CN108117467A - A kind of method and HTPB propellant for reducing HTPB propellant solidification temperature - Google Patents

A kind of method and HTPB propellant for reducing HTPB propellant solidification temperature Download PDF

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CN108117467A
CN108117467A CN201711419556.4A CN201711419556A CN108117467A CN 108117467 A CN108117467 A CN 108117467A CN 201711419556 A CN201711419556 A CN 201711419556A CN 108117467 A CN108117467 A CN 108117467A
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propellant
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htpb
bismuth
htpb propellant
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CN108117467B (en
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庞爱民
李爽
贾方娜
胡期伟
刘学
毛羽
刘长宝
侯斌
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Hubei Institute of Aerospace Chemical Technology
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    • C—CHEMISTRY; METALLURGY
    • C06—EXPLOSIVES; MATCHES
    • C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
    • C06B33/00—Compositions containing particulate metal, alloy, boron, silicon, selenium or tellurium with at least one oxygen supplying material which is either a metal oxide or a salt, organic or inorganic, capable of yielding a metal oxide
    • C06B33/06—Compositions containing particulate metal, alloy, boron, silicon, selenium or tellurium with at least one oxygen supplying material which is either a metal oxide or a salt, organic or inorganic, capable of yielding a metal oxide the material being an inorganic oxygen-halogen salt
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
    • B01J—CHEMICAL OR PHYSICAL PROCESSES, e.g. CATALYSIS OR COLLOID CHEMISTRY; THEIR RELEVANT APPARATUS
    • B01J31/00—Catalysts comprising hydrides, coordination complexes or organic compounds
    • B01J31/02—Catalysts comprising hydrides, coordination complexes or organic compounds containing organic compounds or metal hydrides
    • B01J31/12—Catalysts comprising hydrides, coordination complexes or organic compounds containing organic compounds or metal hydrides containing organo-metallic compounds or metal hydrides
    • B01J31/122—Metal aryl or alkyl compounds
    • C—CHEMISTRY; METALLURGY
    • C06—EXPLOSIVES; MATCHES
    • C06D—MEANS FOR GENERATING SMOKE OR MIST; GAS-ATTACK COMPOSITIONS; GENERATION OF GAS FOR BLASTING OR PROPULSION (CHEMICAL PART)
    • C06D5/00—Generation of pressure gas, e.g. for blasting cartridges, starting cartridges, rockets
    • C06D5/02—Generation of pressure gas, e.g. for blasting cartridges, starting cartridges, rockets by decompressing compressed, liquefied or solidified gases

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  • Organic Chemistry (AREA)
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  • Inorganic Chemistry (AREA)
  • Metallurgy (AREA)
  • Adhesives Or Adhesive Processes (AREA)
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  • Organic Low-Molecular-Weight Compounds And Preparation Thereof (AREA)

Abstract

The present invention relates to a kind of methods and HTPB propellant for reducing HTPB propellant solidification temperature, by adding in a certain amount of efficient bismuth class curing catalysts in using TMXDI as the HTPB propellant of curing agent, and give the specific component of efficient bismuth class curing catalysts and optimization dosage, can by using TMXDI as the solidification temperature of the HTPB propellant of curing agent by using common curing catalysts triphenyl bismuth TPB when 70 DEG C be reduced to 50 DEG C, significantly reduce cure temperature-fall period in thermal stress and cure cost；In addition the present invention provide using end hydroxy butadiene HTPB as adhesive, using TMXDI as curing agent, using efficient bismuth class substance as the HTPB propellant of curing catalysts, pass through the optimization design to each component in HTPB propellant and content, significantly reduce the solidification temperature using TMXDI as the propellant of curing agent, reduce the temperature difference between solidification temperature and engine operating temperature, so as to reduce thermal stress of the propellant in temperature-fall period is cured, while propellant still keeps excellent mechanical property and ageing properties.

