store separation is not guaranteed and the store may collide with the helicopter. It is, then, clear that carrying external stores can pose safety issues. The first objective of this dissertation is the evaluation of helicopter handling qualities in presence of an external suspended load. A simple helicopter model is coupled with two different load models (pendulum and 6-DoFs). The system is, then, linearised, the modal and the frequency domain responses are evaluated and the handling qualities are assessed according to the current regulations. This approach requires very little knowledge of the actual helicopter an can be useful as a tool for preliminary handling qualities assessment during the design phase. The coherence of external load modal dynamics and the helicopter response to control input obtained with the present approach is compared with available reference data. Finally, the impact of the slung load parameters on helicopter handling qualities is assessed. The second objective of this dissertation is the study of a comprehensive approach to the problem of external load jettison from a helicopter and the development of an associated software tool. First a specialised tool for the simulation of the release of an external store is devel- oped. An important aspect of the simulation is the collision detection. The minimum distance between the helicopter and the store is evaluated at each simulation step. Multiple simulations are performed in order to determine the safe drop envelope. The following section describes a methodology to reconstruct the trajectory and the attitude of the jettisoned load from video frames. A manual procedure is developed to identify the same markers in two video frames taken at the same time by video cameras mounted on the helicopter. A simple camera calibration technique, capable of computing camera orientation and aperture angle, is also discussed. Finally the possibility to identify the aerodynamics properties of the released body from flight test data is investigated. The objective is to build, from the reconstructed trajectory, an aerodynamic model functional to the refining of the store drop simulation. The problem is a minimization one. An Evolutionary Algorithm is used with good results on different test cases, also including measurement noise.
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Willmott, Alexander Peter. "The mechanics of hawkmoth flight." Thesis, University of Cambridge, 1995. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.390186.

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Merlet, Pierre Miguel. "Flight Mechanics of an Airship." Thesis, KTH, Flygdynamik, 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-290178.

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Airships were very popular 90 years ago with, for example, german Zeppelins. Now theyare back for several reasons, like their low energy consumption.But there are also still many problems to deal with like their sensitivity to wind gusts.In addition, the airships need more studies to improve their flight mechanics and sensitivityto the wind.This degree project, done with the French Aerospace Lab ONERA in Lille, studies a specificairship which is 5mlong and 1.7mwide. First, the airship is studied without wind to determineaerodynamic coefficients and added masses. Then, the model is confronted to experiments withwind gusts.
Luftskepp var mycket populär för 90 år sedan, till exempel med tyska Zeppelinare. Nu ärde tillbaka av flera skäl, som deras låga energiförbrukning.Men det finns fortfarande många problem att hantera som deras känslighet för vindbyar.Dessutom behöver luftskeppen fler studier för att förbättra sina flygegenskaper och vindkänslighet.Detta examsarbete, utfört vid den franska institutionenONERAi Lille, studerar ett specifiktluftskepp som är 5 m långt och 1.7 m brett. Först, studeras luftskeppet utan vind för attbestämma aerodynamiska data och tröghetsegenskaper. Sedan genomförs experiment därmodellen utsätts för vindbyar.
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Dudley, Theodore Robert. "Mechanics of forward flight in insects." Thesis, University of Cambridge, 1987. https://www.repository.cam.ac.uk/handle/1810/250902.

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Zhou, Hui M. S. Massachusetts Institute of Technology. "Micromechanical actuators for insect flight mechanics." Thesis, Massachusetts Institute of Technology, 2008. http://hdl.handle.net/1721.1/44319.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Materials Science and Engineering, 2008.
Includes bibliographical references (p. 95-97).
This project aims to develop MEMS actuators to aid in the study of insect flight mechanics. Specifically, we are developing actuators that can stimulate the antennae of the crepuscular hawk moth Manduca Sexta. The possible mechanosensory function of antennae as airflow sensors has been suggested, and recent discoveries of our collaborators reveal that mechanosensory input from the antennae of flying moths serves a similar role to that of the hind wings of two-winged insects, detecting Coriolis forces and thereby mediating flight stability during maneuvers. Early evidence suggests that mechanical stimulus of the antennae may enable flight control. In addition, the crepuscular hawk moth Manduca Sexta has a wide wingspan (~110 mm) and is capable of carrying at least one quarter of its own weight. Thus, studying the flight of Manduca Sexta by attachment of microsystems seems plausible. The goal of our project is to design and fabricate micromechanical actuators, which will be mounted onto the moth antennae. Our collaborators will study the flight control mechanism by mechanical stimulation. Our first step was to fabricate "dummy" silicon rings for our biologist collaborators for implant experiment. A series of mounting kits were developed, and due to the nature of the moth antennae, ring-beam-ring construction was finally designed and fabricated, like a "shackle", to meet the mounting requirements. Next, we integrated actuators onto the mounting kit. Piezoelectric film/sheet, piezoelectricbender and piezoelectric-stack were considered as the actuators. Live testing was also taken while the moth was resting or flapping its wings. The moth apparently responds to the mechanical stimulus under both circumstances, by swinging its wings and abdomen. Actuation amplifier was also modeled and tested, which might be used for future mechanical stimulators.
by Hui Zhou.
S.M.
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Falquier, Rene. "Longitudinal Flight Mechanics of Paraglider Systems." Thesis, KTH, Flygdynamik, 2019. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-261698.

