Готові списки джерел за темами / Jet Vehicle

Добірка наукової літератури з теми "Jet Vehicle"

Автор: Grafiati
Опубліковано: 6 вересня 2023

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Статті в журналах з теми "Jet Vehicle"

1

Zhang, Lin, Junli Yang, Tiecheng Duan, Jie Wang, Xiuyi Li, and Kunyuan Zhang. "Numerical and Experimental Investigation on Nosebleed Air Jet Control for Hypersonic Vehicle." Aerospace 10, no. 6 (June 9, 2023): 552. http://dx.doi.org/10.3390/aerospace10060552.

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Анотація:
A new idea of nosebleed air jets with strong coupled internal and external flow is put forward using the lateral jet control principle to improve the maneuverability and fast reaction capabilities of hypersonic vehicles. The hypersonic vehicle’s nose stagnant high-pressure and high-temperature gas is utilized as the drive source for long-term jet control. The significant coupled jet interaction of the internal and external flow changes the aerodynamic characteristics. As a result, the structure is basic and does not rely on any external source to achieve flight attitude control. The complicated flow characteristics of the nosebleed jet in supersonic crossflow surrounding the vehicle were numerically and experimentally investigated. The jet interaction characteristics and the aerodynamic characteristic changes generated by the nosebleed air jet are verified by comparing the flow field with and without the jet. Results indicate that the nosebleed air jet alters the center-of-pressure coefficient, which is subsequently coupled with the interference aerodynamic force. This results in a variation in pitch moment. The jet decreases the pitching moment coefficient when compared with the case without a jet. It is probable that combining nosebleed air jets with model centroid adjustment yields an optimal trim angle of attack.
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2

Sabak, Ryszard. "Synthetic Diagnostics Of The JET System Of The JET-2 Unmanned Drone." Journal of KONBiN 32, no. 1 (December 1, 2014): 37–44. http://dx.doi.org/10.2478/jok-2014-0029.

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Анотація:
Abstract In recent years, , newer and newer designs of unmanned air vehicles have been appeared and in a spread and spread area. That is why, their service and in particular their diagnostics should be carried out both before and in each flight. In this paper, a description of both unmanned air vehicle JET-2 and its units and control system are presented. The paper includes also description of signals which are transmitted in a real time from the dron to the flight control station. These signals enable to state whether the vehicle works in a correct way. An interactive diagnostics model is presented as two united equations of state which are based on an observation that the usable value of the UAV resulting from its working standards, depends on its technical condition and what is more, technical condition depends on its working condition (intensity of usage). It should be stated that technical conditions are an environment for working conditions and working conditions are an environments for technical conditions. Presented model gives a comprehensive information about technical and working capability of a vehicle. It enables to plan next flights taking into account their currant potential and capability.
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3

Park, Byoungjik, Yangkyun Kim, Jin Ouk Park, and Ohk Kun Lim. "Jet Flame Risk Analysis for Safe Response to Hydrogen Vehicle Accidents." Sustainability 15, no. 13 (June 21, 2023): 9884. http://dx.doi.org/10.3390/su15139884.

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Анотація:
With an increase in the use of eco-friendly vehicles such as hybrid, electric, and hydrogen vehicles in response to the global climate crisis, accidents related to these vehicles have also increased. Numerical analysis was performed to optimize the safety of first responders responding to hydrogen vehicle accidents wherein hydrogen jet flames occur. The influence range of the jet flame generated through a 1.8-mm-diameter nozzle was analyzed based on five discharge angles (90, 75, 60, 45, and 30°) between the road surface and the downward vertical. As the discharge angle decreases toward the road surface, the risk area that could cause damage moves from the center of the vehicle to the rear; at a discharge angle of 90°, the range above 9.5 kW/m2 was 1.59 m and 4.09 m to the front and rear of the vehicle, respectively. However, at a discharge angle of 30°, it was not generated at the front but was 10.39 m to the rear. In response to a hydrogen vehicle accident, first responders should perform rescue activities approaching from a diagonal direction to the vehicle front to minimize injury risk. This study can be used in future hydrogen vehicle design to develop the response strategy of the first responders.
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4

Whittlesey, Robert W., and John O. Dabiri. "Optimal vortex formation in a self-propelled vehicle." Journal of Fluid Mechanics 737 (November 15, 2013): 78–104. http://dx.doi.org/10.1017/jfm.2013.560.

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Анотація:
AbstractPrevious studies have shown that the formation of coherent vortex rings in the near-wake of a self-propelled vehicle can increase propulsive efficiency compared with a steady jet wake. The present study utilizes a self-propelled vehicle to explore the dependence of propulsive efficiency on the vortex ring characteristics. The maximum propulsive efficiency was observed to occur when vortex rings were formed of the largest physical size, just before the leading vortex ring would pinch off from its trailing jet. These experiments demonstrate the importance of vortex ring pinch off in self-propelled vehicles, where coflow modifies the vortex dynamics.
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5

Meng, Yu-shan, Zhong-wei Wang, Wei Huang, Yao-bin Niu, and Li Yan. "Coupled fluid–thermal analysis of the reduction mechanism for the drag and heat flux induced by jet interaction in a hypersonic reusable launch vehicle." AIP Advances 12, no. 10 (October 1, 2022): 105124. http://dx.doi.org/10.1063/5.0124608.