Description

A kind of method and HTPB propellant for reducing HTPB propellant solidification temperature
Technical field
The present invention relates to a kind of method and HTPB propellant for reducing HTPB propellant solidification temperature, more particularly to one Kind solid propellant rocket motor charge is related to propellant technical field to the HTPB propellant formula that TMXDI is curing agent.
Background technology
Tetramethylxylylene diisocyanate (TMXDI) be it is a kind of permit through U.S.'s food and Drug Administration, can It is almost non-hazardous to human body for the curing agent of packaging material for food, and without the use of nitration mixture and severe toxicityization in its building-up process Object is closed, is a kind of preferable green curing agent.Its structural formula is as shown in Equation 1.
TMXDI has meta position (m-) and aligns (p-) two kinds of isomers, is white crystal, fusing point 72 under p-TMXDI room temperature DEG C, it is colourless liquid under m-TMXDI room temperature, solidification point is -10 DEG C.TMXDI used is m-TMXDI in the present invention.
The NCO group of TMXDI is not conjugated on the methylene being connected with phenyl ring with phenyl ring, thus its with aliphatic and The characteristics of both aromatic series.Also, after the hydrogen atom on its methylene is substituted by methyl, improve ultraviolet-resistant aging and water Numerical solution reduces the effect of hydrogen bond.The characteristics of in these structures, causes the HTPB propellant using TMXDI as curing agent to have The advantages that mechanical property is good, insensitive to water, the laundering period is long, anti-aging property is good has good application prospect.But also it is exactly Since the NCO group of TMXDI is not connected with phenyl ring, and steric hindrance is larger, and the reactivity for causing TMXDI is low, is applied In HTPB propellant, there are propellant solidification temperature it is higher the problem of.And the solidification temperature of propellant is excessively high can cause to push away Very big thermal stress is generated in temperature-fall period is cured into agent powder column, easily leads to and is cracked in powder column and interfacial detachment phenomenon, The structural intergrity of propellant is destroyed, security incident is likely to occur when serious.Therefore there is an urgent need to reduce using TMXDI as curing agent Propellant solidification temperature, to reduce the temperature difference between solidification temperature and engine operating temperature, exist so as to reduce propellant Cure the thermal stress in temperature-fall period.(US, 4913753 [P] in document；PCT/US98/20891) report is solid using TMXDI The HTPB propellant of agent be all with common triphenyl bismuth (TPB) be curing catalysts, since the catalytic activity of TPB is relatively low, It is that solidification temperature of the curing catalysts using TMXDI as the HTPB propellant of curing agent is 70 using TPB in actual application DEG C, solidification temperature is higher, and the thermal stress generated in propellant curing temperature-fall period is larger, and cost is higher.
The content of the invention
It is an object of the invention to overcome the drawbacks described above of the prior art, a kind of reduction HTPB propellant solidification temperature is provided Method, the method by adding in efficient bismuth class curing catalysts in HTPB propellant, by the solidification temperature of HTPB propellant 50 DEG C are reduced to from 70 DEG C when using TPB, and propellant still keeps excellent mechanical property and ageing properties.
Another object of the present invention is to provide a kind of HTPB propellant.
What the above-mentioned purpose of the present invention was mainly achieved by following technical solution：
A kind of method for reducing HTPB propellant solidification temperature adds in TMXDI is used as the HTPB propellant of curing agent Enter bismuth class curing catalysts, the structural formula of the bismuth class curing catalysts is as follows：
Wherein：R is NO2Or O (CH2)xCH3, x is 0~6.
In the method for above-mentioned reduction HTPB propellant solidification temperature, the bismuth class curing catalysts account for HTPB propellant Mass percentage content is 0.01%~0.1%.
In the method for above-mentioned reduction HTPB propellant solidification temperature, the bismuth class curing catalysts account for HTPB propellant Mass percentage content is 0.02%~0.06%.
