3.3 Mission Analysis
65
energy, high-flux and long term electrons that may induce the Internal Charging
Effects during LTO, circumlunar orbit, powered descent and operation on lunar
surface. So it is unnecessary to consider the Internal Charging Effects in the life
time of lunar lander.
The summary of the space radiation environment of charged particles and their
effects on lunar lander are listed in Table 3.2.
3. Analysis of the environment effects induced by soft landing.
1) Analysis of plume effects
Generally there would be at least one orbit control engine and several thrusters for
attitude control in order to satisfy the requirements of orbit and attitude control in
lunar lander. The plume of engine and thrusters in vacuum when they are ignited
would cause force, thermal and pollution effects on surrounded equipments. Especially, when lunar lander was approaching lunar surface, there might be worse effects
because the plume of orbit control engine was reflected by lunar surface. So it’s
important to analyze and validate effects of engine plume.
Table 3.2 Summary of the space radiation environment of charged particles and their effects on
lunar lander
Flight phase
Earth’s
radiation belt
GCR SCR
Solar wind Radiation effects
LTO
Yes in Earth’s
magnetopause
No beyond
Earth’s
magnetopause
Yes
Yes when there is
solar flare,
otherwise no
Yes
TID: yes for
material in
Earth’s
magnetosphere,
no for electronic
parts and
components
SEE: yes
SCDE: yes, but
no influence on
lunar lander
Damage to solar
cell: ignored
Circumlunar and
powered descent
No
TID: yes when
there is solar
flare, otherwise
no
Damage to solar
cell: yes when
there is solar
flare, otherwise
no
SEE: yes
SCDE: weak
65
energy, high-flux and long term electrons that may induce the Internal Charging
Effects during LTO, circumlunar orbit, powered descent and operation on lunar
surface. So it is unnecessary to consider the Internal Charging Effects in the life
time of lunar lander.
The summary of the space radiation environment of charged particles and their
effects on lunar lander are listed in Table 3.2.
3. Analysis of the environment effects induced by soft landing.
1) Analysis of plume effects
Generally there would be at least one orbit control engine and several thrusters for
attitude control in order to satisfy the requirements of orbit and attitude control in
lunar lander. The plume of engine and thrusters in vacuum when they are ignited
would cause force, thermal and pollution effects on surrounded equipments. Especially, when lunar lander was approaching lunar surface, there might be worse effects
because the plume of orbit control engine was reflected by lunar surface. So it’s
important to analyze and validate effects of engine plume.
Table 3.2 Summary of the space radiation environment of charged particles and their effects on
lunar lander
Flight phase
Earth’s
radiation belt
GCR SCR
Solar wind Radiation effects
LTO
Yes in Earth’s
magnetopause
No beyond
Earth’s
magnetopause
Yes
Yes when there is
solar flare,
otherwise no
Yes
TID: yes for
material in
Earth’s
magnetosphere,
no for electronic
parts and
components
SEE: yes
SCDE: yes, but
no influence on
lunar lander
Damage to solar
cell: ignored
Circumlunar and
powered descent
No
TID: yes when
there is solar
flare, otherwise
no
Damage to solar
cell: yes when
there is solar
flare, otherwise
no
SEE: yes
SCDE: weak