先把简要报告和数据发了，教程以后详细写
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[ASR] Calculation of the combustion of APER (updated)
The calculation has been done to get the main parameters for ASR's latest propellant APER, the brief report was written in English for advanced readers who were expected to be skillful and knowledgeable rocket researchers.
本计算实验是对ASR高能固体火箭燃料APER改进型的一次热力学计算，这篇简短的报告用英文写成，以此来避免在翻译过程中的数据缺失。本文针对进阶火箭爱好者和读者。
The formulation recently developed for the APER is tentative and can later include other components such as aluminum and DOS
FORMULATION TESTED: AP 68%
Epoxy Resin 20%
Al 12%
Due to the rapid and imponderable variations of most of systematic parameters, the environmental settings can hardly be predicted, so it will be pleasurable to set a mean value. For instance, the calculation requires chamber pressure which is altering through out the process of working. I chose 1200psi (8.27MPa) as the calculated one just by experience.
The variables or operationg conditions controlled in this calculation are listed below:
Temperature of the Chamber 298K
Chamber Pressure 1200psi
Exhaust Pressure 14.7psi (1 atm)
The result of calculation:
Code WEIGHT D-H DENS COMPOSITION
0 AMMONIUM PERCHLORATE 68.000 -601 0.07040 1 CL 4 H 1 N 4 O
0 ALUMINUM (PURE CRYSTALINE) 12.000 0 0.09750 1 AL
0 EPOXY 201 20.000 -661 0.04040 24 H 16 C 4 O
the propellant density is 0.06313 lb/cu-in or 1.7474 gm/cc
the total propellant weight is 100.0000 grams
number of gram atoms of each element present in ingredients
4.026989 h
1.141357 c
0.578738 n
2.600292 o
0.444774 al
0.578738 cl
****************************chamber results follow *****************************
t(k) t(f) p(atm) p(psi) enthalpy entropy cp/cv gas rt/v
3098 5118 81.63 1200.00 -54.09 231.26 1.1890 3.773 21.634
specific heat (molar) of gas and total = 9.824 11.814
number mols gas and condensed = 3.773 0.219
1.045827e+000 co 1.016340e+000 h2 6.911820e-001 h2o 5.533573e-001 hcl
2.889427e-001 n2 2.191144e-001 al2o3* 9.530760e-002 co2 4.592917e-002 h
1.687644e-002 cl 1.143639e-002 ho 2.407126e-003 alcl 1.580532e-003 alcl2
1.224398e-003 alocl 6.738470e-004 no 5.082375e-004 alho2 5.012126e-004 alcl3
3.090869e-004 o 2.363468e-004 alho 8.375089e-005 o2 7.942520e-005 nh3
7.168903e-005 cho 4.859937e-005 cl2 3.626335e-005 cocl 3.622675e-005 alo
3.136510e-005 cnh 1.425074e-005 hocl 1.374346e-005 al 1.298290e-005 ch2o
1.258595e-005 nh2 6.236644e-006 ocl 3.808819e-006 alh 3.483641e-006 cnho
2.970532e-006 n 2.702406e-006 nh 2.686548e-006 al2o 1.468401e-006 nho
1.21759e-06 ho2
the molecular weight of the mixture is 25.048
****************************exhaust results follow *****************************
t(k) t(f) p(atm) p(psi) enthalpy entropy cp/cv gas rt/v
1633 2481 1.00 14.70 -130.36 231.26 1.2220 3.734 0.268
specific heat (molar) of gas and total = 9.036 10.324
number mols gas and condensed = 3.734 0.222
1.105206e+000 h2 9.683347e-001 co 6.188583e-001 h2o 5.786071e-001 hcl
2.893394e-001 n2 2.223673e-001 al2o3& 1.729507e-001 co2 1.563261e-004 h
6.418360e-005 cl 7.271502e-006 nh3 3.867836e-006 ho 1.251784e-006 alcl3
the molecular weight of the mixture is 25.278
**********performance: frozen on first line, shifting on second line**********
impulse is ex t* p* c* isp* opt-ex d-isp a*m ex-t
252.1 1.1982 2819 46.11 4977.8 10.22 440.5 0.12896 1496
257.6 1.1447 2896 46.97 5120.3 194.5 10.50 450.2 0.13265 1633
