Aircraft battery lockout device

An aircraft battery lockout device is used to isolate the connector assembly for the aircraft's wiring harness from the battery power receptacle. In one embodiment the device comprises a cover, lock, and insulative material. The cover is locked onto the battery power receptacle. The insulative material provides electrical isolation between the locking device and the battery power receptacle. In a second embodiment the device is locked onto the connector assembly.

BACKGROUND OF THE INVENTION

1. Field of the Invention

This invention relates in general to aircraft security, in particular to a device for securing the electrical system of an aircraft when not in use.

2. Description of the Prior Art

The National Transportation Safety Board is evaluating various security measures to prevent aircraft on the ground from being seized. In some areas of the country it is required that there be two methods of locking the aircraft. Typically, one acceptable method is locking the cabin. Another is to disconnect the battery from the aircraft electrical system and lock the compartment where the battery is housed.

The latter solution is lacking in that the compartment can be broken into and the aircraft's electrical system quickly connected to the battery power source for the aircraft.

SUMMARY OF THE INVENTION

A primary object of this invention is providing security for the electrical system of an aircraft when the aircraft is not in use.

Another object is the provision of security for an aircraft without the need for any modification to the aircraft or to the electrical system of the aircraft.

These and other objects are accomplished in accordance with the teachings of the present invention. An aircraft battery lockout device is used to isolate the connector assembly for the aircraft's wiring harness from the battery power receptacle. In one embodiment the device comprises a cover, lock, and insulative material. The cover is locked onto the battery power receptacle. The insulative material provides electrical isolation between the locking device and the battery power receptacle. In a second embodiment the device is locked onto the connector assembly.

DETAILED DESCRIPTION

In most aircraft today, at the point where the aircraft's electrical system is connected to the battery, a quick connect-disconnect system is utilized. So much of one such system is illustrated in the accompanying drawing figures as is necessary for an understanding of the present invention, and involves the mating of a connector assembly to a battery power receptacle. An example of same may be found in U.S. Pat. No. 5,427,541.

Referring toFIG. 1Aof the drawing, a battery power receptacle is generally designated by the numeral11and is designed for mounting, usually at the top center on the sidewall of a battery B, by means of screws12passed through mounting holes and includes conductor pins which are connected to a respective one of the terminals of the battery B.

The battery power receptacle, with which the present invention is utilized conforms with Mil. Spec. MS 3509.

As shown inFIGS. 1B and 3C, a connector assembly designated generally by reference numeral21is constructed for mating with the receptacle11.

The connector assembly21includes a two piece insulative housing22. The housing22has a mating projection (not shown) adapted for insertion into a complementary recess (not shown) of the receptacle11. Conductive socket members (not shown) are mounted within the housing22for mating with the conductive pins. The conductive socket members are mounted to respective base members (not shown), each having a terminal assembly that is fed from the aircraft's wiring harness25,26.

A shaft27of the connector assembly21is adapted for insertion into a cavity14in the receptacle11. The shaft27is formed with diametrically opposed helical grooves28with terminating detents28A, which grooves mate with diametrically opposed plug retaining pins15in the receptacle cavity14. The connector assembly with which the present invention is utilized conforms with either Mil. Spec. MS 25182 or MS 3349.

When the connector assembly shaft27is inserted into the receptacle cavity14and turned in a first direction by a knob29affixed to the shaft on the opposite side of the housing22, the projection is drawn into the recess. When the shaft is turned in the opposite direction, the projection is withdrawn from the recess. This arrangement of shaft27, cavity14, socket members and conductive pins provides a quick connect-disconnect feature at the point where the battery receptacle11is electrically connected to the connector assembly21.

When an aircraft is in use, the battery receptacle11and connector assembly21are, of course, coupled together in electrical continuity. But shortly after the aircraft is parked and no longer in use, the connector assembly21is disconnected from the battery receptacle11so that the aircraft electrical system does not drain the battery and the crew does not come back to a dead battery.

With the connector assembly21merely disconnected from the battery receptacle11, there is no deterrent to reconnecting the connector assembly21to the battery receptacle11, allowing for unauthorized use of the aircraft.

In accordance with the teachings of the present invention, a locking device that includes an electrically isolating member is locked onto either the battery receptacle or the connector assembly, thereby preventing reconnection of the connector assembly21and battery receptacle11by an unauthorized person and preventing unauthorized use and theft of the aircraft.