Повний текст джерела
Анотація:
The analysis of heat transfer is crucial to hypersonic vehicles that operate under high pressure and aerodynamic heat flux due to severe aero-heating. The jet concept has been applied to reduce drag and increase thermal protection. In this paper, a flow control mechanism introduced through a jet strategy equipped on the blending area with a freestream Mach number of 6 is analyzed numerically. The thermal response of the hypersonic vehicle is numerically investigated with a three-dimensional fluid–thermal coupling approach based on a loosely coupled fluid–thermal analysis. The results indicate that, throughout the coupling process, the reduced temperature growth inside the structure contributes to lowered fluid temperature gradient, thus depressing external aerodynamic heating and gradually decreasing the rate of variation in heat flux as a consequence. The calculations focus on the influence of drag reduction on the aerodynamic characteristics of the hypersonic vehicle, and the thermal protection effects of different methods are compared. The study finds that manipulating the shock structure through jet interaction is practical and promising for alleviating high flight resistance and severe aero-heating, and the jet strategy is an advantageous means of reducing drag and thermal protection for the blending area. A maximum 2.22% increase in lift coefficient and 1.98% decrease in drag coefficient are obtained, and the lift-to-drag ratio of the vehicle is improved by 4.23% with the porous jet strategy. Moreover, this strategy remarkably reduces overall heat flux to less than 108 kW/m2 along the characteristic centerline of the jet orifices.
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6

Abbas, Mohammad, and David W. Riggins. "Analysis of Energy Utilization and Losses for Jet-Propelled Vehicles." Aerospace 8, no. 11 (November 12, 2021): 342. http://dx.doi.org/10.3390/aerospace8110342.

Повний текст джерела
Анотація:
The global control volume-based energy utilization balance for an aerospace vehicle is extended to allow for the analysis of jet-propelled vehicles. The methodology is first developed for analyzing the energy utilization and entropy generation characteristics of jet engines without airframe considerations. This methodology, when combined with separate energy utilization analysis for an unpowered airframe, allows for the assessment of a powered vehicle. Wake entropy generation for a powered vehicle is shown to be the summation of the wake entropy generation associated with the propulsion system (no airframe) and the unpowered airframe. The fundamental relationship between overall entropy generation and the flight conditions required for maximum range and endurance of a powered vehicle are also derived. Example energy utilization results obtained for a modeled turbojet engine in off-design operation are provided; wake and engine component entropy generation characteristics are directly related to engine operation and flight conditions. This engine model is then integrated with a legacy (twin-engine) Northrop F-5E Tiger II airframe. The overall entropy generation temporal rate for the vehicle is minimized, as predicted by our analysis, at flight conditions corresponding to maximum endurance. For flight conditions corresponding to maximum range, the overall entropy spatial rate is minimized.
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7

Xue, Fei, Yunlong Zhang, Ning Cao, and Liugang Li. "Solving the Moment Amplification Factor of a Lateral Jet by the Unsteady Motion Experimental Method." Applied Sciences 12, no. 16 (August 22, 2022): 8387. http://dx.doi.org/10.3390/app12168387.

Повний текст джерела
Анотація:
In this paper, unsteady motion tests of a lateral jet adjusting an air vehicle’s attitude are carried out. Curves of pitch moment amplification factors (KM) for a lateral jet versus angle of attack (α) are obtained using a wind tunnel free-flight test technique with a jet and data processing method. This new method overcomes the disadvantage of previous experiments that can study only one unsteady characteristic. The free-flight test technique in the proposed method ensures that the test model can be coupled in real-time with multiple parameters (unsteady flow caused by the jet, unsteady air vehicle aerodynamic force, and unsteady air vehicle motion). This approach simulates an actual air vehicle’s complete jet test process and ensures more authentic and reliable test results. In the new data processing method, continuous data curves are fitted to discrete data points, making it easier to convert the angular displacement versus time curve into the pitch moment versus α curve to obtain KM. The results show that when the pressure of the micro high-pressure gas cylinder is 2.0 MPa, KM is below 1, indicating that the lateral jet does not significantly promote the pitching moment. When the gas cylinder pressure is 4.0 MPa and the angle of attack is 5° < |α| < 16°, KM is greater than 1, and the lateral jet promotes the pitching moment. When 16° < |α| < 20°, KM is less than 1, and the lateral jet does not significantly contribute to the pitching moment. It was further found that KM decreases slowly with increasing α. When |α| > 30°, the influence of the jet on the pitching moment nearly disappears.
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8

Sioma, Andrzej, and Wojciech Lepiarz. "Vision Analysis of a Biomimetic Water Vehicle Propeller." Solid State Phenomena 198 (March 2013): 144–49. http://dx.doi.org/10.4028/www.scientific.net/ssp.198.144.

Повний текст джерела
Анотація:
Water and underwater vehicles are driven by propellers. Various models use propellers with 2 to 7 blades with either fixed or controllable pitch. Another known solution are water-jet propellers. Water is sucked from the front of the vehicle and ejected through a nozzle at the rear. A propeller is usually the water pumping component. This paper presents the design of a novel type of water-jet propeller, inspired by the way animals move in the aquatic environment. It discusses the mechanisms of propeller operation and its structural solutions. It also presents theoretical simulation studies and actual studies on a real object, which enabled assessment of the propellers parameters.
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9

Fikri, Hasnul, Wanda Afnison, Wagino Wagino, and Hendra Dani Saputra. "Analisis Penggunaan Variasi Turbo Cyclone Terhadap Performa Kendaraan." JTPVI: Jurnal Teknologi dan Pendidikan Vokasi Indonesia 1, no. 1 (February 13, 2023): 105–18. http://dx.doi.org/10.24036/jtpvi.v1i1.18.

