This is an introductory for beginners who do not know where to start or how to start, so this comprehensive session states the major types of RC Aircrafts which shall allow you to search deeply in one or all of these categories
This document summarizes the design of a remote controlled aircraft. It discusses selecting a symmetrical airfoil with a NACA0012 profile for its low speed stability. It describes control surfaces like ailerons and elevators. Calculations are shown for wing area based on lift and drag coefficients. A CATIA model and flow simulation were also created. The design focuses on stability concepts like neutral point, center of pressure, and aerodynamic center. References include aerodynamics textbooks and software used like JAVA, Flow Design, and CATIA V5.
Basic Info regarding making a RC aeroplaneZubair Ahmed
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.
This document provides an overview of aircraft wings, including their:
- Historical development from ancient kites to the Wright brothers' fixed-wing aircraft.
- Construction, with internal structures like ribs, spars, stringers, and skin covering the framework. Wings also contain fuel tanks, flaps, and other devices.
- Functions, as wings generate lift through Bernoulli's principle and critical angle of attack. Wing design factors like aspect ratio and camber also affect lift.
- Types based on position (fixed or movable) and structure (cantilever or strut-braced). Stability devices like ailerons and flaps are also described.
- Unconventional designs that
This document provides an overview of aircraft landing gear systems. It describes the main components, including the types of landing gear arrangements (tail wheel, tandem, tricycle), construction details, alignment and retraction mechanisms, nose wheel steering, braking systems, tires, and antiskid systems. The purpose of landing gear is to support the aircraft during landing and taxiing. Retractable gear stows in the fuselage or wings to reduce drag while flying. Nose wheel steering and braking systems provide directional control on the ground. Aircraft tires must withstand high loads and provide traction for takeoff and landing. Antiskid systems help maintain braking effectiveness.
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
This document provides information on different types of aircraft. It discusses the main categories of aircraft as being aerostats and aerodynes, with aerostats being lighter than air and aerodynes being heavier than air. It then describes various types of fixed wing aircraft, including those classified by number of wings (monoplane, biplane, triplane), wing position (low wing, mid wing, high wing), wing shape, tail configuration, and motion. It also discusses aerodynamic forces, control surfaces like flaps, ailerons, and elevators, as well as components like the fuselage and aerofoils. In summary, the document categorizes and describes different types of aircraft based on factors like
This document is an aircraft design project report for a twin engine business jet. It includes dimensions, weight configurations, and performance parameters for 20 existing medium business jets analyzed to determine ideal specifications for the new design. Weight estimation was conducted and various design elements were researched and selected, including a cantilever low wing with tapered airfoils. Performance calculations and graphs were included to analyze the 17-seater twin turbofan jet, which will have a maximum speed of 750mph. The report concludes with future work plans and references.
This document summarizes the design of a remote controlled aircraft. It discusses selecting a symmetrical airfoil with a NACA0012 profile for its low speed stability. It describes control surfaces like ailerons and elevators. Calculations are shown for wing area based on lift and drag coefficients. A CATIA model and flow simulation were also created. The design focuses on stability concepts like neutral point, center of pressure, and aerodynamic center. References include aerodynamics textbooks and software used like JAVA, Flow Design, and CATIA V5.
Basic Info regarding making a RC aeroplaneZubair Ahmed
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.
This document provides an overview of aircraft wings, including their:
- Historical development from ancient kites to the Wright brothers' fixed-wing aircraft.
- Construction, with internal structures like ribs, spars, stringers, and skin covering the framework. Wings also contain fuel tanks, flaps, and other devices.
- Functions, as wings generate lift through Bernoulli's principle and critical angle of attack. Wing design factors like aspect ratio and camber also affect lift.
- Types based on position (fixed or movable) and structure (cantilever or strut-braced). Stability devices like ailerons and flaps are also described.
- Unconventional designs that
This document provides an overview of aircraft landing gear systems. It describes the main components, including the types of landing gear arrangements (tail wheel, tandem, tricycle), construction details, alignment and retraction mechanisms, nose wheel steering, braking systems, tires, and antiskid systems. The purpose of landing gear is to support the aircraft during landing and taxiing. Retractable gear stows in the fuselage or wings to reduce drag while flying. Nose wheel steering and braking systems provide directional control on the ground. Aircraft tires must withstand high loads and provide traction for takeoff and landing. Antiskid systems help maintain braking effectiveness.
