Emergency supply system for an aircraft control system

• US 4,754,940 A
• Filed: 08/20/1986
• Issued: 07/05/1988
• Est. Priority Date: 09/21/1985
• Status: Expired due to Fees

• Current Assignee: Messerschmitt-Bolkow-Blohm GmbH
• Original Assignee: Messerschmitt-Bolkow-Blohm GmbH
• Inventors: Deter, Burkhard
• Primary Examiner(s): Peters, Jr., Joseph F.
• Assistant Examiner(s): Corl, Rodney
• Application Number:
  US06/898,257
• Time in Patent Office: 685 Days
• Field of Search: 244/226, 244/227, 244/228, 244/75 R, 244/78, 244/76 R, 91/509, 91/510, 60/403, 60/404, 60/911
• US Class Current: 244/75.1
• CPC Class Codes: B64C 13/42 having duplication or stand-by provisions
• CPC Class Codes: B64C 13/50 using electrical energy
• CPC Class Codes: Y10S 60/911 Fluid motor system incorporating electrical system

Abstract

An emergency supply system for maintaining the emergency flight control of a high-performance aircraft of aerodynamically unstable design having three energy systems, namely, two identical hydraulic systems, connected in parallel for redundancy, for actuation of the control surfaces of the aircraft required for its ability to fly, and an electric on-board system having at least one generator, a rechargeable battery and a non-rechargeable emergency battery, the three energy systems being interconnectible in terms of energy by a power transmission unit, and wherein the two hydraulic systems are divided into subsystems associated with single or several rudder functions which, if necessary, can be disconnected singly.

Claims

1. An emergency supply system for maintaining the emergency flight control of a high-performance aircraft of aerodynamically unstable design comprising two substantially identical parallel-connected hydraulic systems for actuating the control surfaces of the aircraft required for flight, the hydraulic systems under normal operating conditions being supplied with energy by two independent hydraulic pumps operatively connected to the propulsion system of the aircraft, each hydraulic system including at least two subsystems operatively connected to at least one rudder of the aircraft and being interconnectable in terms of energy by a power transmission unit, the supply system further comprising an electric on-board energy system, three different electric energy sources being provided in the electric on-board energy system comprising at least one propulsion system driven generator, at least one rechargeable battery, and at least one non-rechargeable emergency battery, the power transmission unit operatively connected to each of the three electric energy sources such that power therefrom may be supplied to the two hydraulic systems, and further allowing power from each of the two hydraulic systems to be transmitted to the electric on-board system for recharging the rechargeable battery and providing power to other electric power using devices, said subsystems including means enabling them selectively connected and disconnected by said power transmission unit.

2. The emergency supply system recited in claim 1, wherein the power transmission unit comprises a hydraulic pump for each hydraulic system, said hydraulic pump being selectively operated as a hydraulic motor, further comprising a d-c motor/generator for the electric on-board system, said hydraulic pumps operable in pump and motor operation and said motor/generator operable in motor and generator operation, each with the same direction of rotation and being connected by a common input/output shaft, the d-c motor/generator being arranged between the hydraulic pumps.

3. The emergency supply system recited in claim 2, wherein the hydraulic pumps comprise axial piston pumps having control by swash plates which can be pivoted continuously from a zero delivery position perpendicular to the input/output shaft about an axis intersecting the input/output shaft at right angles to both sides, for flow control and selection of the mode of operation.

4. The emergency supply system recited in claim 2, further comprising a 2/2 distributing valve assigned to each of the hydraulic pumps.

5. The emergency supply system recited in claim 2 wherein the d-c motor/generator comprises an adjustable shunt motor/generator with collector.