US20110148192A1 - Aircraft security system - Google Patents
Aircraft security system Download PDFInfo
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- US20110148192A1 US20110148192A1 US13/036,630 US201113036630A US2011148192A1 US 20110148192 A1 US20110148192 A1 US 20110148192A1 US 201113036630 A US201113036630 A US 201113036630A US 2011148192 A1 US2011148192 A1 US 2011148192A1
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- Prior art keywords
- switch
- security
- starter
- aircraft
- relay
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60R—VEHICLES, VEHICLE FITTINGS, OR VEHICLE PARTS, NOT OTHERWISE PROVIDED FOR
- B60R25/00—Fittings or systems for preventing or indicating unauthorised use or theft of vehicles
- B60R25/01—Fittings or systems for preventing or indicating unauthorised use or theft of vehicles operating on vehicle systems or fittings, e.g. on doors, seats or windscreens
- B60R25/04—Fittings or systems for preventing or indicating unauthorised use or theft of vehicles operating on vehicle systems or fittings, e.g. on doors, seats or windscreens operating on the propulsion system, e.g. engine or drive motor
- B60R25/045—Fittings or systems for preventing or indicating unauthorised use or theft of vehicles operating on vehicle systems or fittings, e.g. on doors, seats or windscreens operating on the propulsion system, e.g. engine or drive motor by limiting or cutting the electrical supply to the propulsion unit
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60R—VEHICLES, VEHICLE FITTINGS, OR VEHICLE PARTS, NOT OTHERWISE PROVIDED FOR
- B60R25/00—Fittings or systems for preventing or indicating unauthorised use or theft of vehicles
- B60R25/10—Fittings or systems for preventing or indicating unauthorised use or theft of vehicles actuating a signalling device
- B60R25/102—Fittings or systems for preventing or indicating unauthorised use or theft of vehicles actuating a signalling device a signal being sent to a remote location, e.g. a radio signal being transmitted to a police station, a security company or the owner
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60R—VEHICLES, VEHICLE FITTINGS, OR VEHICLE PARTS, NOT OTHERWISE PROVIDED FOR
- B60R25/00—Fittings or systems for preventing or indicating unauthorised use or theft of vehicles
- B60R25/10—Fittings or systems for preventing or indicating unauthorised use or theft of vehicles actuating a signalling device
- B60R25/104—Fittings or systems for preventing or indicating unauthorised use or theft of vehicles actuating a signalling device characterised by the type of theft warning signal, e.g. visual or audible signals with special characteristics
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60R—VEHICLES, VEHICLE FITTINGS, OR VEHICLE PARTS, NOT OTHERWISE PROVIDED FOR
- B60R2325/00—Indexing scheme relating to vehicle anti-theft devices
- B60R2325/30—Vehicles applying the vehicle anti-theft devices
- B60R2325/302—Airplanes
Definitions
- This application relates generally to methods and apparatus for an aircraft security and alarm system.
- an aircraft security system that is simple, light-weight, easy to install in new and existing aircraft, and is difficult to detect by an unauthorized person—yet prevents operation of the aircraft when armed.
- a security system that does not draw power from the aircraft when armed, and is functional only when the aircraft is on the ground and parked.
- FIG. 1A illustrates a block diagram of one embodiment of the present Aircraft Security System configured for both single and multi engine aircraft.
- FIG. 1B illustrates a block diagram of one embodiment of the present Aircraft Security System configured for both single and multi engine aircraft.
- FIG. 2 illustrates a schematic view of one embodiment of the present Aircraft Security System configured for single engine aircraft.
- FIG. 3 illustrates a schematic view of one embodiment of the present Aircraft Security System configured for multi engine aircraft.
- FIG. 4 illustrates a schematic view of one embodiment of the present Aircraft Security System configured for single engine aircraft.
- FIG. 5 illustrates a schematic view of one embodiment of the present Aircraft Security System configured for multi engine aircraft.
- references made to actuation of a switch may include opening or closing of a switch. It is understood that embodiments demonstrating a circuit having a switch in a first state may also be reconfigured to a circuit having a switch in a second state without departing from the scope of the present subject matter. Thus, an embodiment having a normally closed switch may be realized in an embodiment having a normally open switch without departing from the present subject matter.
- FIG. 1A illustrates a block diagram of one embodiment of an aircraft security system 100 , including block 71 including an aircraft battery, block 72 including an aircraft master switch and an electrical buss, block 73 including an anti-theft system, block 74 including one or more aircraft starter switches for single and multiple engines, and block 75 including one or more aircraft starter relays and starter motors for single and multiple engines.