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
This document provides information on different types of aircraft. It discusses the main categories of aircraft as being aerostats and aerodynes, with aerostats being lighter than air and aerodynes being heavier than air. It then describes various types of fixed wing aircraft, including those classified by number of wings (monoplane, biplane, triplane), wing position (low wing, mid wing, high wing), wing shape, tail configuration, and motion. It also discusses aerodynamic forces, control surfaces like flaps, ailerons, and elevators, as well as components like the fuselage and aerofoils. In summary, the document categorizes and describes different types of aircraft based on factors like
This document is an aircraft design project report for a twin engine business jet. It includes dimensions, weight configurations, and performance parameters for 20 existing medium business jets analyzed to determine ideal specifications for the new design. Weight estimation was conducted and various design elements were researched and selected, including a cantilever low wing with tapered airfoils. Performance calculations and graphs were included to analyze the 17-seater twin turbofan jet, which will have a maximum speed of 750mph. The report concludes with future work plans and references.
This document describes the design of a fighter aircraft. It discusses the conceptual design phase where the overall shape, size, weight and performance are determined. Comparative studies are conducted on different types of airplanes to select the appropriate configuration. Key parameters like wing type, engine selection and aerodynamic surfaces are analyzed and optimized. Performance calculations are carried out to evaluate the design. Three views and design specifications of the final fighter aircraft are presented.
Gliders are aircraft that are supported in flight through the dynamic reaction of air against their lifting surfaces without an engine. Some gliders have small engines to extend flight or for launching. The Wright Brothers spent years experimenting with gliders to develop efficient airfoils and flight control before attempting powered flight. Modern gliders include sailplanes for recreation, hang gliders that are foot-launched, and almost ready-to-fly models that require minor assembly. Gliders find lift through thermals or slope lift and pilots circle to remain in rising air. Winches are commonly used to launch larger sailplanes a few hundred feet and electric motors now assist some gliders. Efficiency is measured by glide ratio and half the drag
The presentation was prepared for an Technical Paper Presentation competition. It contains basic conceptual explanations pertaining to the BWB concept.
The document summarizes the basic control systems of an aircraft, including primary, secondary, and auxiliary flight controls. Primary controls include elevators, ailerons, and rudders which control pitch, roll, and yaw respectively. Secondary controls include trim tabs which help balance aircraft forces. Auxiliary controls include flaps, spoilers, and slats which provide additional lift, especially at lower speeds. The document describes the purpose and function of each control surface.
This document provides details on the design of a 1-seater military aircraft. It discusses the aircraft's specifications including its weight, performance characteristics, and dimensions of the wing. It also summarizes the structural analysis and material selection for the fuselage and wings. Several chapters describe the preliminary and detailed design of the aircraft's wing, fuselage, and tail section. Load distributions and structural components of each section are analyzed.
THIS PRESENTATION TAKES OVERVIEW OF AIRCRAFT CABIN PRESSURIZATION SYSTEM. IN THIS I EXPLAINED BASIC SYSTEM USED FOR PRESSURIZATION , AND HOW THIS SYSTEM IS SAFE, PRECISE. AND HOW AIR IS KEPT HEALTHY.
Conceptual Design of a Light Sport AircraftDustan Gregory
The document provides a conceptual design for a light sport aircraft. It defines key parameters for light sport aircraft and summarizes the design of several existing models. The design process described initializes parameters like wing area and airfoil selection. Equations are presented to calculate performance metrics like drag, power required, climb rate, endurance and range. Requirements for the conceptual design are specified, including taking off, cruising, and landing with sufficient fuel reserves.
This document discusses the basics of aerodynamics and the forces acting on aircraft in flight. It covers key concepts like:
1. Aerodynamic forces like lift, weight, thrust and drag that act on aircraft in motion through the air based on Newton's Laws of motion.
2. How the shape of airfoils and wings generate lift using Bernoulli's principle and how control surfaces like ailerons, elevators and rudders allow for rolling, pitching and yawing.
3. The different types of drag forces - induced, parasite and wave drag - and how configuration changes and altitude affect aircraft performance.
