ANALYSIS OF CHANGES IN BURNING RATE COEFFICIENT (A) ON 1HE BURNING RATE OF PROPELLANT BASED ON PARTICLE SIZE ALUMINUM

Image of ANALYSIS OF CHANGES IN BURNING RATE COEFFICIENT (A) ON 1HE BURNING RATE OF PROPELLANT BASED ON PARTICLE SIZE ALUMINUM
Abstract
Propellant made by LAPAN basically consists of raw materials HTPB (Hydroxy Terminated Polybutadiene) and TDI (toluene diisocyanate) as Binder and Curing Agent, Ammonium Perchlorate or AP as oxidizing agents and Aluminum Powder as additive. Aluminumpowderin the form offine powderwhichhas acertainparticlesize. Frompropellantburningrate measurements, it wasobtainedthat thealuminurnparticlesizeaffects theburning rate coefficientvalue. Burning rate of propellant was measured using the Strand Burner instrument. Propellant burning rate was conducted with 3 different Aluminium Powder particle sizes 100, 30 and
Informasi Detil
Judul Seri -
No. Panggil -
Penerbit Indonesia Book Project : Jakarta.,
Deskripsi Fisik ;Il.; 28 Cm.Hal. 57-66
Bahasa English
ISBN/ISSN 978-602-70353-4-8
Klasifikasi NONE
Edisi Aeronautic and Space Technology....
Subyek propelant
burning rate coerricient
particle size
Pernyataan Tanggungjawab
Pusat Teknologi Roket
Versi lain/terkait
JudulEdisiBahasa
Aeronautic and Space Technology : Research and Engineering of Unmanned Aerial ,Vechicle, Rocket, and Satelliteen
DESIGN AND ANALYSIS OF MAIN LANDING GEAR FRAME OF LSU-05 BY FINITE ELEMENT METHODEAeronautic and Space Technology....en
DESIGN REQUIREMENT ANALYSIS OF LAPAN ELECTRO HYBRID AIRCRAFTAeronautic and Space Technology....en
PRELIMINARY FUNCTIONAL HAZARD ANALYSIS FOR ELECTRONIC SYSTEM OF THE LSA-02 AIR CRAFT FLIGHT CONTROL SYSTEM FOR LONGITUDINAL MOTIONAeronautic and Space Technology....en
DESIGN AND PERFORMANCE ANALYSIS OF AEROSPIKE NOZZLE USING COMPUTATIONAL FLUID DYNAMICSAeronautic and Space Technology....en
THE COMPARISON BETWEEN THEORETICAL AND ACTUAL MEASUREMENT OF TEMPERATURE AT RX 3240 ROCKET EXIT WALL NOZZLEAeronautic and Space Technology....en
SIMULATION OF EMC BY USING MOBILE PHONE FREQUENCY FOR SENSOR OUTPUT DATA ACCELEROMETER MMA7361 CONNECTED WITH MAXSTREAM 900M HZAeronautic and Space Technology....en
ANALYSIS OF THE FUEL BINDER ISOMERS TO IMPROVE THE QUALITY OF THE\' PROPELLANTAeronautic and Space Technology....en
EVALUATION OF MOTOR ROCKET RX-450 WITH RADIOGRAPHIC TESTING METHODEAeronautic and Space Technology....en
BURN RATE DETERMINATION FROM THE STATIC TEST RESULTSAeronautic and Space Technology....en
DESIGN AND PERFORMANCE PREDICTION OF SOLID ROKET MOTOR FOR RX450 BALLISTIC ROCKETAeronautic and Space Technology....en
AERODYNAMIC DESIGN OF IMPULSE TURBINE FOR LIQUID ROCKET TURBOPUMP RCX2000H1Aeronautic and Space Technology....en
INTERFEROMETRIC SYNTHETIC-APERTURE RADAR (INSAR) TO MAPPING THE TROPICSAeronautic and Space Technology....en
GEOMETRIC AND RADIOMETRIC CORRECTION SATELLITE IMAGE PROCESSING STUDY CASEAeronautic and Space Technology....en
ANALYSIS OF TEMPERATURE ON ORBIT SATELLITEAeronautic and Space Technology....en
ANALYSIS OF TEMPERATURE CHANGES ON SOLAR PANELS EFFICIENCY OF LAPAN A-2 SATELLITEAeronautic and Space Technology....en
FURTHER ANALYSIS OF LAPAN TUBSAT SATELLITE ANOMALY USING SPACE WEATHER PARAMETERSAeronautic and Space Technology....en
SPECTRUM TRANSMITTANCE IN VISIBLE WAVELENGTH REGION OF ALUMINUM THIN FILM DEPOSITED ON GLASS BK7 MADE USING VACUUM EVAPORATION METHODAeronautic and Space Technology....en
Lampiran Berkas
Komentar

Pilih Bahasa

Tipe Koleksi Dipublikasikan

Tipe Koleksi Tidak Dipublikasikan.

Advanced Search

License

This software and this template are released Under GNU GPL License Version 3.