直升机飞行力学 Helicopter dynamics chapter 6
•Download as PPT, PDF•
1 like•1,105 views
The document discusses various methods for modeling and analyzing 3D incompressible flows, including: 1. Lifting surface theory which extends lifting line theory to model low aspect ratio wings by placing multiple lifting lines on the wing. 2. The vortex lattice method for numerically solving lifting surface theory using a discrete number of horseshoe vortices on the wing. 3. Modeling a 3D source/sink and doublet and using them to represent flow over a sphere. 4. General panel methods which cover a 3D body with source/vortex panels and apply flow tangency to solve for the unknown flow distributions. Challenges include properly distributing panels over complex geometries.
Report
Share
Report
Share
![Outline ,[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],Chapter 5](data:image/gif;base64,R0lGODlhAQABAIAAAAAAAP///yH5BAEAAAAALAAAAAABAAEAAAIBRAA7)
Recommended
直升机飞行力学 Helicopter dynamics chapter 1
This document provides an introduction to helicopter flight dynamics, including:
- Definitions of helicopter flight dynamics, characteristics of helicopter flight, and scopes and methodologies used.
- Coordinate systems used including gravity, body, wind, and hub axes.
- Transformations between different coordinate systems.
- Angles used to describe helicopter orientation and motion, including Euler angles.
- Prerequisites, syllabus, and references for further study are also included.
Helicopter rotor blade design process
The document discusses the design process of helicopter rotor blades. It covers the structural loads on rotor blades, available materials for manufacturing, examples of materials used in existing helicopter blades, and design considerations. Composite materials are now commonly used instead of metals due to advantages in strength, stiffness, corrosion resistance, and reduced fatigue cracking allowing for unlimited operational lifetimes. The rotor blade design process requires analyzing loads, material selection, aerodynamics, and costs while meeting regulatory requirements.
Aerodynamics of a_rotary_wing_type_aircraft
This document provides an overview of basic aerodynamic concepts related to rotary wing aircraft, including definitions of key rotorcraft components and terminology. It describes principles such as lift, drag, torque, dissymmetry of lift, and retreating blade stall. Key concepts covered include how rotor blades generate lift via angle of attack and airspeed, how flapping helps compensate for differences in advancing and retreating blade lift, and factors that influence helicopter performance such as ground effect and density altitude.
Flight controls translift
The document discusses the major flight controls of a helicopter - collective pitch control, cyclic pitch control, and antitorque pedals. The collective pitch control adjusts the pitch of all main rotor blades simultaneously to control altitude. The cyclic pitch control tilts the main rotor disk to control horizontal movement. The antitorque pedals control the pitch of the tail rotor blades to counteract torque from the main rotor. Throttle or a governor system maintains a constant main rotor RPM as collective pitch is adjusted.
Aerodynamics aeronautics and flight mechanics
The document discusses the history of aeronautics and provides an overview of key topics in aerodynamics and aircraft performance. It begins with a brief summary of the Wright Brothers' first controlled, powered flight on December 17, 1903. The document then outlines several chapters that will cover topics like fluid mechanics, lift generation, drag, high-speed aerodynamics, thrust production, aircraft performance, stability and control. It provides the table of contents to guide the discussion of aeronautical science concepts.
Aerodinamica helicoptero
This document provides an overview of helicopter aerodynamics, covering key topics such as relative wind, induced flow, angle of attack, lift and drag forces, airflow during hover, dissymmetry of lift, retreating blade stall, compressibility, settling with power, offset hinges, and dynamic rollover. It includes diagrams and explanations of each concept, as well as the causes, indications, and corrective actions for issues like retreating blade stall and compressibility. The goal is to give students a simplified but applied understanding of helicopter aerodynamic characteristics and how they relate to one another.
Lesson 2 basic aerodynamics
The document provides an overview of basic aerodynamics and principles of helicopter flight. It discusses the four forces acting on a helicopter - lift, weight, thrust, and drag. It explains airfoils, including their camber, angle of attack, and pitch angle. It describes how the venturi effect and Bernoulli's principle relate to lift and drag on an airfoil. The key factors that determine lift are explained as the coefficient of lift, air density, airfoil velocity, and surface area in the lift equation.
Po f lo5 p1
The document discusses principles of flight for rotary wing aircraft, specifically focusing on propellers. It defines key terms like blade angle and angle of attack. It explains the aerodynamic forces acting on propeller blades, including lift, drag, thrust, and rotational drag. It also discusses how fixed and variable pitch propellers are affected by changes in airspeed, and factors that can cause take-off swings for nose-wheel and tail-wheel aircraft.
Recommended
直升机飞行力学 Helicopter dynamics chapter 1
This document provides an introduction to helicopter flight dynamics, including:
- Definitions of helicopter flight dynamics, characteristics of helicopter flight, and scopes and methodologies used.
- Coordinate systems used including gravity, body, wind, and hub axes.
- Transformations between different coordinate systems.
- Angles used to describe helicopter orientation and motion, including Euler angles.
- Prerequisites, syllabus, and references for further study are also included.
Helicopter rotor blade design process
The document discusses the design process of helicopter rotor blades. It covers the structural loads on rotor blades, available materials for manufacturing, examples of materials used in existing helicopter blades, and design considerations. Composite materials are now commonly used instead of metals due to advantages in strength, stiffness, corrosion resistance, and reduced fatigue cracking allowing for unlimited operational lifetimes. The rotor blade design process requires analyzing loads, material selection, aerodynamics, and costs while meeting regulatory requirements.
Aerodynamics of a_rotary_wing_type_aircraft
This document provides an overview of basic aerodynamic concepts related to rotary wing aircraft, including definitions of key rotorcraft components and terminology. It describes principles such as lift, drag, torque, dissymmetry of lift, and retreating blade stall. Key concepts covered include how rotor blades generate lift via angle of attack and airspeed, how flapping helps compensate for differences in advancing and retreating blade lift, and factors that influence helicopter performance such as ground effect and density altitude.
Flight controls translift
The document discusses the major flight controls of a helicopter - collective pitch control, cyclic pitch control, and antitorque pedals. The collective pitch control adjusts the pitch of all main rotor blades simultaneously to control altitude. The cyclic pitch control tilts the main rotor disk to control horizontal movement. The antitorque pedals control the pitch of the tail rotor blades to counteract torque from the main rotor. Throttle or a governor system maintains a constant main rotor RPM as collective pitch is adjusted.
Aerodynamics aeronautics and flight mechanics
The document discusses the history of aeronautics and provides an overview of key topics in aerodynamics and aircraft performance. It begins with a brief summary of the Wright Brothers' first controlled, powered flight on December 17, 1903. The document then outlines several chapters that will cover topics like fluid mechanics, lift generation, drag, high-speed aerodynamics, thrust production, aircraft performance, stability and control. It provides the table of contents to guide the discussion of aeronautical science concepts.