boost velocities for propellant density of 0.06313 (s.g. of 1.747)
10/ 20535 15/ 17515 25/ 13923 30/ 12715 55/ 9061 60/ 8589
69/ 7860 71/ 7716 88/ 6684 100/ 6114 150/ 4530 175/ 4016
200/ 3609 300/ 2571 1000/ 858 3000/ 296 5000/ 179 5000/ 179
code weight d-h dens composition
0 ammonium perchlorate 68.000 -601 0.07040 1 cl 4 h 1 n 4 o
0 aluminum (pure crystaline) 12.000 0 0.09750 1 al
0 epoxy 201 20.000 -661 0.04040 24 h 16 c 4 o
the propellant density is 0.06313 lb/cu-in or 1.7474 gm/cc
the total propellant weight is 100.0000 grams
number of gram atoms of each element present in ingredients
4.026989 h
1.141357 c
0.578738 n
2.600292 o
0.444774 al
0.578738 cl
****************************chamber results follow *****************************
t(k) t(f) p(atm) p(psi) enthalpy entropy cp/cv gas rt/v
3098 5118 81.63 1200.00 -54.09 231.26 1.1890 3.773 21.634
specific heat (molar) of gas and total = 9.824 11.814
number mols gas and condensed = 3.773 0.219
1.045827e+000 co 1.016340e+000 h2 6.911820e-001 h2o 5.533573e-001 hcl
2.889427e-001 n2 2.191144e-001 al2o3* 9.530760e-002 co2 4.592917e-002 h
1.687644e-002 cl 1.143639e-002 ho 2.407126e-003 alcl 1.580532e-003 alcl2
1.224398e-003 alocl 6.738470e-004 no 5.082375e-004 alho2 5.012126e-004 alcl3
3.090869e-004 o 2.363468e-004 alho 8.375089e-005 o2 7.942520e-005 nh3
7.168903e-005 cho 4.859937e-005 cl2 3.626335e-005 cocl 3.622675e-005 alo
3.136510e-005 cnh 1.425074e-005 hocl 1.374346e-005 al 1.298290e-005 ch2o
1.258595e-005 nh2 6.236644e-006 ocl 3.808819e-006 alh 3.483641e-006 cnho
2.970532e-006 n 2.702406e-006 nh 2.686548e-006 al2o 1.468401e-006 nho
1.21759e-06 ho2
the molecular weight of the mixture is 25.048
****************************exhaust results follow *****************************
t(k) t(f) p(atm) p(psi) enthalpy entropy cp/cv gas rt/v
1633 2481 1.00 14.70 -130.36 231.26 1.2220 3.734 0.268
specific heat (molar) of gas and total = 9.036 10.324
number mols gas and condensed = 3.734 0.222
1.105206e+000 h2 9.683347e-001 co 6.188583e-001 h2o 5.786071e-001 hcl
2.893394e-001 n2 2.223673e-001 al2o3& 1.729507e-001 co2 1.563261e-004 h
6.418360e-005 cl 7.271502e-006 nh3 3.867836e-006 ho 1.251784e-006 alcl3
the molecular weight of the mixture is 25.278
**********performance: frozen on first line, shifting on second line**********
impulse is ex t* p* c* isp* opt-ex d-isp a*m ex-t
252.1 1.1982 2819 46.11 4977.8 10.22 440.5 0.12896 1496
257.6 1.1447 2896 46.97 5120.3 194.5 10.50 450.2 0.13265 1633
boost velocities for propellant density of 0.06313 (s.g. of 1.747)
10/ 20535 15/ 17515 25/ 13923 30/ 12715 55/ 9061 60/ 8589
69/ 7860 71/ 7716 88/ 6684 100/ 6114 150/ 4530 175/ 4016
200/ 3609 300/ 2571 1000/ 858 3000/ 296 5000/ 179 5000/ 179
code weight d-h dens composition
0 ammonium perchlorate 68.000 -601 0.07040 1 cl 4 h 1 n 4 o
0 aluminum (pure crystaline) 12.000 0 0.09750 1 al
0 epoxy 201 20.000 -661 0.04040 24 h 16 c 4 o
the propellant density is 0.06313 lb/cu-in or 1.7474 gm/cc
the total propellant weight is 100.0000 grams
number of gram atoms of each element present in ingredients
4.026989 h
1.141357 c
0.578738 n
2.600292 o
0.444774 al
0.578738 cl
****************************chamber results follow *****************************
t(k) t(f) p(atm) p(psi) enthalpy entropy cp/cv gas rt/v
3098 5118 81.63 1200.00 -54.09 231.26 1.1890 3.773 21.634
specific heat (molar) of gas and total = 9.824 11.814
