Aircraft turbomachine computer
View Patent ↗An aircraft turbomachine calculator including a parallelepiped metal casing including an electronic circuit wherein a control channel and a monitoring channel are integrated. The casing includes a first cavity wherein a first electronic board is provided for managing the control channel and a second cavity, independent of the first cavity, wherein a second electronic board is provided for managing the monitoring channel, these electronic boards being provided in two planes oriented with respect to each other at an angle of 90°.
1. An aircraft turbomachine calculator comprising:
a parallelepiped metal casing comprising a single mount, a first cavity and a second cavity, the first cavity and the second cavity being sealed with respect to each other; and
an electronic circuit comprising a first electronic board configured for managing an aircraft turbomachine control channel, and a second electronic board configured for managing an aircraft turbomachine monitoring channel, the second electronic board being separate from the first electronic board,
wherein the first electronic board is arranged in the first cavity, the first electronic board extending in a first plane,
wherein the second electronic board is arranged in the second cavity, the second electronic board extending in a second plane,
wherein the first electronic board and the second electronic board are permanently oriented with respect to each other at an angle of 90°, and
wherein the first cavity and the second cavity are airtight.
2. The calculator according to claim 1 , wherein each electronic board is connected to at least one connector located on a face of the casing.
3. The calculator according to claim 2 , wherein each connector is a multipin connector.
4. The calculator according to claim 1 , further comprising a third electronic board provided in the first cavity, the third electronic board being electrically connected to the first electronic board.
5. The calculator according to claim 1 , wherein the first and second electronic boards are galvanically isolated from each other.
6. The calculator according to claim 5 , wherein the first and second electronic boards are connected to each other by an optical link.
7. The calculator according to claim 1 , wherein the casing is made of aluminum or titanium.
8. The calculator according to claim 1 , wherein the casing has a width between 10 and 40 cm, a height between 10 and 30 cm, and a thickness between 3 and 10 cm.
9. An aircraft comprising a calculator according to claim 1 .
10. The calculator according to claim 1 , wherein a partition is provided between the first cavity and the second cavity such that the first cavity and the second cavity are sealed relative to one another.
11. An aircraft turbomachine calculator, comprising:
a parallelepiped metal casing comprising a single mount, a first cavity and a second cavity, the first cavity and the second cavity being sealed in relation to each other; and
an electronic circuit comprising a first electronic board configured for managing an aircraft turbomachine control channel, and a second electronic board configured for managing an aircraft turbomachine monitoring channel, the second electronic board being mechanically independent from the first electronic board,
wherein the first electronic board is arranged in the first cavity, the first electronic board extending in a first plane,
wherein the second electronic board is arranged in the second cavity, the second electronic board extending in a second plane,
wherein the first electronic board and the second electronic board are permanently oriented with respect to each other at an angle of 90°, and
wherein the first cavity and the second cavity are airtight.
12. The calculator according to claim 11 , wherein a partition is provided between the first cavity and the second cavity such that the first cavity and the second cavity are sealed relative to one another.
13. An aircraft turbomachine calculator comprising:
a parallelepiped metal casing defined by six faces including a first face and a second face, the casing comprising a first cavity on the first face and a second cavity on the second face, the first cavity and the second cavity being sealed with respect to each other; and
an electronic circuit comprising a first electronic board configured for managing an aircraft turbomachine control channel, and a second electronic board configured for managing an aircraft turbomachine monitoring channel, the second electronic board being separate from the first electronic board,
wherein the first electronic board is arranged in the first cavity,
wherein the second electronic board is arranged in the second cavity, and
wherein the first face and the second face are permanently oriented with respect to each other at an angle of 90°.