In the method for above-mentioned reduction HTPB propellant solidification temperature, the bismuth class curing catalysts are three (4- ethyoxyls Phenyl) bismuth, three (3- ethoxyl phenenyls) bismuths, three (4- nitrobenzophenones) bismuths, three (3- nitrobenzophenones) bismuths, three (3- butyl phenyl ethers Base) bismuth or three (3- methoxyphenyls) bismuths.
A kind of HTPB propellant includes the component of following mass percentage content：
Adhesive：End hydroxy butadiene HTPB 6.5%~10.0%；
Curing agent TMXDI：0.05%~1.0%；
Oxidant AP：60.0%~85.0%；
Metal fuel：3.0%~20%；
Bismuth class curing catalysts：0.01%~0.1%
Plasticizer：2.0%~5.0%；
Burning ratemodifier：0~4.0%；
Bonding agent：0.05%~0.2%；
Anti-aging agent：0.05%~0.3%
The structural formula of the bismuth class curing catalysts is as follows：
Wherein：R is NO2Or O (CH2)xCH3, x is 0~6.
In above-mentioned HTPB propellant, the bismuth class curing catalysts are three (4- ethoxyl phenenyls) bismuths, three (3- ethyoxyls Phenyl) bismuth, three (4- nitrobenzophenones) bismuths, three (3- nitrobenzophenones) bismuths, three (3- butoxy phenyls) bismuths or three (3- methoxybenzenes Base) bismuth；The mass percentage content of the bismuth class curing catalysts is 0.02%~0.06%.
In above-mentioned HTPB propellant, the oxidant amine perchlorate AP granularities are in I class, II class, III class or IV class At least two classes mix, wherein I class is d4.3=335 ± 10 μm, II class be d4.3=245 ± 10 μm, III class be d4.3=135 ± 10 μm, IV class be d4.3≤20μm。
In above-mentioned HTPB propellant, the metal fuel is Al powder or one kind in Mg powder or combination.
In above-mentioned HTPB propellant, the plasticizer is Plexol 201 DOS, dioctyl adipate DOA or neighbour One kind or combination in dioctyl phthalate DOP.
In above-mentioned HTPB propellant, the burning ratemodifier is CuO, CuS, Cr2O3、PbCrO4、 Fe2O3, calcium carbonate, Calcirm-fluoride, magnesium fluoride, strontium carbonate, magnesium carbonate, ammonium oxalate, octyl ferrocene T27, butyl ferrocene or 2,2- (double two cyclopentadienyls of ethyl Iron-based) one kind in propane GFP or combination.
In above-mentioned HTPB propellant, the bonding agent is three [1- (2- methyl) '-aziridino] phosphine oxygen MAPO, isophthalic Two formyl Propyleneimine HX-752, tetren, butyl diethanolamine BIDE, triethanolamine TEA, triethanolamine boron trifluoride Complex compound, tetrahydroxyethyl-ethylene diamine or one kind in triethylenetetramine TETAN or combination.
In above-mentioned HTPB propellant, the anti-aging agent be N, N '-diphenyl-para-phenylene diamine, N- phenyl -1- naphthylamines, 2, One kind in 2 '-methylene-bis--(- 6 t-butyl phenol of 4- methyl) or thiobis-(3,5- di-tert-butyl -4- hydroxybenzyls) Or combination.
The present invention has the advantages that compared with prior art：
(1), the present invention is cured by adding in a certain amount of efficient bismuth class in using TMXDI as the HTPB propellant of curing agent Catalyst, and the specific component of efficient bismuth class curing catalysts and optimization dosage are given, it can be by the fourth using TMXDI as curing agent The solidification temperature of hydroxyl propellant is significantly dropped by using 70 DEG C during common curing catalysts triphenyl bismuth (TPB) to be reduced to 50 DEG C Thermal stress and curing cost in low curing temperature-fall period；
(2), the present invention is cured by adding in a certain amount of efficient bismuth class in using TMXDI as the HTPB propellant of curing agent Catalyst, while reducing using HTPB propellant solidification temperatures of the TMXDI as curing agent, propellant still keeps excellent mechanics Performance and ageing properties.
(3), the present invention provide using end hydroxy butadiene HTPB as adhesive, using TMXDI as curing agent, with efficient bismuth class Substance is the HTPB propellant formula of curing catalysts, by the optimization design to each component in HTPB propellant and content, is shown The solidification temperature reduced using TMXDI as the propellant of curing agent is write, is reduced between solidification temperature and engine operating temperature Temperature difference, so as to reduce thermal stress of the propellant in temperature-fall period is cured, while propellant still keeps excellent mechanical property And ageing properties.
(4), the present invention not only overcomes high as the solidification temperature of the HTPB propellant of curing agent using TMXDI, and then causes The problem of thermal stress generated in propellant curing temperature-fall period is larger, can also be big by reducing HTPB propellant solidification temperature The big curing cost for reducing propellant.