number mols gas and condensed = 3.773 0.219
1.045827e+000 co 1.016340e+000 h2 6.911820e-001 h2o 5.533573e-001 hcl
2.889427e-001 n2 2.191144e-001 al2o3* 9.530760e-002 co2 4.592917e-002 h
1.687644e-002 cl 1.143639e-002 ho 2.407126e-003 alcl 1.580532e-003 alcl2
1.224398e-003 alocl 6.738470e-004 no 5.082375e-004 alho2 5.012126e-004 alcl3
3.090869e-004 o 2.363468e-004 alho 8.375089e-005 o2 7.942520e-005 nh3
7.168903e-005 cho 4.859937e-005 cl2 3.626335e-005 cocl 3.622675e-005 alo
3.136510e-005 cnh 1.425074e-005 hocl 1.374346e-005 al 1.298290e-005 ch2o
1.258595e-005 nh2 6.236644e-006 ocl 3.808819e-006 alh 3.483641e-006 cnho
2.970532e-006 n 2.702406e-006 nh 2.686548e-006 al2o 1.468401e-006 nho
1.21759e-06 ho2
the molecular weight of the mixture is 25.048
****************************exhaust results follow *****************************
t(k) t(f) p(atm) p(psi) enthalpy entropy cp/cv gas rt/v
1633 2481 1.00 14.70 -130.36 231.26 1.2220 3.734 0.268
specific heat (molar) of gas and total = 9.036 10.324
number mols gas and condensed = 3.734 0.222
1.105206e+000 h2 9.683347e-001 co 6.188583e-001 h2o 5.786071e-001 hcl
2.893394e-001 n2 2.223673e-001 al2o3& 1.729507e-001 co2 1.563261e-004 h
6.418360e-005 cl 7.271502e-006 nh3 3.867836e-006 ho 1.251784e-006 alcl3
the molecular weight of the mixture is 25.278
The results also include the relationship between the impulse and the exp ratio
I plotted the graph for the data. The graph indicates that when the exp ratio is between 9 and 12, the impulse gets its maximum value, which is about 257s
![QQ截图20130529211254.jpg]()
![QQ截图20130519193655.jpg]()
Think & Discovery
本计算实验是对ASR高能固体火箭燃料APER改进型的一次热力学计算，这篇简短的报告用英文写成，以此来避免在翻译过程中的数据缺失。本文针对进阶火箭爱好者和读者。
The formulation recently developed for the APER is tentative and can later include other components such as aluminum and DOS
FORMULATION TESTED: AP 68%
Epoxy Resin 20%
Al 12%
Due to the rapid and imponderable variations of most of systematic parameters, the environmental settings can hardly be predicted, so it will be pleasurable to set a mean value. For instance, the calculation requires chamber pressure which is altering through out the process of working. I chose 1200psi (8.27MPa) as the calculated one just by experience.
The variables or operationg conditions controlled in this calculation are listed below:
Temperature of the Chamber 298K
Chamber Pressure 1200psi
Exhaust Pressure 14.7psi (1 atm)
The result of calculation:
Code WEIGHT D-H DENS COMPOSITION
0 AMMONIUM PERCHLORATE 68.000 -601 0.07040 1 CL 4 H 1 N 4 O
0 ALUMINUM (PURE CRYSTALINE) 12.000 0 0.09750 1 AL
0 EPOXY 201 20.000 -661 0.04040 24 H 16 C 4 O
the propellant density is 0.06313 lb/cu-in or 1.7474 gm/cc
the total propellant weight is 100.0000 grams
number of gram atoms of each element present in ingredients
4.026989 h
1.141357 c
0.578738 n
2.600292 o
0.444774 al
0.578738 cl
****************************chamber results follow *****************************
t(k) t(f) p(atm) p(psi) enthalpy entropy cp/cv gas rt/v
3098 5118 81.63 1200.00 -54.09 231.26 1.1890 3.773 21.634
specific heat (molar) of gas and total = 9.824 11.814
number mols gas and condensed = 3.773 0.219
1.045827e+000 co 1.016340e+000 h2 6.911820e-001 h2o 5.533573e-001 hcl
2.889427e-001 n2 2.191144e-001 al2o3* 9.530760e-002 co2 4.592917e-002 h
1.687644e-002 cl 1.143639e-002 ho 2.407126e-003 alcl 1.580532e-003 alcl2