Aerodinamica helicoptero
This document provides an overview of helicopter aerodynamics, covering key topics such as relative wind, induced flow, angle of attack, lift and drag forces, airflow during hover, dissymmetry of lift, retreating blade stall, compressibility, settling with power, offset hinges, and dynamic rollover. It includes diagrams and explanations of each concept, as well as the causes, indications, and corrective actions for issues like retreating blade stall and compressibility. The goal is to give students a simplified but applied understanding of helicopter aerodynamic characteristics and how they relate to one another.
Lesson 2 basic aerodynamics
The document provides an overview of basic aerodynamics and principles of helicopter flight. It discusses the four forces acting on a helicopter - lift, weight, thrust, and drag. It explains airfoils, including their camber, angle of attack, and pitch angle. It describes how the venturi effect and Bernoulli's principle relate to lift and drag on an airfoil. The key factors that determine lift are explained as the coefficient of lift, air density, airfoil velocity, and surface area in the lift equation.
Po f lo5 p1
The document discusses principles of flight for rotary wing aircraft, specifically focusing on propellers. It defines key terms like blade angle and angle of attack. It explains the aerodynamic forces acting on propeller blades, including lift, drag, thrust, and rotational drag. It also discusses how fixed and variable pitch propellers are affected by changes in airspeed, and factors that can cause take-off swings for nose-wheel and tail-wheel aircraft.
Basic Info regarding making a RC aeroplane
The document provides information on the control surfaces and aerodynamic components of an aircraft. It discusses that elevators control pitch, ailerons control roll, and the rudder controls yaw. It also mentions vertical and horizontal stabilizers provide stability and prevent pitching and yawing motions. The document further provides details on requirements, wing design and construction, airfoils, servos, engines, batteries, and tips for stability.
Aircraft basics
This document provides an overview of aircraft basics including:
- The main components of an aircraft including wings, empennage, landing gear, and power plants. Wings can be high-wing, mid-wing, or low-wing and include ailerons and flaps. The empennage includes vertical and horizontal stabilizers with rudders and elevators.
- The four main forces acting on an aircraft during flight: lift, thrust, weight, and drag. Bernoulli's equation is presented relating to lift.
- Primary flight controls including ailerons, elevators, rudders, and various tail configurations. Pitch, yaw, and V-tail are also explained.
- Secondary flight controls
Basic aerodynamics
This document provides an overview of basic aerodynamic principles and aircraft flight theory. It covers key topics such as the atmosphere, Newton's laws of motion, Bernoulli's principle, airfoils, the four forces of flight, stability and control surfaces. The presentation introduces fundamental concepts including pressure, density, humidity, inertia, lift, drag, thrust, weight, angles of attack and incidence, and the three axes of movement. It also explains how stability is achieved through aircraft design elements like dihedral wings, sweepback, and keel effect.
Aviation basic no background
This document discusses the primary flight controls of aircraft:
1. The elevator controls pitch around the lateral axis using upward and downward deflection. Larger aircraft use hydraulic or electric systems.
2. The rudder controls yaw around the normal axis and is operated by rudder pedals, which also control steering while taxiing. Some aircraft with V-tails use linked ruddervator surfaces.
3. Ailerons control roll around the longitudinal axis and work differentially to bank the aircraft, sometimes assisted by differential rudder inputs to coordinate the turn. Some light aircraft use flaperons.
Aerodynamics of ahelicopter_pp
The document summarizes the aerodynamics of helicopters. It describes how helicopters generate lift through rotating wings and discusses key concepts like torque. It also analyzes airfoil shapes, pressure distributions, and how different airfoil designs impact lift and drag properties. Additionally, the summary defines important rotor system components and terminology used in helicopter aerodynamics.
Aerodynamic theories
This document discusses various aerodynamic theories and concepts including definitions of force and aerodynamic force. It describes fundamental sources of aerodynamic force such as pressure distribution and shear stress. It also covers types of flows, Bernoulli's theorem, flat plate effect, and steady, two-dimensional, and three-dimensional flows. The document examines different types of forces including contact, frictional, tensional, gravitational, electrical, and magnetic forces. It discusses balanced and unbalanced forces as well as vector representation of forces.
Flight basics
1) The document provides an overview of flight basics, including the four forces of flight (lift, weight, thrust, drag), Newton's laws of motion, Bernoulli's principle, airfoils, parts of an airplane, stability, and control.
2) It explains concepts such as angles of attack and incidence, how wings generate lift, the role of thrust and drag, and the three axes of movement for an aircraft.
3) The document discusses different types of stability, including static and dynamic stability, and how control surfaces like ailerons, elevators, and rudders are used to control an airplane's movement around each axis.
Why airplanes fly aerodynamics
The document presents information on the aerodynamics of airplanes. It discusses the four main forces of flight - weight, lift, thrust, and drag. It explains that the motion of the airplane depends on the balance of these forces. It also provides details on how lift is generated, discussing Newton's laws of motion, Bernoulli's principle, air velocity and pressure differences, and how the wing shape contributes to creating lift. The document uses diagrams to illustrate these concepts.
EASA PART-66 MODULE 8.2 : AERODYNAMICS
Slide for student who want to take EASA part66 exam
Other note you can get at
http://part66.blogspot.com
Flight Basics
The document summarizes the four main forces that act on an aircraft in flight - lift, thrust, gravity, and drag. It explains how lift is generated by the wing's airfoil shape and angle of attack, how thrust provides forward momentum, how drag creates resistance, and how gravity affects G-forces. It also describes the primary control surfaces - ailerons, elevators, rudder, and flaps - and how they control the aircraft's roll, pitch, and yaw.
EASA PART 66 MODULE 5.1 : ELECTRONIC INSTRUMENT SYSTEMS
Slide for student who want to take EASA part66 exam
Other note you can get at
http://part66.blogspot.com
1 Evolution And Type Of Structures
The document summarizes the evolution of aircraft structures from early designs using wooden ribs and fabric to modern aluminum and composite designs. It describes key structural components such as those that produce lift (wings, airfoils), control (elevators, ailerons, rudders), modify lift (flaps, slats), and hold other components. Early aircraft had open wooden frameworks and fabric coverings while later warplanes used metal tubing and stressed skin construction. Modern jets widely use semi-monocoque construction.
ppt 1
This document analyzes the aerodynamic performance of three different wing configurations for unmanned air vehicles (UAVs) using computational fluid dynamics (CFD). The three wings analyzed are a hybrid wing, joined wing, and tailless wing. CFD simulations were run at varying Mach numbers and angles of attack. Results show the tailless wing generates the lowest vortices and has the highest lift-to-drag ratio and stall angle, indicating it provides the best aerodynamic performance of the three wings analyzed for UAV applications.
Basics of airplanes
Nomenclature and classification of controls in an airplane (slide # 3-4).
Which are the aerodynamic forces acting on airplane (slide # 5).
Working principle of an airplane (slide # 6).
How an airplane flies (basic motions of an airplane) (slide # 7).
How controls play their roles in these motions (slide # 8-22).
Simulate a flight in Cessna Skyhawk (slide # 23-28).
References and Questions & answers (slide # 30).