- FIG. 1A illustrates blocks 71 , 72 , 73 , 74 , and 75 as being coupled by connections 80 , 81 , 82 , and 83 all being shown as a single line.
- connections 80 , 81 , 82 , and 83 may include one or more conductors and one or more other forms of electrical or mechanical couplings between blocks 71 , 72 , 73 , 74 , and 75 without departing from the scope of the present subject matter.
- the aircraft battery of block 71 couples through connection 80 to the aircraft master switch and electrical buss of block 72 .
- the aircraft master switch of block 72 when closed, allows power from the aircraft battery to reach the electrical buss of block 72 , and when the aircraft master switch is open, power from the aircraft battery is disconnected from the electrical buss.
- the master switch is closed, power from the electrical buss of block 72 is coupled through connection 81 to the anti-theft system of block 73 .
- the anti-theft system operates in both an activated or armed mode, and a deactivated or unarmed mode. The apparatus and methods for determining the modes and operations of the anti-theft system are described in further detail below.
- the anti-theft system will disconnect the power supplied from block 72 , and thus not allow power for the aircraft battery to power block 74 or block 75 .
- the anti-theft system of block 73 prevents the starting of the engine or engines present on the aircraft, even if the aircraft starter switch or switches of block 74 , as described below, are actuated (closed).
- block 74 includes one aircraft starter switch, associated with the singe engine of a single engine aircraft. If power is supplied to block 74 and the aircraft starter switch is actuated (closed), power will be coupled through connection 83 to block 75 .
- block 75 includes an aircraft starter relay that will be energized by the power supplied through connection 83 . When energized, the aircraft starter relay will allow power to reach the starter motor associated with the aircraft engine, and thus allow starting of the aircraft's engine.
- block 74 includes multiple aircraft starter switches, wherein each of the switches is associated with one of the engines of a multiple engine aircraft. If power is supplied to block 74 and one of the aircraft starter switches of block 74 is actuated (closed), power will be coupled through connection 83 to block 75 . It will be realized by those of ordinary skill in the art that for multiple engine applications, connection 83 may include separate connections associated with each of the engines of the multiple engine aircraft.
- block 75 includes multiple aircraft starter relays, each one being associated with a starter motor. When power is supplied to block 75 through connection 83 , the particular starter relay associated with the starter switch being actuated will be energized. When energized, the particular starter relay energized will allow power to reach the aircraft starter motor associated with that starter relay, allowing the aircraft engine associated with that starter motor to be started.
- the anti-theft system will disconnect the power supplied from block 72 , and thus not allow power from the aircraft battery of block 71 to power block 74 or block 75 .
- the anti-theft system prevents starting of the engines present on the aircraft, even if the aircraft starter switch of the one or more starter switches of block 74 are actuated (closed).
- the anti-theft system prevents starting for any of the engines on the multiple engine aircraft.
- FIG. 1B illustrates a block diagram of one embodiment of an aircraft security system 110 .
- the embodiment of aircraft security system 110 is similar to the embodiment of system 100 , except that block 74 (aircraft starter switch -single and multiple engine) is coupled to block 72 through connection 81 , and block 74 is further coupled to the anti-theft system of block 73 through connection 82 .
- the anti-theft system of block 73 is coupled to block 75 through connection 83 .
- System 110 functions in a similar manner to system 100 . However, one embodiment may be preferred over the other with regards to installment of the system on an aircraft due to, among other factors, physical access to the various portions of the circuits in the aircraft.
- FIG. 2 illustrates one embodiment of an aircraft security system 200 including a starter breaker 4 electrically connected to main power bus 3 and a starter switch 5 , where the main power bus 3 is powered by a master switch 2 from a main battery 1 .
- main power bus 3 may be an instrument bus.
- System 200 further includes a security relay 11 having activation means for a first set of contacts 20 and a second set of contacts 21 , where the first set of contacts 20 are normally closed, and are electrically connected to a starter switch 5 , a starter relay 6 , and where the second set of contacts 21 are normally open and are electrically connected to a remote battery 14 , a remote switch 12 , an alarm 13 , and a diode 10 A.
- a security switch 9 is electrically connected to the security relay 11 .
- security switch 9 is a key lock switch. Other embodiments having different types of switches are possible without departing from the scope of the present subject matter.
