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- The experimentalresults proved that CdS is a better additive for lowering HTPB compositesolid propellant burning rate pressure exponent. 实验发现,硫化镉是一种较好的降低HTPB复合固体推进剂燃速压力指数的添加剂。
- The burning rate pressure exponent of GAP/AN propellant was high for the thermal decomposition characteristics of ammonium nitrate and easter nitrate(BG). 硝酸铵及硝酸酯的分解对压力比较敏感,是造成GAP/AN推进剂压强指数高的主要原因;
- When CdS was used withother burning rate catalyst as a mixture additive, it may obviously lowerpropellant burning rate pressure exponent and enhance propellant burning rate. 当硫化镉与其它燃速催化剂混合使用时,在提高推进剂燃速的同时,仍能达到较大幅度降低燃速压力指数的目的。
- The propellant containing DDI possess the long pot time of slurry, high mechanical properties at low temperature and low burning rate pressure exponents (compared with IPDI). 用作丁羟推进剂的固化剂;推进剂具有长的工艺使用期、好的低温力学性能和低的燃速压力指数.
- Keywords NEPE propellants;Burning rate pressure exponent;Combustion performance;Additive; NEPE推进剂;燃速压强指数;燃烧性能;添加剂;
- Keywords impulse thruster;solid propellant;modified double-base propellant;burning rate pressure exponent; 脉冲推力器;固体推进剂;改性双基推进剂;燃速压强指数;
- burning rate pressure exponent 燃速压力指数
- When FG and YB are incorporated, they may obviously reduce the pressure exponent of HTPB propellant as well as enhancing the burning rate. 当FG与亚铬酸铜组合使用时,可在提高推进剂燃速的同时大幅度地降低燃速压强指数。
- The effects of TMOs and their mixtures on the burning rate and the pressure exponent of the aluminum magnesium fuel rich propellant for unchoked ducted rocket are investigated. 研究了过渡金属氧化物(TMO)及其复配物对非壅塞固体火箭冲压发动机铝镁贫氧推进剂燃烧特性的影响。
- Keywords physical chemistry;nitramine propellant;burning behavior;burning rate;pressure exponent; 物理化学;硝胺发射药;燃烧性能;燃速;压力指数;
- Keywords composite solid propellant;hydroxy terminated polybutadiene propellant (HTPB);burning rate catalyst;pressure exponent; 复合固体推进剂;丁羟推进剂(HTPB);燃速催化剂;压力指数;
- The results show that ferrocene derivant (RMT) can effectively enhance burn rate of propellants and reduce its pressure exponent under high pressures; 结果表明:二茂铁衍生物(RMT)能大幅提高推进剂燃速和降低高压燃速压强指数。
- Numerical Simulation of the Burning Rate Pressure Index of Nitramine Modified Double Based Propellants 硝胺改性双基推进剂燃速压力指数的数值模拟
- Keywords Nitramine modified double based propellant;Burning rate pressure index;Numerical simulation;Combustion mechanism;Combustion model; 硝胺改性双基推进剂;燃速压力指数;数值模拟;燃烧机理;燃烧模型;
- Keywords burning rate;burning rate pressure index;combustion chemical kinetics;combustion mechanism;NQ propellant;numerical modeling.; 燃烧动力学;燃速压力指数;数值模拟;硝基胍发射药;
- Figure 8 -- Burn rate as function of O/F ratio. 图8 -烧伤率为功能的 O / 空燃比。
- The fuel rich propellant used for the unchoked ram rocket should has high burning rate exponent, appropriate burning rate, low flammability limit and steady combustion properties. 分析结果表明:非壅塞式固体火箭冲压发动机要求贫氧推进剂具有高的燃速压强指数、低的可燃极限和足够好的燃烧稳定性。
- The effect of catalysts of multiple components influencing burning rats and pressure exponent of NEPE propellant is same as catalyst of two components, for example lead carbonate and carbon black. 多组元燃烧催化剂对NEPE推进剂燃速和压力指数有一定影响,但和双组元的相比,并无大的差异。
- Iron oxide may be utilized in achieving propellants of ultrahigh burn rate. 氧化铁可用以制出超高燃速的推进剂。
- Other advantages of the propellent with a negative pressure exponent were also presented. 还指出了负压力指数推进剂的其它优点。