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Анотація:
Penelitian ini dilatar belakangi banyaknya kendaraan dengan usia pakai dan pola perawatan yang tidak rutin yang berakibat turunannya performa dan emisi yang meningkat. Penelitian ini bertujuan untuk mengetahui pengaruh penggunaan Turbo Cyclone terhadap performa kendaraan serta simulasi bentuk aliran udara yang melewati Turbo Cyclone. Peneliti menggunakan variasi berupa Turbo Cyclone merek Jet Ranger dan JSC. Penelitian ini menggunakan metode eksperimen yang dilakukan 3 kali pengujian pada masing – masing variabel, kendaraan yang digunakan yaitu Honda Beat PGM-FI. Variabel penelitian yaitu Turbo Cyclone Jet Ranger dan Turbo Cyclone JSC, performa kendaraan. Hasil penelitian menunjukkan, penggunaan Turbo Cyclone menyebabkan torsi dan daya maksimum berkurang jika. Emisi gas buang menggunakan Turbo Cyclone Jet Ranger dan tanpa Turbo Cyclone. Penggunaan bahan bakar spesifik terbaik dengan memasang Turbo Cyclone JSC. The background of this research is the large number of vehicles with long service life and non-routine maintenance patterns which result in decreased performance and increased emissions. This study aims to determine the effect of using a Turbo Cyclone on vehicle performance and to simulate the shape of the airflow passing through the Turbo Cyclone. The researcher used variations in the form of Turbo Cyclone, Jet Ranger and JSC brands. This study used an experimental method which was tested 3 times on each variable, the vehicle used was the Honda Beat PGM-FI. The research variables are Turbo Cyclone Jet Ranger and Turbo Cyclone JSC, vehicle performance. The results showed that the use of Turbo Cyclone causes maximum torque and power to decrease if. Exhaust emissions use Turbo Cyclone Jet Ranger and without Turbo Cyclone. Best use of specific fuel by installing Turbo Cyclone JSC.
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10

Huang, Jian. "Research on Water Sprays Shielding Device for Transport Vehicle." Applied Mechanics and Materials 707 (December 2014): 317–20. http://dx.doi.org/10.4028/www.scientific.net/amm.707.317.

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Анотація:
Water sprays shielding device for transport vehicle, by use of its own power system and storage devices, make the gases within the air tank filling the water storage tank, and jet out from the small hole of roof-shaped spray tube, by means of cyclone atomizing, to form water sprays wall with shielding effect at the top and around the transport vehicle, In order to eliminate exposure symptoms for transport vehicle in the optical, infrared and radar band, to improve the battlefield viability of transport vehicles.
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Більше джерел

Дисертації з теми "Jet Vehicle"

1

Nyberg, Ludwig. "Thrust Allocation for Jet Driven Surface Vessels." Thesis, KTH, Mekatronik, 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-271905.

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Анотація:
Dynamic positioning systems have been under development since the first implementation in the early 1960s. The purpose of a dynamic position system is to allow for automatic positioning of a vessel when circumstances do not allow for mooring or anchoring. Historically the development has been driven forward by the offshore industry, while in recent years such systems have been found useful in other parts of the maritime industry as well. However, very few options exist today for jet driven vessels. One of the main parts of a dynamic positioning system is the control allocation. The purpose of this part is to allocate desired actuation to available actuators. It is often desirable to do this while considering a secondary objective, often energy consumption. One allocation algorithm option is direct allocation, which is considered to be quite a basic solution. More advanced options exist in the literature but implementations of them are still uncommon. An example of a more advanced option, allowing for better tuning, is using model-based allocators. Formulating the allocation problem as a linear quadratic problem and using a linear quadratic regulator is one viable option that has been proven to work well for non-jet driven vessels. A general vessel model is developed and used for simulating and testing different allocators. Furthermore, a method for transforming the allocated actuation into parameters that can control the jet engine is also proposed. This is a necessary step in order to be able to implement the allocation onto a vessel. Comparing the allocation options based on step responses with and without disturbances shows that the linear quadratic regulator preforms better than the direct allocator in almost every way. However, the main drawback of model-based controllers is the needed knowledge about the system. This is something that is not required for the direct allocator and is worth taking into account.
Dynamiska positioneringssystem har vart under utveckling sedan den första implementeringen i början av 1960-talet. Syftet med ett dynamiskt positioneringssystem är att möjliggöra automatisk positionering av ett fartyg när omständigheterna inte tillåter förtöjning eller förankring. Historiskt har utvecklingen drivits framåt av behovet inom offshoreindustrin, men under senare år har systemen visat sig vara användbara även i andra delar av den marina industrin. Idag finns dock få alternativ anpassade för jetdrivna fartyg. En av huvuddelarna i ett dynamiskt positioneringssystem är kraftallokering. Syftet med denna del är att fördela önskad styrkraft till tillgängliga ställdon. Ofta är det önskvärt att göra detta samtidigt som ett sekundärt mål tas hänsyn till, vanligtvis energiförbrukning. Ett alternativ för kraftallokering är en direkt allokeringsalgoritm, detta är en ganska enkel algoritm. Mer avancerade alternativ finns i litteraturen, men implementerade exempel är fortfarande ovanliga. Ett exempel på ett mer avancerat alternativ, som möjliggör bättre anpassning, är att använda modellbaserade algoritmer. Att formulera allokeringsproblemet som ett linjärt kvadratiskt problem och använda en linjär kvadratisk regulator är ett alternativ som har visat sig fungera bra för icke jetdrivna fartyg. En generell fartygsmodell utvecklas och anvnnds för att simulera och testa de olika allokeringsalgoritmerna. Vidare föreslås en metod för att omvandla den allokerade styrkraften till parametrar som kan styra jetmotorerna. Detta är ett nödvändigt steg för att, i slutändan, kunna implementera styrkrafterna på ett riktigt fartyg. En jämförelse av allokeringsalgoritmer baserade på stegsvar med och utan störningar visar att den linjära kvadratiska regulatorn hanterar de uppsatta testfallen bättre än den direkta allokeraren. Däremot dras den modellbaserade algoritmen med det problemet att omfattande kunskapen krävs angående systemets dynamik. Detta är något som inte krävs för direktallokeraren och är värt att ta hänsyn till.
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2