Specific embodiment
Below by specific embodiment, the present invention is described in further detail.
The method that the present invention reduces HTPB propellant solidification temperature, is using TMXDI as in the HTPB propellant of curing agent Bismuth class curing catalysts are added in, the structural formula of the bismuth class curing catalysts is as follows：
Wherein：R is NO2Or O (CH2)xCH3, x is 0~6.
The mass percentage content that above-mentioned bismuth class curing catalysts account for HTPB propellant is 0.01%~0.1%, is preferably 0.02%~0.06%.
Above-mentioned bismuth class curing catalysts are preferably：Three (4- ethoxyl phenenyls) bismuths, three (3- ethoxyl phenenyls) bismuths, three (4- Nitrobenzophenone) bismuth, three (3- nitrobenzophenones) bismuths, three (3- butoxy phenyls) bismuths or three (3- methoxyphenyls) bismuths.
HTPB propellant of the present invention specifically includes the component of following mass percentage content：
Adhesive：End hydroxy butadiene HTPB 6.5%~10.0%；
Curing agent TMXDI：0.05%~1.0%；
Oxidant AP：60.0%~85.0%；
Metal fuel：3.0%~20%；
Bismuth class curing catalysts：0.01%~0.1%
Plasticizer：2.0%~5%；
Burning ratemodifier：0~4.0%；
Bonding agent：0.05%~0.2%；
Anti-aging agent：0.05%~0.3%.
The structural formula of the bismuth class curing catalysts is as follows：
Wherein：R is NO2Or O (CH2)xCH3, x is 0~6.
The preferred structure of above-mentioned bismuth class curing catalysts for three (4- ethoxyl phenenyls) bismuths, three (3- ethoxyl phenenyls) bismuths, One in three (4- nitrobenzophenones) bismuths, three (3- nitrobenzophenones) bismuths, three (3- butoxy phenyls) bismuths, three (3- methoxyphenyls) bismuths Kind.
The mass percentage content of above-mentioned burning ratemodifier or 0.05~4.0%.
Above-mentioned oxidant amine perchlorate AP granularities are at least two classes mixing in I class, II class, III class or IV class, wherein I class For d4.3=335 ± 10 μm, II class be d4.3=245 ± 10 μm, III class be d4.3=135 ± 10 μm, IV class be d4.3≤20μm。
Above-mentioned metal fuel is Al powder or one kind in Mg powder or combination.
Above-mentioned plasticizer is in Plexol 201 DOS, dioctyl adipate DOA or dioctyl phthalate DOP One kind or combination.
Above-mentioned burning ratemodifier is CuO, CuS, Cr2O3、PbCrO4、Fe2O3, calcium carbonate, strontium carbonate, magnesium carbonate, ammonium oxalate, Octyl ferrocene T27, butyl ferrocene or one kind in 2,2- (double ethyl dicyclopentadienyl iron bases) propane GFP or combination.
Above-mentioned bonding agent is MAPO (three [1- (2- methyl) '-aziridino] phosphine oxygens), HX-752 (phenyl-diformyl trimethylene Imines), tetren, BIDE (butyl diethanolamine), TEA (triethanolamine), triethanolamine boron trifluoride complex, four hydroxyls One or more of ethylethylenediamine, TETAN (triethylenetetramine)；
Above-mentioned anti-aging agent is antioxidant H (N, N '-diphenyl-para-phenylene diamine), antioxidant A (N- phenyl -1- naphthylamines), A0- 2246 (2,2 '-methylene-bis--(- 6 t-butyl phenol of 4- methyl)), Hs (thiobis-(3,5- di-tert-butyl -4- hydroxyl benzyls One or more of base)).
Embodiment 1
It is as shown in table 1 as the propellant formulation (mass percent) of curing agent using TMXDI：
Table 1 is using TMXDI as the propellant formulation of curing agent
As it can be seen from table 1 using TMXDI as in the HTPB propellant formula of curing agent, the difference of 1# and 2# are only used Curing catalysts are different, and it is common curing catalysts TPB reported in the literature that 1#, which is used, and it is efficient bismuth class to be used in 2# Curing catalysts three (4- nitrobenzophenones) bismuth.The solidification temperature of 1# is formulated as 70 DEG C, is formulated the solidification temperature of 2# as 50 DEG C, two The mechanical property of a formulation cured different number of days is as shown in table 2.
Table 2 is using TMXDI as the ambient temperature mechanical properties of the HTPB propellant of curing agent
From Table 2, it can be seen that be curing catalysts using TMXDI using TPB being the HTPB propellant of curing agent in 70 DEG C of items Vulcanization is needed to can be only achieved within 9 days sulfurizing point under part, and the propellant using three (4- nitrobenzophenones) bismuths as curing catalysts only need to be Sulfurizing point can be basically reached by curing 7 days under the conditions of 50 DEG C, and solidification temperature significantly reduces, and hardening time also shortens, and be promoted The mechanical property of agent keeps suitable with using TPB, therefore this efficient curing catalysts of bismuth class are well suited for using TMXDI as curing agent HTPB propellant.
