Patent US3263236A successfully refreshed from Google Patents.
Patent EP0307974A2 successfully refreshed from Google Patents.
EP0307974A2
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Hydraulic power supplies
Assignee: Boeing Co
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Filing: 1988-04-21
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Granted: —
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Expires: 2008-04-21
Abstract
Abstract Hydraulic power supplies for aircraft which have such hydraulically operated systems as flaps, ailerons, spoilers, rudders, elevators, brakes, and retractable and steerable landing gear. Typically, the aircraft will be of the multiengine type; and there will also be a multiplicity of hydraulic power supplies and engines. This scheme can be utilized to provide operating redundancy for the hydraulically operated devices of the aircraft. Each hydraulic power supply has a solid state controller which has a number of inputs as well as control and information providing functions. Control over the functioning of each hydraulic power supply can also be exercised by flight deck crew-operated switches which are connected to inputs of the solid state controllers.
Inventors
- 👤 Ralph Archung
Bibliographic Details
Application Number
—
Jurisdiction
EP
Data Source
google_patents
Last Synchronized
2026-11-01 16:56
CPC Classifications
B; B64; B64D; B64D41/00; Y; Y02; Y02T; Y02T50/00; Y02T50/40
Claims Analysis
Total Claims: 26
Claim 1
Independent Claim
62 words
A hydraulic power supply for making pressurized hydraulic fluid available to one or more hydraulically operated devices, said power supply comprising: a pump means which provides pressurized hydraulic fluid for the operation of said device(s) and a centralized solid state controller which: controls the operation of said pump means and makes available information relating to the operational status of the power supply.
Claim 2
Dependent Claim
62 words
A hydraulic power supply for making pressurized hydraulic fluid available to one or more hydraulically operated devices, said power supply comprising: a pump means which provides pressurized hydraulic fluid for the operation of said device(s) and a centralized solid state controller which: controls the operation of said pump means and makes available information relating to the operational status of the power supply.
Claim 3
Dependent Claim
21 words
A hydraulic power supply as defined in claim 1 which comprises manually operable means for enabling and disenabling said pump means.
Claim 4
Dependent Claim
54 words
A hydraulic power supply as defined in claim 1 in which said pump means comprises a first, engine driven pump and a second, demand pump which can be activated at the option of an operator and/or activated automatically upon a predicted increase in demand to prevent precipitous drops in the hydraulic fluid delivery pressure.
Claim 5
Dependent Claim
36 words
A hydraulic power supply as defined in claim 3 wherein the solid state controller has means which is effective to shut down said demand pump after that pump has run for a period of selected duration.
Claim 6
Dependent Claim
79 words
An aircraft which has a hydraulic power supply as defined in claim 3 and means activated from a solid state controller output for warning the flight deck crew that: (a) the pressure on the hydraulic fluid made available by the engine driven pump has fallen below a specified minimum, (b) the pressure on the hydraulic fluid made available by the demand pump has fallen below a specified minimum, and/or (c) there is a fault in the hydraulic power supply.
Claim 7
Dependent Claim
37 words
An aircraft which has a hydraulic power supply as defined in claim 1 and means activated by a solid state controller output for displaying in real time information relating to operating parameters of said hydraulic power supply.
Claim 8
Dependent Claim
41 words
An aircraft which has a hydraulic power supply as defined in claim 1 and means for processing information made available from said solid state controller and relating to problems in the hydraulic power supply that require the attention of maintenance personnel.
Claim 9
Dependent Claim
39 words
A hydraulic power supply as defined in claim 3 which includes switch means which can be thrown at the option of an operator to cause said demand pump to operate continuously and irrespective of the demand for hydraulic power.
Claim 10
Dependent Claim
22 words
A hydraulic power supply as defined in claim 3 which comprises operator exercisable means for enabling and disenabling said engine driven pump.
Claim 11
Dependent Claim
62 words
An aircraft which includes a hydraulic power supply as defined in claim 3 and wherein the solid state controller of said power supply includes means for effecting operation of said demand pump: (a) while the aircraft is airborne and the flaps of the aircraft are down, and/or (b) upon the receipt of a signal indicative of the imminent movement of said flaps.