Introduction to flight 1
The document provides an overview of an introductory aeronautics course, including:
- Course details like instructor, textbook, term work and exams
- Topics covered across two terms like history of flight, aerodynamics, airfoils, and aircraft performance and stability
- A brief history of the development of flight from early attempts to imitate birds to modern airplanes
- Descriptions of key aircraft components like the fuselage, wings, tail assembly, landing gear, and power plants
CFD analysis of aerofoil
1) The document discusses a study and CFD analysis of an aerofoil at different angles of attack. It outlines the inputs and boundary conditions used in the CFD model including the velocity, temperature, pressure, and turbulence model.
2) The methodology section describes how the aerofoil model was created in CAD software and meshed. The solver settings applied in the CFD analysis are also outlined.
3) The results and discussion section analyzes the static pressure contours on the aerofoil surface at different angles of attack from 0° to 22.5°. It is observed that lift increases with angle of attack until 20°, beyond which stall may occur.
Assy Rigging
The document discusses rigging specifications and procedures for aircraft assembly and flight control systems. It provides details on:
1) Aligning and leveling the fuselage, wings, empennage and other components during assembly according to manufacturer specifications.
2) Installing and rigging the aileron, elevator, rudder and other flight control systems, including adjusting cable tension and travel to manufacturer standards.
3) Checking control surface movements and aircraft symmetry after assembly and making adjustments as needed.
Principles of flight
This document provides an overview of principles of flight, including subsonic, transonic, and supersonic aerodynamics. It discusses properties of fluids, aerodynamic forces, airfoil theory, and airplane performance. A key topic is transonic aerodynamics, explaining how shock waves form as local airflow exceeds the speed of sound. This leads to sudden increases in drag, loss of lift, and control issues. Solutions like supercritical wing sections can raise the critical Mach number and widen the safe speed range.
Autorotations
Autorotation is the process by which a helicopter can descend and land without engine power by using the airflow coming up from the ground or air during descent to turn the rotor blades and maintain control. During autorotation, the helicopter trades altitude for the energy required to spin the rotor blades at a speed that provides enough lift to control the aircraft. The pilot lowers the collective to reduce blade drag and tilt the total aerodynamic force vector forward to maintain rotor RPM as the helicopter descends.
直升机飞行力学 Helicopter dynamics chapter 3
The document discusses rotor flapping motion in helicopters. It covers three key topics:
1) The equation of rotor flapping motion and three origins of flapping motion: forward speed, controls, and angular velocity.
2) Factors that affect flapping motion, including hinge offset, hub moments, and whether the rotor is hinged or hingeless.
3) How the pilot controls the helicopter through inducing flapping motion by changing blade pitch via the controls.
Helicopter Simulation
This document outlines the development of a helicopter flight simulator in Matlab/Simulink. It discusses (1) the equations of motion for modeling a rotorcraft's attitude and position using Newton's laws of motion and forces/moments. (2) Stability and control theory using a states vector to model aerodynamic forces from changes in states using stability derivatives for forces, moments, speeds and angular speeds. (3) The simulation model using a controls/states vector and linear differential equations. It then details the (4) Simulink schematic, (5) 6 degree of freedom Simulink model, and (6) including cockpit instruments and controls to evaluate (7) helicopter performance.
直升机飞行力学 Helicopter dynamics chapter 2
The document summarizes helicopter flight controllers, including the external forces acting on helicopters, different control manners, and the development of helicopter controllers. It describes the aerodynamic forces on the main rotor, tail rotor, fuselage, horizontal and vertical tails. It then explains the control manners of helicopters with main and tail rotors, twin rotor helicopters, and tilt-rotor aircraft. Finally, it discusses early direct control methods and the progression to modern fly-by-wire and fly-by-light control systems.
More Related Content
What's hot
Basic Info regarding making a RC aeroplane
The document provides information on the control surfaces and aerodynamic components of an aircraft. It discusses that elevators control pitch, ailerons control roll, and the rudder controls yaw. It also mentions vertical and horizontal stabilizers provide stability and prevent pitching and yawing motions. The document further provides details on requirements, wing design and construction, airfoils, servos, engines, batteries, and tips for stability.
Aircraft basics
This document provides an overview of aircraft basics including:
- The main components of an aircraft including wings, empennage, landing gear, and power plants. Wings can be high-wing, mid-wing, or low-wing and include ailerons and flaps. The empennage includes vertical and horizontal stabilizers with rudders and elevators.
- The four main forces acting on an aircraft during flight: lift, thrust, weight, and drag. Bernoulli's equation is presented relating to lift.
- Primary flight controls including ailerons, elevators, rudders, and various tail configurations. Pitch, yaw, and V-tail are also explained.
- Secondary flight controls
Basic aerodynamics
This document provides an overview of basic aerodynamic principles and aircraft flight theory. It covers key topics such as the atmosphere, Newton's laws of motion, Bernoulli's principle, airfoils, the four forces of flight, stability and control surfaces. The presentation introduces fundamental concepts including pressure, density, humidity, inertia, lift, drag, thrust, weight, angles of attack and incidence, and the three axes of movement. It also explains how stability is achieved through aircraft design elements like dihedral wings, sweepback, and keel effect.
Aviation basic no background
This document discusses the primary flight controls of aircraft:
1. The elevator controls pitch around the lateral axis using upward and downward deflection. Larger aircraft use hydraulic or electric systems.
2. The rudder controls yaw around the normal axis and is operated by rudder pedals, which also control steering while taxiing. Some aircraft with V-tails use linked ruddervator surfaces.
3. Ailerons control roll around the longitudinal axis and work differentially to bank the aircraft, sometimes assisted by differential rudder inputs to coordinate the turn. Some light aircraft use flaperons.
Aerodynamics of ahelicopter_pp
The document summarizes the aerodynamics of helicopters. It describes how helicopters generate lift through rotating wings and discusses key concepts like torque. It also analyzes airfoil shapes, pressure distributions, and how different airfoil designs impact lift and drag properties. Additionally, the summary defines important rotor system components and terminology used in helicopter aerodynamics.
Aerodynamic theories
This document discusses various aerodynamic theories and concepts including definitions of force and aerodynamic force. It describes fundamental sources of aerodynamic force such as pressure distribution and shear stress. It also covers types of flows, Bernoulli's theorem, flat plate effect, and steady, two-dimensional, and three-dimensional flows. The document examines different types of forces including contact, frictional, tensional, gravitational, electrical, and magnetic forces. It discusses balanced and unbalanced forces as well as vector representation of forces.
Flight basics
1) The document provides an overview of flight basics, including the four forces of flight (lift, weight, thrust, drag), Newton's laws of motion, Bernoulli's principle, airfoils, parts of an airplane, stability, and control.
2) It explains concepts such as angles of attack and incidence, how wings generate lift, the role of thrust and drag, and the three axes of movement for an aircraft.
3) The document discusses different types of stability, including static and dynamic stability, and how control surfaces like ailerons, elevators, and rudders are used to control an airplane's movement around each axis.
Why airplanes fly aerodynamics
The document presents information on the aerodynamics of airplanes. It discusses the four main forces of flight - weight, lift, thrust, and drag. It explains that the motion of the airplane depends on the balance of these forces. It also provides details on how lift is generated, discussing Newton's laws of motion, Bernoulli's principle, air velocity and pressure differences, and how the wing shape contributes to creating lift. The document uses diagrams to illustrate these concepts.