Bergman, Niklas. "Effects of Mach cruise number on conventional civil jet aircraft sizing." Thesis, Mälardalen University, School of Innovation, Design and Engineering, 2009. http://urn.kb.se/resolve?urn=urn:nbn:se:mdh:diva-7450.

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Анотація:

This thesis work was executed at Swift Engineering Incorporated located in San Clemente, California during spring in 2009. Placement supervisor from Swift was Mark Page and advisor and examiner from the Division of future products at Mälardalen University, Sweden was Gustaf Enebog.

The objective with this thesis work was to examine the effects of fitness ratio, lift over drag, lift coefficient at cruise, winglet span, wing sweep angle, wing aspect ratio, wing area and weights with respect to Mach number for a conventional business jet capable of 18 passengers. The cruise speed study range from Mach 0.88 to 0.99.

The Excel based conceptual design tool Jetsizer 2008c was used to make four models with similar configuration and mission but with different cruise Mach numbers.

A new Jetsizer module was then created to handle a modification process where the models are optimized for their speed and configuration. The result in this report gives guidelines for the needed values when creating an initial CFD model for this type of airplane.

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3

Schumacher, Viking Alex. "Jet Stream Velocity fromAzipod on Stadsgården : A Litterature Study of PIANC W.G. 180Application for Stadsgården." Thesis, KTH, Marina system, 2018. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-243091.

Повний текст джерела
Анотація:
The ferry line company VIKING LINE has put in an order for a new vessel with a planned delivery for the year 2020. The vessel will berth and depart daily from the Stockholm port, Stadsgården. The vessel is equipped with two 10 MW Azipod propeller systems. This new propulsion system has the capability of rotating the direction of the propeller thrust 360° which is different from other vessels currently using the same port. The direction and distance of the propeller from the quay has raised concern at the Ports of Stockholm. The integrity and design of the quay wall at Stadsgården is to be related to the guidelines set in place by the World Association for Waterborne Transport Infrastructure (PIANC) Working Group 180: “Guidelines for Protecting Berthing Structures from Scour Caused by Ships.” The guidelines have been compared to the actuator disc theory in order to validate the initial jet stream velocity from the new propeller system. The propagation of the jet stream was later analyzed and a velocity at the quay wall is calculated. A lack of information from certain parameters in the guidelines has led to implementations of assumptions. Uncertainties in the methods and equations presented by the guidelines are discussed. Overall, the guidelines were applicable in the investigation of the new vessel at Stadsgården. The jet stream velocity from the new vessel is compared to the velocity from a similar vessel currently using the same berthing structure. From the comparison it is seen that the berthing structure will be exposed to velocities four times larger than the current jet stream velocities at Stadsgården. A list with recommended action that can be performed by the Ports of Stockholm is presented.
Fartygsföretaget VIKING LINE har beställt ett nytt fartyg med planerad leverans år 2020. Fartyget kommer att trafikera dagligen från Stockholm hamnen, Stadsgården. Fartyget är utrustat med två 10 MW Azipod propeller system. Detta nya framdrivningssystem har förmågan att rotera riktningen för propellern 360° vilket skiljer sig från andra fartyg som för närvarande använder samma hamn. Propeller riktning och avstånd från kajen har uppmärksammats hos Stockholms Hamnar. Stabiliteten av kajväggen på Stadsgården ska relateras till de riktlinjer som fastställs av PIANC Arbetsgrupp 180: "Guidelines for Protecting Berthing Structures from Scour Caused by Ships." Riktlinjerna har jämförts med ’actuator disc theory’ för att validera den ursprungliga jetströmhastigheten från den nya propellern. Spridningen av strålströmmen analyserades senare och en hastighet vid kajväggen beräknas. Brist på information från vissa parametrar i riktlinjerna har lett till implementeringar av antaganden. Osäkerheter i de metoder och ekvationer som presenteras i riktlinjerna diskuteras. Jetströmshastigheten från det nya fartyget jämförs med hastigheten från ett liknande fartyg som för närvarande utnyttjar samma hamn. Från jämförelsen framgår det att kajfronten kommer att exponeras för hastigheter fyra gånger större än de nuvarande jetströmshastigheterna på Stadsgården. En lista med rekommenderad åtgärd som kan utföras av Stockholms Hamnar presenteras.
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4

Fung, Pearl Haiyan. "Flow control over a micro unmanned aerial vehicle using synthetic jet actuators." Thesis, Georgia Institute of Technology, 2001. http://hdl.handle.net/1853/16950.

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5

Ohanian, Osgar John. "Ducted Fan Aerodynamics and Modeling, with Applications of Steady and Synthetic Jet Flow Control." Diss., Virginia Tech, 2011. http://hdl.handle.net/10919/27687.

