Table 3. Energy Performance of AP and AN Propellants Doped with Different Nanocatalystsa.
| codes | propellants | Isp (N s kg–1) | C* (m s–1) | Tc (K) | Mc (g mol–1) | Qp (kJ kg–1) |
|---|---|---|---|---|---|---|
| #1-AP | AP0.8/GAP0.2 | 2438.2 | 1510.9 | 3017 | 27.132 | 4774.1 |
| #2-AP | AP0.7/TAGN0.1/GAP0.2 | 2498.0 | 1551.1 | 3068 | 25.964 | 5029.5 |
| #3-AP | AP0.7/Fe2O3,0.1/GAP0.2 | 2312.8 | 1428.4 | 2952 | 29.637 | 4440.2 |
| #4-AP | AP0.7/CuO0.1/GAP0.2 | 2333.4 | 1445.2 | 2975 | 29.406 | 4370.9 |
| #5-AP | AP0.7/NiO0.1/GAP0.2 | 2312.8 | 1428.6 | 2943 | 29.844 | 4370.8 |
| #6-AP | AP0.7/Fe0.1/GAP0.2 | 2343.2 | 1465.0 | 3081 | 29.507 | 4632.9 |
| #7-AP | AP0.7/Cu0.1/GAP0.2 | 2328.5 | 1430.6 | 2991 | 29.488 | 4368.4 |
| #8-AP | AP0.7/Ni0.1/GAP0.2 | 2325.5 | 1424.3 | 2992 | 29.946 | 4407.7 |
| #9-AP | AP0.7/RDX0.1/GAP0.2 | 2513.7 | 1554.9 | 3121 | 26.600 | 5017.5 |
| #10-AP | AP0.7/HMX0.1/GAP0.2 | 2513.6 | 1554.3 | 3120 | 26.602 | 5016.3 |
| #11-AN | AN0.8/GAP0.2 | 2263.8 | 1431.4 | 2373 | 22.672 | 4309.3 |
| #12-AN | AN0.7/TAGN0.1/GAP0.2 | 2248.1 | 1425.1 | 2282 | 21.867 | 4108.8 |
| #13-AN | AN0.7/Fe2O3,0.1/GAP0.2 | 2102.1 | 1344.9 | 2204 | 24.052 | 3708.1 |
| #14-AN | AN0.7/CuO0.1/GAP0.2 | 2130.5 | 1365.1 | 2279 | 23.956 | 3797.6 |
| #15-AN | AN0.7/NiO0.1/GAP0.2 | 2115.8 | 1357.1 | 2242 | 23.991 | 3755.8 |
| #16-AN | AN0.7/Fe0.1/GAP0.2 | 2112.9 | 1360.4 | 2223 | 23.745 | 3729.1 |
| #17-AN | AN0.7/Cu0.1/GAP0.2 | 2115.8 | 1357.9 | 2252 | 23.856 | 3722.3 |
| #18-AN | AN0.7/Ni0.1/GAP0.2 | 2113.9 | 1362.1 | 2239 | 23.783 | 3723.1 |
| #19-AN | AN0.7/RDX0.1/GAP0.2 | 2287.3 | 1446.7 | 2414 | 22.515 | 4335.1 |
| #20-AN | AN0.7/HMX0.1/GAP0.2 | 2286.4 | 1446.5 | 2413 | 22.514 | 4332.7 |
a
The superscripts (0.1, 0.2, 0.7, and 0.8) in propellant formulas represent the mass fraction of the corresponding ingredients. Isp is the standard specific impulse; C* is the characteristic speed; Tc is the combustion chamber temperature; Mc is the average molecular weight of combustion products; and Qp is the explosion heat. All of the parameters for energy performances were calculated by means of software ProPep 3.0 at a condition of Pc/Pe = 70:1 and T0 = 298 K, in which Pc is the pressure of combustion chamber (Pc = 7 MPa), Pe is the pressure of the nozzle (Pe = 0.1 MPa), and T0 is the initial temperature of propellants.