Landing gear for spacecraft
A pivotal connection and a substantially rigid yet disruptable mechanical connection mount a respective foot pad on a distal end of each one of plural landing legs of a lander spacecraft. The mechanical connection includes at least one predetermined rated breaking point designed to break when the foot pad makes contact with a landing ground surface. At least two sensor elements, preferably electrical conductors or switches, are incorporated in the mechanical connection(s) of one or more foot pads. When the foot pad makes ground contact, the mechanical connection breaks at the rated breaking point(s), which also disrupts or actuates the sensor element(s), which thus provides a signal to an evaluating unit, which triggers the shut-down of at least one braking retrorocket or retrothruster.
1. A landing gear system for a spacecraft that includes plural landing legs connected to and extending from a spacecraft body, and at least one retrorocket or retrothruster mounted on said spacecraft body;
wherein said landing gear system comprises an evaluating unit that is connected for control signal transmission to said at least one retrorocket or retrothruster; and
wherein said landing gear system further comprises respectively for each landing leg of said plural landing legs:
a landing foot pad arranged at a distal end of said landing leg,
a pivotal connection joint that pivotally connects said landing foot pad with said distal end of said landing leg,
a substantially rigid truss arrangement of plural hollow struts that immovably connects said landing foot pad with said distal end of said landing leg, wherein at least two respective hollow struts of said plural hollow struts each respectively have a rated breaking point with a lower mechanical strength than a remaining portion of each one of said at least two respective hollow struts, and
at least two electrical sensor elements selected from the group consisting of electrical switches and breakable electrical conductor wires, wherein said sensor elements are respectively arranged in said at least two respective hollow struts that each have said rated breaking point, wherein said sensor elements are connected by at least one electrical conduction path to said evaluating unit, and wherein said sensor elements are respectively adapted to open or close said at least one electrical conduction path in reaction to a mechanical disruption of said rated breaking points of said at least two respective hollow struts in which said sensor elements are arranged.
2. The landing gear system according to claim 1 , wherein each one of said sensor elements respectively comprises one of said breakable electrical conductor wires.
3. The landing gear system according to claim 1 , wherein each one of said sensor elements respectively consists of one of said breakable electrical conductor wires.
4. The landing gear system according to claim 1 , wherein each one of said sensor elements respectively comprises one of said electrical switches.
5. The landing gear system according to claim 1 , wherein each one of said sensor elements respectively consists of one of said electrical switches.
6. The landing gear system according to claim 1 , wherein said evaluating unit is adapted to transmit to said at least one retrorocket or retrothruster a shut-down signal effective to shut-down said at least one retrorocket or retrothruster responsive to a sensor signal produced by at least one of said sensor elements sensing said mechanical disruption.
7. The landing gear system according to claim 1 , wherein said truss arrangement is substantially rigid so as to render said landing foot pad immovable relative to said landing leg until said at least one rated breaking point is disrupted, and after said at least one rated breaking point is disrupted said truss arrangement releases said landing foot pad to be movable relative to said landing leg via said pivotal connection joint.