This document provides an overview of basic aerodynamics and flight controls. It explains the four main forces that act on aircraft - lift, gravity/weight, thrust, and drag. It describes how control surfaces like the ailerons, elevators, and rudder are used to control the aircraft's roll, pitch, and yaw. Finally, it gives a brief tour of common flight instruments that provide information to pilots like airspeed, altitude, heading, and vertical speed. The goal is to help readers understand how aircraft fly and how pilots control and navigate them.
Aircraft can be categorized in three ways: by basic design as either lighter-than-air or heavier-than-air, by propulsion as either power driven or non-power driven, and by wing design as either aeroplanes with fixed wings or rotorcraft with rotary wings. Lighter-than-air aircraft rely on gases for lift while heavier-than-air aircraft use air flowing over wings. Power driven aircraft use engines for propulsion and non-power driven use gravity and aerodynamic forces. Aeroplanes have stationary wings and rotorcraft have rotating wings.
This document provides information about various aircraft instruments including:
- The airspeed indicator which uses ram air from the pitot tube and static air, and displays airspeeds like Vso and Vfe. Blockages of the pitot tube or static vent can cause errors.
- The altimeter which uses only static air input and displays various altitudes like indicated, pressure, and density altitude. Not updating the altimeter setting can cause errors.
- Gyroscopic instruments like the attitude indicator and heading indicator which function based on the principles of rigidity in space and precession.
- The turn coordinator and inclinometer which indicate aircraft bank and slip/skid.
- The magnetic compass
This document discusses gyroscopic instruments and their principles of operation. It explains that a gyroscope will maintain its orientation in space due to its high-speed rotation and angular momentum. It can rotate about perpendicular axes, with any change in its axis of rotation called precession. It describes different types of gyroscopes like attitude gyros and rate gyros, and errors they may experience like drift, wander, gimbal lock, and gimbal error. It also briefly discusses directional gyros, gyro horizons, and fuel quantity indication systems using sight glasses, mechanical floats, electrical resistance transmitters, and electronic capacitance sensors.
The document discusses the aircraft powerplant system, including the engine and propeller. It describes how the engine converts fuel energy into mechanical energy through the combustion process to power the propeller and propel the airplane. It then provides details on different types of reciprocating engines and their components. The document discusses the combustion process, propeller design and function, carburetor systems, ignition systems, fuel systems, and engine cooling systems that all work together to power the aircraft.
This document presents the conceptual design of a new business jet. It begins with an introduction and objectives. Market research on competitor aircraft is presented, along with a defined mission profile. Preliminary sizing calculations are shown to estimate takeoff weight. Wing, tail, thrust, and landing gear designs are conceptualized. Component weights are estimated and stability, control, and other aircraft characteristics are analyzed. The document concludes with a discussion of health, safety, economic, and environmental impacts of the design.
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.
This document discusses the V-n diagram, which plots the velocity of an aircraft against the load factor it experiences. It outlines how load factors are calculated based on the lift and weight of the aircraft. Limit, proof and ultimate load factors are explained which specify the maximum loads aircraft structures must be designed to withstand. Typical load factors for different aircraft types are shown, with fighters experiencing the highest positive load factors due to high-performance maneuvering. The V-n diagram defines the flight envelope and structural limits for an aircraft.
A Blended Wing Body (BWB) aircraft is a configuration where the wing and fuselage are integrated which essentially results in a large flying wing. BWB aircraft were previously called ‘tailless airplanes’ and ‘Flying-Wing aircraft’. The BWB configuration has shown promise in terms of aerodynamic efficiency, in particular for very large transport aircraft, because the configuration has a single lifting surface that means an aerodynamically clean configuration.
The document discusses the key components and structures of aircraft, including:
1) The fuselage, which is the main body and includes different structural types like truss, monocoque, and semi-monocoque.
2) Wings, which provide lift and include various designs attached at different positions on the fuselage, as well as wing structures using spars, ribs, and stringers.
3) The empennage or tail section, consisting of the vertical and horizontal stabilizers along with movable surfaces like the rudder and elevators.