- System 200 includes one or more modes of operation.
- security switch 9 In normal, unarmed operation, security switch 9 is open, and the control coil of security relay 11 is de-energized. In this mode, normally closed contacts 20 of security relay 11 will be in a closed state.
- Activation of the master switch 2 and the starter switch 5 in this mode causes current to flow through the normally closed contacts 20 of the security relay 11 , allowing current flow from main power bus 3 and starter breaker 4 , to the starter relay 6 , which, when energized, closes contacts 22 of starter relay 6 .
- With contacts 22 closed power is delivered to starter motor 7 from starter bus 23 through electrical connection 55 , contacts 22 , and electrical connection 56 .
- security switch 9 is closed.
- the control coil of security relay 11 is electrically coupled to main power bus 3 through electrical connection 60 , security switch 9 , electrical connection 57 .
- diode 10 B couples electrical connection 60 with electrical connection 59 , electrical connection 59 being coupled to security switch 9 .
- Activation of master switch 2 with a closed (armed) security switch 9 allows current from main battery 1 to flow through master switch 2 to the main power bus 3 , and thus energizes the control coil of security relay 11 , causing normally closed contacts 20 to open.
- normally closed contacts 20 open the current flow from the main power bus 3 to starter relay 6 is disconnected.
- Starter relay 6 remains de-energized, and contacts 22 remain open. With contacts 22 open, no power is delivered to starter motor 7 from the starter bus 23 .
- With normally closed contacts 20 open activation of starter switch 5 will not allow power from main battery 1 to energize starter relay 6 , and thus will prevent starting of the aircraft.
- FIG. 2 illustrates an embodiment of the security system 200 in which at least one application is configured for single engine aircraft.
- the master switch 2 is closed, allowing battery power from the main battery 1 to flow to the main power bus 3 through electrical connections 50 and 51 .
- current flows from the main power bus 3 through electrical connection 67 to starter breaker 4 , then through electrical connection 52 to starter switch 5 .
- starter switch 5 is actuated (closed)
- current flows through starter switch 5 , and through electrical connection 58 to the normally closed contacts 20 of the security relay 11 .
- electrical connection 54 energizing the control coil of starter relay 6 , and closing contacts 22 , providing power to the engine starter motor 7 from starter bus 23 through electrical connection 55 , contacts 22 , and electrical connection 56 .
- the security switch 9 includes, but is not limited to, a toggle switch, a key pad, or a biometric security device which is activated for proper operation of the aircraft. In various embodiments, activation may include entering a Personal Identification Number (PIN) on a key pad before proper operation of the aircraft will be enabled. In various embodiments, the function and location of the security switch 9 is known only to authorized operators of the aircraft. In one or more embodiments, when the owner/operator desires security, the normally open security switch 9 is closed. Once security switch 9 is closed, activating the master switch 2 causes current to flow from the main power bus 3 along electrical connection 57 to the now closed (armed) contacts of the security switch 9 . Power is now available, through electrical connection 60 , to the control coil of security relay 11 , activating security relay 11 . In various embodiments, the path of current flow includes electrical connection 59 and diode 10 B.
- Activation of security relay 11 causes various events to occur.
- the energized security relay 11 opens the normally closed contacts 20 , thus opening the start circuit and preventing starter motor 7 from energizing, even when starter switch 5 is actuated, or if starter switch 5 is tampered with.
- the normally open contacts 20 will prevent power from being delivered to starter relay 6 , and thus prevent starting of the aircraft's engine.
- the energization of security relay 11 will close normally open contacts 21 . With normally open contacts 21 closed, current can flow from remote battery 14 through electrical connection 61 and through remote switch 12 and through electrical connection 62 , and through the now closed normally open contacts 21 of the security relay 11 . Current then continues to flow through electrical connection 63 and diode 10 A to electrical connection 60 , providing a second source of current flow through the control coil of security relay 11 , keeping security relay 11 energized (latched). In various embodiments, the current flow to electrical connection 63 will allow alarm 13 to become activated.
- security relay 11 and alarm 13 will remain activated even if starter breaker 4 is opened or if the aircraft's primary power is removed from the main power bus 3 by opening the aircraft's master switch 2 .
- Alarm 13 is deactivated by opening the contacts of remote switch 12 .
- the function and location of the remote switch 12 is known only to the owner/operator of the aircraft or other authorized persons.