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This project outlines a cost-effective numerical simulation method for the analysis of the longitudinal mechanics of paraglider systems. It is built on static stability methods for the analyses of low subsonic aircraft, non-linear lifting line methods for aerodynamic parameterization, and frequency domain analysis methods derived from system theory. Paragliders possess a glide polar in the range of ≈ 25-60 km.h−1 and display underdamped dynamic responses dominated by a long-period mode. The simulation results for performance and dynamic response are qualitatively valid relative to experimental data and in the same order of magnitude.
Projektet handlar om utveckling och utvärdering av en kostnadseffektiv simuleringsmodell för longitudinella frihetsgrader av skärmflyg. Modellen är byggd med fundamentala metoder för stabilitetsanalys av låghastighetsflygplan, ickelinjära liftingline metoden för aerodynamikanalys samt frekvensanalys från systemteori. Ett skärmflygs glidepolar är definierad på hastighetsintervallet ≈ 25-60 km.h−1 och visar ett underdämpat dynamiskt svar med lång period. Simuleringsresultaten för prestanda och dynamisk stabilitet ¨ar kvalitativt giltiga i förhållande till experimentella data och visar samma magnitud.
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Helgesson, Fredrik. "Analysis of a flight mechanics simulator." Thesis, KTH, Flygdynamik, 2019. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-265616.

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Aircraft design is an act of art requiring dedication and careful work to ensure good results. An essential tool in that work is a flight mechanics simulator. Such simulators are often built up of modules/models that are executed in a sequential order in each time iteration. This project aims to analyze potential improvements to the model execution order based on the dependency structure of one such simulator. The analysis method Design Structure Matrix (DSM), was used to define/map the dependencies and then Binary Linear Programming (BLP) was utilized to find five new potentially improved model orders to minimize the number of feedbacks from one iteration to the next one. Those five proposed execution orders were next compared and evaluated. The result is a model order that reduce the number of models receiving feedbacks from the previous iteration from 13 to 6, with insignificant changes in the precision of the simulator.
Vid flygplanskonstruktion krävs hårt och noggrant arbete för att säkerställa gott resultat. Ett oumbärligt verktyg är då en flygmekanisk simulator. Den typen av simulatorer är ofta uppbyggda av moduler/modeller som exekveras i en bestämd sekventiellt ordning i varje tidsteg. Syftet med detta projekt är att undersöka möjliga förbättringar av exekverings ordningen av de olika modellerna i en existerande simulator, baserat på beroendestrukturen. Analysmetoden Design Structure Matrix (DSM) användes för att bestämma beroendestrukturen och sedan utnyttjades Binär Linjär Programmering (BLP) för att hitta fem förbättrade modellordningar med avseende på att minimera antalet modeller som erhåller indata från föregående tidsiteration. De fem förbättringsförslagen jämfördes och utvärderades. Resultatet är en modellordning som kan minska antalet återkopplande modeller från 13 till 6, med insignifikanta skillnader i precisionen av simulatorn.
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Karail, Kursat. "Image Based Flight Data Reconstruction Using Aeroballistic Range Yaw Cards." Master's thesis, METU, 2005. http://etd.lib.metu.edu.tr/upload/2/12605768/index.pdf.