4) The landing gear, usually a wheeled structure but sometimes floats or skis, which supports the airplane during takeoff, landing,
This presentation discusses swept wing configurations and their applications for supersonic flight. Swept wings reduce wave drag at transonic speeds by angling shock waves away from the aircraft. Swept wings were first developed in Germany in the 1930s and became prominent with aircraft like the MiG-15 and F-86. Variations include forward swept wings, which provide maneuverability but are expensive, and variable sweep wings which can change sweep angle during flight. Swept wings provide benefits like lateral stability and delaying compressibility effects at transonic speeds.
Do you look for a guide about how to build a rc plane? We are focusing parkjet designs, here is a guide that you can learn to build a parkjet. Check out http://onlinereview101.blogspot.com/2014/12/how-to-make-rc-airplane.html
This Powerpoint Presentation reviews on the topic - Aeroplane and Its Parts (With aerodynamics).
It was made for Educational Purpose.
If anyone want source file, E-mail:- moideenthashreef@hotmail.com
This document describes the design of a fighter aircraft. It discusses the conceptual design phase where the overall shape, size, weight and performance are determined. Comparative studies are conducted on different types of airplanes to select the appropriate configuration. Key parameters like wing type, engine selection and aerodynamic surfaces are analyzed and optimized. Performance calculations are carried out to evaluate the design. Three views and design specifications of the final fighter aircraft are presented.
Gliders are aircraft that are supported in flight through the dynamic reaction of air against their lifting surfaces without an engine. Some gliders have small engines to extend flight or for launching. The Wright Brothers spent years experimenting with gliders to develop efficient airfoils and flight control before attempting powered flight. Modern gliders include sailplanes for recreation, hang gliders that are foot-launched, and almost ready-to-fly models that require minor assembly. Gliders find lift through thermals or slope lift and pilots circle to remain in rising air. Winches are commonly used to launch larger sailplanes a few hundred feet and electric motors now assist some gliders. Efficiency is measured by glide ratio and half the drag
The presentation was prepared for an Technical Paper Presentation competition. It contains basic conceptual explanations pertaining to the BWB concept.
The document summarizes the basic control systems of an aircraft, including primary, secondary, and auxiliary flight controls. Primary controls include elevators, ailerons, and rudders which control pitch, roll, and yaw respectively. Secondary controls include trim tabs which help balance aircraft forces. Auxiliary controls include flaps, spoilers, and slats which provide additional lift, especially at lower speeds. The document describes the purpose and function of each control surface.
This document provides details on the design of a 1-seater military aircraft. It discusses the aircraft's specifications including its weight, performance characteristics, and dimensions of the wing. It also summarizes the structural analysis and material selection for the fuselage and wings. Several chapters describe the preliminary and detailed design of the aircraft's wing, fuselage, and tail section. Load distributions and structural components of each section are analyzed.
THIS PRESENTATION TAKES OVERVIEW OF AIRCRAFT CABIN PRESSURIZATION SYSTEM. IN THIS I EXPLAINED BASIC SYSTEM USED FOR PRESSURIZATION , AND HOW THIS SYSTEM IS SAFE, PRECISE. AND HOW AIR IS KEPT HEALTHY.
Conceptual Design of a Light Sport AircraftDustan Gregory
The document provides a conceptual design for a light sport aircraft. It defines key parameters for light sport aircraft and summarizes the design of several existing models. The design process described initializes parameters like wing area and airfoil selection. Equations are presented to calculate performance metrics like drag, power required, climb rate, endurance and range. Requirements for the conceptual design are specified, including taking off, cruising, and landing with sufficient fuel reserves.
This document discusses the basics of aerodynamics and the forces acting on aircraft in flight. It covers key concepts like:
1. Aerodynamic forces like lift, weight, thrust and drag that act on aircraft in motion through the air based on Newton's Laws of motion.
2. How the shape of airfoils and wings generate lift using Bernoulli's principle and how control surfaces like ailerons, elevators and rudders allow for rolling, pitching and yawing.
3. The different types of drag forces - induced, parasite and wave drag - and how configuration changes and altitude affect aircraft performance.
This document provides an overview of basic aerodynamics and flight controls. It explains the four main forces that act on aircraft - lift, gravity/weight, thrust, and drag. It describes how control surfaces like the ailerons, elevators, and rudder are used to control the aircraft's roll, pitch, and yaw. Finally, it gives a brief tour of common flight instruments that provide information to pilots like airspeed, altitude, heading, and vertical speed. The goal is to help readers understand how aircraft fly and how pilots control and navigate them.
