Presentasi menjelaskan bagaimana pesawat terbang dapat terbang di udara. Pesawat terbang mampu terbang karena gaya angkat yang dihasilkan dari perbedaan kecepatan aliran udara di bagian atas dan bawah sayap pesawat sesuai hukum Bernoulli. Dua bersaudara Wright diakui sebagai penemu pesawat terbang modern.
Dokumen tersebut membahas berbagai aspek struktur sayap pesawat udara, termasuk jenis konstruksi sayap, bentuk sayap, variasi jumlah sayap, dan cara pemasangan sayap pada fuselage."
This document discusses aircraft flight control systems. It describes three main categories of flight controls: primary, secondary, and auxiliary.
Primary flight controls include elevators, ailerons, and the rudder. Elevators control pitch, ailerons control roll, and the rudder controls yaw. Secondary flight controls include trim tabs which help balance aircraft control forces. Auxiliary controls include flaps and other high lift devices which allow aircraft to fly at slower speeds. The document provides details on how each of these various control surfaces and systems function.
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.
The document provides information on the landing gear system of the Boeing 737 NG. It describes the main components and operation of the landing gear including:
- The aircraft has two main landing gears and a single nose gear.
- Hydraulic system A normally controls extension, retraction and nose wheel steering. System B provides alternatives.
- Extension and retraction are controlled by the landing gear lever and occur through hydraulic pressure and mechanical locks.
- Sensors monitor gear position and provide inputs to warning systems.
- Manual extension is possible if system A fails using gear releases.
This document discusses approach and landing performance requirements. It covers topics like approach definition, maximum and minimum speeds, landing weight limitations, climb requirements, landing distances, and factors affecting landing distance. Specifically, it defines speeds like VREF (reference landing approach speed) and VAPP (actual landing speed). It also discusses requirements for landing and approach climb gradients, and how to calculate landing distance required versus landing distance available on the runway.
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
Presentasi menjelaskan bagaimana pesawat terbang dapat terbang di udara. Pesawat terbang mampu terbang karena gaya angkat yang dihasilkan dari perbedaan kecepatan aliran udara di bagian atas dan bawah sayap pesawat sesuai hukum Bernoulli. Dua bersaudara Wright diakui sebagai penemu pesawat terbang modern.
Dokumen tersebut membahas berbagai aspek struktur sayap pesawat udara, termasuk jenis konstruksi sayap, bentuk sayap, variasi jumlah sayap, dan cara pemasangan sayap pada fuselage."
This document discusses aircraft flight control systems. It describes three main categories of flight controls: primary, secondary, and auxiliary.
Primary flight controls include elevators, ailerons, and the rudder. Elevators control pitch, ailerons control roll, and the rudder controls yaw. Secondary flight controls include trim tabs which help balance aircraft control forces. Auxiliary controls include flaps and other high lift devices which allow aircraft to fly at slower speeds. The document provides details on how each of these various control surfaces and systems function.
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.
The document provides information on the landing gear system of the Boeing 737 NG. It describes the main components and operation of the landing gear including:
- The aircraft has two main landing gears and a single nose gear.
- Hydraulic system A normally controls extension, retraction and nose wheel steering. System B provides alternatives.
- Extension and retraction are controlled by the landing gear lever and occur through hydraulic pressure and mechanical locks.
- Sensors monitor gear position and provide inputs to warning systems.
- Manual extension is possible if system A fails using gear releases.
This document discusses approach and landing performance requirements. It covers topics like approach definition, maximum and minimum speeds, landing weight limitations, climb requirements, landing distances, and factors affecting landing distance. Specifically, it defines speeds like VREF (reference landing approach speed) and VAPP (actual landing speed). It also discusses requirements for landing and approach climb gradients, and how to calculate landing distance required versus landing distance available on the runway.
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
The document provides information on the pneumatic and bleed air systems of the Boeing 737 NG. It discusses how bleed air is supplied by the engines or APU to systems like air conditioning, anti-icing, and hydraulics. Key components discussed include the engine bleed valves, isolation valve, packs, and ram air system. The bleed air is regulated and cooled before being supplied to the air conditioning system to produce conditioned air for the aircraft.
A presentation that guides the student through the forces acting on an aircraft, and how to fly a circuit at a typical airfield. This includes aircraft instrumentation and radio use. THIS PRESENTATION IS FOR INTEREST AND SIMULATED FLIGHT ONLY, AS PROPER FLIGHT INSTRUCTION SHOULD BE TAKEN FOR ACTUAL FLIGHT
The document provides information on anti-ice and rain protection systems for the Boeing 737 NG, including thermal anti-icing, electrical anti-icing, and windshield wipers. It describes the flight deck window heat, probe and sensor heat, engine anti-ice system, wing anti-ice system, ice detection system, and corresponding controls and indicators. The wing and engine anti-ice systems use bleed air to prevent ice buildup, while probes and sensors are heated electrically. Lights indicate system status and faults like overheat conditions.
