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2019, vol. 69, br. 2, str. 8-16
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Uticaj cikličnih opterećenja na strukturna oštećenja pogonskih punjenja raketnih motora
Effect of cyclic loads on structural damage of rocket propellant grain
Sažetak
Pogonsko punjenje raketnog motora, direktno liveno ili vezano za komoru ili čvrstu oblogu, izloženo je različitim opterećenjima tokom veka upotrebe. Raketno gorivo je viskoelastični materijal, čije mehaničke osobine značajno zavise od temperature i brzine deformacije. Dejstvo cikličnih opterećenja, pre svega termičkih, na raketni motor na skladištu, može da izazove neželjena oštećenja pogonskog punjenja. Vremenom, posle dugog skladištenja, nagomilana oštećenja mogu da porastu toliko da izazovu lom punjenja. Jedan od načina da se proceni ova pojava je da se odredi zakon akumulacije oštećenja. U ovom primeru, zakon je određen za jedan sastav kompozitnog raketnog goriva na bazi hidroksi-terminiranog polibutadiena (HTPB), izlaganjem njegovih uzoraka različitim dugotrajnim naprezanjima. Pomoću ovog zakona moguće je izračunati verovatnoću loma i vremensku promenu strukturne pouzdanosti pogonskog punjenja, sa ciljem da se proceni vek upotrebe. Pored toga, analiza je pokazala da postoji moguća korelacija zakona akumulacije oštećenja i zatezne čvrstoće. Ova činjenica može da se iskoristi umesto izvođenja dugotrajnog eksperimenta kojim se precizno određuje zakon akumulacije oštećenja.
Abstract
Rocket motor propellant grain, cast or bonded into the motor chamber or solid coating, is exposed to various loads during its service life. Rocket propellant is a viscoelastic material, whose mechanical properties strongly depend on temperature and strain rate. Application of cyclic loads, primarily thermal, onto a rocket motor on the field stock, may cause an undesirable mechanical damage of the grain. Over time, after long storage, it may grow up and lead to the grain failure. One of the ways for evaluation of this phenomenon is to determine a cumulative damage law. In this example, this law has been evaluated for hydroxy terminated polybutadiene (HTPB) composite rocket propellant by exposing a number of specimens to different long term stress levels. Using this law, it is possible to calculate a probability of failure and time distribution of the structural reliability of the grain in order to determine the useful life. Besides, the analysis has shown that there is a possible correlation between tensile strength of the propellant and the cumulative damage law. This fact can be used instead of carrying a longterm experiment for the exact determination of the law.
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