Aircraft can be categorized in three ways: by basic design as either lighter-than-air or heavier-than-air, by propulsion as either power driven or non-power driven, and by wing design as either aeroplanes with fixed wings or rotorcraft with rotary wings. Lighter-than-air aircraft rely on gases for lift while heavier-than-air aircraft use air flowing over wings. Power driven aircraft use engines for propulsion and non-power driven use gravity and aerodynamic forces. Aeroplanes have stationary wings and rotorcraft have rotating wings.
This document provides information about various aircraft instruments including:
- The airspeed indicator which uses ram air from the pitot tube and static air, and displays airspeeds like Vso and Vfe. Blockages of the pitot tube or static vent can cause errors.
- The altimeter which uses only static air input and displays various altitudes like indicated, pressure, and density altitude. Not updating the altimeter setting can cause errors.
- Gyroscopic instruments like the attitude indicator and heading indicator which function based on the principles of rigidity in space and precession.
- The turn coordinator and inclinometer which indicate aircraft bank and slip/skid.
- The magnetic compass
This document discusses gyroscopic instruments and their principles of operation. It explains that a gyroscope will maintain its orientation in space due to its high-speed rotation and angular momentum. It can rotate about perpendicular axes, with any change in its axis of rotation called precession. It describes different types of gyroscopes like attitude gyros and rate gyros, and errors they may experience like drift, wander, gimbal lock, and gimbal error. It also briefly discusses directional gyros, gyro horizons, and fuel quantity indication systems using sight glasses, mechanical floats, electrical resistance transmitters, and electronic capacitance sensors.
The document discusses the aircraft powerplant system, including the engine and propeller. It describes how the engine converts fuel energy into mechanical energy through the combustion process to power the propeller and propel the airplane. It then provides details on different types of reciprocating engines and their components. The document discusses the combustion process, propeller design and function, carburetor systems, ignition systems, fuel systems, and engine cooling systems that all work together to power the aircraft.
This document presents the conceptual design of a new business jet. It begins with an introduction and objectives. Market research on competitor aircraft is presented, along with a defined mission profile. Preliminary sizing calculations are shown to estimate takeoff weight. Wing, tail, thrust, and landing gear designs are conceptualized. Component weights are estimated and stability, control, and other aircraft characteristics are analyzed. The document concludes with a discussion of health, safety, economic, and environmental impacts of the design.
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.
This document discusses the V-n diagram, which plots the velocity of an aircraft against the load factor it experiences. It outlines how load factors are calculated based on the lift and weight of the aircraft. Limit, proof and ultimate load factors are explained which specify the maximum loads aircraft structures must be designed to withstand. Typical load factors for different aircraft types are shown, with fighters experiencing the highest positive load factors due to high-performance maneuvering. The V-n diagram defines the flight envelope and structural limits for an aircraft.
A Blended Wing Body (BWB) aircraft is a configuration where the wing and fuselage are integrated which essentially results in a large flying wing. BWB aircraft were previously called ‘tailless airplanes’ and ‘Flying-Wing aircraft’. The BWB configuration has shown promise in terms of aerodynamic efficiency, in particular for very large transport aircraft, because the configuration has a single lifting surface that means an aerodynamically clean configuration.
The document discusses the key components and structures of aircraft, including:
1) The fuselage, which is the main body and includes different structural types like truss, monocoque, and semi-monocoque.
2) Wings, which provide lift and include various designs attached at different positions on the fuselage, as well as wing structures using spars, ribs, and stringers.
3) The empennage or tail section, consisting of the vertical and horizontal stabilizers along with movable surfaces like the rudder and elevators.
4) The landing gear, usually a wheeled structure but sometimes floats or skis, which supports the airplane during takeoff, landing,
This presentation discusses swept wing configurations and their applications for supersonic flight. Swept wings reduce wave drag at transonic speeds by angling shock waves away from the aircraft. Swept wings were first developed in Germany in the 1930s and became prominent with aircraft like the MiG-15 and F-86. Variations include forward swept wings, which provide maneuverability but are expensive, and variable sweep wings which can change sweep angle during flight. Swept wings provide benefits like lateral stability and delaying compressibility effects at transonic speeds.