- FIG. 3 illustrates an embodiment where the security system 300 is useful in applications, including, but not limited to, use in multiple engine aircrafts. Reference numbers are repeated for elements of FIG. 3 which are the same or similar to those of FIG. 2 . Elements in FIG. 3 depicting additional iterations of the same or similar elements as depicted in FIG. 2 are shown using the same reference numbers with the addition of a letter, for example, “A” or “B.”
- master switch 2 is activated allowing battery power to flow from main battery 1 to main power bus 3 .
- current flows from main power bus 3 through electrical connection 67 and starter breaker 4 , then through electrical connection 52 to the normally closed contacts 20 of security relay 11 .
- the current continues to flow through electrical connections 53 A and 53 B to the normally open contacts of the engine starter switches 5 A and 5 B respectively.
- current also flows to additional engine starting circuits, for example, electrical connections 53 C and 53 D to the normally open contacts of starter switches 5 C and 5 D respectively.
- electrical connections 53 C and 53 D to the normally open contacts of starter switches 5 C and 5 D respectively.
- starter switches 5 A and 5 B are operated by separate means. In one embodiment, starter switches 5 A and 5 B may be operated at separate times.
- starter switch 5 A When starter switch 5 A is activated, current flows through its closed contacts and electrical connection 54 A to the associated starter relay 6 A, energizing the control coil of starter relay 6 A, and closing contacts 22 A. With contacts 22 A closed, current from starter bus 23 A flows through electrical connection 55 A, contacts 22 A, and electrical connection 56 A to power starter motor 7 A. Thus, the starting of the aircraft's engine associated with starter motor 7 A is enabled.
- starter switch 5 B When the starter switch 5 B is activated, current flows through its closed contacts and electrical connection 54 B to the associated engine starter relay 6 B, energizing the control coil of starter relay 6 B, and closing contacts 22 B. With contacts 22 B closed, current from starter bus 23 B flows through electrical connection 55 B, contacts 22 B, and electrical connection 56 B to power starter motor 7 B. Thus, the starting of the aircraft's engine associated with starter motor 7 B is enabled.
- security system 300 includes additional electrical connections 53 C and 53 D that are coupled to starter switches 5 C and 5 D respectively. These additional circuits and starter switches are coupled to additional starter relays (not shown) and starter motors (not shown). It will be realized by those of skill in the art that additional circuits and various combinations of starter switches are possible without departing from the scope of the present subject matter.
- the function and location of the security switch 9 is known only to authorized operators of the aircraft.
- security switch 9 When the owner/operator desires security, security switch 9 is activated (closed).
- security switch 9 when security switch 9 is activated and an unauthorized start is attempted, current flows from main power bus 3 , through electrical connection 57 and the now closed security switch 9 , through electrical connection 60 , and to the control coil of security relay 11 , thus activating security relay 11 .
- electrical connection 60 is coupled to security switch 9 through electrical connection 59 and diode 10 B.
- security relay 11 When security relay 11 is activated, various events occur. In an embodiment, the normally closed contacts 20 of the security relay 11 open, removing power from the starter switches 5 A and 5 B, and preventing either of the engines from being started, even if starter switches 5 A or 5 B are actuated. In an embodiment, when security relay 11 is activated, the normally open contacts 21 of security relay 11 close, allowing power to flow from the remote battery 14 through the remote switch 12 and electrical connections 61 , and 62 , through the now closed contacts of normally open contacts 21 , and through electrical connection 63 to the audio alarm 13 .
- FIG. 4 illustrates an embodiment of the security system 400 enhanced to provide security against unauthorized entry and unauthorized removal of installed devices.
- the embodiment is shown for single engine aircraft, but is equally applicable to multi-engine aircraft as shown in FIG. 5 .
- Reference numbers are repeated for elements of FIG. 4 that are the same or similar to those of FIG. 2 .
- Elements in FIG. 5 depicting additional iterations of the same or similar elements as depicted in FIG. 4 are shown using the same reference numbers with the addition of a letter, for example, “A” or “B.”
- security system 400 are enhanced to include security switch 9 coupled to main power bus 3 through electrical connection 57 and a circuit protection device, for example, an in-line fuse 26 , is included between electrical connections 57 and 58 .
- Electrical connection 58 couples circuit 24 of security switch 9 through diode 10 B to electrical connection 60 , which then is coupled to the coil (the control portion) of security relay 11 .
