42 research outputs found
Metoda Short Takeoff Landing (Studi Kasus Prestasi Terbang Takeoff-Landing Pesawat Udara Turbo Prop CN235)
No full textPesawat dengan kategori Short Take-Off Landing pada umumnya adalah pesawat ringan yang mempunyai berat take-off antara 20.000 lb (9.072 kg) hingga 50.000 lb (22.680 kg) dengan kemampuan melewat irintangan setinggi 50 ft (15 m) untuk jarak take-off dan landing sejauh 1.500 ft (450 m). Pengembangan pesawat dengan kategori tersebut perlu memperhatikan tiga persyaratan umum yaitu kemampuan aerodinamika yang tinggi, tenaga mesin yang besar, dan teknik pilot yang baik yang disertai dengan kekuatan struktur yang mampu menahan beban berat. Pada studi kasus ini, penulis menggunakan data prestasi terbang Short Field Landing pesawat CN235-100 (serial N-16) dengan menggunakan flap 230 pada saat pengujian performance trade-off di PT Dirgantara Indonesia pada tahun 1996. Pengujian tersebut juga termasuk uji rejected take-off atau accelerate stop distance dengan menggunakan flap 100 pada tenaga penuh dimana kemudian salah satu mesin dimatikan untuk mencapai kondisi kritis dan pilot mengurangi daya propulsi mesin lainnya untuk dapat berhenti di ujung landasan. Beberapa rekomendasi pilot diberikan pada bagian kesimpulan.
[The Short Takeoff Landing Method (CN235 Turbo Prop Field Performance Test Case Study)] The aircraft category of Short Take-Off Landing, in general, including lightweight aircrafts with take-off weight between 20.000 lb (9.072 kg) and 50.000 lb (22.680 kg) and capable in exceeding 50 ft (15 m) obstacle height with only 1.500 ft (450 m) of take-off and landing distance. Thera are, at least, three general requirements that have to be considered in order to develop this category of aircraft; high aerodynamic performance, powerful engine, qualified skill of pilot, and also the strength of aircraft structure that can sustain heavy load.As for the study case, the author used the flight performance data of CN235-100 (serial N-16) Short Field Landing with 230 flap that was tested in Indonesian Aerospace Industry in 1996 for its trade-off performance. There was also rejected take-off or accelerate stop distance test with 100 flap and full throttle where one of the engine, then suddenly, shut down in order to achieve critical condition and later the power of the another engine being reduced by the pilot so that the aircraft can stop at the end of the runway. Several pilot recommendations are given in the conclusion chapter.</jats:p
Karakteristik Aerodinamika Flying Boat pada Ketinggian Ground Effect (Studi Kasus Model Remote Control Flying Boat Pada Ketinggian 0,2 m dan 1 m)
No full textThe paper presents an analysis of the flight performance and stability
and control of a Flying Boat remote control model on the ground effect altitude. It begins with a three dimensional measurement of a Flying Boat remote control model by using a laser tracking photo camera and a drawing software. The 3 D model was drawn by solid drawing on the CATIA software. The 3 D model was analyzed by using computational fluid dynamics CFx AnSys due to the rectangular wing with dihedral configuration with NACA 23012 airfoil. The maximum takeoff weight is around 25.0 kg powered with a single engine propeller, 5.5 HP. The surface effect phenomena of the Flying
Boat remote control model was simulated by using CFx omputational Fluid Dynamics software, AnSys with the airspeed, V = 35.0 knots and shows a good results at the altitude of 20.0 cm. The longitudinal static stability analysis provides a good result at 1.0 meter altitude. Simulations were performed to the PUNA “Alap alap” flight performance test during cruise at 7800 feet as data verification. The adaptive ground effect control system is solved by transfer function equation matrix.
Keywords: Flying Boat, remote control model, ground effect altitude.

