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 PDFInfo
- Publication number
- 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
- Authority
- CN
- China
- Prior art keywords
- propellant
- class
- htpb
- bismuth
- htpb propellant
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- 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
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Organic Chemistry (AREA)
- Materials Engineering (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Combustion & Propulsion (AREA)
- Inorganic Chemistry (AREA)
- Metallurgy (AREA)
- Adhesives Or Adhesive Processes (AREA)
- Polyurethanes Or Polyureas (AREA)
- 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
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)
- 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. 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. 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. 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. 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. 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. 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. 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. 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. 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. 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. 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.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN201711419556.4A CN108117467B (en) | 2017-12-25 | 2017-12-25 | Method for reducing curing temperature of butylated hydroxytoluene propellant and butylated hydroxytoluene propellant |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN201711419556.4A CN108117467B (en) | 2017-12-25 | 2017-12-25 | Method for reducing curing temperature of butylated hydroxytoluene propellant and butylated hydroxytoluene propellant |
Publications (2)
Publication Number | Publication Date |
---|---|
CN108117467A true CN108117467A (en) | 2018-06-05 |
CN108117467B CN108117467B (en) | 2020-10-20 |
Family
ID=62231758
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CN201711419556.4A Active CN108117467B (en) | 2017-12-25 | 2017-12-25 | Method for reducing curing temperature of butylated hydroxytoluene propellant and butylated hydroxytoluene propellant |
Country Status (1)
Country | Link |
---|---|
CN (1) | CN108117467B (en) |
Cited By (4)
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 |
Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4913753A (en) * | 1989-09-25 | 1990-04-03 | The United States Of America As Represented By The Secretary Of The Army | TMXDI, curing agent for hydroxy terminated propellant binders |
USH934H (en) * | 1990-07-09 | 1991-07-02 | The United States Of America As Represented By The Secretary Of The Army | Maleic anhydride adjunct to triphenylbismuthine to improve mechanical properties of hydroxy terminated binders |
US6051087A (en) * | 1992-01-29 | 2000-04-18 | Cordant Technologies Inc. | Low smoke rocket motor liner compositions |
CN101733154A (en) * | 2009-12-03 | 2010-06-16 | 苏州大学 | Cure catalyst for solid propellant and preparation method thereof |
CN103102634A (en) * | 2013-02-05 | 2013-05-15 | 常熟市中联光电新材料有限责任公司 | Natural silane cross-linked polyethylene cable material capable of resisting 110 DEG C |
CN103351837A (en) * | 2013-05-10 | 2013-10-16 | 北京理工大学 | Non-ester plasticizer-containing energetic material casting curing system and curing method thereof |
CN106831279A (en) * | 2016-11-28 | 2017-06-13 | 湖北航天化学技术研究所 | A kind of cold curing propellant |
-
2017
- 2017-12-25 CN CN201711419556.4A patent/CN108117467B/en active Active
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4913753A (en) * | 1989-09-25 | 1990-04-03 | The United States Of America As Represented By The Secretary Of The Army | TMXDI, curing agent for hydroxy terminated propellant binders |
USH934H (en) * | 1990-07-09 | 1991-07-02 | The United States Of America As Represented By The Secretary Of The Army | Maleic anhydride adjunct to triphenylbismuthine to improve mechanical properties of hydroxy terminated binders |
US6051087A (en) * | 1992-01-29 | 2000-04-18 | Cordant Technologies Inc. | Low smoke rocket motor liner compositions |
CN101733154A (en) * | 2009-12-03 | 2010-06-16 | 苏州大学 | Cure catalyst for solid propellant and preparation method thereof |
CN103102634A (en) * | 2013-02-05 | 2013-05-15 | 常熟市中联光电新材料有限责任公司 | Natural silane cross-linked polyethylene cable material capable of resisting 110 DEG C |
CN103351837A (en) * | 2013-05-10 | 2013-10-16 | 北京理工大学 | Non-ester plasticizer-containing energetic material casting curing system and curing method thereof |
CN106831279A (en) * | 2016-11-28 | 2017-06-13 | 湖北航天化学技术研究所 | A kind of cold curing propellant |
Non-Patent Citations (1)
Title |
---|
李爽: "固化剂TMXDI在丁羟推进剂中的应用", 《固体火箭技术》 * |
Cited By (6)
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 |
CN109438149B (en) * | 2018-12-05 | 2021-06-11 | 湖北航天化学技术研究所 | Thermosetting composite solid propellant 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 |
CN110330395B (en) * | 2019-08-06 | 2021-06-22 | 湖北航天化学技术研究所 | High-strength butylated hydroxytoluene 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 |
Also Published As
Publication number | Publication date |
---|---|
CN108117467B (en) | 2020-10-20 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
CN108117467A (en) | A kind of method and HTPB propellant for reducing HTPB propellant solidification temperature | |
CN106631644B (en) | A kind of azide propellant and preparation method thereof having superior low-temperature adaptability | |
CN107867961B (en) | Method for improving mechanical property of butylated hydroxytoluene propellant and butylated hydroxytoluene propellant prepared by same | |
CN106316729B (en) | Azide polyether propellant with wide adaptability | |
CN110156547A (en) | A kind of high intensity low pressure index HTPB composite propellant and preparation method thereof | |
CN108117466B (en) | Low-burning-rate high-energy butylated hydroxytoluene propellant and application of alicyclic diisocyanate | |
KR101334732B1 (en) | Insensitive propellant composition | |
CN110156548B (en) | Casting type high-energy insensitive explosive and preparation method thereof | |
CN108129248B (en) | Method for solving post-curing problem of room-temperature cured butyl hydroxyl propellant and prepared product | |
CN108164377B (en) | Method for improving TMXDI-HTPB propellant process performance and product | |
CN108530239A (en) | A kind of highly filled NEPE solid propellants slurry, propellant and preparation method | |
CN109467495A (en) | It is a kind of using polyethers-fourth hydroxyl block polymer as the solid propellant of adhesive | |
CN110423184A (en) | A kind of solid propellant rocket propellant and preparation method thereof | |
KR102621576B1 (en) | A HIGH PERFORMANCE COMPOSITE PYROTECHNIC PRODUCT WITHOUT Pb IN ITS COMPOSITION, AND PREPARATION THEREOF | |
CN110963866B (en) | Temperature-sensitive time-varying solid propellant | |
CN106336335A (en) | High-intensity high-percentage elongation solid propellant | |
KR101974125B1 (en) | Solid propellant composition and manufacturing method thereof | |
CN107512997B (en) | Low-burning-rate high-energy solid propellant | |
CN109438147A (en) | A kind of HTPB base casting composite explosives formula that processing performance improves | |
CN109628053A (en) | A kind of flammable liners formulation and its manufacturing method | |
CN106748600B (en) | Containing AlH3High theoretical specific impulse and high density propellant and preparation method thereof | |
CN108794284A (en) | It is a kind of using dimer (fatty acid) yl diisocyanate as the gas generator propellant of curing agent | |
CN105131238B (en) | A kind of polyurethane material and its application | |
CN107879869A (en) | Reduce the method for azide polyethers propellant glass transition temperature and the propellant of preparation | |
KR101296690B1 (en) | Deformable solid propellant composition using thermoplastic binder |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PB01 | Publication | ||
PB01 | Publication | ||
SE01 | Entry into force of request for substantive examination | ||
SE01 | Entry into force of request for substantive examination | ||
GR01 | Patent grant | ||
GR01 | Patent grant |