- security relay 11 opens normally closed contacts 20 and closes normally open contacts 21 , latching security relay 11 through remote battery 14 and remote switch 12 while preventing the powering of starter relay 6 , as described above. Further, in various embodiments, alarm 13 is activated when security relay 11 is energized.
- switches 15 and 16 are shown as magnetic switches. However, switches 15 and 16 are not limited to being magnetic switches. In one embodiment, switches 15 and 16 are motion activated. In an embodiment, switches 15 and 16 are proximity switches. In various embodiments, other type switches are possible, including, but not limited to, optical, Hall effect, pressure, or other types of switches, such as proximity or motion activated switches. In various embodiments, additional switches are included. In various embodiments, switches 15 and 16 will not be the same type of switch. It will be recognized that various type switches, and various combinations of types of switches, may be used in a variety of applications and in various combinations. In various embodiments, switches 15 and 16 are in communication with system 400 using a wireless form of coupling.
- switches 15 and 16 are arranged so that when a door or a hatch of the aircraft is opened, or in the case of installed equipment, the equipment is tampered with or removed from its housing, the associated switch 15 or 16 is actuated. This allows current to flow from remote battery 14 through electrical connection 61 and remote switch 12 , on through electrical connection 64 and the now actuated contacts of switches 15 or 16 , then on through electrical connection 65 to the circuit 25 of the security switch 9 . If the security system is set on (armed), the circuit 25 of security switch 9 will be closed, allowing current to flow through electrical connection 66 and diode 10 C to activate and latch security relay 11 , as discussed above. In various embodiments, alarm 13 is also activated when security relay 11 is activated or latched.
- alarm 13 includes an audible alarm. In various embodiments, the alarm is a silent alarm. In various embodiments, alarm 13 includes notification of the activation of the alarm to one or more various parties, including but not limited to, the aircraft owner, the aircraft operator, airport security officials, and law enforcement officials.
- activation of security relay 11 will cause normally closed contacts 20 to open, and thus prevent starting of the engine associated with starter motor 7 , even if starter switch 5 is tampered with as discussed above.
- alarm 13 is turned off by opening remote switch 12 as discussed above.
- FIG. 5 illustrates an embodiment where the security system 500 is useful in applications, including, but not limited to, use in multiple engine aircrafts. Reference numbers are repeated for elements of FIG. 5 which are the same or similar to those of FIG. 4 . Elements in FIG. 5 depicting additional iterations of the same or similar elements as depicted in FIG. 4 are shown using the same reference numbers with the addition of a letter, for example, “A” or “B.”
- switches 15 and 16 are arranged so that when the door or hatch of the aircraft is opened, or in the case of installed equipment, the equipment is tampered with or removed from its housing, the associated switch 15 or 16 is actuated.
- switches 15 and 16 are in communication with the system 500 through a wireless coupling. In various embodiments, if either of switches 15 or 16 actuate when security switch 9 is activated (armed), security relay 11 will be energized, and normally closed contacts 20 will open.
- starter switches 5 A and 5 B With normally closed contacts 20 open, power is disconnected from starter switches 5 A and 5 B, and thus activation of either of starter switches 5 A or 5 B, even if tampered with or bypassed, will not enable the starting of either of the aircraft's engines associated with starter relays 6 A and 6 B.
- additional engine starting circuits for example, circuits associated with starter switches 5 C and 5 D (associated starter relays and starter motors not shown), would also be disconnected from power, and thus would also disable the starting of the aircraft's engine associated with that circuit.
- activation of security relay 11 will latch relay 11 .
- alarm 13 is also activated when security relay 11 is activated or latched. In an embodiment, alarm 13 is turned off by opening remote switch 12 as discussed above.
Abstract
The security system provides an aircraft security system capable of protecting both single and multiple engine aircraft. Variations of the present system prevent unauthorized starting of protected aircraft and activate an alarm when engine starting it is attempted. Embodiments of the system draw no power from the aircraft when the security system is armed and in no way interferes with the normal starting or operation of the aircraft when the system is disarmed. Embodiments of the present system can activate an alarm when an aircraft's doors or panels are opened. Embodiments of the present invention can activate an alarm when installed equipment or other devices are tampered with or removed from their housings.
Description
- This application is a continuation of U.S. patent application Ser. No. 12/197,538, filed Aug. 25, 2008, which is a continuation of U.S. Pat. No. 7,423,554, Ser. No. 11/138,652, filed May 26, 2005, which application claims the benefit under 35 U.S.C. 119(e) from U.S. Provisional Application Ser. No. 60/576,262, filed Jun. 2, 2004, which are incorporated herein by reference in their entirety.