Makalah ini berisikan analisis prestasi terbang dan kestabilan dari
pesawat remote control model jenis Flying Boat pada ketinggian terbang ground effect. Pada awalnya, dilakukan pemotretan 3 D terhadap pesawat model Flying Boat menggunakan kamera laser beserta piranti lunak pendukung dan kemudian menggunakan solid drawing pada program CATIA. Model 3D dianalisis dengan menggunakan piranti lunak CFx AnSys untuk keseluruhan badan dan sayap dengan airfoil jenis NACA 23012. Karakteristik dinamik dari pesawat model dengan MTOW = 25.0 kg dengan power 5.5 HP terlihat dengan baik pada ketinggian terbang 20.0 cm dengan
kecepatan, V = 35.0 knots. Sedangkan, analisis kestabilan statik matra longitudinal terlihat dengan respons waktu (t) yang baik pada ketinggian terbang 1.0 meter. Simulasi terbang menampilkan uji prestasi terbang pesawat nir awak PUNA “Alap alap” saat cruise pada ketinggian 7800 feet sebagai data verifikasi. Model matematika sistem Kendali Terbang Adaptif Ground Effect dianalisis dengan matriks persamaan fungsi transfer.
Kata kunci: Flying Boat, remote control model, ketinggian terbang
ground effect.</jats:p
Analisis Sistem Kendali Terbang dengan Gain Scheduling Pada Pesawat Efek Permukaan
Get PDFThis paper provides an overview of the design of adaptive flight control system of wing in surface effect craft Lippisch configuration 8 passengers capacity during cruise in the low speed and low altitude. The control system will be used the control surface, such as elevator deflection as input and pitch angle deflection as output response or by using engine throttle setting as input and others output response in the longitudinal mode. This paper describes some methodologies control system method and analysis such as PID controller system with gain scheduling approach, and root locus method. The observable matrices (4 x 4) on the longitudinal mode that used in the control system became from aerodynamic derivative parameters of 8 seaters configuration that calculated by DATCOM numerical simulation or wind tunnel test result and dummy data.
Kajian ini merupakan rancangan sistem kendali terbang adaptif pada pesawat efek permukaan konfigurasi Lippisch kapasitas 8 orang saat terbang mendatar pada kecepatan dan ketinggian terbang rendah. Sistem kendali terbang yang digunakan, seperti defleksi elevator sebagai input dan defleksi sudut pitch sebagai respon output atau penggunaan defleksi throttle mesin sebagai input dan parameter respon output lain pada gerak matra longitudinal. Kajian menjelaskan penggunaan beberapa metodologi dan analisis sistem kendali terbang adaptif, seperti kontroler PID dengan pendekatan gain scheduling, dan metoda root locus. Matriks ruang keadaan berukuran (4 x 4) pada matra longitudinal yang digunakan pada sistem kendali terbang adaptif diperoleh dari parameter turunan aerodinamika hasil perhitungan numerik DATCOM atau hasil uji terowongan angin dan data dummy.</jats:p
Simulasi dan Verifikasi Prestasi Terbang Model Remote Control Flying Boat Saat Hidroplaning
No full textPesawat Wing In Surface Effect A2B tipe B konfigurasi Lippisch mempunyai hambatan air yang cukup besar dibandingkan tenaga mesin saat hydroplaning. Makalah ini berisikan bagian dari analisis dalam perancangan untuk mengetahui karakteristik aerodinamika dan hidrodinamika dari remote control model jenis Flying Boat pada fase hydroplaning. Pada awalnya, dilakukan pemotretan 3D terhadap pesawat model Flying Boat menggunakan kamera laser untuk menghasilkan solid drawing pada program CATIA. Model 3D dianalisis dengan menggunakan piranti lunak CFx pada program AnSys. Planform sayap, memiliki dihedral dan menggunakan airfoil jenis NACA 23012. Karakteristik aerodinamika dan hidrodinamika untuk model 3 D dipresentasikan pada posisi sudut alpha =00. Sedangkan kecepatan yang digunakan adalah 0 sampai25 knots. Untuk memverifikasi data hasil simulasi, digunakan data uji terbang pesawat udara tanpa awak Alap-alap yang mempunyai T/W rasio yang sama, yaitu sudut pitch, kecepatan arah sumbu Z pada sumbu benda, ketinggian dan kecepatan. Gaya angkat aerodimaka arah sumbu Z pada simulasi RC model Flying Boat sebanding dengan gaya angkat aerodinamika arah sumbu Z pada UAV Alap-alap saat take off.