EASA PART-66 MODULE 8.2 : AERODYNAMICS
Slide for student who want to take EASA part66 exam
Other note you can get at
http://part66.blogspot.com
Flight Basics
The document summarizes the four main forces that act on an aircraft in flight - lift, thrust, gravity, and drag. It explains how lift is generated by the wing's airfoil shape and angle of attack, how thrust provides forward momentum, how drag creates resistance, and how gravity affects G-forces. It also describes the primary control surfaces - ailerons, elevators, rudder, and flaps - and how they control the aircraft's roll, pitch, and yaw.
EASA PART 66 MODULE 5.1 : ELECTRONIC INSTRUMENT SYSTEMS
Slide for student who want to take EASA part66 exam
Other note you can get at
http://part66.blogspot.com
1 Evolution And Type Of Structures
The document summarizes the evolution of aircraft structures from early designs using wooden ribs and fabric to modern aluminum and composite designs. It describes key structural components such as those that produce lift (wings, airfoils), control (elevators, ailerons, rudders), modify lift (flaps, slats), and hold other components. Early aircraft had open wooden frameworks and fabric coverings while later warplanes used metal tubing and stressed skin construction. Modern jets widely use semi-monocoque construction.
ppt 1
This document analyzes the aerodynamic performance of three different wing configurations for unmanned air vehicles (UAVs) using computational fluid dynamics (CFD). The three wings analyzed are a hybrid wing, joined wing, and tailless wing. CFD simulations were run at varying Mach numbers and angles of attack. Results show the tailless wing generates the lowest vortices and has the highest lift-to-drag ratio and stall angle, indicating it provides the best aerodynamic performance of the three wings analyzed for UAV applications.
Basics of airplanes
Nomenclature and classification of controls in an airplane (slide # 3-4).
Which are the aerodynamic forces acting on airplane (slide # 5).
Working principle of an airplane (slide # 6).
How an airplane flies (basic motions of an airplane) (slide # 7).
How controls play their roles in these motions (slide # 8-22).
Simulate a flight in Cessna Skyhawk (slide # 23-28).
References and Questions & answers (slide # 30).
Introduction to flight 1
The document provides an overview of an introductory aeronautics course, including:
- Course details like instructor, textbook, term work and exams
- Topics covered across two terms like history of flight, aerodynamics, airfoils, and aircraft performance and stability
- A brief history of the development of flight from early attempts to imitate birds to modern airplanes
- Descriptions of key aircraft components like the fuselage, wings, tail assembly, landing gear, and power plants
CFD analysis of aerofoil
1) The document discusses a study and CFD analysis of an aerofoil at different angles of attack. It outlines the inputs and boundary conditions used in the CFD model including the velocity, temperature, pressure, and turbulence model.
2) The methodology section describes how the aerofoil model was created in CAD software and meshed. The solver settings applied in the CFD analysis are also outlined.
3) The results and discussion section analyzes the static pressure contours on the aerofoil surface at different angles of attack from 0° to 22.5°. It is observed that lift increases with angle of attack until 20°, beyond which stall may occur.
Assy Rigging
The document discusses rigging specifications and procedures for aircraft assembly and flight control systems. It provides details on:
1) Aligning and leveling the fuselage, wings, empennage and other components during assembly according to manufacturer specifications.
2) Installing and rigging the aileron, elevator, rudder and other flight control systems, including adjusting cable tension and travel to manufacturer standards.
3) Checking control surface movements and aircraft symmetry after assembly and making adjustments as needed.
Principles of flight
This document provides an overview of principles of flight, including subsonic, transonic, and supersonic aerodynamics. It discusses properties of fluids, aerodynamic forces, airfoil theory, and airplane performance. A key topic is transonic aerodynamics, explaining how shock waves form as local airflow exceeds the speed of sound. This leads to sudden increases in drag, loss of lift, and control issues. Solutions like supercritical wing sections can raise the critical Mach number and widen the safe speed range.
Autorotations
Autorotation is the process by which a helicopter can descend and land without engine power by using the airflow coming up from the ground or air during descent to turn the rotor blades and maintain control. During autorotation, the helicopter trades altitude for the energy required to spin the rotor blades at a speed that provides enough lift to control the aircraft. The pilot lowers the collective to reduce blade drag and tilt the total aerodynamic force vector forward to maintain rotor RPM as the helicopter descends.
What's hot (19)
EASA PART 66 MODULE 5.1 : ELECTRONIC INSTRUMENT SYSTEMS
EASA PART 66 MODULE 5.1 : ELECTRONIC INSTRUMENT SYSTEMS
Viewers also liked
直升机飞行力学 Helicopter dynamics chapter 3
The document discusses rotor flapping motion in helicopters. It covers three key topics:
1) The equation of rotor flapping motion and three origins of flapping motion: forward speed, controls, and angular velocity.
2) Factors that affect flapping motion, including hinge offset, hub moments, and whether the rotor is hinged or hingeless.
3) How the pilot controls the helicopter through inducing flapping motion by changing blade pitch via the controls.
Helicopter Simulation
This document outlines the development of a helicopter flight simulator in Matlab/Simulink. It discusses (1) the equations of motion for modeling a rotorcraft's attitude and position using Newton's laws of motion and forces/moments. (2) Stability and control theory using a states vector to model aerodynamic forces from changes in states using stability derivatives for forces, moments, speeds and angular speeds. (3) The simulation model using a controls/states vector and linear differential equations. It then details the (4) Simulink schematic, (5) 6 degree of freedom Simulink model, and (6) including cockpit instruments and controls to evaluate (7) helicopter performance.
直升机飞行力学 Helicopter dynamics chapter 2
The document summarizes helicopter flight controllers, including the external forces acting on helicopters, different control manners, and the development of helicopter controllers. It describes the aerodynamic forces on the main rotor, tail rotor, fuselage, horizontal and vertical tails. It then explains the control manners of helicopters with main and tail rotors, twin rotor helicopters, and tilt-rotor aircraft. Finally, it discusses early direct control methods and the progression to modern fly-by-wire and fly-by-light control systems.
3DoF Helicopter Trim , Deceleration manouver simulation, Stability
This document describes trim calculations for a helicopter's longitudinal 3 degree-of-freedom model at varying forward flight speeds using two different methods: the TU Delft method and Bramwell's method. For each method, the document provides the algorithms, implementation in C++ code to generate trim data, and plots of the results. The TU Delft method iteratively calculates collective pitch and longitudinal cyclic pitch, while Bramwell's method directly calculates these values based on thrust and force coefficients. Source code is included for both trim calculation programs.
Helicopter rotor dynamics
This document contains a student's answers to questions regarding helicopter performance, stability, and control. The student analyzed flapping blade angle, angle of attack, coning angle, and disc tilt angles for a helicopter blade over one revolution. Equations were derived for blade angular velocities, the flapping equation when the helicopter has body rates, and aerodynamic moment about the flapping hinge. Diagrams of flapping blade angle and angle of attack variation over azimuth angle were included.