1.224398e-003 alocl 6.738470e-004 no 5.082375e-004 alho2 5.012126e-004 alcl3
3.090869e-004 o 2.363468e-004 alho 8.375089e-005 o2 7.942520e-005 nh3
7.168903e-005 cho 4.859937e-005 cl2 3.626335e-005 cocl 3.622675e-005 alo
3.136510e-005 cnh 1.425074e-005 hocl 1.374346e-005 al 1.298290e-005 ch2o
1.258595e-005 nh2 6.236644e-006 ocl 3.808819e-006 alh 3.483641e-006 cnho
2.970532e-006 n 2.702406e-006 nh 2.686548e-006 al2o 1.468401e-006 nho
1.21759e-06 ho2
the molecular weight of the mixture is 25.048
****************************exhaust results follow *****************************
t(k) t(f) p(atm) p(psi) enthalpy entropy cp/cv gas rt/v
1633 2481 1.00 14.70 -130.36 231.26 1.2220 3.734 0.268
specific heat (molar) of gas and total = 9.036 10.324
number mols gas and condensed = 3.734 0.222
1.105206e+000 h2 9.683347e-001 co 6.188583e-001 h2o 5.786071e-001 hcl
2.893394e-001 n2 2.223673e-001 al2o3& 1.729507e-001 co2 1.563261e-004 h
6.418360e-005 cl 7.271502e-006 nh3 3.867836e-006 ho 1.251784e-006 alcl3
the molecular weight of the mixture is 25.278
**********performance: frozen on first line, shifting on second line**********
impulse is ex t* p* c* isp* opt-ex d-isp a*m ex-t
252.1 1.1982 2819 46.11 4977.8 10.22 440.5 0.12896 1496
257.6 1.1447 2896 46.97 5120.3 194.5 10.50 450.2 0.13265 1633
boost velocities for propellant density of 0.06313 (s.g. of 1.747)
10/ 20535 15/ 17515 25/ 13923 30/ 12715 55/ 9061 60/ 8589
69/ 7860 71/ 7716 88/ 6684 100/ 6114 150/ 4530 175/ 4016
200/ 3609 300/ 2571 1000/ 858 3000/ 296 5000/ 179 5000/ 179
code weight d-h dens composition
0 ammonium perchlorate 68.000 -601 0.07040 1 cl 4 h 1 n 4 o
0 aluminum (pure crystaline) 12.000 0 0.09750 1 al
0 epoxy 201 20.000 -661 0.04040 24 h 16 c 4 o
the propellant density is 0.06313 lb/cu-in or 1.7474 gm/cc
the total propellant weight is 100.0000 grams
number of gram atoms of each element present in ingredients
4.026989 h
1.141357 c
0.578738 n
2.600292 o
0.444774 al
0.578738 cl
****************************chamber results follow *****************************
t(k) t(f) p(atm) p(psi) enthalpy entropy cp/cv gas rt/v
3098 5118 81.63 1200.00 -54.09 231.26 1.1890 3.773 21.634
specific heat (molar) of gas and total = 9.824 11.814
number mols gas and condensed = 3.773 0.219
1.045827e+000 co 1.016340e+000 h2 6.911820e-001 h2o 5.533573e-001 hcl
2.889427e-001 n2 2.191144e-001 al2o3* 9.530760e-002 co2 4.592917e-002 h
1.687644e-002 cl 1.143639e-002 ho 2.407126e-003 alcl 1.580532e-003 alcl2
1.224398e-003 alocl 6.738470e-004 no 5.082375e-004 alho2 5.012126e-004 alcl3
3.090869e-004 o 2.363468e-004 alho 8.375089e-005 o2 7.942520e-005 nh3
7.168903e-005 cho 4.859937e-005 cl2 3.626335e-005 cocl 3.622675e-005 alo
3.136510e-005 cnh 1.425074e-005 hocl 1.374346e-005 al 1.298290e-005 ch2o
1.258595e-005 nh2 6.236644e-006 ocl 3.808819e-006 alh 3.483641e-006 cnho
2.970532e-006 n 2.702406e-006 nh 2.686548e-006 al2o 1.468401e-006 nho
1.21759e-06 ho2
the molecular weight of the mixture is 25.048
****************************exhaust results follow *****************************
t(k) t(f) p(atm) p(psi) enthalpy entropy cp/cv gas rt/v
1633 2481 1.00 14.70 -130.36 231.26 1.2220 3.734 0.268
specific heat (molar) of gas and total = 9.036 10.324
number mols gas and condensed = 3.734 0.222
1.105206e+000 h2 9.683347e-001 co 6.188583e-001 h2o 5.786071e-001 hcl
2.893394e-001 n2 2.223673e-001 al2o3& 1.729507e-001 co2 1.563261e-004 h