[The Hydroplaning Flight Performance Simulation and Verfication of a Flying Boat Remote Control Model] The Wing in Surface Effect Aircraft A2B type B with Lippisch configuration has higher hydrodynamics drag compared to engine powered aircraft during hydroplaning. This paper explains parts of analysis in aircraft design to identify the aerodynamics and hydrodynamics characteristics of flying boat remote control model during hydroplaning phase. At first, flying boat model was three dimensional photographed using laser camera in order to produce solid drawing for CATIA program. The three dimensional model, later, analyzed by using CFx software in AnSys program. The wing planform has dihedral angle while the airfoil used is NACA 23012. The aerodynamics and hydrodynamics characteristics of this three-dimensional model is represented for alpha =00. Whilst the speed used in simulation was 0 to 25 knots. In verifying the data of the simulation results, the Unmanned Aerial Vehicle UAV Alap-alap flight test data was used in which it has the same T/W ratio for the pitch angle, acceleration in Z body axis, altitude, and speed. The aerodynamics lift in Z axis of flying boat model during simulation is proportional to the aerodynamics lift in Z axis of UAV Alap-alap during take-off.</jats:p
Gaya Hambat Saat Hidro Planing dan Gaya Angkat Aerodinamika Saat Cruise di Efek Permukaan pada Pesawat Wing in Surface Effect
No full textPerhitungan komputasional dinamika fluida pada model 3 Dimensi pada pesawat Wung In Surface Effect sangat penting untuk mengetahui data hasil uji towing tank dan uji terbang. Konfigurasi Lippisch mempunyai sayap berbentuk inverse delta dan punuk di atasnya menggunakan airfoil jenis Clark Y yang telah dirancang untuk memenuhi karakteristik efek permukaan. Piranti lunak pertama Maxsurf digunakan untuk membandingkan hasil uji model towing tank saat fase hydro planing. Piranti lunak kedua ANSYS CFX digunakan untuk menghitung gaya hambat air dan gaya angkat aerodinamika dari pesawat Wing In Surface Effect kapasitas 8 orang model 3 Dimensi dengan konfigurasi Berat Maksimum saat take off sebesar 32000 Newton pada kecepatan cruise 80 knots pada ketinggian terbang 2.5 meter. Aspek eksperimen pada uji model towing tank dan data uji terbang pada prototipe pesawat Wing In Surface Effect kapasitas (1-2) orang saat hydro planing dijelaskan dengan menggunakan teori gelombang hidrodinamika dan porpoising efek.
[The Hump Drags During Hydro planing and Aerodynamic Lift During Cruise in Surface Effect Altitude Of Wing in Surface Effect Craft] The computational fluid dynamics of 3 Dimensions model of Wing in Surface Effect craft is very important to proof the model towing test and flight testing data. The inverse delta wing and shoulder airfoil is by using Clark Y of Lippisch configurations have been designed for the surface effect characteristics. The first Maxsurf software are used to compared the towing test results during hydro planing phase. The second ANSYS CFX software is used to calculate the hump drags and aerodynamic lift of Wing In Surface Effect craft 8 seaters 3 Dimensions model to verified the Design Requirement and Objectives. The forces equilibrium on the body axis during hydro planing are very important to fulfill the take off phase on the water surface. And, the aerodynamic lift for Maximum Take off Weight of 8 seaters configuration is 32000 Newton during cruise speed at 80 knots on the 2.5 meter altitude. The experimental aspects of towing tank test model and Wing In Surface Effect craft (1-2) seaters prototype during hydro planing test have been proposed by using the hydrodynamic wave and porpoising effect theory.</jats:p