- This application relates generally to methods and apparatus for an aircraft security and alarm system.
- The physical security of aircraft is historically poor on most aircraft in operation today. Aside from the ignition switches, the only security provided on most aircraft is key-type door locks which are generally of poor quality and can be readily opened with a wide variety of keys. Once inside the aircraft, an intruder has easy access to a multitude of easily removable and often expensive avionics and instrumentation devices. Engine ignition is also easily accomplished by an unauthorized person. For example, most single engine aircraft have key-type, turn-to-start ignition switches. The switch units are readily accessible and clearly marked on the back as to the function of each terminal, making the switch units easily bypassed and/or hot wired to achieve ignition. Multi-engine aircraft have no start security in that they have only toggle and/or push-button ignition switches.
- Accordingly, there is a need for an aircraft security system that is simple, light-weight, easy to install in new and existing aircraft, and is difficult to detect by an unauthorized person—yet prevents operation of the aircraft when armed. In addition, there is a need for a security system that does not draw power from the aircraft when armed, and is functional only when the aircraft is on the ground and parked.
- The various embodiments described herein relate to methods and apparatus of an aircraft security system. The teachings provided herein solve the earlier mentioned problems and additional problems not stated herein.
- _write
- This summary is an overview of some of the teachings of the present application and is not intended to be an exclusive or exhaustive treatment of the present subject matter. Further details about the present subject matter are found in the detailed description below and in the appended claims. Other aspects of the system will be apparent to persons skilled in the art upon reading and understanding the following detailed description and viewing the drawings that form a part thereof, each of which are not to be taken in a limiting sense. The scope of the present system is defined by the appended claims and their legal equivalents.
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FIG. 1A illustrates a block diagram of one embodiment of the present Aircraft Security System configured for both single and multi engine aircraft. -
FIG. 1B illustrates a block diagram of one embodiment of the present Aircraft Security System configured for both single and multi engine aircraft. -
FIG. 2 illustrates a schematic view of one embodiment of the present Aircraft Security System configured for single engine aircraft. -
FIG. 3 illustrates a schematic view of one embodiment of the present Aircraft Security System configured for multi engine aircraft. -
FIG. 4 illustrates a schematic view of one embodiment of the present Aircraft Security System configured for single engine aircraft. -
FIG. 5 illustrates a schematic view of one embodiment of the present Aircraft Security System configured for multi engine aircraft. - In the following description, for purposes of explanation, numerous specific details are set forth in order to provide a thorough understanding of the various embodiments. It will be apparent, however, to one skilled in the art that the various embodiments may be practiced without some of these specific details. The following description and drawings provide examples for illustration, but are not intended in a limiting sense and are not intended to provide an exhaustive treatment of all possible implementations.
- It should be noted that references to “an embodiment” or “one embodiment” in this disclosure are not necessarily to the same embodiment, and such references may contemplate more than one embodiment. Further, the terms “bus” and “buss” are used interchangeably throughout the specification and in the drawings.
- Further, references made to actuation of a switch may include opening or closing of a switch. It is understood that embodiments demonstrating a circuit having a switch in a first state may also be reconfigured to a circuit having a switch in a second state without departing from the scope of the present subject matter. Thus, an embodiment having a normally closed switch may be realized in an embodiment having a normally open switch without departing from the present subject matter. Those of skill in the art upon reading and understanding the present application will appreciate that differences in configuration and components may be employed without departing from the scope of the present teachings.