Claim 12
Dependent Claim
51 words
An aircraft which has a hydraulic power supply as defined in claim 3 and wherein the solid state controller of said power supply has means which is effective to cause said demand pump to shut down following the touchdown of the aircraft and the subsequent lapse of a specified time period.
Claim 13
Dependent Claim
34 words
A hydraulic power supply as defined in claim 3 wherein said solid state controller includes means for automatically shutting off said demand pump after that pump has run for a period of preselected duration.
Claim 14
Dependent Claim
64 words
A hydraulic power supply as defined in claim 3 in which the solid state controller includes means for delaying the start-up of said demand pump for a predetermined period after the receipt of an input indicative of an increased demand on the hydraulic power supply, thereby preventing transient anomalies in the pressure on the hydraulic fluid from effecting a start-up of said demand pump.
Claim 15
Dependent Claim
55 words
An aircraft which includes a hydraulic power supply as defined in claim 3 and wherein the solid state controller of said power supply comprises means for automatically effecting start-up of said demand pump in the event of an occurrence which results in the shutdown of the first, engine driven pump while the aircraft is operating.
Claim 16
Dependent Claim
81 words
An aircraft which includes a hydraulic power supply as defined in claim 3, an engine for driving the first pump of said power supply, and a fuel cut-off actuator for terminating the supply of fuel to said engine, the solid state controller of said power supply comprising means for effecting the start-up of said demand pump upon receipt of an input indicating that said fuel cut-off has been so actuated as to cut off the supply of fuel to said engine.
Claim 17
Dependent Claim
60 words
An aircraft which has a hydraulic power supply as defined in claim 1; wherein the pump means of said power supply comprises a first, aircraft engine driven pump and a second, auxiliary pump which is operable independently of the aircraft engine; and wherein said solid state controller includes means for disenabling said auxiliary pump when said aircraft engine is running.
Claim 18
Dependent Claim
36 words
An aircraft as defined in claim 16 wherein the solid state controller has means for effecting the start-up of said pump means only if an external power supply for said second pump is operatively connected thereto.
Claim 19
Dependent Claim
43 words
A hydraulic power supply as defined in claim 1 wherein said solid state controller comprises means for making available information relating to: the quantity of the hydraulic fluid in the system, the temperature of the hydraulic fluid, and the pressure on said fluid.
Claim 20
Dependent Claim
49 words
An aircraft which includes a hydraulic power supply as defined in claim 1 and a pilot-operated switch for disenabling said pump means if a fire breaks out in said aircraft in a location such that the fire could be fueled by hydraulic fluid escaping from the hydraulic power supply.
Claim 21
Dependent Claim
38 words
An aircraft which has a plurality of hydraulic power supplies as defined in claim 1 and at least one hydraulic device which can be operated by fluid supplied by either one of two of said hydraulic power supplies.
Claim 22
Dependent Claim
72 words
An aircraft as defined in claim 20 wherein there is a solid state controller as aforesaid for each of said hydraulic power supplies; wherein all of said solid state controllers have the same logic; and wherein said controllers have selectively available inputs and outputs which can be employed to make each of said solid state controllers capable of performing a selected part, or all, of the functions of which it is capable.
Claim 23
Dependent Claim
20 words
An aircraft as defined in claim 21 wherein each of said solid state controllers is contained on a single card.
Claim 24
Dependent Claim
37 words
An aircraft which has at least one hydraulic power supply as defined in claim 1 and means for making available information relating to failures in the solid state controller and other components of said hydraulic power system.
Claim 25
Dependent Claim
98 words
An aircraft which has at least two hydraulic power supplies as defined in claim 1; wherein the pump means of each of said hydraulic power supplies includes a first, aircraft engine driven pump and a second electrically driven pump which can be operated independently of the first, engine driven pump; and wherein the solid state controllers of each power supplies include means for preventing the electrically driven pumps of the two hydraulic power supplies from being started up simultaneously, thereby keeping the electrical system of the aircraft from being overloaded by the start-up of the electrically driven pumps.
Claim 26
Dependent Claim
59 words
An aircraft which has a hydraulic power supply as defined in claim 1 and wherein the solid state controller of the power supply includes means for activating a signal in the cockpit or on the flight deck of the aircraft if the hydraulic pressure in all braking systems with which the aircraft is equipped falls below a specified level.
References Cited (Backward Citations)
No citation records indexed.
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