Повний текст джерела
Анотація:
Ducted fan vehicles possess a superior ability to maximize payload capacity while minimizing vehicle size. Their ability to both hover and fly at high speed is a key advantage for information-gathering missions, particularly when close proximity to a target is essential. However, the ducted fanâ s aerodynamic characteristics pose difficulties for stable vehicle flight and therefore require complex control algorithms. In particular, they exhibit a large nose-up pitching moment during wind gusts and when transitioning from hover to forward flight. Understanding ducted fan aerodynamic behavior and how it can be altered through flow control techniques are the two prime objectives of this work. This dissertation provides a new paradigm for modeling the ducted fanâ s nonlinear behavior and new methods for changing the duct aerodynamics using active flow control. Steady and piezoelectric synthetic jet blowing are employed in the flow control concepts and are compared. The new aerodynamic model captures the nonlinear characteristics of the force, moment, and power data for a ducted fan, while representing these terms in a set of simple equations. The model attains excellent agreement with current and legacy experimental data using twelve non-dimensional constants. Synthetic jet actuators (SJA) have potential for use in flow control applications in UAVs with limited size, weight, and power budgets. Piezoelectric SJAs for a ducted fan vehicle were developed through two rounds of experimental designs. The final SJA design attained peak jet velocities in the range of 225 ft/sec (69 m/s) for a 0.03â x 0.80â rectangular slot. To reduce the magnitude of the nose-up pitching moment in cross-winds, two flow control concepts were explored: flow separation control at the duct lip, and flow turning at the duct trailing edge using a CoandÄ surface. Both concepts were experimentally proven to be successful. Synthetic jets and steady jets were capable of modifying the ducted fan flow to reduce pitching moment, but some cases required high values of steady blowing to create significant responses. Triggering leading edge separation on the duct lip was one application where synthetic jets showed comparable performance to steady jets operating at a blowing coefficient an order of magnitude higher.
Ph. D.
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6

Wemming, Hannes. "Validation and integration of a rubber engine model into an MDO environment." Thesis, Linköpings universitet, Fluid och mekanisk systemteknik, 2010. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-61028.

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Анотація:
Multidisciplinary design optimization (MDO) is a technique that has found use in the field of aerospace engineering for aircraft design. It uses optimization to simultaneously solve design problems with several disciplines involved. In order to predict aircraft performance an engine performance simulation model, also called “rubber engine”, is vital. The goal of this project is to validate and integrate a rubber engine model into an MDO environment. A method for computer simulation of gas turbine aero engine performance was created. GasTurb v11, a commercial gas turbine performance simulation software, was selected for doing the simulation models. The method was validated by applying it to five different jet engines of different size, different type and different age. It was shown that the simulation engine model results are close to the engine manufacturer data in terms of SFC and net thrust during cruise, maximum climb (MCL) and take off (MTO) thrust ratings. The cruise, take off and climb SFC was in general predicted within 2% error when compared to engine manufacturer performance data. The take off and climb net thrust was in general predicted with less than 5% error. The integration of the rubber engine model with the MDO framework was started and it was demonstrated that the model can run within the MDO software. Four different jet engine models have been prepared for use within the optimization software. The main conclusion is that GasTurb v11 can be used to make accurate jet engine performance simulation models and that it is possible to incorporate these models into an MDO environment.
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7

Kiran, Amit. "Jet noise : aeroacoustic distribution of a subsonic co-axial jet." Thesis, University of Warwick, 2008. http://wrap.warwick.ac.uk/3914/.

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Анотація:
The noise generated by aircraft can be easily heard by those living under the flight path of passenger or cargo carriers. It is considered an environmental pollutant and is treated as such by the International Civil Aviation Organization (ICAO) who monitor and review noise levels. The ICAO imposes substantial fines on those carriers who do not adhere to the decibel limitations. With the new limit or `stage' enforced in 2006, aircraft manufacturers (including jet engine manufacturers) are seeking ways to reduce the noise created by an aircraft. A 1/150th scale model, based on the exit geometry typically found on commercial jet engines, was designed and manufactured at Warwick. The laboratory jet flow conditions operated at 0.7 Mach. The work presented in this thesis looks at the noise generated in a subsonic, co- owing jet, with particular focus given to the distribution sound sources from 5 kHz to 80 kHz (0.375 St to 6.0 St). An acoustic mirror mounted on a motorized 3-way traverse measured radiated sound in the co-flowing jet to produce 2D sound source maps. This is done using combinations of smooth cowl and chevrons for the core and bypass nozzles. For frequencies less than 30 kHz, a reduction of noise was observed using the bypass chevron nozzle compared with the bypass smooth cowl nozzle. Laser Doppler Anemometry (LDA) was used to reveal the 2D flow dynamics of the jet, supporting the acoustic distribution results with velocity profiles of the flow. The change in the flow dynamics with different nozzle combinations is discussed and different regions of the flow were identified.
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8

Muse, Jonathan Adam. "An H-Infinity norm minimization approach for adaptive control." Diss., Georgia Institute of Technology, 2010. http://hdl.handle.net/1853/34830.