Embodiment 2
It is as shown in table 3 as the propellant formulation (mass percent) of curing agent using TMXDI：
Table 3 is using TMXDI as the propellant formulation of curing agent
From table 3 it can be seen that using TMXDI as in the HTPB propellant formula of curing agent, the difference of 3# and 4# are only used Curing catalysts are different, and it is TPB that 3#, which is used, and efficient bismuth class curing catalysts three (4- methoxyphenyls) bismuth used in 4# Instead of the TPB in 3#.Formula 3# and 4# is cured 7 days under the conditions of 70 DEG C and 50 DEG C respectively, the mechanical property of two formulas As shown in table 4.
Table 4 is using TMXDI as the mechanical property of the HTPB propellant of curing agent
As can be seen from Table 4, it is fourth of the curing catalysts using TMXDI as curing agent using three (4- methoxyphenyls) bismuths Hydroxyl propellant cures 7 days under the conditions of 50 DEG C, and the propellant with TPB is used to be curing catalysts cures 7 days under the conditions of 70 DEG C, The mechanical properties of propellant of gained is suitable.Therefore, three (4- methoxyl groups are used in using TMXDI as the HTPB propellant of curing agent Phenyl) bismuth can significantly reduce the solidification temperature of propellant for curing catalysts, so as to reduce in propellant curing temperature-fall period Thermal stress, reduce the curing cost of propellant.
Embodiment 3
It is as shown in table 5 as the propellant formulation (mass percent) of curing agent using TMXDI：
Table 5 is using TMXDI as the propellant formulation of curing agent
As can be seen from Table 5, using TMXDI as in the HTPB propellant formula of curing agent, the difference of 5# and 6# are only used Curing catalysts are different, and it is TPB that 5#, which is used, and efficient bismuth class curing catalysts three (4- ethoxyl phenenyls) bismuth used in 6# Instead of the TPB in 5#.Formula 5# and 6# is cured 7 days under the conditions of 70 DEG C and 50 DEG C respectively, the mechanical property of two formulas As shown in table 6.
Table 6 is using TMXDI as the mechanical property of the HTPB propellant of curing agent
As can be seen from Table 6, it is fourth of the curing catalysts using TMXDI as curing agent using three (4- ethoxyl phenenyls) bismuths Hydroxyl propellant cures 7 days under the conditions of 50 DEG C, and the propellant with TPB is used to be curing catalysts cures 7 days under the conditions of 70 DEG C, The mechanical properties of propellant of gained is suitable.Therefore, three (4- ethyoxyls are used in using TMXDI as the HTPB propellant of curing agent Phenyl) bismuth can significantly reduce the solidification temperature of propellant for curing catalysts, so as to reduce in propellant curing temperature-fall period Thermal stress, reduce the curing cost of propellant.
In addition, be curing catalysts using TMXDI using three (4- ethoxyl phenenyls) bismuths being the HTPB propellant of curing agent 70 The ageing properties of accelerated ageing three are as shown in table 7 under the conditions of DEG C.
Table 7 is using TMXDI as 70 DEG C of accelerated aging tests of the propellant of curing agent
As can be seen from Table 7, though using efficient curing catalysts three (4- ethoxyl phenenyls) bismuth as using TMXDI as The curing catalysts of the HTPB propellant of curing agent, propellant still keep good anti-aging property, can meet practical application Needs, this efficient bismuth class curing catalysts illustrated in the present invention is well suited for being applied to propellant using TMXDI as curing agent In, application can not only reduce the solidification temperature of propellant, and propellant can still keep good mechanical property and ageing properties.
The above is only the optimal specific embodiment of the present invention, but protection scope of the present invention is not limited thereto, Any one skilled in the art in the technical scope disclosed by the present invention, the change or replacement that can be readily occurred in, It should be covered by the protection scope of the present invention.
The content not being described in detail in description of the invention belongs to the known technology of professional and technical personnel in the field.

