3.5 System Components and Specifications
83
Table 3.3 (continued)
Item
Major specifications
Data rate of telemetry
128 b/s, 1024 b/s (without
channel coding)
256 b/s, 2048 b/s (with channel
coding)
Data rate of mid-gain antenna
500 kb/s (with channel coding)
Data transmission rate
2.5 Mb/s (with channel coding)
lunar surface at last. Thus design of propellant budget margin should be traded off
in a reasonable scope.
3.6 System Configuration Design
3.6.1 Design Principles
To implement soft landing, there was usually landing cushion mechanism which
was folded before launch and unfolded after injection of launch trajectory. The mass
of propellant might be 2/3 of the launch mass to meet the requirements of LOI
and powered descent. There should be sensors for speedometer, ranging, terrain
identification during powered descent to be installed oriented to lunar surface. The
position of the lunar rover on lunar lander should be convenient for separation and
deployment.
According to above analysis, the design of lunar lander configuration should
follow principles as following:
(1) Compatible with mechanic interface between lunar lander and the launch
vehicle.
(2) Lower vertical height of mass center to ensure landing stability.
(3) Assurance of safety and reliability of the lunar rover deployment.
(4) Satisfying requirements of installation accuracy, orientation, field of view,
power supply and thermal control.
(5) Protection against lunar dust activated by landing impact.
(6) Satisfying requirements of accessibility for assembling, lifting, turning over,
shipping, fueling, docking and test.
The basic idea for design of the CE-3 lunar lander configuration is listed as following:
(1) Cross strut structure with lateral plates. The main structure of CE-3 lunar
lander was cross strut plates with the interface ring. There were four instrument
modules on +Y, −Y, +Z, and −Z plates. The load could be transferred to the
interface ring by cross strut. The dynamics of lunar lander was good because
the path for force transfer was short and the bearing is reasonable. At the same
83
Table 3.3 (continued)
Item
Major specifications
Data rate of telemetry
128 b/s, 1024 b/s (without
channel coding)
256 b/s, 2048 b/s (with channel
coding)
Data rate of mid-gain antenna
500 kb/s (with channel coding)
Data transmission rate
2.5 Mb/s (with channel coding)
lunar surface at last. Thus design of propellant budget margin should be traded off
in a reasonable scope.
3.6 System Configuration Design
3.6.1 Design Principles
To implement soft landing, there was usually landing cushion mechanism which
was folded before launch and unfolded after injection of launch trajectory. The mass
of propellant might be 2/3 of the launch mass to meet the requirements of LOI
and powered descent. There should be sensors for speedometer, ranging, terrain
identification during powered descent to be installed oriented to lunar surface. The
position of the lunar rover on lunar lander should be convenient for separation and
deployment.
According to above analysis, the design of lunar lander configuration should
follow principles as following:
(1) Compatible with mechanic interface between lunar lander and the launch
vehicle.
(2) Lower vertical height of mass center to ensure landing stability.
(3) Assurance of safety and reliability of the lunar rover deployment.
(4) Satisfying requirements of installation accuracy, orientation, field of view,
power supply and thermal control.
(5) Protection against lunar dust activated by landing impact.
(6) Satisfying requirements of accessibility for assembling, lifting, turning over,
shipping, fueling, docking and test.
The basic idea for design of the CE-3 lunar lander configuration is listed as following:
(1) Cross strut structure with lateral plates. The main structure of CE-3 lunar
lander was cross strut plates with the interface ring. There were four instrument
modules on +Y, −Y, +Z, and −Z plates. The load could be transferred to the
interface ring by cross strut. The dynamics of lunar lander was good because
the path for force transfer was short and the bearing is reasonable. At the same