Helicopter moment of inertia
This document provides calculations to determine the moment of inertia (IYY) of an MBB Bo105 helicopter. The helicopter is broken down into six main components: main rotor, tail rotor, fuel tank, engines, fuselage, and tail boom. The mass and geometry of each component is estimated, and the parallel axis theorem is used to calculate the individual IYY contribution of each. By summing the contributions, the total IYY of the helicopter is calculated to be 3827 kgm2, with a total mass of 2200 kg. This value is compared to a published IYY value of 4973 kgm2, with potential sources of error discussed.
Helicopter structure
This document outlines the course details and topics for a 18-week rotorcraft systems, maintenance, and role equipment class at the Malaysian Institute of Aviation Technology. The course will cover 10 topics related to helicopter structure and maintenance, and will evaluate students based on assignments, quizzes, and a final exam. Students who miss more than 10% of classes will be barred from the final exam. The document then provides details on helicopter structural design, including tubular, stressed skin, and bonded construction methods, as well as the stresses and loads placed on helicopter structures.
Aerodynamic Data of Space Vehicles
This document provides an overview and summary of aerodynamic data for various space vehicles. It begins with a preface describing the history and development of understanding planetary motion from a geocentric to heliocentric model. It then presents aerodynamic data for several types of space vehicles, including capsules, probes, winged vehicles, and airbreathing hypersonic vehicles. The data includes configurational details, coefficients of steady and unsteady aerodynamic forces, and other technical specifications. The intent is to provide graduate students and engineers with reference aerodynamic information to support new space vehicle design projects.
Automatic control of aircraft and missiles 2nd ed john h. blakelock
This document is the preface to the second edition of the book "Automatic Control of Aircraft and Missiles" by John H. Blakelock. The preface outlines the changes and additions made to the material in the second edition, including expanded coverage of topics like missile guidance systems, multivariable control systems, and modeling of human pilots. It also thanks those who provided assistance in preparing the second edition.
Viewers also liked (9)
3DoF Helicopter Trim , Deceleration manouver simulation, Stability
3DoF Helicopter Trim , Deceleration manouver simulation, Stability
Automatic control of aircraft and missiles 2nd ed john h. blakelock
Automatic control of aircraft and missiles 2nd ed john h. blakelock
Similar to 直升机飞行力学 Helicopter dynamics chapter 6
K12020 VARUN RAC PPT
This document outlines concepts in three-dimensional fluid flow, including:
1) Lifting surface theory which extends lifting line theory to low aspect ratio wings by placing lifting lines across the wing surface.
2) The vortex lattice method which superimposes horseshoe vortices on the wing to obtain equations relating vortex strengths that satisfy flow tangency.
3) A three-dimensional source defined as a flow with radial streamlines emanating from a point, and a doublet defined as a sink and source of equal strength.
4) Flow over a sphere is analyzed using a uniform flow and doublet, finding two stagnation points and that maximum surface velocity is less than over a cylinder, demonstrating three
Marinello_ProjectReport.pdf
This document summarizes the Hess-Smith panel method for analyzing aerodynamic forces on airfoils. It begins with background on aerodynamics and the different types of air flow. It then describes the 2D Hess-Smith panel method, which involves discretizing an airfoil shape into panels and calculating source strengths to model the air flow. The document provides the theoretical equations for calculating velocity potential and solving for source strengths. It concludes by explaining the Python code used to implement the 2D source panel method on a NACA 0010 airfoil.
Three-dimensional Streamline Design of the Pump Flow Passage of Hydrodynamic...
The design methods of three-element, centripetal turbine hydrodynamic torque converters
were investigated. A new design method, three-dimensional streamline design method, was proposed.
Firstly, the three-dimensional central streamline of the flow passage was designed and the streamline
consists of a circular arc and a short straight line segment. After that, the central streamline equation was
obtained and the design path equation was derived. Next, any other meridional flow path can numerically be
obtained. Finally, the three-dimensional streamline corresponding to any meridional flow path was
computed numerically. Investigation results show that the proposed method is feasible and possesses
obvious advantages. First, the curvature radius of the three-dimensional central streamline remains
unchanged, while any other three-dimensional streamline is close to a circular arc as well. Therefore, the
energy losses caused by streamline bending can be reduced. Second, because the fluid particle near the flow
passage outlet flows in a straight line law and the energy losses due to flow deviation can be reduced. Third,
all the three-dimensional streamlines are theoretically located in an identical plane. Thereby energy losses
caused by the turbulence can be reduced. Fourth, because of the flat blades, the manufacture cost of a torque
converter can be reduced.
Fluid machinery hydraulic turbines i
Classification of Hydraulic Turbines
Turbines that use water as the working fluid
for the production of power are known as
hydraulic turbines.
Main categories are impulse and reaction
turbines (based on the interaction of the
fluid on the blades)
Can further be classified on the basis of
head available at the inlet, specific speed, and
according to flow direction
1. Action of water on the runner (the rotating element of
turbine)—impulse and reaction
2. Direction of flow—tangential flow, radial flow, axial flow, and
mixed (radial + axial) flow
3. Available head—high head (H > 300 m), medium head (50 m
< H < 300 m), and low head (H < 50 m)
4. Specific speed is the speed of geometrically similar turbine
which produces unit power when operated under unit head—
low, medium, and high specific speed turbines
Heads and Efficiencies
Two types of heads as far as turbines
are concerned—gross head and net
head.
Gross head indicates the difference in
head and tail race levels.
Net head is the actual head available at
the turbine inlet and is computed as
gross head minus frictional losses in the
penstock
Power system stability 3.pptx
- The document discusses the equal-area criterion, which is used to determine power system stability under transient conditions without solving swing equations. It involves analyzing the areas on a power-angle diagram before, during, and after a fault.
- The criterion states that for a system to be stable, the acceleration and deceleration area curves must be equal. This allows calculation of critical clearing times and angles for faults.
- Examples are provided to demonstrate calculating critical clearing times and angles using the equal-area criterion for different fault scenarios like three-phase faults on transmission lines.
Theory of Turbomachines aaaaaaaaaaaa.ppt
The one-dimensional theory of turbomachines makes simplifying assumptions to analyze the complex three-dimensional flow through an impeller. It assumes blades are infinitely thin and the flow is frictionless with no variation in the meridional plane or across blade passages. This reduces the flow to changes between the inlet and outlet, treating the space between as a "black box". Velocity triangles are used to relate absolute, relative and tangential velocities at the inlet and outlet. Euler's turbine equation equates the change in fluid kinetic and potential energy to the work done or power produced. It is applied to analyze centrifugal pumps and turbines by resolving velocities into tangential and radial components.
B012620814
1) The document analyzes the interaction forces between two non-identical cylinders spinning around their stationary and parallel axes in an ideal fluid.
2) It derives the exact equations for the velocity field of the fluid using Laplace's equation and the boundary conditions.
3) It then determines the pressure field from the velocity field using Bernoulli's equation and integrates the pressure around the cylinder surfaces to find the forces acting on their axes.