Kajian Perilaku Pesawat WISE L8 Dan Verifikasi Sistem Kendali Terbang Adaptif
Get PDFDisertasi ini menyampaikan pembahasan tentang kajian perilaku pesawat WISE L8 dan verifikasi sistem kendali terbang adaptif yang diusulkan untuk diterapkan di kemudian hari. Dalam aspek perilaku secara khusus akan disampaikan intensitas gaya-gaya angkat-hambat hidrodinamika dan aerodinamika, gaya propulsi, gaya berat saat bergerak pada fase high speed water run, hydro planing dan mengudara di surface effect. Masalah kriteria terbang, diselesaikan melalui komputasional dinamika fluida CFD terhadap gambar 3-D CATIA, sehingga diperoleh distribusi tekanan P di sekitar permukaan sayap, badan dan permukaan air di surface effect. Pada bagian ini, juga dilakukan analisis downwash dan vortex yang terjadi di sekitar permukaan sayap dan permukaan air, di mana terlihat aliran udara dengan masing-masing intensitas yang bergerak mengitari sayap menuju ujung luar sayap dan winglet. Hal inilah yang menimbulkan bantalan udara dinamika antara permukaan air atau tanah dengan permukaan bawah sayap. Perhitungan komputasional dinamika fluida CFD terhadap gambar 3-D CATIA pesawat WISE L8 menggunakan input data inersia massa menghasilkan daya propulsi EHP= 299.73 HP, kecepatan VCRUISE ≈ 80.0 knots dan ketinggian terbang di surface effect h = 2.50 m menghasilkan gaya angkat aerodinamika Laero = 33.524 kN dan gaya hambat aerodinamika Daero = 5.357 kN dengan berat pesawat WISE L8 W = 32,000 N sesuai dengan D R & O.
Perhitungan pergerakan pesawat WISE L8 fase high speed water run, hydro planing dan mengudara menghasilkan gaya propulsi dinamik Td, gaya gaya hidrodinamika, gaya gaya aerodinamika, kurva kecepatan versus waktu dan jarak take off oleh program Matlab. Pada bagian lain, dilakukan perhitungan pertumbuhan gaya gaya hidrodinamika, aerodinamika dan propulsi berdasarkan luas permukaan basah dan sarat saat hydro planing menurut metoda Savitsky melalui komputasional dinamika fluida CFD dengan model turbulensi k-ε serta perhitungan dengan program Matlab. Pengontrolan ketinggian terbang surface effect menggunakan defleksi elevator dan defleksi throttle mulai saat hydro planing sampai dengan pesawat WISE L8 mengudara sesuai dengan persyaratan take off masih memanfaatkan tenaga Pilot diperlihatkan oleh kurva diskontiniu.
Pemodelan matematik sistem kendali terbang adaptif pesawat WISE L8 dalam gerak matra longitudinal dengan matriks controller observable berukuran (4 x 4) pada kondisi terbang mendatar stasioner di efek permukaan. Analisis kestabilan dinamik matra longitudinal dengan sistem lingkar terbuka dan tertutup pada pesawat WISE L8 menggunakan program root locus dan kontroler Tune PID dengan gain scheduling di Matlab. Variasi penguatan KP, KD dan KI sebagai gain scheduling yang memberikan interaksi dari permukaan atur defleksi elevator δe dan defleksi throttle δth ke beberapa respons output (u, w, q dan θ) oleh servo pada sistem kendali terbang adaptif. Kemudian dilakukan verifikasi sistem kendali terbang adaptif menggunakan metoda neural networks dengan sistem SISO pada sistem lingkar tertutup, di mana input adalah defleksi elevator δe, atau defleksi throttle δth dengan respons output sudut pitch θ atau pitch rate q sebagai sistem kontrol otomatik Pitch Attitude Hold dengan memberikan error minimum antara input dan respons output pada keadaan steady.
