Electrical Combustion Control of AP- and AN-Based Propellants for Upper-Stage Applications
Electrical Combustion Control of AP- and AN-Based Propellants for Upper-Stage Applications
复制标题
上级应用的 AP 和 AN 推进剂的电燃烧控制
DOI：
10.2514/2.5510
复制
发表时间：
1999
期刊：
影响因子：
--
通讯作者：
Hiromichi Ohisa
中科院分区：
文献类型：
--
作者：
T. Tachibana;Hiromichi Ohisa
为了科普未来各种各样的使命应用，例如大型空间结构、快速轨道转移等，寻求研制一种用于上面级的大推力一牛顿级火箭发动机。通过对固体推进剂电弧喷射推力器的试制和不同推进剂的对比试验，证明了在使用高氯酸铵（AP）基复合推进剂时，如端羟基聚丁二烯（HTPB）/AP/LiF = 20/80/2（质量比），加入氟化锂作为燃烧抑制剂或HTPB/AP/Ti = 40/50/10，减少氧化剂，加入钛，该发动机可以控制数据放电功率约1千瓦，当使用不自燃硝酸铵（AN）基推进剂，如（BAMO/NMMO）/AN = 15/85或PPG/AN = 10/90，发动机燃烧在较小的推力和较高的物质c冲量下比在同等工作条件下使用AP基推进剂的情况更稳定。
To cope with a variety of future mission applications, such as for large space structures, quick orbital transfers, etc., development of a high-thrust one Newton class rocket motor for upper stage is sought after. Our research consists of the trial manufacture of a solid propellant arc-jet thruster capable of electrically controlling and sustaining the combustion of a solid propellant and a comparative examination of the thruster’ s performance throughactualtestingwithdifferentpropellants.Thesetestsdemonstratedthatwhenusingammoniumperchlorate (AP)-based composite propellants, such as hydroxy terminated poly-butadiene (HTPB)/AP/LiF = 20/80/2 (mass ratio) with lithium e uoride added as a combustion suppressor or HTPB/AP/Ti = 40/50/10 with reduced oxidizing agentandaddedtitanium,themotorcouldbecontrolledatadischargepoweraround1kWandthatwhenusingnonself-combustible ammonium nitrate (AN)-based propellants, such as (BAMO/NMMO)/AN = 15/85 or PPG/AN = 10/90, the motor combustion was more stable with less thrust and higher specie c impulse than the case with AP-based propellants under equivalent operating conditions.