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The only aeroballistic laboratory of Turkey is the Flight Mechanics Laboratory, FML of TÜ
BITAK - SAGE. In FML, flight profiles of projectiles are reconstructed using their tear marks on paper sheets, called yaw cards. Tear marks are created on yaw cards as projectiles pass through them. These yaw cards are tightly stretched to metal frames which are positioned normal to the direction of projectile flight path. The use of yaw cards for flight profile reconstruction is a low cost and reliable solution. However, the yaw card method requires a heavy workload for the analysis of tear marks. Yaw cards collected from the frames are fed through an optical scanner and converted to digital images. These digital images are then processed by operators to calculate the projectile&rsquo
s flight position and angles. To automate this manual process, an algorithm is developed by using histogram based segmentation techniques, custom search algorithms, and Radon transform. This algorithm identifies and locates the projectile marks and finds angle of attack, angle of side slip and roll angle at each frame station by conducting the necessary transformations. Using this automated algorithm, a considerable amount of improvement is accomplished in terms of both decreasing the analysis time and increasing the accuracy of flight profile reconstruction.
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Goupil, Marc Y. "Dynamic Pressure Sensing for the Flight Test Data System." DigitalCommons@CalPoly, 2019. https://digitalcommons.calpoly.edu/theses/2115.

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This thesis describes the design, assembly, and test of the FTDS-K, a new device in the Boundary Layer Data System (BLDS) family of flight data acquisition systems. The FTDS-K provides high-frequency, high-gain data acquisition capability for up to two pressure sensors and an additional three low-frequency pressure sensors. Development of the FTDS-K was separated into a core module, specialized analog subsystem, and practical testing of the FTDS-K in a flow measurement mission. The core module combines an nRF52840-based microcontroller module, switching regulator, microSD card, real-time clock, temperature sensor, and trio of pressure sensors to provide the same capabilities as previous-generation BLDS-P devices. An expansion header is included in the core module to allow additional functionality to be added via daughter boards. An analog signal chain comprised of two-stage amplification and fourth-order active antialiasing filters was implemented as a daughter board to provide an AC-coupled end-to-end gain of 7,500 and a DC-coupled end-to-end gain of 50. This arrangement was tested in a wind tunnel to demonstrate that sensors with a full-scale range of 103 kPa can be used to reliably discriminate between laminar and turbulent flows based on pressure fluctuation differences on the order of tens of Pa. A combination of wind-off correction and band-filtering was used to reduce the effect of inherent and induced electrical noise, while two-sensor correlation was tested and shown to be effective at removing certain types of noise. Total power consumption for the FTDS-K in a representative mission is 208 mW, which translates to an operational endurance of 9 hours with 2 AAA LiFeS2 cells at -40°C.
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Larsson, Roger. "System Identification of Flight Mechanical Characteristics." Licentiate thesis, Linköpings universitet, Reglerteknik, 2013. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-92823.

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With the demand for more advanced fighter aircraft, relying on relaxed stability or even unstable flight mechanical characteristics to gain flight performance, more focus has been put on model-based system engineering to help with the design work. The flight control system design is one important part that relies on this modeling. Therefore it has become more important to develop flight mechanical models that are highly accurate in the whole flight envelop. For today’s newly developed fighters, the basic aircraft characteristics change between linear and nonlinear as well as stable and unstable as an effect of the desired capability of advanced maneuvering at subsonic, transonic and supersonic speeds. This thesis combines the subject of system identification, which is the art of building mathematical models of dynamical systems based on measurements, with aeronautics in order to find methods to identify flight mechanical characteristics from flight tests. Here, a challenging aeronautical identification problem combining instability and nonlinearity is treated. Two aspects are considered. The first is identification during a flight test with the intent to ensure that enough information is available in the resulting test data. Here, a frequency domain method is used. This idea has been taken from an existing method to which some improvements have been made. One of these improvements is to use an Instrumental Variable approach to take care of disturbances coming from atmospheric turbulence. The method treats linear systems that can be both stable and unstable. The improved method shows promising results, but needs further work to become robust against outliers and missing data. The other aspect is post-flight identification. Here, five different direct identification methods, which treat unstable and nonlinear systems, have been compared. Three of the methods are variations of the prediction-error method. The fourth is a parameter and state estimation method and the fifth method is a state estimation method based on an augmented system approach. The simplest of the prediction-error methods, based on a parametrized observer approach, is least sensitive to noise and initial offsets of the model parameters for the studied cases. This approach is attractive since it does not have any parameters that the user has to tune in order to get the best performance. All methods in this thesis have been validated on simulated data where the system is known, and have also been tested on real flight test data.
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Books on the topic "Flight mechanic"

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United States. Flight Standards Service., ed. Computerized testing supplement replacement pages for recreational pilot and private pilot: Flight and ground instructor, flight engineer and aviation mechanic general, powerplant, and airframe ; and parachute rigger. Washington, D.C: U.S. Dept. of Transportation, Federal Aviation Administration, Flight Standards Service, 1995.