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This dissertation discusses about the of WISE L8 craft behavior and adaptive control system verification that has been introduced and will be applicated in the future. On the behavior as, special aspect of the WISE L8 craft are being introduce the intensities of hydrodynamics and aerodynamics forces, thrust, weight during high speed water run, hydro planing and airborne phase in the surface effect. The flight criteria base on the computational fluid dynamic (CFD) analysis on the (three view drawing) 3D CATIA configuration to obtain the pressure distribution around the water and wing surface. Also, the investigations on downwash and vortex around the wing and water surface have been carried out the dynamic cushion. The CFD analysis on the model of WISE L8 with the mass inertia as input produces information on power engine EHP = 299.73 HP, cruise speed (Vcruise) = 80.0 knots, and surface effect altitude (h) = 2.50 m from the water surface to obtain the aerodynamic forces Laero = 33.524 kN and aerodynamic drag Daero = 5.357 kN with WISE L8 W maximum take off weight = 32,000 N in accordance with D R & O.
The calculation of the WISE L8 movement from high speed water run, hydro planing and airborne and takeoff distance starting from high-speed water run, hydroplaning and airborne has been calculated by Matlab. On the other hand, the hydrodynamic force, as well as aerodynamic force and thrust, are calculated considering the wetted surface area and draft during hydroplaning based on the Savitsky method using CFD and Matlab program. Note that the turbulence is approached using the k-ε model. The altitude during hydroplaning and airborne phase is controlled by deflecting elevator δe and throttle deflection δth. Some of the results are gave discontinue curve because the trayectory has been handled by the Pilot.
The mathematical model of adaptive flight control system of WISE L8 in the longitudinal plane uses observable matrix (4 x 4) at stationary cruise in surface effect. The analysis of the dynamic longitudinal stability of open and close loop for WISE L8 craft by using root locus method and PID controller with gain scheduling on the Matlab. The strengthening variation of KP, KD, KI as gain scheduling that governs the deflection of control surface (δe and δth) to response outputs (u, w, q, and θ) by the servo in the adaptive flight control system. And then, the verification of the control system uses the neural network method with the SISO close loop system with elevator deflection δe is input with pitch angle θ output response as Pitch Attitude Hold automatic control that gave minimum error between input and output steady state response
Karakterisktik Hidrodinamika dan Aerodinamika Pesawat WISE L8 Pada Saat Hydro Planing dan Mengudara Berdasarkan Perhitungan CFD
No full textThe Hydrodynamic and Aerodynamic Characteristics of WISE L8 During Hydro Planing and Airborne Base On CFD: This paper explains why the computational fluid dynamics is used on the model 3-D CATIA of Wing in Surface Effect craft WISE Lippisch configuration 8 seaters capacity for medium and high-speed conditions during hydro planing and airborne. The analysis stage on the calculation used the k-ε model turbulence with 1,690,862 mesh consists of 4 stages procedures that are ICEM, preprocessor, solver and convergence. On each programming stage that are gave the nominal value results. On this paper, there are showed the results of even keel and trimmed condition by using Savitsky method where the changes of trim angle τ (t) are being influence the hydrodynamic drag and total hydrodynamic force versus airspeed results. Based on this research, that propose for the Pilot using trim angle variation during takeoff procedure.