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This dissertation seeks to merge the ideas from robust control theory such as H-Infinity control design and the Small Gain Theorem, L stability theory and Lyapunov stability from nonlinear control, and recent theoretical achievements in adaptive control. The fusion of frequency domain and linear time domain ideas allows the derivation of an H-Infinity Norm Minimization Approach (H-Infinity-NMA) for adaptive control architecture that permits a control designer to simplify the adaptive tuning process and tune the uncertainty compensation characteristics via linear control design techniques, band limit the adaptive control signal, efficiently handle redundant actuators, and handle unmatched uncertainty and matched uncertainty in a single design framework. The two stage design framework is similar to that used in robust control, but without sacrificing performance. The first stage of the design considers an ideal system with the system uncertainty completely known. For this system, a control law is designed using linear H-Infinity theory. Then in the second stage, an adaptive process is implemented that emulates the behavior of the ideal system. If the linear H-Infinity design is applied to control the emulated system, it then guarantees closed loop system stability of the actual system. All of this is accomplished while providing notions of transient performance bounds between the ideal system and the true system. Extensions to the theory include architectures for a class of output feedback systems, limiting the authority of an adaptive control system, and a method for improving the performance of an adaptive system with slow dynamics without any modification terms. Applications focus on using aerodynamic flow control for aircraft flight control and the Crew Launch Vehicle.
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9

Luo, Xinfu. "Plasma based jet actuators for flow control." Thesis, University of Southampton, 2012. https://eprints.soton.ac.uk/348870/.

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A set of plasma based jet actuators were designed for flow control applications. The characteristics of these actuators and their flow control applications were studied experimentally in a low speed wind tunnel. A dielectric barrier discharge (DBD) based jet actuator is designed, which is made of a covered cavity with two spanwise aligned parallel slots. Two-component particle image velocimetry (PIV) measurements were conducted to determine the effect of actuator in quiescent air and on a canonical zero pressure gradient turbulent boundary layer. It was found that the designed plasma jet actuator produced a transverse jet similar to a continuously blowing jet but with no mass addition into the flow field. The device is different from a traditional alternative blowing-and-suction synthetic jet as the current jet is continuously blown. As such, the DBD based jet actuator is different from either a mass injection blowing jet actuator or a traditional diaphragm based synthetic jet actuator. The impact of the actuation with the designed actuator on the boundary layer characteristics was investigated in detail at different Reynolds numbers. Circular cylinder wake flow control using a newly designed five-electrode plasma jet actuator is also presented in this thesis. This plasma actuator configuration mounted on the cylinder model can easily produce either a downward or upward jet into the flow around the circular cylinder by simply adjusting the same five electrodes’ electrical circuits. The experiments were performed at Reynolds numbers from 7,000 to 24,000. Wake profile measurements were made to evaluate the modification to the mean and fluctuation velocities in the cylinder wake. The results shown that the cylinder wake flow and the turbulence levels in the wake were modified under the actuations, sectional drag reduction and drag increment were obtained by different actuator actuation directions. The study suggested that this new designed five-electrode actuator can be applied to practical separation suppression or enhancement control by adjusting the plasma actuator electric circuits conveniently.
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10

McLaughlin, Philip. "A contribution to the jet noise installation problem." Thesis, University of Southampton, 2010. https://eprints.soton.ac.uk/190205/.

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The main objective of this thesis is to understand and predict jet noise installation effects for engines mounted below aircraft wings. This is done through a variety of empirical, analytical and computational methods. Aspects of the jet source are examined and a jet source model, suitable for determining installation effects is derived. As part of this research programme a novel and extensive set of model scale jet noise installation effects experiments were undertaken. These results are presented and analyzed in this thesis. A new semi-empirical method, which can readily predict installation effects for heated coaxial jets is presented and validated using experimental data. A new 3D ray theory jet propagation method for sources in a steady inhomogeneous moving medium is presented. This method is benched marked using an analytical solution of the Lilley equation. The 3-D method is further enhanced by combing it with realistic CFD jet velocity profiles, and bench marked using the data from the experimental programme
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Книги з теми "Jet Vehicle"

1

Corporation, Intertec Publishing, ed. Personal water vehicle service manual. Overland Park, KS: Intertec Pub. Corp., 1988.

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2

Davis, Mark C. In-flight wing pressure distributions for the NASA F/A-18A High Alpha Research Vehicle. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 2000.

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3

International, Symposium on the Aerodynamics and Ventilation of Vehicle Tunnels (6th 1988 Durham England). Papers presented at the 6th International Symposium on the Aerodynamics and Ventilation of Vehicle Tunnels, Durham, UK: 27-29 September, 1988. Bedford: BHRA, 1988.

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4

W, Pahle Joseph, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., eds. Thrust vectoring on the NASA F-18 high alpha research vehicle. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1996.

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5

W, Pahle Joseph, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., eds. Thrust vectoring on the NASA F-18 high alpha research vehicle. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1996.

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6

United States. National Aeronautics and Space Administration., ed. A vehicle health monitoring system for the space shuttle reaction control system during reentry. Cambridge, Mass: Charles Stark Draper Laboratory, 1995.

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7

Freudinger, Lawrence C. Flutter clearance of the F-18 high-angle-of-attack research vehicle with experimental wingtip instrumentation pods. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1989.

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8

Iliff, Kenneth W. Flight-determined, subsonic, lateral-directional stability and control derivatives of the thrust-vectoring F-18 high angle of attack research vehicle (HARV), and comparisons to the basic F-18 and predicted derivatives. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 1999.

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9

Iliff, Kenneth W. Flight-determined subsonic longitudinal stability and control derivatives of the F-18 High Angle of Attack Research Vehicle (HARV) with thrust vectoring. Edwards, Calif: NASA, Dryden Flight Research Center, 1997.

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10

Iliff, Kenneth W. Flight-determined subsonic longitudinal stability and control derivatives of the F-18 High Angle of Attack Research Vehicle (HARV) with thrust vectoring. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 1997.