Do you look for a guide about how to build a rc plane? We are focusing parkjet designs, here is a guide that you can learn to build a parkjet. Check out http://onlinereview101.blogspot.com/2014/12/how-to-make-rc-airplane.html
This Powerpoint Presentation reviews on the topic - Aeroplane and Its Parts (With aerodynamics).
It was made for Educational Purpose.
If anyone want source file, E-mail:- moideenthashreef@hotmail.com
How ro choose an electric motor for RC Planesmustafa sarac
The document discusses selecting an electric motor for RC aircraft. It begins by explaining how electric power systems were once intimidating for hobbyists due to complexity and cost, but that improvements have made electric easier. It then provides a step-by-step process for choosing a motor based on the aircraft's weight and intended use. Key factors include determining the wattage needed using 50-150 watts per pound as a guideline, and selecting a motor that provides that wattage. The document also discusses motor specifications and marketing techniques used by different retailers to help customers choose.
The document discusses the design process for building things from conceptual design through detail design. It notes that design is a fluid process. It also discusses factors that affect lift to drag ratio at subsonic speeds, namely wing span and wetted area, and different wing vertical locations of high wing, mid wing, and low wing.
- The document traces the history of human flight from ancient myths of Icarus and Garuda to early attempts with balloons and gliders. Key developments include the Montgolfier brothers' hot air balloon in 1783, the Wright brothers' first powered flight in 1903 in Kitty Hawk, and J.R.D. Tata founding Tata Airlines (now Air India) in 1932, bringing passenger flight to India. The document describes how aircraft have advanced incredibly since the early 1900s, allowing for supersonic flight, modern passenger jets, and military aircraft. It briefly explains the principles of lift, thrust, and drag that allow for heavier-than-air flight.
This document discusses various modes of water transportation and some facts about their history. It lists common types of watercraft like speed boats, canoes, sailboats and submarines that are used for purposes such as travel, fishing, cargo transport, and rescue missions. The document also provides some brief facts, such as that water transportation has been used for thousands of years starting with simple canoes, and now there are over 3 million shipwrecks on ocean floors. It concludes by recounting the author's experience taking a Seabus in Vancouver and the activities it allowed them to access.
The document discusses the history of airplanes from their invention by the Wright brothers in 1903 to their use in modern transportation. It outlines key developments like airplanes being used in World Wars I and II and how they have changed transportation by allowing for long distance and international travel. Advantages are discussed like faster travel over long distances, while disadvantages include costs and some people's fear of flying.
The document discusses the history and development of airplanes from the Wright Brothers' first powered flight in 1903 to modern jet airliners. It describes how the Wright Flyer worked by generating lift from its specially shaped wings. It then discusses how airplanes were used in World War I and the development of commercial flights in the 1920s using small propeller planes. Later developments included the use of planes for exploration, in World War II with more advanced propeller-driven bombers and fighters, and the introduction of jet planes after the war which became the standard for passenger and military aviation. The document concludes that planes have transformed long-distance transportation over the past 110 years.
The document discusses several key factors in landing gear design:
1. Landing gear must provide adequate ground clearance for the propeller tips and allow the plane to rotate on takeoff and landing to achieve the stalling angle of the airfoil.
2. Factors that affect landing and takeoff speeds and angles include the airfoil characteristics, planform, effect of flaps, and ground effect.
3. NASA's droop wing design increases takeoff and landing angles by delaying wing tip stalling and providing effective aileron control in a stall.
The document discusses head transplantation surgery (HTS). It provides an introduction to HTS, outlines the history of attempts at the procedure in animals from 1908 onwards, and describes the proposed procedure for the first attempted human head transplant. This would involve removing the head and grafting it onto a donor body below 20 degrees Celsius, reattaching arteries and cooling the patient for 4 weeks of artificial coma and treatment. While controversial, the document argues HTS could help those with incurable conditions and may be theoretically feasible, though risky.
The document discusses the Answer to Reset (ATR) from a UICC card during initialization. The ATR provides information about the card's capabilities and requirements for communication. It consists of start characters followed by optional interface and historical characters, and a check character. The ATR puts the card in specific or negotiable mode depending on the presence of an interface character TA2. It also discusses the optional PPS procedure for negotiating transmission speeds between the mobile equipment and UICC card.
