Design Optimization and Parameter Analysis of a Hybrid Rocket Motor-Powered Small LEO Launch Vehicle

Table 10

Optimal results of SLV cases with different payload mass/orbit heights.

Parameter	Description
DV1	(m)	1.466	1.426	1.510	1.394	1.518
DV2		0.994	0.994	0.981	0.980	1.000
DV3		0.936	0.958	0.979	0.977	0.979
DV4		0.498	0.473	0.392	0.405	0.477
DV5		0.989	0.979	0.927	0.949	0.989
DV6	(m)	0.058	0.082	0.071	0.069	0.061
DV7	(m)	0.254	0.342	0.229	0.257	0.222
DV8	(m)	0.283	0.228	0.319	0.299	0.243
DV9	(kN)	359.836	364.718	465.276	350.354	464.752
DV10	(kN)	92.776	91.446	116.690	100.868	116.972
DV11	(kN)	16.448	10.369	11.016	10.958	19.369
DV12	(MPa)	5.288	5.529	6.994	6.902	6.081
DV13	(MPa)	5.928	7.000	6.288	6.952	6.501
DV14	(MPa)	3.772	5.656	2.037	5.579	2.095
DV15		7.000	4.343	4.890	3.701	4.444
DV16		3.151	3.014	2.923	3.289	3.046
DV17		2.829	2.072	2.351	2.755	2.250
DV18		20.916	22.300	30.020	17.212	32.685
DV19		85.460	62.732	88.940	84.065	93.787
DV20		81.554	100.000	97.231	91.644	99.179
DV21	(°)	2.189	1.682	0.958	2.734	2.168
DV22		0.516	0.563	0.269	0.524	0.437
DV23	(s)	83.285	131.649	131.352	27.845	84.972
Target	(kg)	16489	19675	22149	17256	20890
Constraint	(kg/(sm^2))	98	105	115	100	105
Constraint	(kg/(sm^2))	105	260	95	125	90
Constraint	(kg/(sm^2))	59	25	40	40	45
Constraint		13.1	14.9	16.0	15.8	15.2
Constraint	(g)	15.8	15.7	16.0	15.8	15.2
Constraint	(g)	0.96	0.38	0.49	0.96	0.86
Constraint	(MPa)	0.066	0.048	0.057	0.066	0.066
Constraint	(km)	306	510	728	309	321