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Tewari, Ashish. Basic Flight Mechanics. Cham: Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-30022-1.

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H, Barnard R., and Philpott D. R, eds. Mechanics of flight. Harlow, England: Pearson, 2012.

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Mechanics of flight. 9th ed. Harlow: Longman Scientific and Technical, 1987.

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Kermode, Alfred Cotterill. Mechanics of flight. 9th ed. Harlow, England: Longman Scientific and Technical, 1987.

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Phillips, Warren F. Mechanics of flight. 2nd ed. Hoboken, N.J: J. Wiley, 2010.

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Weiland, Claus. Computational Space Flight Mechanics. Berlin, Heidelberg: Springer Berlin Heidelberg, 2010. http://dx.doi.org/10.1007/978-3-642-13583-5.

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Development, North Atlantic Treaty Organization Advisory Group for Aerospace Research and. Space vehicle flight mechanics. Neuilly sur Seine, France: AGARD, 1990.

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Buydos, John F. Aerodynamics (mechanics of flight). Washington, D.C. (101 Independence Ave., S.E., Washington 20540-4750): Science Reference Section, Science, Technology and Business Division, Library of Congress, 2000.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Space vehicle flight mechanics. Neuilly-sur-Seine: AGARD, 1990.

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Book chapters on the topic "Flight mechanic"

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Ng, Tian Seng. "Flight Mechanics." In Flight Systems and Control, 3–11. Singapore: Springer Singapore, 2018. http://dx.doi.org/10.1007/978-981-10-8721-9_2.

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Suresh, B. N., and K. Sivan. "Flight Mechanics." In Integrated Design for Space Transportation System, 285–328. New Delhi: Springer India, 2015. http://dx.doi.org/10.1007/978-81-322-2532-4_8.

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Sebbane, Yasmina Bestaoui. "Flight Mechanics." In A First Course in Aerial Robots and Drones, 35–58. Boca Raton: Chapman and Hall/CRC, 2022. http://dx.doi.org/10.1201/9781003121787-3.

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Dirkx, Dominic, and Erwin Mooij. "Flight Mechanics." In Conceptual Shape Optimization of Entry Vehicles, 19–39. Cham: Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-46055-0_2.

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Tewari, Ashish. "Space Flight." In Basic Flight Mechanics, 99–121. Cham: Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-30022-1_6.

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Tewari, Ashish. "Rocket Flight." In Basic Flight Mechanics, 123–31. Cham: Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-30022-1_7.

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Polyakhov, Nikolai Nikolaevich, and Mikhail Petrovich Yushkov. "Flight Dynamics." In Foundations of Engineering Mechanics, 437–67. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-64118-4_10.

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Tewari, Ashish. "Introduction." In Basic Flight Mechanics, 1–21. Cham: Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-30022-1_1.

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Tewari, Ashish. "Aerodynamics." In Basic Flight Mechanics, 23–41. Cham: Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-30022-1_2.

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Tewari, Ashish. "Flight of Airplanes and Gliders: Vertical Plane." In Basic Flight Mechanics, 43–72. Cham: Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-30022-1_3.

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Conference papers on the topic "Flight mechanic"

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Wang Tao and Yan Lei. "UAV aerotriangulation with flight-control data support." In 2011 Second International Conference on Mechanic Automation and Control Engineering (MACE). IEEE, 2011. http://dx.doi.org/10.1109/mace.2011.5987568.

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Stettner, Martin, and Ralph Voss. "Aeroelastic, Flight Mechanic, and Handling Qualities of the MOB BWB Configuration." In 9th AIAA/ISSMO Symposium on Multidisciplinary Analysis and Optimization. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2002. http://dx.doi.org/10.2514/6.2002-5449.

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Sachs, Gottfried, and Florian Holzapfel. "Flight Mechanic and Aerodynamic Aspects of Extremely Large Dihedral in Birds." In 45th AIAA Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2007. http://dx.doi.org/10.2514/6.2007-46.

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Qiang Wang. "Flight control system design for miniature unmmaned helicopter based on PowerPC." In 2011 Second International Conference on Mechanic Automation and Control Engineering (MACE). IEEE, 2011. http://dx.doi.org/10.1109/mace.2011.5987901.