B012620814
1) The document analyzes the interaction forces between two non-identical cylinders spinning around their stationary and parallel axes in an ideal fluid.
2) It derives the exact equations for the velocity field of the fluid using Laplace's equation and the boundary conditions.
3) It then determines the pressure field from the velocity field using Bernoulli's equation and integrates the pressure around the cylinder surfaces to find the forces acting on their axes.
4) It finds that the cylinders will repel or attract each other in inverse relation to their separation distance, depending on whether their directions of rotation are similar or opposite.
The Interaction Forces between Two non-Identical Cylinders Spinning around th...
This paper derives the equations that describe the interaction forcesbetween two non-identical
cylinders spinningaround their stationary and parallel axes in a fluid that isassumed to be in-viscous, steady, invortical,
and in-compressible. The paper starts by deriving the velocity field from Laplace equation,governing
this problem,and the system boundary conditions. It then determines the pressure field from the velocity field
using Bernoulli equation. Finally, the paper integrates the pressure around both cylinder-surface to find the
force acting on their axes.All equations and derivationsprovided in this paper are exact solutions. No numerical
analysesor approximations are used.The paper finds that such cylinders repel or attract each other in inverse
relation with separation between their axes, according to similar or opposite direction of rotation, respectively.
Physics details
This document provides information on the Honda CB 500E motorcycle from 1998-2000, including its engine specifications, dimensions, performance characteristics, and other technical details. Some key specifications include:
- Liquid cooled parallel twin cylinder 499cc engine producing 58 hp
- 6-speed transmission and chain drive
- 37mm telescopic forks and twin shock rear suspension
- Disc brakes front and rear
- 17-inch wheels
- 173 kg dry weight
- 18-liter fuel capacity
CFD Final Report-2
This project analyzed subsonic flow over a blended wing body (BWB) aircraft model based on Lockheed Martin's X-56A/MUTT using computational fluid dynamics (CFD). Aerodynamic coefficients were obtained for angles of attack of 0, 5, and 10 degrees. The CFD analysis found lift-to-drag ratios up to 14.61 and low drag coefficients, validating the aerodynamic efficiency of BWB designs. Skin friction and pressure drag breakdowns showed drag contributions varied reasonably with angle of attack. Results provide validation data for stability augmentation system design for a tailless BWB configuration.
Conformal Mapping of Rotating Cylinder into Jowkowski Airfoil
To theoretically analyze the effects of Angle of Attack on Pressure Difference on airfoil.
To suggest the best port location on different airfoils, in order to install Pressure Differential Angle of Attack measuring instrument on them
NONLINEAR CONTROL SYSTEM(Phase plane & Phase Trajectory Method).pdf
This document discusses nonlinear control systems using phase plane and phase trajectory methods. It defines nonlinear systems and common physical nonlinearities like saturation, dead zone, relay, and backlash. Phase plane analysis is introduced as a graphical method to study nonlinear systems using a plane with state variables x and dx/dt as coordinates. Key concepts are defined like phase plane, phase trajectory, and phase portrait. Methods for sketching phase trajectories include analytical solutions and graphical methods like isoclines. Examples are given to illustrate phase portraits for different linear systems.
NONLINEAR CONTROL SYSTEM (Phase plane & Phase Trajectory Method)
This document discusses nonlinear control systems using phase plane and phase trajectory methods. It defines nonlinear systems and common physical nonlinearities like saturation, dead zone, relay, and backlash. Phase plane analysis is introduced as a graphical method to study nonlinear systems using a plane with state variables x and dx/dt. Key concepts are defined like phase plane, phase trajectory, and phase portrait. Methods for sketching phase trajectories include analytical solutions and graphical methods using isoclines. Examples are given to illustrate phase portraits for different linear systems.
Aeroelasticity
This 3 sentence summary provides the high level information from the document:
The document discusses simulations of a 2D aerofoil model conducted using MATLAB to analyze wing divergence and flutter. Three simulations were conducted - a 2 degree of freedom model without C(k), a 2 degree model with C(k), and a 3 degree model with a trailing edge flap. The results found that flutter was avoided without C(k) but present with C(k), and flutter was present throughout the 3 degree of freedom model with the trailing edge flap.
09_chapter4SPACEVECTORPULSEWIDTHMODULATION.pdf
This document discusses space vector pulse width modulation (SVPWM) techniques for multilevel inverters. It begins by introducing SVPWM and explaining that it provides advantages over sinusoidal PWM, including better fundamental output voltage and improved harmonic performance. It then defines two-dimensional and three-dimensional space vectors and discusses how SVPWM can be implemented in both 2D and 3D. The document focuses on SVPWM for three-leg voltage source inverters, describing the voltage space vectors and how SVPWM can be used to synthesize the required output voltage vector through PWM of the switching state vectors.
Transient flow analysis for horizontal axial upper-wind turbine
This study is to carry out a transient flow field analysis on the condition that the wind turbine is working to generate turbine, the wind turbine operating conditions change over time, Purpose of this study is try to find out the rule from the wind turbine changing over time . In transient analysis, the wind velocity on inlet boundary and rotation speed in the rotor field will change over time, and an analytical process is provided that can be used for future reference. At present, the wind turbine model is designed on the concept of upwind horizontal axis type. The computer engineering software GH Bladed is used to obtain the relationship between the rotor velocity and the wind turbine. Then the ANSYS engineering software is used to calculate the stress and strain distribution in the blades over time. From the analytical result, the relationship between the stress distribution in the blades and the rotor velocity is got to be used as a reference for future wind turbine structural optimization.
Mechanism (engineering)
In engineering, a mechanism is a device that transforms input forces and movement into a desired set of output forces and movement. Mechanisms generally consist of moving components that can include:
Gears and gear trains
Belt and chain drives
Cam and followers
Linkage
Friction devices, such as brakes and clutches
Structural components such as a frame, fasteners, bearings, springs, lubricants
Various machine elements, such as splines, pins, and keys.
The German scientist Reuleaux provides the definition "a machine is a combination of resistant bodies so arranged that by their means the mechanical forces of nature can be compelled to do work accompanied by certain determinate motion." In this context, his use of machine is generally interpreted to mean mechanism.
The combination of force and movement defines power, and a mechanism manages power to achieve a desired set of forces and movement.
A mechanism is usually a piece of a larger process or mechanical system. Sometimes an entire machine may be referred to as a mechanism. Examples are the steering mechanism in a car, or the winding mechanism of a wristwatch. Multiple mechanisms are machines.
Fluid_Mechanics_6 (1).pdf
The document discusses the momentum equation in fluid mechanics. It defines the momentum equation as relating the sum of forces acting on a fluid element to its rate of change of momentum. Examples are provided to illustrate applications of the momentum equation, including: (1) the force on a pipe bend due to changes in fluid velocity and direction, (2) the force of a perpendicular jet impacting a plane, and (3) the force on a curved vane deflecting a jet. Diagrams and step-by-step calculations are shown for analyzing the forces in each example using the momentum equation.
Similar to 直升机飞行力学 Helicopter dynamics chapter 6 (20)
Three-dimensional Streamline Design of the Pump Flow Passage of Hydrodynamic...
