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Self-ignition rocket fuel and self-ignition propellant

A rocket fuel and propellant technology, applied in the field of bicomponent liquid rocket propellant, can solve the problems of reducing practical application value, failing to meet practical needs, and difficulty in large-scale production, so as to facilitate multiple ignitions and start, improve system Reliability and maintenance of safety, safety and stability good effect

Active Publication Date: 2019-04-05
HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

(2) Long ignition delay time
Such as dicyandiamide and nitrocyanamide-based spontaneous combustion ionic liquids have good stability and simple synthesis, but the ignition delay time is too long to meet practical needs; (3) poor safety and stability
-BH 4 、-BH 3 CN,-Al(BH 4 ) 4 The ignition time of similar ionic liquids reaches or exceeds the level of hydrazine propellants, but they are not stable enough relative to water and cannot be stored in the air for a long time, which greatly reduces their practical application value; (4) preparation is tedious and expensive
-BH 2 (CN 2 ) 2 and-BH 3 CNBH 2 Although the performance of CN-type self-igniting ionic liquids has basically reached the level of hydrazine-type propellants, their synthesis is cumbersome, the yield is low, and it is difficult to produce on a large scale.

Method used

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Examples

Experimental program
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Effect test

Embodiment 1

[0028] Embodiment 1: the synthesis of cyclopropyl ketone azine (CPMKA):

[0029] In a 500mL three-necked reaction flask equipped with a stirrer, a thermometer, and a constant pressure dropping funnel, add 100mL of ethanol and 62.5g (1mol) of 80% hydrazine hydrate, dropwise add 168g (2mol) of cyclopropyl ketone, and heat to reflux for 16 hours , the reactant was extracted with ether, dried, concentrated under reduced pressure and then rectified to obtain about 74g of light yellow transparent liquid CPMKA product with a yield of about 45%. Its structure and properties are shown in Table 1.

Embodiment 2

[0030] Embodiment 2: the synthesis of acetone azine (ATA)

[0031] In a 500mL three-necked reaction flask equipped with a stirrer, a thermometer, and a constant pressure dropping funnel, add 150mL of ethanol and 87g (1.5mol) of 80% hydrazine hydrate, dropwise add 252g (3mol) of acetone, and heat to reflux for 12 hours. Extracted with ether, dried, concentrated under reduced pressure and then rectified to obtain about 134 g of ATA product as light yellow transparent liquid with a yield of about 80%. Its structure and properties are shown in Table 1.

Embodiment 3

[0032] Embodiment 3: the synthesis of butanone azine (DTA)

[0033] In a 500mL three-neck reaction flask equipped with a stirrer, a thermometer, and a constant pressure dropping funnel, add 150mL of ethanol and 26g (0.5165mol) of 80% hydrazine hydrate, dropwise add 74.5 (1.033mol) of methyl ethyl ketone, heat and reflux for 12 hours, and react The product was extracted with ether, dried, concentrated under reduced pressure and then rectified to obtain about 69 g of light yellow transparent liquid DTA product with a yield of 94.69%. Its structure and properties are shown in Table 1.

[0034] The structure and performance of many substituted azine compounds obtained in table 1 embodiment 1-3

[0035]

[0036] And it can be seen from the data in Table 1 that the three kinds of spontaneous combustion additives have good compatibility with rocket kerosene, and have lower freezing points, and better low-temperature performance; higher boiling points, will not produce hydrazines ...

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Abstract

The invention provides self-ignition rocket fuel and a self-ignition propellant comprising the same. The self-ignition rocket fuel is a polysubstituted azine compound or rocket kerosene added with anadditive. The self-ignition rocket fuel can form self-ignition after contacting with oxidants like dinitrogen tetroxide and nitric acid, thereby being used as the self-ignition propellant. Compared with self-ignition propellants, the self-ignition rocket fuel or propellant has the advantages of being higher in fuel energy density, low in toxicity and higher in safety and stability and being an excellent candidate of high-energy self-ignition bi-component liquid propellants.

Description

technical field [0001] The present invention generally relates to the technical field of bicomponent liquid rocket propellants, and in particular to a rocket fuel capable of spontaneous combustion with nitro oxidants and a self-ignitable propellant containing the fuel. Background technique [0002] Liquid rocket propellant is a substance that enters the rocket engine in a liquid state and undergoes chemical reactions and thermodynamic changes to provide energy and working fluid for the propulsion system. The dual-component liquid rocket propellant is a propellant that works in combination with two components of liquid oxidant and liquid fuel stored separately. Bicomponent liquid propellant has the characteristics of high energy and relatively safe use, and is the most widely used propellant in liquid rocket and missile propulsion systems. [0003] According to different ignition methods, bicomponent liquid propellants can be divided into pyrophoric propellants and non-pyrop...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C10L1/04C10L1/226C10L1/12C06B43/00C06D5/08
CPCC06B43/00C06D5/08C10L1/04C10L1/10C10L1/1266C10L1/226C10L2270/04
Inventor 鲁统洁韦伟金凤蔡克龙韦雪梅
Owner HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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