The document discusses different modes of transportation such as aeroplanes and helicopters that will fly and bring passengers quickly and on time in locations around India, abroad, and the world including hangars and helipads. It also mentions the Wright brothers and provides contact information for a dental consultant in Tamil Nadu, India.
"Intelligent PCB Drilling Machine"
Nowadays, many industries use the Computerized Numerical Control (CNC) for Printed Circuit Board (PCB) drilling machines in industrial operations. It takes a long time to find optimal tour for large number of nodes (up to thousands). To achieve more effective results, optimization systems approach is required to be equipped in drilling machine. Euclidean Traveling Salesman Problem (TSP) is one of optimization method that gives fast near optimal solution for the drilling machine movement using novel friendly techniques. This project deals with the development of that CNC PCB drilling machine with novel approach to Euclidean TSP. This design can be widely applied to various CNC PCB drilling machines in small and medium scale manufacturing industries.
• My Role In Project:- Project Leader - Design of project , Analysis
• Achievements Of Projects : -
a. Reduce human efforts and errors in PCB drilling.
b. Automation of a traditional PCB drilling m/c.
c. Cost effective automated PCB drill m/c which is affordable by the small scale PCB makers.
d. Most use of electronic waste was from printers or other part of old m/c’s which are scrap.
The document discusses the key components of mini drones, including:
1. The frame, motors, electronic speed controllers, flight controller board, propellers, radio transmitter and receiver, batteries, and other parts.
2. Mini drone frames come in different materials like aluminum, carbon fiber, and plastics, with each having pros and cons.
3. Drones use electronic speed controllers to convert battery power to alternating current to drive the motors and control speed and direction.
This document discusses different types of drones and their parts. It describes four main types of drones: multi-rotor drones with multiple rotors like quadcopters; fixed wing drones that function like airplanes; single rotor drones similar to helicopters; and fixed wing hybrid drones that can hover and fly horizontally. It outlines key parts of drones like flight controllers, sensors for navigation and stabilization. It provides steps for flight preparation and calibration. Finally, it lists benefits of using drone systems like risk-free data collection from the sky and fast decision making.
K. Alexis, A. Tzes, "Revisited Dos Samara Unmanned Aerial Vehicle: Design and...Kostas Alexis
This document presents the design and modeling of a revisited Dos Samara unmanned aerial vehicle. It describes a convertible UAV concept that can operate in both helicopter and fixed-wing modes with less mechanical complexity than previous designs. The aircraft uses two samara-like blades for lift in helicopter mode and as wings in fixed-wing mode. Control surfaces below the blades provide control authority. The document outlines the aircraft design principles, nonlinear modeling approach, and development of an LQ controller for hovering. Future work will involve experimental analysis of the samara blade properties and actuation challenges.
The document describes the key components of a multi-copter drone. It lists components such as the flight controller, battery, brushless DC motor, electronic speed controller, power module, propellers, power distribution board, GPS, landing gear, transmitter and receiver, telemetry, pump motor, nozzles, tank, and provides a block diagram. It then provides more details on selected components, describing their purpose and characteristics.
Skyworks is developing gyroplane and gyrodyne technology that uses sustained autorotative flight, allowing for vertical takeoff and landing without needing runways. Their aircraft have fewer moving parts than helicopters, making them simpler, safer, and more reliable. Skyworks' technology could disrupt transportation by enabling aircraft to operate from more locations like city centers, farmers' fields, and smaller airports.
This document provides information about a course on GPS drone mapping. The course objectives are for students to safely operate and autonomously fly drones, create efficient flight plans, and pass a final assessment. The outline covers introductory topics like drone parts, safety guidelines, and flight modes over 6 days, with practice manual and autonomous flights culminating in a final evaluation.
