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4 Structure and Mechanism Technology of Lunar Lander
4.4 Mechanism Design and Verification of Lunar Lander
4.4.1 Solar Panel Mechanism
The solar panel provide electric energy for the spacecraft and are key components
of the spacecraft. The solar panel is generally divided into mechanical parts (solar
panel mechanism) and electrical parts according to the functions of the components.
The solar panel mechanism serves as a carrier for the electrical part, and its structural
substrate provides an installation surface of a specified area for the solar cell circuit,
as well as providing sufficient strength and rigidity to support the normal operation
of the solar cell circuit; And the mechanism driving part deploys solar panel to a
designated position as well as keeping solar cell’s orientation to the sun.
With the development of aerospace technology, solar panel has evolved from
body-mounted to deployable solar panel to meet the greater power requirements of
spacecraft. To date, the solar panel used on Chinese satellites is all multi-panel and
deployable type of solar panel. The solar cell circuit is laid on a rigid substrate. The
solar panel is folded and held down on the lateral plates of space craft in launch
vehicle fairing and deployed into designated position to form a complete plane after
orbit injection. The sun orientation of solar panel is realized by Solar Array Drive
Assembly (SADA) controlled by the GNC subsystem according to the characteristics of orbit. For the solar panel mechanism of the lunar lander, in addition to
the functions including holddown and release on orbit as usual spacecraft, it was
generally necessary to be capable of folding and unfolding repeatedly, i.e., the solar
panels could be folded(and sometimes be held auxiliary if necessary) before orbit
maneuver and soft-landing to withstand load, as well as unfolded after orbit change
and soft-landing.
1. Determination of Design Requirements
As an important component of the entire spacecraft, the basic specification of solar
panel is determined by spacecraft configuration, orbit and power energy requirement,
such as the area, folding/unfolding position, orientation and loading conditions, etc.
in phase B.
Generally, there were following requirements for the solar panels of the lunar
lander:
(1) Capable of folding, hold down and release, unfolding. In order to meet the
requirements of fairing envelope volume and load of the launch vehicle, the
solar panels were often folded and held down, while released and deployed
after orbit injection.
(2) Supporting the solar cell circuit. As part of the solar panel mechanism, the solar
panel substrate provided effective support for the solar cell circuit to ensure
the normal operation.
(3) Capable of folding and unfolding repeatedly. During orbiting maneuver, there
would be overload when the engine as ignited and shut off. To prevent the solar
4 Structure and Mechanism Technology of Lunar Lander
4.4 Mechanism Design and Verification of Lunar Lander
4.4.1 Solar Panel Mechanism
The solar panel provide electric energy for the spacecraft and are key components
of the spacecraft. The solar panel is generally divided into mechanical parts (solar
panel mechanism) and electrical parts according to the functions of the components.
The solar panel mechanism serves as a carrier for the electrical part, and its structural
substrate provides an installation surface of a specified area for the solar cell circuit,
as well as providing sufficient strength and rigidity to support the normal operation
of the solar cell circuit; And the mechanism driving part deploys solar panel to a
designated position as well as keeping solar cell’s orientation to the sun.
With the development of aerospace technology, solar panel has evolved from
body-mounted to deployable solar panel to meet the greater power requirements of
spacecraft. To date, the solar panel used on Chinese satellites is all multi-panel and
deployable type of solar panel. The solar cell circuit is laid on a rigid substrate. The
solar panel is folded and held down on the lateral plates of space craft in launch
vehicle fairing and deployed into designated position to form a complete plane after
orbit injection. The sun orientation of solar panel is realized by Solar Array Drive
Assembly (SADA) controlled by the GNC subsystem according to the characteristics of orbit. For the solar panel mechanism of the lunar lander, in addition to
the functions including holddown and release on orbit as usual spacecraft, it was
generally necessary to be capable of folding and unfolding repeatedly, i.e., the solar
panels could be folded(and sometimes be held auxiliary if necessary) before orbit
maneuver and soft-landing to withstand load, as well as unfolded after orbit change
and soft-landing.
1. Determination of Design Requirements
As an important component of the entire spacecraft, the basic specification of solar
panel is determined by spacecraft configuration, orbit and power energy requirement,
such as the area, folding/unfolding position, orientation and loading conditions, etc.
in phase B.
Generally, there were following requirements for the solar panels of the lunar
lander:
(1) Capable of folding, hold down and release, unfolding. In order to meet the
requirements of fairing envelope volume and load of the launch vehicle, the
solar panels were often folded and held down, while released and deployed
after orbit injection.
(2) Supporting the solar cell circuit. As part of the solar panel mechanism, the solar
panel substrate provided effective support for the solar cell circuit to ensure
the normal operation.
(3) Capable of folding and unfolding repeatedly. During orbiting maneuver, there
would be overload when the engine as ignited and shut off. To prevent the solar