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Частини книг з теми "Jet Vehicle"

1

Yin, Yankai, Feng Duan, and Fei Kang. "Design and Control of Penta-Jet Aerial Vehicle." In Intelligent Robotics and Applications, 760–70. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-89134-3_69.

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2

Abdullah, Mahir Faris, Humam Kareem Jalghaf, and Rozli Zulkifli. "A Critical Review of Multiple Impingement Jet Mechanisms for Flow Characteristics and Heat Transfer Augmentation." In Vehicle and Automotive Engineering 4, 374–93. Cham: Springer International Publishing, 2022. http://dx.doi.org/10.1007/978-3-031-15211-5_32.

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3

Liu, Yuwei, Zheng Chen, and Yaofeng Liu. "Numerical Investigation of RCS Jet Interaction on a Hypersonic Vehicle." In Lecture Notes in Electrical Engineering, 485–98. Singapore: Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-3305-7_40.

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4

Caunii, Vasile, and Adrian Sachelarie. "Simulation of the Air Conditioning Curtains with Turbulent Circular Jet Flows Inside the Cabin Vehicle Using ANSYS CFD." In Proceedings of the European Automotive Congress EAEC-ESFA 2015, 357–66. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-27276-4_33.

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5

Lahaussois, Dorothee, Heather Hamje, Per Hanarp, Laura Lonza, Yugo Marta, and Heiko Maas. "Fueling clean transport to 2025+: update of JEC Well-To-Wheel (WTW) methodology for comparing alternative fuels and vehicle options to 2025+." In Proceedings, 385–93. Wiesbaden: Springer Fachmedien Wiesbaden, 2018. http://dx.doi.org/10.1007/978-3-658-21015-1_25.

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6

Guo, Shuxiang, and Xichuan Li. "Development of a Vectored Water-Jet-Based Spherical Underwater Vehicle." In Autonomous Underwater Vehicles. InTech, 2011. http://dx.doi.org/10.5772/24087.

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7

Mehta, Rakhab. "Analysis of supersonic free jets and impinging supersonic jets on deflector." In Simulation Modeling - Recent Advances, New Perspectives, and Applications [Working Title]. IntechOpen, 2023. http://dx.doi.org/10.5772/intechopen.1002372.

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The computational fluid dynamics analysis is carried out to analyze the shock and flow characteristics of under- and over expanded supersonic free jets emanating from convergent-divergent nozzles. Influence of exit Mach number on shock cell lengths are analyzed with the help of density contours and schlieren images. A parameter based on an exit Mach number is obtained to characterize the pressure variation along the jet axis which shows them independent of the exit to ambient pressure ratio. Impingement flow fields over axisymmetric and wedge deflector are investigated employing numerically and compared with experimental results. Effects of jet expansion ratio and distance between the nozzle to deflector apex has been studied at various expansion ratios and distances. Impingement load is computed at various conditions. Pressure distributions over a surface of wedge and axisymmetric jet deflector are computed and compared between them. Pressure load on a diaphragm of a solid motor during lift-off of a satellite launch vehicle having four liquid engines is numerically simulated.
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8

Odetti, Angelo, Marco Altosole, Marco Bibuli, Gabriele Bruzzone, Massimo Caccia, and Michele Viviani. "Advance Speed-Hull-Pump-Jet Interactions in Small ASV." In Progress in Marine Science and Technology. IOS Press, 2020. http://dx.doi.org/10.3233/pmst200043.

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This paper is related to the technological development of an innovative small-size Autonomous Surface Vehicle designed to meet the requirement of accessing, monitoring and protecting the shallow waters peculiar of the Wetlands. The first prototype of a fully electric, modular, portable, lightweight, and highly-controllable Autonomous Surface Vehicle (ASV) for extremely shallow water and remote areas, namely SWAMP, was developed by CNR-INM and DITEN-Unige. This catamaran is equipped with four azimuth Pump-Jet Modular (PJM) actuators designed for small-size (1 to 1.5 m long) ASV. The main advantage of Pump-Jet thrusters is that they are flush with the hull, thus minimizing the risks of damages due to possible grounding. This system is used to increase the manoeuvrability in narrow spaces and to increase the spacial resolution by allowing the access also in extremely shallow waters with smaller risk of loosing manoeuvrability. The knowledge of the hydrodynamic characteristics of the thruster and of the vessel allows to partly or fully identifying the vessel for a better controllability. With this aim a series of tests have been conducted in the DITEN towing tank. In particular advance resistance on the SWAMP hull in deep and shallow water, bollard pull and self-propelling tests with the Pump-Jet Module working have been carried out. The results of the tests with the effects of advance speed on the PJM performance is reported in this paper together with the description of the modelling of the thruster itself.
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9

Suzuki, Toshiyuki, Satoshi Nonaka, and Yoshifumi Inatani. "Numerical Analysis of Supersonic Jet Flow from Vertical Landing Rocket Vehicle in Landing Phase." In Parallel Computational Fluid Dynamics 2006, 253–60. Elsevier, 2007. http://dx.doi.org/10.1016/b978-044453035-6/50034-1.

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10

Ali Mergheni, Mohamed, Mohamed Mahdi Belhajbrahim, Toufik Boushaki, and Jean-Charles Sautet. "A New Combustion Method in a Burner with Three Separate Jets." In Numerical and Experimental Studies on Combustion Engines and Vehicles. IntechOpen, 2020. http://dx.doi.org/10.5772/intechopen.90571.