Three-dimensional Streamline Design of the Pump Flow Passage of Hydrodynamic...
The Interaction Forces between Two non-Identical Cylinders Spinning around th...
The Interaction Forces between Two non-Identical Cylinders Spinning around th...
Conformal Mapping of Rotating Cylinder into Jowkowski Airfoil
Conformal Mapping of Rotating Cylinder into Jowkowski Airfoil
NONLINEAR CONTROL SYSTEM(Phase plane & Phase Trajectory Method).pdf
NONLINEAR CONTROL SYSTEM(Phase plane & Phase Trajectory Method).pdf
NONLINEAR CONTROL SYSTEM (Phase plane & Phase Trajectory Method)
NONLINEAR CONTROL SYSTEM (Phase plane & Phase Trajectory Method)
Transient flow analysis for horizontal axial upper-wind turbine
Transient flow analysis for horizontal axial upper-wind turbine
Recently uploaded
Skybuffer AI: Advanced Conversational and Generative AI Solution on SAP Busin...
Skybuffer AI, built on the robust SAP Business Technology Platform (SAP BTP), is the latest and most advanced version of our AI development, reaffirming our commitment to delivering top-tier AI solutions. Skybuffer AI harnesses all the innovative capabilities of the SAP BTP in the AI domain, from Conversational AI to cutting-edge Generative AI and Retrieval-Augmented Generation (RAG). It also helps SAP customers safeguard their investments into SAP Conversational AI and ensure a seamless, one-click transition to SAP Business AI.
With Skybuffer AI, various AI models can be integrated into a single communication channel such as Microsoft Teams. This integration empowers business users with insights drawn from SAP backend systems, enterprise documents, and the expansive knowledge of Generative AI. And the best part of it is that it is all managed through our intuitive no-code Action Server interface, requiring no extensive coding knowledge and making the advanced AI accessible to more users.
Your One-Stop Shop for Python Success: Top 10 US Python Development Providers
Simplify your search for a reliable Python development partner! This list presents the top 10 trusted US providers offering comprehensive Python development services, ensuring your project's success from conception to completion.
A Comprehensive Guide to DeFi Development Services in 2024
DeFi represents a paradigm shift in the financial industry. Instead of relying on traditional, centralized institutions like banks, DeFi leverages blockchain technology to create a decentralized network of financial services. This means that financial transactions can occur directly between parties, without intermediaries, using smart contracts on platforms like Ethereum.
In 2024, we are witnessing an explosion of new DeFi projects and protocols, each pushing the boundaries of what’s possible in finance.
In summary, DeFi in 2024 is not just a trend; it’s a revolution that democratizes finance, enhances security and transparency, and fosters continuous innovation. As we proceed through this presentation, we'll explore the various components and services of DeFi in detail, shedding light on how they are transforming the financial landscape.
At Intelisync, we specialize in providing comprehensive DeFi development services tailored to meet the unique needs of our clients. From smart contract development to dApp creation and security audits, we ensure that your DeFi project is built with innovation, security, and scalability in mind. Trust Intelisync to guide you through the intricate landscape of decentralized finance and unlock the full potential of blockchain technology.
Ready to take your DeFi project to the next level? Partner with Intelisync for expert DeFi development services today!
Fueling AI with Great Data with Airbyte Webinar
This talk will focus on how to collect data from a variety of sources, leveraging this data for RAG and other GenAI use cases, and finally charting your course to productionalization.
Nunit vs XUnit vs MSTest Differences Between These Unit Testing Frameworks.pdf
When it comes to unit testing in the .NET ecosystem, developers have a wide range of options available. Among the most popular choices are NUnit, XUnit, and MSTest. These unit testing frameworks provide essential tools and features to help ensure the quality and reliability of code. However, understanding the differences between these frameworks is crucial for selecting the most suitable one for your projects.
How to Interpret Trends in the Kalyan Rajdhani Mix Chart.pdf
A Mix Chart displays historical data of numbers in a graphical or tabular form. The Kalyan Rajdhani Mix Chart specifically shows the results of a sequence of numbers over different periods.
GraphRAG for Life Science to increase LLM accuracy
GraphRAG for life science domain, where you retriever information from biomedical knowledge graphs using LLMs to increase the accuracy and performance of generated answers
Presentation of the OECD Artificial Intelligence Review of Germany
Consult the full report at https://www.oecd.org/digital/oecd-artificial-intelligence-review-of-germany-609808d6-en.htm
dbms calicut university B. sc Cs 4th sem.pdf
Its a seminar ppt on database management system using sql
HCL Notes und Domino Lizenzkostenreduzierung in der Welt von DLAU
Webinar Recording: https://www.panagenda.com/webinars/hcl-notes-und-domino-lizenzkostenreduzierung-in-der-welt-von-dlau/
DLAU und die Lizenzen nach dem CCB- und CCX-Modell sind für viele in der HCL-Community seit letztem Jahr ein heißes Thema. Als Notes- oder Domino-Kunde haben Sie vielleicht mit unerwartet hohen Benutzerzahlen und Lizenzgebühren zu kämpfen. Sie fragen sich vielleicht, wie diese neue Art der Lizenzierung funktioniert und welchen Nutzen sie Ihnen bringt. Vor allem wollen Sie sicherlich Ihr Budget einhalten und Kosten sparen, wo immer möglich. Das verstehen wir und wir möchten Ihnen dabei helfen!
Wir erklären Ihnen, wie Sie häufige Konfigurationsprobleme lösen können, die dazu führen können, dass mehr Benutzer gezählt werden als nötig, und wie Sie überflüssige oder ungenutzte Konten identifizieren und entfernen können, um Geld zu sparen. Es gibt auch einige Ansätze, die zu unnötigen Ausgaben führen können, z. B. wenn ein Personendokument anstelle eines Mail-Ins für geteilte Mailboxen verwendet wird. Wir zeigen Ihnen solche Fälle und deren Lösungen. Und natürlich erklären wir Ihnen das neue Lizenzmodell.
Nehmen Sie an diesem Webinar teil, bei dem HCL-Ambassador Marc Thomas und Gastredner Franz Walder Ihnen diese neue Welt näherbringen. Es vermittelt Ihnen die Tools und das Know-how, um den Überblick zu bewahren. Sie werden in der Lage sein, Ihre Kosten durch eine optimierte Domino-Konfiguration zu reduzieren und auch in Zukunft gering zu halten.
Diese Themen werden behandelt
- Reduzierung der Lizenzkosten durch Auffinden und Beheben von Fehlkonfigurationen und überflüssigen Konten
- Wie funktionieren CCB- und CCX-Lizenzen wirklich?
- Verstehen des DLAU-Tools und wie man es am besten nutzt
- Tipps für häufige Problembereiche, wie z. B. Team-Postfächer, Funktions-/Testbenutzer usw.
- Praxisbeispiele und Best Practices zum sofortigen Umsetzen
Programming Foundation Models with DSPy - Meetup Slides
Prompting language models is hard, while programming language models is easy. In this talk, I will discuss the state-of-the-art framework DSPy for programming foundation models with its powerful optimizers and runtime constraint system.