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FIG. 1A illustrates a block diagram of one embodiment of anaircraft security system 100, includingblock 71 including an aircraft battery,block 72 including an aircraft master switch and an electrical buss,block 73 including an anti-theft system,block 74 including one or more aircraft starter switches for single and multiple engines, andblock 75 including one or more aircraft starter relays and starter motors for single and multiple engines.FIG. 1A illustratesblocks connections connections blocks - In one embodiment, the aircraft battery of
block 71 couples throughconnection 80 to the aircraft master switch and electrical buss ofblock 72. In one embodiment, the aircraft master switch ofblock 72, when closed, allows power from the aircraft battery to reach the electrical buss ofblock 72, and when the aircraft master switch is open, power from the aircraft battery is disconnected from the electrical buss. When the master switch is closed, power from the electrical buss ofblock 72 is coupled throughconnection 81 to the anti-theft system ofblock 73. In one embodiment, the anti-theft system operates in both an activated or armed mode, and a deactivated or unarmed mode. The apparatus and methods for determining the modes and operations of the anti-theft system are described in further detail below. - If power from
block 72 reachesblock 73 and the anti-theft system is activated, the anti-theft system will disconnect the power supplied fromblock 72, and thus not allow power for the aircraft battery topower block 74 orblock 75. By not allowing power to reachblocks block 73 prevents the starting of the engine or engines present on the aircraft, even if the aircraft starter switch or switches ofblock 74, as described below, are actuated (closed). - If power from
block 72 reachesblock 73 and the anti-theft system is deactivated, the anti-theft system will allow the power to be coupled throughconnection 82 to block 74. In various embodiments,block 74 includes one aircraft starter switch, associated with the singe engine of a single engine aircraft. If power is supplied toblock 74 and the aircraft starter switch is actuated (closed), power will be coupled throughconnection 83 toblock 75. In various embodiments,block 75 includes an aircraft starter relay that will be energized by the power supplied throughconnection 83. When energized, the aircraft starter relay will allow power to reach the starter motor associated with the aircraft engine, and thus allow starting of the aircraft's engine. - In various embodiments,
block 74 includes multiple aircraft starter switches, wherein each of the switches is associated with one of the engines of a multiple engine aircraft. If power is supplied toblock 74 and one of the aircraft starter switches ofblock 74 is actuated (closed), power will be coupled throughconnection 83 toblock 75. It will be realized by those of ordinary skill in the art that for multiple engine applications,connection 83 may include separate connections associated with each of the engines of the multiple engine aircraft. In various embodiments, block 75 includes multiple aircraft starter relays, each one being associated with a starter motor. When power is supplied to block 75 throughconnection 83, the particular starter relay associated with the starter switch being actuated will be energized. When energized, the particular starter relay energized will allow power to reach the aircraft starter motor associated with that starter relay, allowing the aircraft engine associated with that starter motor to be started. - As described above with regards to a single engine aircraft, for a multiple engine aircraft, if power from
block 72 reaches block 73 and the anti-theft system is activated, the anti-theft system will disconnect the power supplied fromblock 72, and thus not allow power from the aircraft battery ofblock 71 topower block 74 orblock 75. By not allowing power to reachblocks block 74 are actuated (closed). Thus, when activated, the anti-theft system prevents starting for any of the engines on the multiple engine aircraft. -
FIG. 1B illustrates a block diagram of one embodiment of anaircraft security system 110. The embodiment ofaircraft security system 110 is similar to the embodiment ofsystem 100, except that block 74 (aircraft starter switch -single and multiple engine) is coupled to block 72 throughconnection 81, and block 74 is further coupled to the anti-theft system ofblock 73 throughconnection 82. The anti-theft system ofblock 73 is coupled to block 75 throughconnection 83.System 110 functions in a similar manner tosystem 100. However, one embodiment may be preferred over the other with regards to installment of the system on an aircraft due to, among other factors, physical access to the various portions of the circuits in the aircraft. -
FIG. 2 illustrates one embodiment of anaircraft security system 200 including a starter breaker 4 electrically connected tomain power bus 3 and astarter switch 5, where themain power bus 3 is powered by amaster switch 2 from amain battery 1. In various embodiments,main power bus 3 may be an instrument bus.System 200 further includes asecurity relay 11 having activation means for a first set ofcontacts 20 and a second set ofcontacts 21, where the first set ofcontacts 20 are normally closed, and are electrically connected to astarter switch 5, astarter relay 6, and where the second set ofcontacts 21 are normally open and are electrically connected to aremote battery 14, aremote switch 12, analarm 13, and adiode 10A. Asecurity switch 9 is electrically connected to thesecurity relay 11. In one embodiment,security switch 9 is a key lock switch. Other embodiments having different types of switches are possible without departing from the scope of the present subject matter. -