Fuel systems on aircraft can be complex, utilizing multiple tank designs located throughout the aircraft. Fuel is distributed via pumps and valves, and aircraft may have systems to prevent issues like fuel starvation, icing, and contamination. Large aircraft often carefully manage fuel burn between tanks to control weight and balance. Fuel gauges indicate quantity, but dipsticks provide backup readings, and crossfeed capabilities are important for multi-engine aircraft in emergencies. Fuel systems aim to reliably deliver clean fuel to aircraft engines.
The pneumatic system provides compressed air for aircraft functions like air conditioning, engine starting, and anti-ice systems. It obtains air from the engine bleed ports and controls the air pressure, temperature, and cleanliness. Leak detection loops monitor the hot air ducts and can isolate leaks by closing valves. The pneumatic system is controlled and monitored via panels and ECAM displays.
The document discusses the International Standard Atmosphere (ISA) model, which defines standard atmospheric conditions as a function of altitude. Key points:
- The ISA was developed in the 1920s and standardized in 1952 to provide a reference model for aircraft/rocket design and performance.
- It defines how temperature, pressure, and density vary with altitude up to 80,000 ft based on hydrostatic equilibrium equations for a stationary, dry atmosphere.
- Temperature decreases at a constant rate from sea level to the tropopause at -6.5°C/1000m and remains constant above. Pressure and density decrease exponentially with altitude based on the gas laws.
- The ISA provides a baseline for comparing
This document discusses various equipment and systems related to aircraft cabins and flight decks. It covers topics such as cabin interior design aspects for comfort and safety, flight compartment equipment like seats and emergency gear, passenger compartment furnishings including seats and service units, and maintenance procedures for seats and harnesses. Key requirements for cabin interior and flight deck equipment outlined include providing safety, comfort and convenience for passengers and crew.
This document provides an overview of low visibility operations (LVO) including Category II, Category IIIA, and low visibility takeoffs. It defines key concepts such as decision height, runway visual range, operating minima, and requirements for aircraft, airfields, and flight crews to conduct these special operations. Category II allows for a manual landing at DH between 100-200 feet while Category IIIA requires an automatic landing system and has a DH under 100 feet or no DH with an RVR no less than 200 meters.
1. The A380 is a large, double-deck widebody airliner with seating for 644-868 passengers.
2. The A380 landing gear system includes wheels, brakes, doors and related control computers and devices to extend, retract, steer and brake the landing gear.
3. The landing gear consists of two wing landing gears, two body landing gears, and a nose landing gear, each with related doors and retraction/extension mechanisms.
Laporan tugas besar lampu navigasi pesawatIqbalArdy1
Pada laporan ini akan dijelaskan tentang studi lampu navigasi pesawat dengan menggunakan literatur dan sumber-sumber daring lainnya. Studi ini memuat gambaran umum mengenai topik, produsen yang tersedia dan potensial, proses pengujian secara umum, regulasi, dan tempat pengujian topik yang kami angkat.
This document defines key distances related to aircraft takeoff and landing performance. It discusses:
- Screen height definitions for different aircraft types
- Definitions for runway, stopway, and clearway areas
- Declared distances including TORA, TODA, ASDA, and LDA that define available field lengths
- Required distances including TORR, TODR, and ASDR that must be met for safe takeoff and landing
- How to determine a balanced field length takeoff where TODR and ASDR are equal versus an unbalanced takeoff that takes advantage of a stopway or clearway.
El documento clasifica y describe los diferentes tipos de aeronaves, incluyendo globos, dirigibles, planeadores, helicópteros y aeroplanos. También describe las partes principales de un avión como el fuselaje, alas, cola y superficies de control. Explica dispositivos como flaps, slats y spoilers que modifican la aerodinámica de las alas.
Tab adalah airfoil kecil yang terpasang pada permukaan kontrol pesawat untuk membantu menstabilkan dan mengatur sikap pesawat. Ada beberapa jenis tab seperti trim tab, servo tab, anti-servo tab, dan balanced tab. Tab dikendalikan dari kokpit melalui sistem kontrol sederhana, terbantu, atau fly-by-wire. Tab memainkan peran penting dalam mengurangi beban kerja pilot selama penerbangan.
This document provides a description and overview of the autopilot and yaw damper system for a B727-200 aircraft. It describes the major components, including the Sperry SP-50 MB V Automatic Flight Control System, which provides three-axis flight stabilization and automatic approach capability. It details the functions of the yaw, roll, and pitch axes, and describes the components that control and provide inputs to each axis, such as rudder power units, aileron servos, elevator power units, and sensors. The document also notes the locations of components throughout the aircraft.