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Hongxi Yang and Qingbo Geng. "The design of flight control system for small UAV with static stability." In 2011 Second International Conference on Mechanic Automation and Control Engineering (MACE). IEEE, 2011. http://dx.doi.org/10.1109/mace.2011.5987048.

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Miesner, Sebastian, Manuel Kessler, and Ewald Kramer. "High-fidelity Simulations of Rotors in Compact Configuration." In Vertical Flight Society 78th Annual Forum & Technology Display. The Vertical Flight Society, 2022. http://dx.doi.org/10.4050/f-0078-2022-17466.

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High fidelity CFD simulations of seven rotors in compact configuration at three different flight scenarios are performed. The cases are hover, as well as 50 km/h and 100 km/h forward flight. For comparison each rotor is simulated isolated with the same RPM and pitch angle as in the configuration. Additionally, a bigger isolated rotor with the same area as the complete configuration is simulated. For the configuration as well as the bigger rotor a flight mechanic trim is performed using the flight mechanic tool VFAST. The CFD simulation is performed with FLOWer. In hover, only the center rotor showed a significant Figure of Merit (FM) drop of 16% compared to the isolated rotor. The thrust of the outer rotors is increased at the tip areas facing outwards, while the tip areas towards the center and the tip areas of the center rotor showed reduced thrust compared to the isolated rotor. The wake contraction at the outer rotors is increased compared to the bigger rotor. For the 50 km/h forward flight the efficiency of the front rotors is increased (10%-17%) and the rear ones decreased (11%-16%). In this case the wake is directly convected from the front rotors into the rear rotor planes and strong vortex interactions occur. For the 100 km/h case the efficiency gain of the front rotors is reduced to 3%-11% and the decrease to 5%-9%. Due to the higher pitch the wake of the rotors flows away from the rotor plane and the rotor-rotor interactions are reduced.
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Jianxun Liu, Gang Li, Chunliang Zhang, and Hongjun Du. "Optimization steady state control of turbofan engine in the whole flight envelop based on Support Vector Machines." In 2011 Second International Conference on Mechanic Automation and Control Engineering (MACE). IEEE, 2011. http://dx.doi.org/10.1109/mace.2011.5988225.

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Zimmer, Markus. "Integral Design and Optimisation Process for a Highly Flexible Generic Long Range Jet Transport with Flight Mechanic Derivative Constraints." In AIAA Scitech 2021 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2021. http://dx.doi.org/10.2514/6.2021-1964.

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Božić, O., T. Eggers, and S. Wiggen. "Aerothermal and flight mechanic considerations by development of small launchers for low orbit payloads started from lorentz rail accelerator." In Progress in Propulsion Physics. Les Ulis, France: EDP Sciences, 2011. http://dx.doi.org/10.1051/eucass/201102765.

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Maclise, Douglas (Dougal) C., Richard C. Mains, and Alexander van Dijk. "Flight Opportunities for Testing and Demonstrating Emerging Space Technologies." In ASME 2013 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/imece2013-64703.

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NASA’s Flight Opportunities Program has two primary goals — provide flight opportunities to be used to mature new technologies and foster the new commercial space industry. Since 2010 the Program has contracted with seven commercial flight providers and has flown over 18 campaigns that carried over 45 technology payloads. The flight opportunities are awarded through an open competitive solicitation called the Announcement of Flight Opportunities (AFO) or through other NASA solicitations for new technology development. To date over 100 technologies have been selected for flight testing. This paper profiles four examples of the technologies that have been tested or demonstrated on suborbital flights: 3-D Printing in Space developed by Made In Space Inc., Fine Water Mist Portable Fire Extinguisher developed by ADA Technologies and NASA/Glenn Research Center, Precision Landing Exploration Technology developed by Draper Labs, and On-orbit Propellant Storage Stability developed by Embry-Riddle Aeronautical University.
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Reports on the topic "Flight mechanic"

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Murphy, Charles H., William H. Mermagen, and Sr. Flight Mechanics of an Elastic Symmetric Missile. Fort Belvoir, VA: Defense Technical Information Center, April 2000. http://dx.doi.org/10.21236/ada393951.

