7104 research outputs found
Sort by
Development Of Flight Control Laws For The Basic Electronic Flight Control System of the LSA-02 Tecnology Demonstrator Aircraft
No full textThe usage of light utility high aspect ratio aircraft with payload up to 350kg is deemed to be an economical solution for many particular purposes especially civil airborne surveillance. The Electronic Flight Control System (EFCS) is supplemented to the basic aircraft and shall have full authority to replace pilot work. The basic aircraft which is equipped wit EFCS is called LAPAN Surveillance Aircraft (LSA-02). In order to realize the full authority control system, the EFCS has to be highly reliable and safe. In addition, the EFCS shall enable the aircraft to precisely follow predefined trajectories, to stabilize during disturbed atmospheric flight and to conduct experimental flight functions. The Flight Control Laws (FCL) as part of EFCS ave purposes to control, guide and navigate aircraft through specific pilot commands via the Flight Control Panel (FCP). The work in this thesis has an objective to develop reliable FCL for te EFCS of LSA-02. The development method of FCL shhall follow a very strict development process namely the V model as the flight control functions are safety critical.The development process starts from the requirements definition, followed by the FCL design and ended by the verification of the FCL design. The design of the FCL comprises of inner loops whose purpose is to stabilize and control the aircraft attitude and outer loops whose purpose is to control the flight path of the aircraft. The commands from FCP consist of airspeed, altitude, vertical speed, flight path inclination angle and heading. The responses of te aircraft shall be analyzed with regard to the FCP commands. The conclusions drawn from the result the thesis work are the development of FCL for basic EFCS hhas been completed, the design architecture which applies cascade structure and modularity concept provides solution to design the FCL.Xiii, 129 hlm. : ill. ; 28 c
IEEE International Conference on Aerospace Electronics and Remote Sensing Technology (ICARES)
No full text
Jurnal Sains Dirgantara = Journal of Aerospace Sciences Vol. 15 No.2 Juni 2018
No full textHlm.63-116.,ill.;30 c
No full textAbstractThe characteristic model of MUS-01 wing structure testing has been performed. Planned, this model will be used as an unmanned wing of the LSU-03NG. The test model is made of composite type e-glass. At the time of testing the structure test model is loaded according to MTOW weight. This research method also involves the unmanned aircraft mission, especially on the model test structure, model dimension, and direct experiment in the form of loading on the test model. The result of characterization of the test model during test, showed that the indicated test model has the characteristics as a test model that is unable to accept the unmanned operational load of LSU-03NG series aircraft. So it can not be used as a consideration for the structure of the unmanned aircraft.Hal. 93-10
Desain Dan Analisis Struktur Baling-Baling Pesawat LSU-03 Menggunakan Material Komposit
No full textXvii, 87 hlm
Analysis of Antenna Specification For Very High Resolution Satellite Data Acquisition Through Direct Receiving System (DRS)
No full textVery High Resolution Satellite Image (VHRSI) data for Indonesian Government license is required by ministries/agencies, TNI, police, and local government to support national programs. But Indonesia did not have a VHRSI data recipient facility to directly acquire this data. In accordance with Law 21/2013 on Space, LAPAN is mandate to provide high resolution satellite data, and based on a roadmap for provision of satellite data in 2017, LAPAN will provide a VHRSI data reception facility through direct receiving system (DRS). This will be more efficient than other methods in providing the data. Priority provision of satellite data is for acquiring Pleiades and TerraSAR-X operating in the frequency range 8 GHz (X-Band). Therefore, to receive both data, it requires antenna subsystem with optimum coverage throughout Indonesia. Parameters to obtain the minimum antenna specifications include Free Space Loss (FSL), Carrier to Noise Ratio (C/No) and Antenna Gain to Noise Temperature (G/T). The calculation of G/T antenna is done for both satellites based on satellite parameters and analysis of antenna product availability in the market. Based on the calculation of satellite parameters shows that the minimum G/T value with the elevation of 5 degrees is 27.71 dB/K for Pleiades data reception and the minimum G/T value of 26.10 dB/K for the TerraSAR-X data reception. In general, the minimum G/T value for receiving the Pleiades and TerraSAR-X data is at 28 dB/K. While based on the calculation of antenna products availability in the market is require G/T value of 33.45 dB /K for the elevation of 5 degrees with a diameter of 7.5 mm antenna. This can be conclude that the antenna products meets the minimum requirements specification and to receive both satellite data. However, both calculation for the antenna subsystem still will be evaluated further in order to be directly installed at Parepare Remote Earth Station (SPBJ), South Sulawesi.Hlm. 113-13
OPTIMALISASI DIMENSI REFLEKTOR UNTUK MENINGKATKAN PENGUATAN ANTENA HELIKS OPTIMIZATION OF GROUND PLANE DIMENSIONS TO INCREASE HELICAL ANTENNA GAIN
No full textHlm. 68-7
Simulasi Pengaruh Statik Marjin Pada Arah Memutar Trayektori Roket (Simulation Of Static Margin Effect To Directional Rocket Trajectory)
No full textPaper ini mempelajari hubungan antara static margin, directional stability dan strategi belok menggunakan bank-to-turn yang diaplikasikan pada roket kendali, dalam hal ini rudal. Simulasi difokuskan kepada fase terbang wahana rudal MY-ROCK 122 yang melakukan manuver belok tajam secara horizontal. Dari riset ini, roket yang terkendali mengalami peningkatan jarak jangkau longitudinal secara signifikan, meski penambahan jarak terbang akan direpresentasikan dalam bentuk gerakan memutar. Radius putar minimum digunakan sebagai parameter untuk melihat kualitas prestasi terbang dan rudal. Dalam riset ini ditemukan bahwa radius putar minimum dapat diraih jika kita menggunakan rentang static margin yang sempit, dan selanjutnya rentang ini dapat memberikan jarak yang maksimum juga di sumbu longitudinal. Penempatan titik pusat gravitasi menjadi fase paling fundamental untuk menghasilkan desain rudal yang sukses dari segi aerodinamika dan dan segi controllability. Kata kunci : static margin, directional stability, strategi belok bank-to-turn, manuver belok tajamHlm. 191-19
Modifikasi Digital Elevation Model (DEM) Citra Resolusi Tinggi Menggunakan Fusi Interferometri SAR Dan Stereosar Berbasis Faktor Pembobotan = DEM Modification Using Fusion Of SAR Interferometri And Stereosar Based On Weighting Factor
No full textSensor satelit SAR mampu mengukur elevasi permukaan bumi menggunakan metode interferometri (InSAR) atau radargrametri (StereoSAR). Metode InSAR memanfaatkan fase dari citra SAR, sedangkan StereoSAR menggunakan nilai amplitudo untuk menghasilkan elevasi permukaan bumi. Kedua metode mempunyai kelebihan dan kekurangan. Beberapa permasalahan adalah akurasi rendah DEM menggunakan InSAR citra SAR di area bayangan dan singgahan, sedangkan pada metode kedua, permasalahan muncul jika korelasi silang antara kedua citra rendah. Makalah ini mengajukan metode penggabungan citra DEM InSAR dan StereoSAR untuk pembuatan citra DEM baru menggunakan citra SAR resolusi tinggi. Pasangan citra TerraSAR-X atau TanDEM-X dengan sudut datang 21 derajat digunakan dalam penelitian ini, diolah menggunakan metode InSAR dan sepasang citra dengan sudut masing-masing 21 derajat dan 41 derajat menggunakan metode StereoSAR di area Bandung dan sekitarnya. Hasil eksperimen menunjukkan bahwa DEM fusi kedua metode tersebut mempunyai akurasi yang lebih baik, dengan kesalahan absolut lebih kecil dari pada masing-masing metode InSAR dan StereoSAR, secara terpisah yaitu meningkat sebesar 3.48 m dan 1.80 m.Hlm. 83-9