Redundant aircraft cooling system for redundant aircraft components
A technology for cooling systems and aircraft components, applied to aircraft parts, household refrigeration devices, cooling fluid circulation devices, etc., can solve problems such as electronic devices can no longer work, new takeoffs can no longer be performed, and aircraft availability is reduced
Inactive Publication Date: 2009-10-14
AIRBUS OPERATIONS GMBH
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- Abstract
- Description
- Claims
- Application Information
AI Technical Summary
Problems solved by technology
If the cooling unit fails, e.g. due to a leak, the electronics cooled by it can no longer function
This has a restrictive effect on the operation of the aircraft, because although the flight can continue, taking into account the redundant design of the electronics, a new take-off is certainly not possible for safety reasons
As a result, aircraft availability is reduced
Method used
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Embodiment Construction
[0013] The invention will now be described in more detail with reference to a single schematic diagram showing an aircraft cooling system according to the invention.
[0014] The aircraft cooling system according to the invention cools a first heat load 2a formed by a first electronic device and a second heat load 2b formed by a second electronic device. The first coolant flow 4a cools the first heat load 2a and the second coolant flow 4b cools the second heat load 2b. The first coolant flow 4a and the second coolant flow 4b are in each case an electric circuit, the coolant being generally in liquid state.
[0015] The electronic device to be cooled can be arranged on a so-called cooling plate through which a coolant flow flows. Thus, the cooling plate acts as a heat exchanger. A plurality of electronic devices can be accommodated in so-called electronic compartments.
[0016] The first heat exchanger 6a is located in the first ram air duct 8a. The first pump 10a causes th...
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An aircraft cooling system (1) according to the invention comprises a first coolant stream (4a) which cools at least one first heat load (2a), and a second coolant stream (4b) which cools at least one second heat load (2b), wherein the aircraft cooling system (1) is formed such that the first heat load (2a) and the second heat load (2b) are thermally coupled together. The first heat load (2a) and the second heat load (2b) are formed by two mutually redundant- aircraft components. A third coolant stream (12) can thermally couple the first heat load (2a) and the second heat load (2b) together. The third coolant stream (12) can be cooled by a heat sink (16), and the third coolant stream concurrently cool the first heat load (2a) and the second heat load (2b) after pass through the heat receiver.
Description
technical field [0001] The present invention relates to a redundant aircraft cooling system for redundant aircraft components. Background technique [0002] Safety-relevant components of the aircraft, such as electronics, are provided by redundant design, ie they are provided in the aircraft in duplicate, for example. Because electronic devices dissipate power, they must be cooled. For this purpose, the electronics are typically arranged on a cooling plate and accommodated in so-called electronics bays. Coolant circulated by one or more pumps and cooled in a heat exchanger or another heat receiver flows over the cooling plate. Since electronic components are provided redundantly, redundant cooling is also required in order to safely continue flight if one cooling unit fails. Accordingly, individual cooling devices are associated with each of the redundant electronic devices. If the cooling device fails, for example due to a leak, the electronics cooled by the cooling dev...
Claims
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IPC IPC(8): B64D13/06F25D17/02F25B25/00
CPCF25B25/005B64D2013/0674F25B2500/06B64D13/00B64D2013/0614Y02T50/56B64D13/06Y02T50/50
Inventor 威尔逊·维·卡萨斯诺列加沃尔夫冈古斯·埃比希特安德里亚·弗赖
Owner AIRBUS OPERATIONS GMBH