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Jenkins, Jerry E., Gregory A. Addington, Phillip S. Beran, Deborah S. Grismer, and Ernest S. Hanff. Dynamics of Aerospace Vehicles -- Nonlinear Flight Mechanics. Fort Belvoir, VA: Defense Technical Information Center, May 2000. http://dx.doi.org/10.21236/ada380300.

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Karasopoulos, Harry A., and Kevin J. Langan. Workshop on Trajectory Optimization Methods and Applications, Presentations from the 1992 AIAA Atmospheric Flight Mechanics Conference. Fort Belvoir, VA: Defense Technical Information Center, November 1992. http://dx.doi.org/10.21236/ada259761.

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Auguste, Sebastian, Kathryn M. E. Dominguez, Herman Kamil, and Linda Tesar. Cross-Border Trading as a Mechanism for Capital Flight: ADRs and the Argentine Crisis. Cambridge, MA: National Bureau of Economic Research, November 2002. http://dx.doi.org/10.3386/w9343.

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Hunter, Martha S., and Einat Zchori-Fein. Rickettsia in the whitefly Bemisia tabaci: Phenotypic variants and fitness effects. United States Department of Agriculture, September 2014. http://dx.doi.org/10.32747/2014.7594394.bard.

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The sweet potato whitefly, Bemisia tabaci (Hemiptera: Aleyrodidae) is a major pest of vegetables, field crops, and ornamentals worldwide. This species harbors a diverse assembly of facultative, “secondary” bacterial symbionts, the roles of which are largely unknown. We documented a spectacular sweep of one of these, Rickettsia, in the Southwestern United States in the B biotype (=MEAM1) of B. tabaci, from 1% to 97% over 6 years, as well as a dramatic fitness benefit associated with it in Arizona but not in Israel. Because it is critical to understand the circumstances in which a symbiont invasion can cause such a large change in pest life history, the following objectives were set: 1) Determine the frequency of Rickettsia in B. tabaci in cotton across the United States and Israel. 2) Characterize Rickettsia and B. tabaci genotypes in order to test the hypothesis that genetic variation in either partner is responsible for differences in phenotypes seen in the two countries. 3) Determine the comparative fitness effects of Rickettsia phenotypes in B. tabaci in Israel and the United States. For Obj. 1, a survey of B. tabaci B samples revealed the distribution of Rickettsia across the cotton-growing regions of 13 sites from Israel and 22 sites from the USA. Across the USA, Rickettsia frequencies were heterogeneous among regions, but were generally at frequencies higher than 75% and close to fixation in some areas, whereas in Israel the infection rates were lower and declining. The distinct outcomes of Rickettsia infection in these two countries conform to previouslyreported phenotypic differences. Intermediate frequencies in some areas in both countries may indicate a cost to infection in certain environments or that the frequencies are in flux. This suggests underlying geographic differences in the interactions between bacterial symbionts and the pest. Obj. 2, Sequences of several Rickettsia genes in both locations, including a hypervariableintergenic spacer gene, suggested that the Rickettsia genotype is identical in both countries. Experiments in the US showed that differences in whitefly nuclear genotype had a strong influence on Rickettsia phenotype. Obj. 3. Experiments designed to test for possible horizontal transmission of Rickettsia, showed that these bacteria are transferred from B. tabaci to a plant, moved inside the phloem, and could be acquired by other whiteflies. Plants can serve as a reservoir for horizontal transmission of Rickettsia, a mechanism that may explain the occurrence of phylogenetically-similarsymbionts among unrelated phytophagous insect species. This plant-mediated transmission route may also exist in other insect-symbiont systems, and since symbionts may play a critical role in the ecology and evolution of their hosts, serve as an immediate and powerful tool for accelerated evolution. However, no such horizontal transmission of Rickettsia could be detected in the USA, underlining the difference between the interaction in both countries, or between B. tabaci and the banded wing whitefly on cotton in the USA (Trialeurodes sp. nr. abutiloneus) and the omnivorous bug Nesidiocoristenuis. Additionally, a series of experiments excluded the possibility that Rickettsia is frequently transmitted between B. tabaci and its parasitoid wasps Eretmocerusmundus and Encarsiapergandiella. Lastly, ecological studies on Rickettsia effects on free flight of whiteflies showed no significant influence of symbiont infection on flight. In contrast, a field study of the effects of Rickettsia on whitefly performance on caged cotton in the USA showed strong fitness benefits of infection, and rapid increases in Rickettsia frequency in competition population cages. This result confirmed the benefits to whiteflies of Rickettsia infection in a field setting.
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