Check device for a redundant flight control apparatus

• US 4,601,169 A
• Filed: 09/04/1984
• Issued: 07/22/1986
• Est. Priority Date: 09/07/1983
• Status: Expired due to Fees

• Current Assignee: Feinmechanische Werke Mainz GmbH
• Original Assignee: Feinmechanische Werke Mainz GmbH
• Inventors: Diessel, Guenter, Hesse, Konrad
• Primary Examiner(s): CHAMBERS, A MICHAEL
• Application Number:
  US06/646,951
• Time in Patent Office: 686 Days
• Field of Search: 91/437, 91/438, 91/439, 91/509, 60/406, 60/425
• US Class Current: 60/406
• CPC Class Codes: B64C 13/42 having duplication or stand-by provisions
• CPC Class Codes: F15B 19/005 Fault detection or monitoring
• CPC Class Codes: F15B 19/007 Simulation or modelling

Abstract

Check device for a redundant flight control apparatus comprising at least two servo drive devices. Failure in supplying fluid and wedging of a control valve (20) can be simulated. Failure of the bypass valve (35) can be checked by reading and comparing the volume flows of the respective pumps as well as by evaluating the travelling rate of the servo drives (1, 2) by the pilot.

Claims

1. In a redundant flight control apparatus comprising a plurality of variable displacement pumps each having a zero delivering position, a full stroke position and intermediate positions,

at least a group of servo drive devices, and

at least a manually operable control means for controlling said group of servo drive devices,

each said pump having supply and return line means connected to at least one of said servo drive devices, each said servo drive device including

a control valve for directional control of said supply and return line means,

a bypass valve for putting the servo drive device out of operation, and

an actuator having a double-acting piston,

said control valve including a control spool for directionally controlling said supply and return line means and a push-over spool mounted for relative movement to said control spool for controlling pressure in a control line to said bypass valve,

said control line being normally on high pressure, and, when said push-over spool is moved relative to said control spool, on low pressure,

said bypass valve having a connecting through position for said supply and return line means when said control pressure is high, and a bypass position for shutting off said supply and return line means from said actuator and short circuiting said actuator, when said control pressure is low,

said manually operable control means being linked to said push-over spools of said group of servo drive devices and to said pistons of said actuators,

an improved check device for testing and detecting proper operation of said flight control apparatus comprising:

a group of flow-indicating instruments, each for detecting fluid flow in a particular one of said supply and return line means,

a group of test valves, each included in one of said supply and return line means upstream of said control valve and adapted to normally connect through and, when actuated, to shut off said supply line so as to influence a corresponding said pump,

which is connected to said particular supply and return line means, to take its zero delivering position, even if said manually operable control means is operated for a servo movement, and

locking means for independently locking each said control spool of said control valve of said group, said check device functioning in that situations can be brought about in an arbitrary manner, wherein said bypass valve should go into its bypass position, and wherein achieving of said bypass position can be detected by observing said corresponding flow indicating instrument.

2. The improvement set forth in claim 1, wherein said variable displacement pump is an axial piston pump having a swash plate and said flow indicating instrument is a device for indicating the angle of said swash plate of said axial piston pump.

3. The improvement set forth in claim 1, wherein said test valve includes a restrictor, which will become effective in said return line, when said test valve is in its operated position.

4. The improvement set forth in claim 1, further comprising a group of latching devices, each being arranged adjacent to one of said bypass valves and including a catching means and a releasing means, said catching means being adapted to catch said spool of said bypass valve in said bypass position, said releasing means being connected to said supply and return line means downstream from said control valve and being adapted to release said catching means, when there are pressure changes in said supply and return line means downstream of said control valve.

5. The improvement set forth in claim 4, wherein said releasing means comprises a cylinder unit connected to said supply and return line means downstream of said control valve, said cylinder unit including a piston, a piston rod and a cam mounted on the piston rod, said piston and piston rod having a retracted and an extended position, said cam, in said extended position of said piston and piston rod, making said catching means inoperative.