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Oxy-flames from burners with separated jets present attractive perspectives because the separation of reactants generates a better thermal efficiency and reduction of pollutant emissions. The principal idea is to confine the fuel jet by oxygen jets to favor the mixing in order to improve the flame stability. This chapter concerns the effect of equivalence ratio on characteristics of a non-premixed oxy-methane flame from a burner with separated jets. The burner of 25 kW power is composed with three aligned jets, one central methane jet surrounded by two oxygen jets. The numerical simulation is carried out using Reynolds Average Navier-Stokes (RANS) technique with k-ε as a turbulence closure model. The eddy dissipation model is applied to take into account the turbulence-reaction interactions. The study is performed with different global equivalence ratios (0.7, 0.8 and 1). The validation of the numerical tools is done by comparison with experimental data of the stoichiometric regime (Ф = 1). The two lean regimes of Ф = 0.7 and 0.8 are investigated only by calculations. The velocity fields with different equivalence ratio are presented. It yields to increase of longitudinal and transverse velocity, promotes the fluctuation in interaction zone between fuel and oxygen also a better mixing quality and a decrease of the size of the recirculation zone.
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Тези доповідей конференцій з теми "Jet Vehicle"

1

Huh, Jinbum, and Seungsoo Lee. "Numerical Study on Jet Interaction of Flight Vehicle with Multi-Species Jet." In 2018 AIAA Aerospace Sciences Meeting. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-1270.

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2

Holmes, Christopher, William S. Brocklesby, Christopher Wood, Jeremy G. Frey, Peter G. R. Smith, Senta L. Jantzen, Naruo Yoshikawa, et al. "Mapping Water Contamination of Jet Fuel." In 2019 IEEE Avionics and Vehicle Fiber-Optics and Photonics Conference (AVFOP). IEEE, 2019. http://dx.doi.org/10.1109/avfop.2019.8908177.

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3

Gee, Kent L., Seiji Tsutsumi, Janice Houston, and Alan T. Wall. "Summary of “Acoustics of Supersonic Jets: Launch Vehicle and Military Jet Acoustics”." In 172nd Meeting of the Acoustical Society of America. Acoustical Society of America, 2016. http://dx.doi.org/10.1121/2.0000448.

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4

Lee, SangWook. "Vehicle Aerodynamic Drag Reduction Using Air Jet System." In ASME 2017 Conference on Information Storage and Processing Systems collocated with the ASME 2017 International Technical Conference and Exhibition on Packaging and Integration of Electronic and Photonic Microsystems. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/isps2017-5442.

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Study on the air jet wheel deflector system using state-of-the-art of Computational Fluid Dynamics (CFD) technique based on an open domain CFD software (OpenFOAM) is performed to reduce vehicle aerodynamic drag. Fabijanic’s simple vehicle model [1] is used for both the mesh sensitivity study and validation of current CFD technique. It was found that CFD method used in this study is reliable tool for the forecasting of the aerodynamic drag coefficient. Parametric studies were conducted to investigate aerodynamic effects of the conventional wheel deflector and air jet wheel deflector system. For the conventional wheel deflector, 3.6% of drag reduction was achieved with a non-dimensional deflector height of 1/6, but the drag force tends to increase as the non-dimensional height increased. On the other hand, it was shown that air jet wheel deflector system can reduce vehicle aerodynamic drag up to 7.5% at the non-dimensional air jet velocity of 1.0. Therefore it would be concluded that air jet wheel deflector is a useful device to reduce aerodynamic drag of automobile.
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5

Nichols, J., Ali Moslemi, and Paul Krueger. "Performance of a Self-Propelled Pulsed-Jet Vehicle." In 38th Fluid Dynamics Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-3720.

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6

Bartow, William Bradford, Andres C. Moreyra, Trevor Hirst, Gregory H. Woyczynski, Alexis Lefebvre, and Gecheng Zha. "Experimental Investigations of Vehicle Base Drag Reduction Using Passive Jet Boat-Tail Flow Control." In SAE 2014 Commercial Vehicle Engineering Congress. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 2014. http://dx.doi.org/10.4271/2014-01-2448.

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7

Gutman, Shaul. "Nose Jet Guidance and Control for Exoatmospheric Kill-Vehicle." In AIAA Guidance, Navigation, and Control Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2011. http://dx.doi.org/10.2514/6.2011-6568.

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8

Huang, Shuling, Yuru Xu, Yongjie Pang, Tiedong Zhang, and Gongxing Wu. "Maneuvering simulation for water-jet propulsion unmanned surface vehicle." In 2011 6th IEEE Conference on Industrial Electronics and Applications (ICIEA). IEEE, 2011. http://dx.doi.org/10.1109/iciea.2011.5975876.

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9

Suzuki, Toshiyuki, Satoshi Nonaka, and Yoshifumi Inatani. "Computations of Opposing Jet from Vertical Landing Rocket Vehicle." In 24th AIAA Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.2006-3329.

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10

Boretti, Alberto. "Direct Injection and Spark Controlled Jet Ignition to Convert A Diesel Truck Engine to LPG." In SAE 2010 Commercial Vehicle Engineering Congress. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 2010. http://dx.doi.org/10.4271/2010-01-1976.

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Звіти організацій з теми "Jet Vehicle"

1

Robinson, P., and J. McDougal. Effect of JP-8 Vehicle on Dermal Penetration of Hydrocarbon Components from Jet Fuel. Fort Belvoir, VA: Defense Technical Information Center, March 2000. http://dx.doi.org/10.21236/ada453171.

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