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

Table 4

Description and ranges of variables.

Variable	Description	Unit	Lower bound	Upper bound
DV1	Diameter of the 1st stage	m	1	2.5
DV2	Diameter ratio of the 2nd stage to1st stage	—	0.7	1
DV3	Ratio of the envelope diameter of the 2nd HRM to the diameter of the 2nd stage	—	0.5	1
DV4	Diameter ratio of the 3rd tank to the 3rd stage	—	0.3	0.7
DV5	Ratio of the envelope diameter of the 3rd HRM to the diameter of the 3rd stage	—	0.3	1
DV6	Initial thickness of the 1st grain	m	0.05	0.4
DV7	Initial thickness of the 2nd grain	m	0.05	0.4
DV8	Initial thickness of the 3rd grain	m	0.05	0.4
DV9	Initial thrust at the 1st stage	kN	40	1250
DV10	Initial thrust at the 2nd stage	kN	2	650
DV11	Initial thrust at the 3rd stage	kN	0.25	85
DV12	Initial pressure at the 1st chamber	MPa	2	7
DV13	Initial pressure at the 2nd chamber	MPa	2	7
DV14	Initial pressure at the 3rd chamber	MPa	2	7
DV15	Initial oxidizer-fuel ratio at the 1st stage	—	2	7
DV16	Initial oxidizer-fuel ratio at the 2nd stage	—	2	7
DV17	Initial oxidizer-fuel ratio at the 3rd stage	—	2	7
DV18	Expansion ratio at the 1st stage	—	10	50
DV19	Expansion ratio at the 2nd stage	—	10	100
DV20	Expansion ratio at the 3rd stage	—	10	100
DV21	Maximum attack angle during the program-turn phase	°	0.1	3
DV22	Control parameter of attack angle during the program-turn phase	—	0.15	1
DV23	Glide time between 2nd and 3rd stages	s	0	300