Manual - Full Quadcopters review (watermarked)Quads For Fun
This document provides information about various components and specifications related to quadcopters. It discusses 6-axis gyros, brushless motors, battery discharge rates, voltage, weight and size, charging, and types of batteries that are commonly used in quadcopters. It also covers topics like flight time versus battery capacity, cameras used for recording video and photos from quadcopters, remote controls, and classifications of models like RTF, BNF, PNP, and ARF.
this is about quad-copter component and how we select best for us in this did not analysis about aerodynamics theory and momentum equation. but all basic things are completely explain about quad-copter. circuit diagram also clearly present in this slide. expect all this things applications are describe here
Aiaa Student Design Build Fly Electric Airplaneahmad bassiouny
The document summarizes the design of an electric RC aircraft called Poseidon's Fury. Key features include carrying a 4 liter payload, draining within 30 seconds, lifting around 25 lbs, and having a low rated aircraft cost. The aircraft uses carbon fiber spars and booms, has a tricycle landing gear configuration, and modified Eppler 216 airfoils. Flight testing showed good longitudinal and directional stability. The propulsion system uses 32 NiCad batteries providing over 4 lbs of thrust and a pitch speed of 47 mph, meeting requirements. The aircraft design satisfies competition rules and successfully completed test missions.
The document describes the design and development of a surveillance chopper or unmanned aerial vehicle. It discusses the various components used - including the airframe, brushless motor, electronic speed controller, batteries, radio receiver, and wireless camera. The chopper is designed to be remotely controlled and can potentially be used for applications like surveillance, inspection work, and more. The document provides details on how the various parts work together and how the chopper was configured.
A flying car project by retired Air Force pilot-engineer Rich Strong intended for frequent regional business travellers. The design features automotive features and aviation features with automatic transformation. The project is in the full-size model phase.
This document provides an overview of the key parts that make up a radio controlled airplane system. It discusses both the external parts like the battery, engine/motor, propeller, wings, and control surfaces as well as the internal components like the receiver/controller, servos, and control poles that allow the pilot to control the airplane using a transmitter. The external parts provide power and allow the airplane to fly, while the internal components receive signals from the transmitter and move the control surfaces to control the roll, pitch, yaw, and throttle of the airplane.
This document summarizes a student project to design, develop, and demonstrate a radio-controlled airplane. It describes constructing the airplane, the aerodynamic theories behind flight, and specifications of components. The project aims to enable interested students to learn about building miniature flying machines. It covers airplane parts, aerodynamic principles, construction steps, adjustments, and specifications of electronics and other parts used.
Best ppt on Micro air vehicle with flapping wingsRonak Thakare
This document discusses micro air vehicles (MAVs) with flapping wings. It defines MAVs as unmanned aerial vehicles that are less than 15cm long and weigh less than 4 ounces. They can perform military, commercial, and urban surveillance missions with lightweight designs. MAVs require high resolution sensors, lightweight materials like balsa wood and composites, electric motors and batteries. Flapping wing designs provide more lift than fixed wings. Future work aims to further minimize size and weight while improving flight speed, stability, and battery life. Kelvin's circulation theorem and how flapping wings generate lift through diverting airflow are also summarized.
This document provides information on the AR190 subsonic light transport aircraft concept. It describes the types of transportation aircraft that currently exist, including airliners, cargo aircraft, military transport aircraft, and more. It then outlines some key aspects of the AR190 concept, including its advantages over existing aircraft, its business model, and technical specifications like its communication systems, flight controls, fuel system, and other components. The document aims to introduce the AR190 concept as a potential next step for subsonic light transport.
The team presented the critical design review for DORIS, a deployable oceanic reconnaissance information system. DORIS can be launched from land or boats and breaks down into four pieces for transport and storage. It has LED lights, a payload bay, and an autopilot system. Performance analyses showed the aircraft has a 103 minute endurance at 25 mph and a 43 mile range. Structural analyses found the wing and fuselage can withstand flight loads with a 1.5 safety factor. The team's $1503 budget covers construction and shared experimental costs.
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Practical eLearning Makeovers for EveryoneBianca Woods
Welcome to Practical eLearning Makeovers for Everyone. In this presentation, we’ll take a look at a bunch of easy-to-use visual design tips and tricks. And we’ll do this by using them to spruce up some eLearning screens that are in dire need of a new look.
4. Specifications :
1- High Wing.
2- Straight Wing.
3- Flat Bottomed Airfoil.
4- Low Speed.
5- Ease of Controllability.
5. Specifications :
1- Usually Low Wing.
2- Usually Symmetric Airfoil.
3-Advanced than trainer plane.
4- The Ability of maneuverability.
5- Faster than trainer plane.
6. Specifications :
1- Advanced model of Sport Plane.
2- It’s used for aerobatics.
3- Similar to 3D Planes.
4- Usually mid-wing Plane.