This document provides an overview of aircraft landing gear systems. It describes three common types of landing gear: tricycle gear, taildragger gear, and ski gear. It then discusses key components of landing gear systems like nose wheel steering, shimmy damping systems, and safety systems. Nose wheel steering uses hydraulic power to turn the nose wheel. Shimmy damping systems like piston, vane, and steer types control unwanted vibration. Safety systems include mechanical downlocks, safety switches, and ground locks to prevent accidental gear retraction.
The Common Display System (CDS) supplies navigation and engine information to pilots using 6 identical display units. The CDS uses 2 Display Electronics Units (DEU) that collect data and convert it to video signals for the displays. Either DEU can supply all displays if one fails. The Primary Flight Display normally appears on the outboard display unit while the Navigation Display is on the inboard unit. Engine indications are usually on the upper display unit. The lower display unit shows secondary engine information and can be configured as a multifunction display.
Refueling and defueling aircraft requires specific procedures and safety precautions. There are two main types of aviation fuel - AVGAS for piston engines and AVTUR for turbine engines. Refueling can be done through an open orifice or pressure system. The refueling procedure involves bonding the fuel truck and nozzle, using a mat to protect the wing, and avoiding contact between the nozzle and tank bottom. Defueling uses suction pumps or gravity to drain tanks through valves or petcocks. Safety precautions mandate only trained personnel, fire extinguishers, correct fuel grades, bonding of all components, cleanup of spills, and avoidance of ignition sources during the process.
This document provides an overview of the electrical power system on a Boeing 747-400 aircraft. It describes the various AC and DC power buses, and how electrical power is generated, distributed, and controlled throughout normal operations and different failure conditions. Key components include the integrated drive generators, transformer rectifier units, batteries, and external power connections.
1. Anti icing dan de-icing system digunakan untuk mencegah terbentuknya es atau memecahkan es yang sudah terbentuk pada pesawat terbang.
2. Es pada pesawat dapat menambah drag, mengurangi lift, menimbulkan getaran merusak, dan mengganggu kinerja mesin.
3. Sistem anti icing dan de-icing dapat berupa pemanasan permukaan dengan udara panas, elemen listrik, atau semprotan alkohol.
The document provides information on the pneumatic and bleed air systems of the Boeing 737 NG. It discusses how bleed air is supplied by the engines or APU to systems like air conditioning, anti-icing, and hydraulics. Key components discussed include the engine bleed valves, isolation valve, packs, and ram air system. The bleed air is regulated and cooled before being supplied to the air conditioning system to produce conditioned air for the aircraft.
A presentation that guides the student through the forces acting on an aircraft, and how to fly a circuit at a typical airfield. This includes aircraft instrumentation and radio use. THIS PRESENTATION IS FOR INTEREST AND SIMULATED FLIGHT ONLY, AS PROPER FLIGHT INSTRUCTION SHOULD BE TAKEN FOR ACTUAL FLIGHT
The document provides information on anti-ice and rain protection systems for the Boeing 737 NG, including thermal anti-icing, electrical anti-icing, and windshield wipers. It describes the flight deck window heat, probe and sensor heat, engine anti-ice system, wing anti-ice system, ice detection system, and corresponding controls and indicators. The wing and engine anti-ice systems use bleed air to prevent ice buildup, while probes and sensors are heated electrically. Lights indicate system status and faults like overheat conditions.
Fuel systems on aircraft can be complex, utilizing multiple tank designs located throughout the aircraft. Fuel is distributed via pumps and valves, and aircraft may have systems to prevent issues like fuel starvation, icing, and contamination. Large aircraft often carefully manage fuel burn between tanks to control weight and balance. Fuel gauges indicate quantity, but dipsticks provide backup readings, and crossfeed capabilities are important for multi-engine aircraft in emergencies. Fuel systems aim to reliably deliver clean fuel to aircraft engines.
The pneumatic system provides compressed air for aircraft functions like air conditioning, engine starting, and anti-ice systems. It obtains air from the engine bleed ports and controls the air pressure, temperature, and cleanliness. Leak detection loops monitor the hot air ducts and can isolate leaks by closing valves. The pneumatic system is controlled and monitored via panels and ECAM displays.
The document discusses the International Standard Atmosphere (ISA) model, which defines standard atmospheric conditions as a function of altitude. Key points:
- The ISA was developed in the 1920s and standardized in 1952 to provide a reference model for aircraft/rocket design and performance.
- It defines how temperature, pressure, and density vary with altitude up to 80,000 ft based on hydrostatic equilibrium equations for a stationary, dry atmosphere.
- Temperature decreases at a constant rate from sea level to the tropopause at -6.5°C/1000m and remains constant above. Pressure and density decrease exponentially with altitude based on the gas laws.
- The ISA provides a baseline for comparing
This document discusses various equipment and systems related to aircraft cabins and flight decks. It covers topics such as cabin interior design aspects for comfort and safety, flight compartment equipment like seats and emergency gear, passenger compartment furnishings including seats and service units, and maintenance procedures for seats and harnesses. Key requirements for cabin interior and flight deck equipment outlined include providing safety, comfort and convenience for passengers and crew.
