Philae (spacecraft)
Design
The lander was designed to deploy from the main spacecraft body and descend from an orbit of 22.5 kilometres (14 mi) along a ballistic trajectory.

Philae (spacecraft)

Section Title: Design
Table Section Text: The lander was designed to deploy from the main spacecraft body and descend from an orbit of 22.5 kilometres (14 mi) along a ballistic trajectory.

Spacecraft component	Mass

Structure	18.0 kg	39.7 lb

Thermal control system	3.9 kg	8.6 lb

Power system	12.2 kg	27 lb

Active descent system	4.1 kg	9.0 lb

Reaction wheel	2.9 kg	6.4 lb

Landing gear	10.0 kg	22 lb

Anchoring system	1.4 kg	3.1 lb

Central data management system	2.9 kg	6.4 lb

Telecommunications system	2.4 kg	5.3 lb

Common electronics box	9.8 kg	22 lb

Mechanical support system, harness, balancing mass	3.6 kg	7.9 lb

Scientific payload	26.7 kg	59 lb

Sum	97.9 kg	216 lb

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