Paper ini menjelaskan mengapa diperlukan penggunaan programkomputasional dinamika fluida CFD terhadap model 3-D CATIA dari pesawat WISE L8 untuk kondisi kecepatan medium dan tinggi saat hydro planing dan mengudara. Pada proses perhitungan yang terdiri dari 4 tahap menggunakan model turbulensi k-ε dengan jumlah meshing sekitar 1,690,862, seperti ICEM, preprocessor, solver dan convergence. Pada setiap pemograman, diperoleh hasil konvergensi yang lebih baik. Pada paper ini diperlihatkan hasil perhitungan dengan dan tanpa menggunakan metoda Savitsky, di mana perubahan sudut trim (τ) mempengaruhi hasil pada gaya gaya hidrodinamika versus kecepatan. Hasil penelitian ini, menjadikan pegangan Pilot untuk menggunakan perubahan sudut trim saat melakukan prosedur take of
Gaya Hambat Saat Hidro Planing dan Gaya Angkat Aerodinamika Saat Cruise di Efek Permukaan pada Pesawat Wing In Surface Effect
Get PDFPerhitungan komputasional dinamika fluida pada model 3 Dimensi pada pesawat Wung In Surface Effect sangat penting untuk mengetahui data hasil uji towing tank dan uji terbang. Konfigurasi Lippisch mempunyai sayap berbentuk inverse delta dan punuk di atasnya menggunakan airfoil jenis Clark Y yang telah dirancang untuk memenuhi karakteristik efek permukaan. Piranti lunak pertama Maxsurf digunakan untuk membandingkan hasil uji model towing tank saat fase hydro planing. Piranti lunak kedua ANSYS CFX digunakan untuk menghitung gaya hambat air dan gaya angkat aerodinamika dari pesawat Wing In Surface Effect kapasitas 8 orang model 3 Dimensi dengan konfigurasi Berat Maksimum saat take off sebesar 32000 Newton pada kecepatan cruise 80 knots pada ketinggian terbang 2.5 meter. Aspek eksperimen pada uji model towing tank dan data uji terbang pada prototipe pesawat Wing In Surface Effect kapasitas (1-2) orang saat hydro planing dijelaskan dengan menggunakan teori gelombang hidrodinamika dan porpoising efek.
[The Hump Drags During Hydro planing and Aerodynamic Lift During Cruise in Surface Effect Altitude Of Wing in Surface Effect Craft] The computational fluid dynamics of 3 Dimensions model of Wing in Surface Effect craft is very important to proof the model towing test and flight testing data. The inverse delta wing and shoulder airfoil is by using Clark Y of Lippisch configurations have been designed for the surface effect characteristics. The first Maxsurf software are used to compared the towing test results during hydro planing phase. The second ANSYS CFX software is used to calculate the hump drags and aerodynamic lift of Wing In Surface Effect craft 8 seaters 3 Dimensions model to verified the Design Requirement and Objectives. The forces equilibrium on the body axis during hydro planing are very important to fulfill the take off phase on the water surface. And, the aerodynamic lift for Maximum Take off Weight of 8 seaters configuration is 32000 Newton during cruise speed at 80 knots on the 2.5 meter altitude. The experimental aspects of towing tank test model and Wing In Surface Effect craft (1-2) seaters prototype during hydro planing test have been proposed by using the hydrodynamic wave and porpoising effect theory
Desain dan Eksperimen Uji Getaran di Tanah dari Model Separuh Sayap Pesawat N219
No full textFenomena flutter merupakan salah satu fenomena yang kritis dan dapat membahayakan pesawat. Ketika, pesawat terbang semakin cepat dan mencapai kecepatan flutter, maka akan terjadi ketidakstabilan struktur. Oleh sebab itu, untuk menjamin keselamatan Pilot saat uji terbang, perlu dilakukan analisis awal pada kecepatan flutter. Uji terowongan angin selalu dilakukan untuk memvalidasi hasil dari analisis numerikal. Penelitian ini meliputi analisis program NASTRAN pada model separuh sayap pesawat N219 saat uji getaran di tanah. Prediksi kecepatan flutter secara analisis hampir sama dengan hasil uji terowongan angin. Parameter modus struktur yang ditemukan, seperti frekuensi natural, modus getar dan rasio redaman, dapat digunakan untuk analisis parameter flutter sebagai metoda analisis baru.
[The Design and Experiment of Ground Vibration Test of N219 Aircraft Half Wing Model] Flutter phenomena is a critical phenomenon that can be dangerous for aircraft. When an aircraft fly faster until reach flutter speed, the structure will become unstable. Therefore, it is important to conduct preliminary analysis of flutter speed to ensure the safety of Pilot. Wind tunnel test is necessary to be conducted to validate numerical analysis results. This research consist of NASTRAN software analysis of half wing model of N219 aircraft for ground vibration test. The prediction of flutter speed which is obtained from software analysis is similar with the wind tunnel test result. It is found that the modus parameter of structure like natural frequency, modus of vibration and damping ratio can be used on the parameter analysis as a new analysis method.</jats:p