This document provides an overview of low visibility operations (LVO) including Category II, Category IIIA, and low visibility takeoffs. It defines key concepts such as decision height, runway visual range, operating minima, and requirements for aircraft, airfields, and flight crews to conduct these special operations. Category II allows for a manual landing at DH between 100-200 feet while Category IIIA requires an automatic landing system and has a DH under 100 feet or no DH with an RVR no less than 200 meters.
1. The A380 is a large, double-deck widebody airliner with seating for 644-868 passengers.
2. The A380 landing gear system includes wheels, brakes, doors and related control computers and devices to extend, retract, steer and brake the landing gear.
3. The landing gear consists of two wing landing gears, two body landing gears, and a nose landing gear, each with related doors and retraction/extension mechanisms.
Laporan tugas besar lampu navigasi pesawatIqbalArdy1
Pada laporan ini akan dijelaskan tentang studi lampu navigasi pesawat dengan menggunakan literatur dan sumber-sumber daring lainnya. Studi ini memuat gambaran umum mengenai topik, produsen yang tersedia dan potensial, proses pengujian secara umum, regulasi, dan tempat pengujian topik yang kami angkat.
This document defines key distances related to aircraft takeoff and landing performance. It discusses:
- Screen height definitions for different aircraft types
- Definitions for runway, stopway, and clearway areas
- Declared distances including TORA, TODA, ASDA, and LDA that define available field lengths
- Required distances including TORR, TODR, and ASDR that must be met for safe takeoff and landing
- How to determine a balanced field length takeoff where TODR and ASDR are equal versus an unbalanced takeoff that takes advantage of a stopway or clearway.
El documento clasifica y describe los diferentes tipos de aeronaves, incluyendo globos, dirigibles, planeadores, helicópteros y aeroplanos. También describe las partes principales de un avión como el fuselaje, alas, cola y superficies de control. Explica dispositivos como flaps, slats y spoilers que modifican la aerodinámica de las alas.
Tab adalah airfoil kecil yang terpasang pada permukaan kontrol pesawat untuk membantu menstabilkan dan mengatur sikap pesawat. Ada beberapa jenis tab seperti trim tab, servo tab, anti-servo tab, dan balanced tab. Tab dikendalikan dari kokpit melalui sistem kontrol sederhana, terbantu, atau fly-by-wire. Tab memainkan peran penting dalam mengurangi beban kerja pilot selama penerbangan.
This document provides a description and overview of the autopilot and yaw damper system for a B727-200 aircraft. It describes the major components, including the Sperry SP-50 MB V Automatic Flight Control System, which provides three-axis flight stabilization and automatic approach capability. It details the functions of the yaw, roll, and pitch axes, and describes the components that control and provide inputs to each axis, such as rudder power units, aileron servos, elevator power units, and sensors. The document also notes the locations of components throughout the aircraft.
This document provides an overview of aircraft landing gear systems. It describes three common types of landing gear: tricycle gear, taildragger gear, and ski gear. It then discusses key components of landing gear systems like nose wheel steering, shimmy damping systems, and safety systems. Nose wheel steering uses hydraulic power to turn the nose wheel. Shimmy damping systems like piston, vane, and steer types control unwanted vibration. Safety systems include mechanical downlocks, safety switches, and ground locks to prevent accidental gear retraction.
The Common Display System (CDS) supplies navigation and engine information to pilots using 6 identical display units. The CDS uses 2 Display Electronics Units (DEU) that collect data and convert it to video signals for the displays. Either DEU can supply all displays if one fails. The Primary Flight Display normally appears on the outboard display unit while the Navigation Display is on the inboard unit. Engine indications are usually on the upper display unit. The lower display unit shows secondary engine information and can be configured as a multifunction display.
Refueling and defueling aircraft requires specific procedures and safety precautions. There are two main types of aviation fuel - AVGAS for piston engines and AVTUR for turbine engines. Refueling can be done through an open orifice or pressure system. The refueling procedure involves bonding the fuel truck and nozzle, using a mat to protect the wing, and avoiding contact between the nozzle and tank bottom. Defueling uses suction pumps or gravity to drain tanks through valves or petcocks. Safety precautions mandate only trained personnel, fire extinguishers, correct fuel grades, bonding of all components, cleanup of spills, and avoidance of ignition sources during the process.
This document provides an overview of the electrical power system on a Boeing 747-400 aircraft. It describes the various AC and DC power buses, and how electrical power is generated, distributed, and controlled throughout normal operations and different failure conditions. Key components include the integrated drive generators, transformer rectifier units, batteries, and external power connections.
1. Anti icing dan de-icing system digunakan untuk mencegah terbentuknya es atau memecahkan es yang sudah terbentuk pada pesawat terbang.