In accordance with a first embodiment of the invention and as shown inFIGS. 2A–2C, a locking device31comprises a rectangular, somewhat pyramid-shaped cover32, a rotational key lock33mounted within the cover32, a shaft34with rotary cam35extending from the rotating element of the lock33and an insulating member36.

The shape of cover32diminishes the ability to tamper with device31. The cover32is lipped at32A for keying to the outside periphery of the receptacle11, although the cover could also be keyed to an inner part of the receptacle11. The device cover32is constructed of material more robust than the battery receptacle itself, for example hard anodized aluminum, so that someone trying to remove forcibly the device would destroy the battery receptacle and not be able to establish connection between the battery and the aircraft electrical system and thus not be able to operate the aircraft. The cover is of one-piece construction and forms the outer shell for the lock33.

The insulating member36, as of rubber, covers the bottom surface of the cover32for isolation and electrical insulation purposes. The member36stretches around the rounded off sidewalls and a portion of the upper surface of the cover32.

With the connector assembly21disconnected from the battery receptacle1, the device31is placed over the battery receptacle11. The key shaft34extends into the receptacle cavity14. A key37is turned and the receptacle cavity pins15mate with the key shaft cam35, so that as the key37is turned, the device31is locked in place over the battery receptacle11. The key37is removed and retained by the captain or some other authorized person for safekeeping until the next time the aircraft is to be used. With the device31locked in place to the battery receptacle11, the battery B is no longer available to the aircraft electrical system.

The device31will work on any known aircraft, from a single engine prop plane to a jumbo jet. No modifications are required to the battery or aircraft, thus obviating the need for certification and compliance with Federal Aviation Requirements.

When in place, the device31is a viable aircraft theft deterrent. Besides preventing unauthorized use of an aircraft, it could be used to prevent inadvertent use of an unairworthy aircraft and inadvertent use of an unserviceable battery.

A non-conductive lanyard38may be used to tie a flag39to the device31. The flag, typically, will contain the admonishment “Remove Before Flight”.

When the device31is removed, it restores the aircraft to its original airworthy configuration.

In accordance with a second embodiment of the invention and as shown inFIGS. 3A,3B and4, the locking device41comprises a housing42of two pieces42A (shown also inFIGS. 8A–8C) and42B (shown also inFIGS. 7A–7C), a lock43and cup-shaped rotary cam44.

Upper housing piece42A is provided with a bore45which forms the outer shell for the lock43and has a shoulder at46on which the lock43seats.

Lock43includes lock plug47with threaded stud48, key cam49(See alsoFIGS. 6A–6C) and securing nut50. The cam49is able to rotate, when in position, until hitting stops51,52, which stops together form or define ninety degrees of rotation for the lock43. Cup-shaped rotary cam44has an opening53of square cross section and includes ball bearings54,55trapped in place but projecting partially out from its interior wall. In a first position, shown atFIGS. 5A and 5B, the ball bearings are free to move out. But upon ninety degrees rotation, and as shown inFIGS. 5C and 5D, the ball bearings54,55are forced inwardly.

Upper housing piece42A is further provided with an electrically isolating rubber boot42C. The boot42C will provide electrical isolation for the connector assembly21and its locking device41from the battery power receptacle11, as the device41and the receptacle11will be in fairly close proximity to each other, even in the disconnected mode.

As shown, the pieces42A and42B are screwed together to form the housing42. Locking device41is used in the following manner. First the connector assembly21is disengaged from the battery power receptacle11. Then the shaft27of the connector assembly21is inserted into the socket56and turned. The pins57engage the grooves28until stopped at the detents28A. When at this position, the key of the lock43is now turned ninety degrees. The ball bearings54,55move from the free, unlocked position (FIGS. 5A and 5B) and are forced inwardly into the ball bearing nests58(FIGS. 5C and 5D). Projecting outwardly thereform, the ball bearings54,55fall into the connector assembly grooves28and are aligned with the pins57in the detents28A. The pins57and ball bearings54,55are a fixed distance apart and the device41is now locked onto the connector assembly21. If one attempts any turning, pins57are trying to move laterally, while ball bearings54,55are trying to move diagonally. The conflicting action prevents turning. The key is removed until the next time when access to the connector assembly21is needed for operation of the aircraft.

It should be obvious that changes, additions and omissions may be made in the details and arrangement of parts without departing from the spirit and scope of the invention as hereinafter claimed.