Claims (12)

  1. A kind of 1. method for reducing HTPB propellant solidification temperature, it is characterised in that：It is pushed away using TMXDI for the fourth hydroxyl of curing agent Bismuth class curing catalysts are added in into agent, the structural formula of the bismuth class curing catalysts is as follows：
    Wherein：R is NO2Or O (CH2)xCH3, x is 0~6.
  2. 2. the method according to claim 1 for reducing HTPB propellant solidification temperature, it is characterised in that：The bismuth class cures The mass percentage content that catalyst accounts for HTPB propellant is 0.01%~0.1%.
  3. 3. the method according to claim 2 for reducing HTPB propellant solidification temperature, it is characterised in that：The bismuth class cures The mass percentage content that catalyst accounts for HTPB propellant is 0.02%~0.06%.
  4. 4. the method according to claim 1 for reducing HTPB propellant solidification temperature, it is characterised in that：The bismuth class cures Catalyst is three (4- ethoxyl phenenyls) bismuths, three (3- ethoxyl phenenyls) bismuths, three (4- nitrobenzophenones) bismuths, three (3- nitrobenzophenones) Bismuth, three (3- butoxy phenyls) bismuths or three (3- methoxyphenyls) bismuths.
  5. 5. a kind of HTPB propellant, it is characterised in that：Include the component of following mass percentage content：
    Adhesive：End hydroxy butadiene HTPB 6.5%~10.0%；
    Curing agent TMXDI：0.05%~1.0%；
    Oxidant AP：60.0%~85.0%；
    Metal fuel：3.0%~20%；
    Bismuth class curing catalysts：0.01%~0.1%
    Plasticizer：2.0%~5.0%；
    Burning ratemodifier：0~4.0%；
    Bonding agent：0.05%~0.2%；
    Anti-aging agent：0.05%~0.3%
    The structural formula of the bismuth class curing catalysts is as follows：
    Wherein：R is NO2Or O (CH2)xCH3, x is 0~6.
  6. 6. HTPB propellant according to claim 5, it is characterised in that：The bismuth class curing catalysts are three (4- ethoxies Base phenyl) bismuth, three (3- ethoxyl phenenyls) bismuths, three (4- nitrobenzophenones) bismuths, three (3- nitrobenzophenones) bismuths, three (3- butyl phenyl ethers Base) bismuth or three (3- methoxyphenyls) bismuths；The mass percentage content of the bismuth class curing catalysts is 0.02%~0.06%.
  7. 7. HTPB propellant according to claim 5, it is characterised in that：The oxidant amine perchlorate AP granularities for I class, At least two classes mixing in II class, III class or IV class, wherein I class is d4.3=335 ± 10 μm, II class be d4.3=245 ± 10 μm, III class is d4.3=135 ± 10 μm, IV class be d4.3≤20μm。
  8. 8. HTPB propellant according to claim 5, it is characterised in that：The metal fuel is one in Al powder or Mg powder Kind or combination.
  9. 9. HTPB propellant according to claim 5, it is characterised in that：The plasticizer for Plexol 201 DOS, Dioctyl adipate DOA or one kind in dioctyl phthalate DOP or combination.
  10. 10. HTPB propellant according to claim 5, it is characterised in that：The burning ratemodifier is CuO, CuS, Cr2O3、 PbCrO4、Fe2O3, calcium carbonate, calcirm-fluoride, magnesium fluoride, strontium carbonate, magnesium carbonate, ammonium oxalate, octyl ferrocene T27, the cyclopentadienyl of butyl two Iron or one kind in 2,2- (double ethyl dicyclopentadienyl iron bases) propane GFP or combination.
  11. 11. HTPB propellant according to claim 5, it is characterised in that：The bonding agent is three [1- (2- methyl) nitrogen third Piperidinyl] phosphine oxygen MAPO, phenyl-diformyl Propyleneimine HX-752, tetren, butyl diethanolamine BIDE, triethanolamine TEA, triethanolamine boron trifluoride complex, tetrahydroxyethyl-ethylene diamine or one kind in triethylenetetramine TETAN or combination.
  12. 12. HTPB propellant according to claim 5, it is characterised in that：The anti-aging agent is N, and N '-diphenyl is to benzene two Amine, N- phenyl-1-naphthylamines, 2,2 '-methylene-bis--(- 6 t-butyl phenol of 4- methyl) or thiobis-(3,5- di-tert-butyls -4- Hydroxybenzyl) in one kind or combination.
CN201711419556.4A 2017-12-25 2017-12-25 Method for reducing curing temperature of butylated hydroxytoluene propellant and butylated hydroxytoluene propellant Active CN108117467B (en)

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Cited By (4)

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Publication number Priority date Publication date Assignee Title
CN108753217A (en) * 2018-06-26 2018-11-06 西安近代化学研究所 A kind of composite propellant lining
CN109438149A (en) * 2018-12-05 2019-03-08 湖北航天化学技术研究所 A kind of thermosetting property composite solidpropellant and preparation method thereof
CN110330395A (en) * 2019-08-06 2019-10-15 湖北航天化学技术研究所 A kind of high intensity HTPB propellant and preparation method thereof
CN111019723A (en) * 2019-12-17 2020-04-17 湖北航天化学技术研究所 Clean gas generating agent

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