2. Es pada pesawat dapat menambah drag, mengurangi lift, menimbulkan getaran merusak, dan mengganggu kinerja mesin.
3. Sistem anti icing dan de-icing dapat berupa pemanasan permukaan dengan udara panas, elemen listrik, atau semprotan alkohol.
Dokumen tersebut membahas daftar perguruan tinggi kedinasan di Indonesia di bawah berbagai kementerian dan lembaga pemerintah non-kementerian serta Kepolisian Negara Republik Indonesia beserta lokasi masing-masing.
Makalah ini membahas tentang tiga jenis alat pengangkat berat yaitu derek uap, alat pengangkat mobil, dan kran hidrolik. Derek uap menggunakan tenaga uap untuk mengangkat beban, alat pengangkat mobil menggunakan sistem hidrolik untuk mengangkat kendaraan, sedangkan kran hidrolik dapat digunakan untuk memindahkan beban berat dengan kapasitas angkat beragam.
The document discusses aircraft landing gear, including:
1) The main functions of landing gear such as supporting the aircraft's weight and absorbing landing shocks.
2) The basic types of landing gear including fixed, retractable, and types based on arrangement like single, double, and tandem.
3) Key components of landing gear like shock struts, torque links, and the various actuators, links, and mechanisms involved.
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.
1. Sekolah Tinggi Penerbangan Indonesia
Curug, Kab. Tangerang, Banten.
Introduction
Flight Control
System
Flight Control
Theodery MR – Chapter 5
Primary Flight
Control
Secondary Flight
Control
Autopilot & Chapter
Summary
Credits
Click NEXT
2. Sekolah Tinggi Penerbangan Indonesia
Curug, Kab. Tangerang, Banten.
Introduction
Flight Control
System
Flight Control
Theodery MR – Chapter 5
Primary Flight
Control
Secondary Flight
Control
Autopilot & Chapter
Summary
Credits
3. Sekolah Tinggi Penerbangan Indonesia
Curug, Kab. Tangerang, Banten.
Introduction
Flight Control
System
Flight Control
Theodery MR – Chapter 5
Primary Flight
Control
Secondary Flight
Control
Autopilot & Chapter
Summary
Credits
I N T R O D U C T I O N
• Bab ini berfokus pada sistem kontrol
penerbangan pilot menggunakan
untuk mengontrol kekuatan
penerbangan, arah pesawat, dan
ketinggian.
4. Sekolah Tinggi Penerbangan Indonesia
Curug, Kab. Tangerang, Banten.
Introduction
Flight Control
System
Flight Control
Theodery MR – Chapter 5
Primary Flight
Control
Secondary Flight
Control
Autopilot & Chapter
Summary
Credits
F L I G H T C O N T R O L S Y S T E M
• Flight Control
• Primary Control
• Secondary Control
5. Sekolah Tinggi Penerbangan Indonesia
Curug, Kab. Tangerang, Banten.
Introduction
Flight Control
System
Flight Control
Theodery MR – Chapter 5
Primary Flight
Control
Secondary Flight
Control
Autopilot & Chapter
Summary
Credits
F L I G H T C O N T R O L
Sistem kontrol penerbangan pesawat terdiri dari sistem
primer dan sekunder. Ailerons, elevator (atau stabilator), dan
rudder merupakan sistem kontrol utama dan diharuskan untuk
mengendalikan pesawat dengan aman selama penerbangan.
Wing flaps, perangkat terdepan, spoiler, dan memangkas sistem
merupakan sistem kontrol sekunder dan meningkatkan
karakteristik kinerja dari pesawat atau meringankan pilot gaya
kontrol yang berlebihan.
6. Sekolah Tinggi Penerbangan Indonesia
Curug, Kab. Tangerang, Banten.
Introduction
Flight Control
System
Flight Control
Theodery MR – Chapter 5
Primary Flight
Control
Secondary Flight
Control
Autopilot & Chapter
Summary
Credits
P R I M A R Y C O N T R O L
Primary control adalah sistem kontrol utama/primer
pada pesawat. Terdiri dari :
1. Ailerons
2. Elevator
3. Rudder
4. Sitem Rekayasa
7. Sekolah Tinggi Penerbangan Indonesia
Curug, Kab. Tangerang, Banten.
Introduction
Flight Control
System
Flight Control
Theodery MR – Chapter 5
Primary Flight
Control
Secondary Flight
Control
Autopilot & Chapter
Summary
Credits
1. Aileron
Ailerons dapat menyebabkan pergerakan Roll pada pesawat.
Para ailerons melekat pada tempel trailing edge dari sayap
masing-masing dan pergerakanya berlawanan satu sama lain.
Ailerons dihubungkan dengan kabel, bellcranks, katrol
dan/atau push-pull tabung untuk roda kontrol atau tongkat
kontrol.
8. Sekolah Tinggi Penerbangan Indonesia
Curug, Kab. Tangerang, Banten.