6.418360e-005 cl 7.271502e-006 nh3 3.867836e-006 ho 1.251784e-006 alcl3
the molecular weight of the mixture is 25.278
**********performance: frozen on first line, shifting on second line**********
impulse is ex t* p* c* isp* opt-ex d-isp a*m ex-t
252.1 1.1982 2819 46.11 4977.8 10.22 440.5 0.12896 1496
257.6 1.1447 2896 46.97 5120.3 194.5 10.50 450.2 0.13265 1633
boost velocities for propellant density of 0.06313 (s.g. of 1.747)
10/ 20535 15/ 17515 25/ 13923 30/ 12715 55/ 9061 60/ 8589
69/ 7860 71/ 7716 88/ 6684 100/ 6114 150/ 4530 175/ 4016
200/ 3609 300/ 2571 1000/ 858 3000/ 296 5000/ 179 5000/ 179
code weight d-h dens composition
0 ammonium perchlorate 68.000 -601 0.07040 1 cl 4 h 1 n 4 o
0 aluminum (pure crystaline) 12.000 0 0.09750 1 al
0 epoxy 201 20.000 -661 0.04040 24 h 16 c 4 o
the propellant density is 0.06313 lb/cu-in or 1.7474 gm/cc
the total propellant weight is 100.0000 grams
number of gram atoms of each element present in ingredients
4.026989 h
1.141357 c
0.578738 n
2.600292 o
0.444774 al
0.578738 cl
****************************chamber results follow *****************************
t(k) t(f) p(atm) p(psi) enthalpy entropy cp/cv gas rt/v
3098 5118 81.63 1200.00 -54.09 231.26 1.1890 3.773 21.634
specific heat (molar) of gas and total = 9.824 11.814
number mols gas and condensed = 3.773 0.219
1.045827e+000 co 1.016340e+000 h2 6.911820e-001 h2o 5.533573e-001 hcl
2.889427e-001 n2 2.191144e-001 al2o3* 9.530760e-002 co2 4.592917e-002 h
1.687644e-002 cl 1.143639e-002 ho 2.407126e-003 alcl 1.580532e-003 alcl2
1.224398e-003 alocl 6.738470e-004 no 5.082375e-004 alho2 5.012126e-004 alcl3
3.090869e-004 o 2.363468e-004 alho 8.375089e-005 o2 7.942520e-005 nh3
7.168903e-005 cho 4.859937e-005 cl2 3.626335e-005 cocl 3.622675e-005 alo
3.136510e-005 cnh 1.425074e-005 hocl 1.374346e-005 al 1.298290e-005 ch2o
1.258595e-005 nh2 6.236644e-006 ocl 3.808819e-006 alh 3.483641e-006 cnho
2.970532e-006 n 2.702406e-006 nh 2.686548e-006 al2o 1.468401e-006 nho
1.21759e-06 ho2
the molecular weight of the mixture is 25.048
****************************exhaust results follow *****************************
t(k) t(f) p(atm) p(psi) enthalpy entropy cp/cv gas rt/v
1633 2481 1.00 14.70 -130.36 231.26 1.2220 3.734 0.268
specific heat (molar) of gas and total = 9.036 10.324
number mols gas and condensed = 3.734 0.222
1.105206e+000 h2 9.683347e-001 co 6.188583e-001 h2o 5.786071e-001 hcl
2.893394e-001 n2 2.223673e-001 al2o3& 1.729507e-001 co2 1.563261e-004 h
6.418360e-005 cl 7.271502e-006 nh3 3.867836e-006 ho 1.251784e-006 alcl3
the molecular weight of the mixture is 25.278
The results also include the relationship between the impulse and the exp ratio
I plotted the graph for the data. The graph indicates that when the exp ratio is between 9 and 12, the impulse gets its maximum value, which is about 257s
Think & Discovery
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回 楼主(反正已经死) 的帖子
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回 2楼(bolide) 的帖子
别急，我自己会重新写中文版的，这个帖子用英文的主要是我最近时间非常紧，而计算输出的数据全是英文的，来不及翻译了，于是就写英文的。后面我会详细介绍这款软件的应用和相关热力学计算理论，并且写中文教程来解释如何用propep辅助开发新燃料。另外，我已指示ASR电子组的程序员们重新校对propep的数据库，并准备汉化本软件，替换美制单位为国际单位。
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Re:回 2楼(bolide) 的帖子
引用第5楼反正已经死于2013-05-30 17:54发表的 回 2楼(bolide) 的帖子 :
我已指示ASR电子组的程序员们重新校对propep的数据库，并准备汉化本软件，替换美制单位为国际单位。
而且我们尝试添加一些符合中国国情的物质的数据
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