Гравитационные потери TLI маневра

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The lower limit on vehicle stage thrust is dictated by the need to minimize the gravity losses. Increased gravity losses mean the need for additional propellant, and, thus, growth of the vehicle mass. Figure 6-58 shows the delta-V loss as a function of stage initial T/W ratio. Fr om this curve, the recommended lower limit on T/W ratio is This value can then be multiplied to the total EDS plus payload mass to calculate the lower thrust limit for the EDS. This figure shows a plot of the delta-V loss as function stage initial T/W ratio. Fr om this curve, recommended lower lim it on ratio is 0.4. This value can then be multiplied to the total EDS plus payload mass to calculate the lower thrust lim it for the EDS.

Параметры миссии на отлетную траекторию к Луне:  

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• ХС TLI - 3120 м/сек; 
• промежуточная НОО 296.32 км х 296.32 км
  

Source: The Exploration Systems Architecture Study (ESAS) Launch Vehicles and Earth Departure Stages

NASA - 150 p.
Link

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Source: Parametric Model of a Lunar Base for Mass and Cost Estimates
By Peter Eckart. Herbert Utz Verlag - 1996 p. 200

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Typical injection velocities as a function of injection altitude are shown in Fig. 12.13 for 50-, 66-, and 90-h transfer
times. The lower and upper values for the shaded regions represent perigee and apogee lunar radii, respectively. These
velocities are impulsive inertial (absolute) velocities and may be partly composed of a component of velocity due to Earth's
rotation.

Source: White, J. F., Flight Performance Handbook for Powered Flight Operations, Wiley,
New York, 1963, pp. 2-54