Introduction
Flight Control
System
Flight Control
Theodery MR – Chapter 5
Primary Flight
Control
Secondary Flight
Control
Autopilot & Chapter
Summary
Credits
2. Elevator
Elevator berada di bagian
belakang pesawat
pada horizontal stabilizer.
Elevator berguna untuk
take off (Nose-up)
dan landing (Nose-Down).
Nama gerakan yang dihasilkan
oleh Elevator untuk Nose-up
dan Nose-down adalah pitch.
9. Sekolah Tinggi Penerbangan Indonesia
Curug, Kab. Tangerang, Banten.
Introduction
Flight Control
System
Flight Control
Theodery MR – Chapter 5
Primary Flight
Control
Secondary Flight
Control
Autopilot & Chapter
Summary
Credits
3. Rudder
Rudder berada di ekor pesawat pada vertikal stabilizer. Rudder
biasanya digunakan pada speed rendah dengan gerakan yang
dinamakan yaw.
Rudder
10. Sekolah Tinggi Penerbangan Indonesia
Curug, Kab. Tangerang, Banten.
Introduction
Flight Control
System
Flight Control
Theodery MR – Chapter 5
Primary Flight
Control
Secondary Flight
Control
Autopilot & Chapter
Summary
Credits
4. Sistem Rekayasa
System rekayasa digunakan untuk mengurangi yaw
yang merugikan. Macam-macam sistem rekayasa :
1. Differensial Aileron
2. Frise-type Aileron
3. Coupled Aileron dan Rudder
4. Flaperon
11. Sekolah Tinggi Penerbangan Indonesia
Curug, Kab. Tangerang, Banten.
Introduction
Flight Control
System
Flight Control
Theodery MR – Chapter 5
Primary Flight
Control
Secondary Flight
Control
Autopilot & Chapter
Summary
Credits
Diferensial Aileron
• Dengan differential aileron, satu aileron diposisikan lebih
tinggi jaraknya sedangkan satu aileron diposisikan lebih
rendah untuk memberikan pergerakan dari control wheel dan
control stick. Hal ini menghasilkan sebuah peningkatan drag
pada descending wing. Drag yg lebih besar hasil dari aileron
atas pada descending wing yg membelok ke sudut yg lebih
tinggi dari aileron bawah pada descending aileron. Sementara
itu yaw merugikan berkurang namun tak sepenuhnya hilang.
12. Sekolah Tinggi Penerbangan Indonesia
Curug, Kab. Tangerang, Banten.
Introduction
Flight Control
System
Flight Control
Theodery MR – Chapter 5
Primary Flight
Control
Secondary Flight
Control
Autopilot & Chapter
Summary
Credits
Fries-type Aileron
• Dengan fries-type aileron, ketika tekanan diaplikasikan ke roda
control atw stik control, saat itu aileron mebangkitkan poros pada
engsel penyeimbang. Tepi dari aileron utama dirancang untuk
menciptakan drag dan airflow . ini membanti menyeimbangkan drag
yang tercipta dari aileron yg rendah pada wing yg berlawanan dan
mengurangi yaw merugikan.
• Fries-type aileron juga membentuk sebuah celah sehingga udara
dengan lembut mengalir melewati aileron rendah, membuatnya
lebih efektif pada AOA yg tinggi.frise type aileron juga dirancang
fungsi tertentu. Seperti differential aileron, fries-type aileron tidak
menghilangkan yaw merugikan secara keseluruhan. Peran serta
rudder tetap dibutuhkan dimanapun aileron diaplikasikan.
13. Sekolah Tinggi Penerbangan Indonesia
Curug, Kab. Tangerang, Banten.
Introduction
Flight Control
System
Flight Control
Theodery MR – Chapter 5
Primary Flight
Control
Secondary Flight
Control
Autopilot & Chapter
Summary
Credits
Coupled Aileron dan Rudder
• Coupled aileron and rudder adalah kendali yg berkaitan. Ini
tercapai karena adanya interkoneksi rudder dengan aileron,
yang membantu menyesuaikan drag aileron dengan
pembelokan rudder secra otomatis pa waktu yg sama aileron
dibelokan.
14. Sekolah Tinggi Penerbangan Indonesia
Curug, Kab. Tangerang, Banten.
Introduction
Flight Control
System
Flight Control
Theodery MR – Chapter 5
Primary Flight
Control
Secondary Flight
Control
Autopilot & Chapter
Summary
Credits
Flaperons
• Flaperons mengkombinasikan kedua aspek dari flaps dan
ailerons. Selain itu untuk mengkontrol sudut bank dari sebuah
aircraft seperti aileron konvensional, flaperon bisa
direndahkan bersamaan untuk menimbulkan kumpulan flaps.
Mixer digunakan untuk mengkombinasikan input dari pilot yg
terpisah menjadi satu set permukaan kendali yg dinamakan
flaperons. Banyak rancangan yang menggabungkan flaperons
untuk meningkatkan control surface dari wing untuk
menyediakan aliran udara yg tidak mengganggu pada Angle of
Attack yg tinggi dan atau kecepatan yg rendah.
