| 摘要 |
The invention relates to the field of rocket engines, and specifically to a propulsion assembly (10) including a first tank (11), for a first liquid propellant, a second tank (12), for a second liquid propellant, a pressurisation device (60) configured to maintain a substantially higher pressure in the second tank (12) than in the first tank (11), and a single-shaft turbopump (30), including a turbine (33), a first pump (31) and a second pump (32). The turbine (33) is actuated by the expansion of the first propellant after passing through a regenerative heat exchanger (44), and in turn actuates, via the single rotary shaft (34) of the turbopump (30), said first and second pumps (31, 32), pumping said first and second propellants, respectively, in order to supply a thrust chamber (40). |