Finale of the Year: Apply for Next One!
Presentation for the event called "Finale of the Year: Apply for Next One!" organized by GDSC PJATK
Trusted Execution Environment for Decentralized Process Mining
Presentation of the paper "Trusted Execution Environment for Decentralized Process Mining" given during the CAiSE 2024 Conference in Cyprus on June 7, 2024.
Energy Efficient Video Encoding for Cloud and Edge Computing Instances
Energy Efficient Video Encoding for Cloud and Edge Computing Instances
Choosing The Best AWS Service For Your Website + API.pptx
Have you ever been confused by the myriad of choices offered by AWS for hosting a website or an API?
Lambda, Elastic Beanstalk, Lightsail, Amplify, S3 (and more!) can each host websites + APIs. But which one should we choose?
Which one is cheapest? Which one is fastest? Which one will scale to meet our needs?
Join me in this session as we dive into each AWS hosting service to determine which one is best for your scenario and explain why!
Columbus Data & Analytics Wednesdays - June 2024
Columbus Data & Analytics Wednesdays, June 2024 with Maria Copot 20
Main news related to the CCS TSI 2023 (2023/1695)
An English 🇬🇧 translation of a presentation to the speech I gave about the main changes brought by CCS TSI 2023 at the biggest Czech conference on Communications and signalling systems on Railways, which was held in Clarion Hotel Olomouc from 7th to 9th November 2023 (konferenceszt.cz). Attended by around 500 participants and 200 on-line followers.
The original Czech 🇨🇿 version of the presentation can be found here: https://www.slideshare.net/slideshow/hlavni-novinky-souvisejici-s-ccs-tsi-2023-2023-1695/269688092 .
The videorecording (in Czech) from the presentation is available here: https://youtu.be/WzjJWm4IyPk?si=SImb06tuXGb30BEH .
Recently uploaded (20)
Skybuffer AI: Advanced Conversational and Generative AI Solution on SAP Busin...
Skybuffer AI: Advanced Conversational and Generative AI Solution on SAP Busin...
Your One-Stop Shop for Python Success: Top 10 US Python Development Providers
Your One-Stop Shop for Python Success: Top 10 US Python Development Providers
A Comprehensive Guide to DeFi Development Services in 2024
A Comprehensive Guide to DeFi Development Services in 2024
Nunit vs XUnit vs MSTest Differences Between These Unit Testing Frameworks.pdf
Nunit vs XUnit vs MSTest Differences Between These Unit Testing Frameworks.pdf
How to Interpret Trends in the Kalyan Rajdhani Mix Chart.pdf
How to Interpret Trends in the Kalyan Rajdhani Mix Chart.pdf
GraphRAG for Life Science to increase LLM accuracy
GraphRAG for Life Science to increase LLM accuracy
Presentation of the OECD Artificial Intelligence Review of Germany
Presentation of the OECD Artificial Intelligence Review of Germany
Overcoming the PLG Trap: Lessons from Canva's Head of Sales & Head of EMEA Da...
Overcoming the PLG Trap: Lessons from Canva's Head of Sales & Head of EMEA Da...
HCL Notes und Domino Lizenzkostenreduzierung in der Welt von DLAU
HCL Notes und Domino Lizenzkostenreduzierung in der Welt von DLAU
Programming Foundation Models with DSPy - Meetup Slides
Programming Foundation Models with DSPy - Meetup Slides
Trusted Execution Environment for Decentralized Process Mining
Trusted Execution Environment for Decentralized Process Mining
Energy Efficient Video Encoding for Cloud and Edge Computing Instances
Energy Efficient Video Encoding for Cloud and Edge Computing Instances
Choosing The Best AWS Service For Your Website + API.pptx
Choosing The Best AWS Service For Your Website + API.pptx
直升机飞行力学 Helicopter dynamics chapter 6
- 1. Three-Dimensional Incompressible Flow Yanjie Li Harbin Institute of Technology Shenzhen Graduate School Chapter 6
- 4. Extend a simple lifting line model by placing a series of lifting lines on the plane of the wing. Line Surface
- 5. Downstream of the trailing edge has no spanwise vortex lines and only trailing vortices. The strength of this wake vortex is given by ,which depends only on
- 7. An expression for induced normal velocity in terms of and Consider a point given by the coordinates Spanwise vortex strength is The strength of filament of the spanwise vortex sheet of incremental length is Using Biot-Savart law, the incremental velocity induced at by a segment of this spanwise vortex filament of strength is Considering the direction and (5.78)
- 8. Similarly, the contribution of the elemental chordwise vortex of strength to the induced velocity at is The velocity induced at point by the complete wake vortex can be given by an equation analogous to the above equation Eq. (5.78) and Eq. (5.79) should be Integrated over the wing planform, Region S, Eq. (*) should be integrated over region W , Noting The normal velocity induced at P by both the lifting surface and the wake is (5.79) (*)
- 9. The central problem of lifting-surface theory is to solve the following equation for and 1. Dividing the wing platform into a number of panels and choosing control points on these panels, Eq. (**) results in simultaneous algebraic equations at these control points. Solving these equations, we can obtain the values of and (**) Numerical solution: 2. Vortex lattice method
- 10. Vortex lattice method Superimpose a finite number of horseshoe vortex of different strength on the wing surface At any control point , applying the Biot-Savart law and flow-tangency condition, we can obtain a system of simultaneous algebraic equations, which can be solved for the unknown
- 11. Chapter 6 Three-Dimensional Incompressible Flow
- 13. Eq. (6.2) describes a flow with straight streamlines emanating from the origin. The velocity varies inversely as the square of the distance from the origin Such a flow is defined as a three-dimensional source or called simply a point source To calculate the constant C in Eq. (6.3a) Consider a sphere of radius and surface centered at the origin. Volume flow is defined as the strength of source. a point source is a point sink.
- 14. Three-Dimensional Doublet Consider a sink and source of equal but opposite strength located at point O and A From Eq. (6.7), the velocity potential at P is where . The flow field produced by Eq. (6.9) is a three-dimensional doublet .
- 15. From Eq. (2.18) and Eq. (6.9) The streamline of this velocity field are the same in all the planes. The flow induced by the three dimensional doublet is a series of stream surfaces generated by revolving the streamlines in this figure. The flow is independent of .Such a flow is defined as axisymmetric flow.
- 16. Flow over a Sphere Consider the superposition of a uniform flow and a three-dimensional doublet Spherical coordinates of the freestream Combining the flow of three-dimensional doublet
- 17. To find the stagnation points in the flow. Two stagnation points on Z axis, with coordinates
- 18. The impressible flow over a sphere of radius R (flow-tangency condition) On the surface of the sphere of radius R, the tangential velocity is From Eq. (6.16),
- 19. Maximum tangential velocity for three-D flow is Maximum tangential velocity for two-D flow is , The maximum surface velocity on a sphere is less than that for a cylinder Three-dimensional relieving effect A general phenomenon for all types of three-dimensional flows Two examples: The pressure distribution on the surface of the sphere is The pressure distribution on a cylinder is