15. Sekolah Tinggi Penerbangan Indonesia
Curug, Kab. Tangerang, Banten.
Introduction
Flight Control
System
Flight Control
Theodery MR – Chapter 5
Primary Flight
Control
Secondary Flight
Control
Autopilot & Chapter
Summary
Credits
S E C O N D A R Y F L I G H T C O N T R O L
• Secondary Flight Control adalah kontrol kedua atau bisa
disebut kontrol untuk membantu kontrol utama. Sifatnya
tidak terlalu memberikan efek yang besar. Secondary Flight
Control Terdiri dari :
A. V-Tail G. Servo Tabs
B. Flaps H. Antiservo tabs
C. Leading Edge Devices I. Gound Adjustable Tab
D. Spoilers J. Adjustable Stabilizer
E. Trim System
F. Trim Tab
16. Sekolah Tinggi Penerbangan Indonesia
Curug, Kab. Tangerang, Banten.
Introduction
Flight Control
System
Flight Control
Theodery MR – Chapter 5
Primary Flight
Control
Secondary Flight
Control
Autopilot & Chapter
Summary
Credits
A. V-Tail
• Desain ekor berbentuk huruf “V”, yaitu dua permukaan
ekor miring yang digunakan untuk melakukan fungsi
yang sama seperti permukaan lift dan kemudi
konfigurasi konvensional. Permukaan tetap bertindak
sebagai stabilisator horisontal dan vertikal.
• Ada permukaan khusus pada V-Tail yang dinamakan
ruddervators. Ruddervators terhubung melalui linkage
khusus yang memungkinkan roda kontrol untuk
memindahkan kedua permukaan secara bersamaan.
17. Sekolah Tinggi Penerbangan Indonesia
Curug, Kab. Tangerang, Banten.
Introduction
Flight Control
System
Flight Control
Theodery MR – Chapter 5
Primary Flight
Control
Secondary Flight
Control
Autopilot & Chapter
Summary
Credits
B. Flaps
• Flaps adalah perangkat paling umum sebagai daya angkat
yang digunakan pada pesawat. Permukaan ini, melekat di
trailing edge sayap, meningkatkan daya angkat dan daya
hambat untuk setiap AOA yang diberikan. Flaps
memungkinkan kompromi antara kecepatan jelajah tinggi dan
kecepatan landas rendah, karena dapat diperpanjang bila
diperlukan, dan ditarik ke dalam struktur sayap ketika tidak
diperlukan. Ada empat jenis umum flaps: polos, split, slotted,
dan Fowler flaps.
Click to
see the
picture
18. Sekolah Tinggi Penerbangan Indonesia
Curug, Kab. Tangerang, Banten.
Introduction
Flight Control
System
Flight Control
Theodery MR – Chapter 5
Primary Flight
Control
Secondary Flight
Control
Autopilot & Chapter
Summary
Credits
19. Sekolah Tinggi Penerbangan Indonesia
Curug, Kab. Tangerang, Banten.
Introduction
Flight Control
System
Flight Control
Theodery MR – Chapter 5
Primary Flight
Control
Secondary Flight
Control
Autopilot & Chapter
Summary
Credits
C. Leading Edge Devices
• Perangkat berdaya angkat tinggi juga
dapat diterapkan ke tepian airfoil.
Jenis yang paling umum adalah fixed
slot, moveble slot, leading edge flaps,
dan cuffs.
Click to
see the
picture
20. Sekolah Tinggi Penerbangan Indonesia
Curug, Kab. Tangerang, Banten.
Introduction
Flight Control
System
Flight Control
Theodery MR – Chapter 5
Primary Flight
Control
Secondary Flight
Control
Autopilot & Chapter
Summary
Credits
21. Sekolah Tinggi Penerbangan Indonesia
Curug, Kab. Tangerang, Banten.
Introduction
Flight Control
System
Flight Control
Theodery MR – Chapter 5
Primary Flight
Control
Secondary Flight
Control
Autopilot & Chapter
Summary
Credits
D. Spoilers
• Spoilers berfungsi untuk mengurangi lift dan
menambah drag.
• Spoilers juga dapat
berfungsi untuk
mengurangi
ground roll ketika
landing.
22. Sekolah Tinggi Penerbangan Indonesia
Curug, Kab. Tangerang, Banten.
Introduction
Flight Control
System
Flight Control
Theodery MR – Chapter 5
Primary Flight
Control
Secondary Flight
Control
Autopilot & Chapter
Summary
Credits
E. Trim System
• Trim system biasa digunakan untuk membantu
pilot dalam mempertahankan tekanan secara
konstant pada flight control.
Biasanya terdiri dari flight deck control dan
perangkat yang berengsel kecil yang melekat pada
trailing edge.
23. Sekolah Tinggi Penerbangan Indonesia
Curug, Kab. Tangerang, Banten.
Introduction
Flight Control
System
Flight Control
Theodery MR – Chapter 5
Primary Flight
Control
Secondary Flight
Control
Autopilot & Chapter
Summary
Credits
F. Trim Tabs
• Trim Tabs berguna untuk mempermudah pergerakan
primary control. Ex : Elevator, Rudder, dan Aileron.
• Berguna untuk mengurangi AoA (Angle Of Attack atau
Climb Angle) juga, agar pada saat crusing, pesawat tetap
stabil ketinggianya.
24. Sekolah Tinggi Penerbangan Indonesia
Curug, Kab. Tangerang, Banten.
Introduction
Flight Control
System
Flight Control
Theodery MR – Chapter 5
Primary Flight
Control
Secondary Flight
Control
Autopilot & Chapter
Summary
Credits
G. Balance Tabs
• Balance Tabs berfungsi untuk mengurangi power control apabila
terlalu tinggi.
• Bentuknya balance tabs hampir sama dengan tab trim, hanya saja
pergerakannya yang berlawanan arah dengan Control Surface.
25. Sekolah Tinggi Penerbangan Indonesia
Curug, Kab. Tangerang, Banten.
Introduction
Flight Control
System
Flight Control
Theodery MR – Chapter 5
Primary Flight
Control
Secondary Flight
Control
Autopilot & Chapter
Summary
Credits
H. Antiservo Tab
• Antiservo tab berfungsi untuk
meningkatkan stabilitas dan
dapat mengontrol berat.
• Pergerakan dari Antiservo Tab
berlawanan dengan
Servo Tab.
26. Sekolah Tinggi Penerbangan Indonesia
Curug, Kab. Tangerang, Banten.
Introduction
Flight Control
System
Flight Control
Theodery MR – Chapter 5
Primary Flight
Control
Secondary Flight
Control
Autopilot & Chapter
Summary
Credits
I. Ground Adjustable Tab
• Banyak diantara pesawat-pesawat kecil yang memiliki Trim
Tab yang tidak bergerak pada bagian Ruddernya.
• Tab ini biasanya dibengkokan dalam satu arah atau
ditancapkan di tanah untuk menerapkan kekuatan trim pada
kemudi.
27. Sekolah Tinggi Penerbangan Indonesia
Curug, Kab. Tangerang, Banten.
Introduction
Flight Control
System
Flight Control
Theodery MR – Chapter 5
Primary Flight
Control
Secondary Flight
Control
Autopilot & Chapter
Summary
Credits
J. Adjustable Stabilizer
• Alih-alih menggunakan tab bergerak pada trailing edge dari lift,
beberapa pesawat memiliki adjust stabilizer. Dengan pengaturan ini,
hubungan poros horizontal stabilizer pada spar di belakangnya. Hal
ini dicapai dengan penggunaan jackscrew yang dipasang di leading
edge stabilator.
• Pada pesawat kecil, jackscrew adalah kabel dioperasikan dengan trim
wheels atau engkol (crank). Pada pesawat yang lebih besar disebut
motor driven.
28. Sekolah Tinggi Penerbangan Indonesia
Curug, Kab. Tangerang, Banten.
Introduction
Flight Control
System
Flight Control
Theodery MR – Chapter 5
Primary Flight
Control
Secondary Flight
Control
Autopilot & Chapter
Summary
Credits
Autopilot
Autopilot adalah control otomatis sistem pesawat untuk menjaga level
flight atau untuk mengatur rangkaian. Autopilot dapat langsung di
aktifkan oleh pilot, atau bisa digabungkan pada sinyal radio navigasi.
Autopilot mengurangi phisic dan mental seorang pilot tapi
meningkatkan keselematan penerbanganya. Fitur yang biasanya tersedia
pada autopilot adalah altitude (ketinggian) dan heading hold.
29. Sekolah Tinggi Penerbangan Indonesia
Curug, Kab. Tangerang, Banten.
Introduction
Flight Control
System
Flight Control
Theodery MR – Chapter 5
Primary Flight
Control
Secondary Flight
Control
Autopilot & Chapter
Summary
Credits
Chapter Summary
• Karena sistem kontrol penerbangan dan
karakteristik aerodinamis sangat bervariasi antara
pesawat, maka itu penting bahwa pilot harus
sudah familiar dengan sistem kontrol pesawat
primer dan sekunder.
• Sumber informasi utama ini adalah AFM atau POH.
Berbagai produsen dan kelompok pemilik website
juga bisa menjadi sumber informasi tambahan
yang berharga.
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30. CREDITS
Sekolah Tinggi Penerbangan Indonesia
Curug, Kab. Tangerang, Banten.
Introduction
Flight Control
System
Flight Control
Theodery MR – Chapter 5
Primary Flight
Control
Secondary Flight
Control
Autopilot & Chapter
Summary
Credits