System 200 includes one or more modes of operation. In normal, unarmed operation,security switch 9 is open, and the control coil ofsecurity relay 11 is de-energized. In this mode, normally closedcontacts 20 ofsecurity relay 11 will be in a closed state. Activation of themaster switch 2 and thestarter switch 5 in this mode causes current to flow through the normally closedcontacts 20 of thesecurity relay 11, allowing current flow frommain power bus 3 and starter breaker 4, to thestarter relay 6, which, when energized, closescontacts 22 ofstarter relay 6. Withcontacts 22 closed, power is delivered tostarter motor 7 fromstarter bus 23 throughelectrical connection 55,contacts 22, andelectrical connection 56. - In another mode of operation of
system 200,security switch 9 is closed. The control coil ofsecurity relay 11 is electrically coupled tomain power bus 3 throughelectrical connection 60,security switch 9,electrical connection 57. In one embodiment,diode 10B coupleselectrical connection 60 withelectrical connection 59,electrical connection 59 being coupled tosecurity switch 9. Activation ofmaster switch 2 with a closed (armed)security switch 9 allows current frommain battery 1 to flow throughmaster switch 2 to themain power bus 3, and thus energizes the control coil ofsecurity relay 11, causing normally closedcontacts 20 to open. With normally closedcontacts 20 open, the current flow from themain power bus 3 tostarter relay 6 is disconnected.Starter relay 6 remains de-energized, andcontacts 22 remain open. Withcontacts 22 open, no power is delivered tostarter motor 7 from thestarter bus 23. With normally closedcontacts 20 open, activation ofstarter switch 5 will not allow power frommain battery 1 to energizestarter relay 6, and thus will prevent starting of the aircraft. -
FIG. 2 illustrates an embodiment of thesecurity system 200 in which at least one application is configured for single engine aircraft. During normal operation, themaster switch 2 is closed, allowing battery power from themain battery 1 to flow to themain power bus 3 throughelectrical connections main power bus 3 throughelectrical connection 67 to starter breaker 4, then throughelectrical connection 52 tostarter switch 5. Whenstarter switch 5 is actuated (closed), current flows throughstarter switch 5, and throughelectrical connection 58 to the normally closedcontacts 20 of thesecurity relay 11. From normally closedcontacts 20, current flows throughelectrical connection 54, energizing the control coil ofstarter relay 6, andclosing contacts 22, providing power to theengine starter motor 7 fromstarter bus 23 throughelectrical connection 55,contacts 22, andelectrical connection 56. - In various embodiments, the
security switch 9 includes, but is not limited to, a toggle switch, a key pad, or a biometric security device which is activated for proper operation of the aircraft. In various embodiments, activation may include entering a Personal Identification Number (PIN) on a key pad before proper operation of the aircraft will be enabled. In various embodiments, the function and location of thesecurity switch 9 is known only to authorized operators of the aircraft. In one or more embodiments, when the owner/operator desires security, the normallyopen security switch 9 is closed. Oncesecurity switch 9 is closed, activating themaster switch 2 causes current to flow from themain power bus 3 alongelectrical connection 57 to the now closed (armed) contacts of thesecurity switch 9. Power is now available, throughelectrical connection 60, to the control coil ofsecurity relay 11, activatingsecurity relay 11. In various embodiments, the path of current flow includeselectrical connection 59 anddiode 10B. - Activation of
security relay 11 causes various events to occur. In an embodiment, the energizedsecurity relay 11 opens the normally closedcontacts 20, thus opening the start circuit and preventingstarter motor 7 from energizing, even whenstarter switch 5 is actuated, or ifstarter switch 5 is tampered with. For example even if the “S” and “B” terminals ofstarter switch 5, as illustrated inFIG. 2 , are jumpered or otherwise shorted, the normallyopen contacts 20 will prevent power from being delivered tostarter relay 6, and thus prevent starting of the aircraft's engine. - In various embodiments, the energization of
security relay 11 will close normallyopen contacts 21. With normallyopen contacts 21 closed, current can flow fromremote battery 14 throughelectrical connection 61 and throughremote switch 12 and throughelectrical connection 62, and through the now closed normallyopen contacts 21 of thesecurity relay 11. Current then continues to flow throughelectrical connection 63 anddiode 10A toelectrical connection 60, providing a second source of current flow through the control coil ofsecurity relay 11, keepingsecurity relay 11 energized (latched). In various embodiments, the current flow toelectrical connection 63 will allowalarm 13 to become activated. Once latched,security relay 11 andalarm 13 will remain activated even if starter breaker 4 is opened or if the aircraft's primary power is removed from themain power bus 3 by opening the aircraft'smaster switch 2.Alarm 13 is deactivated by opening the contacts ofremote switch 12. In various embodiments, the function and location of theremote switch 12 is known only to the owner/operator of the aircraft or other authorized persons. -
FIG. 3 illustrates an embodiment where thesecurity system 300 is useful in applications, including, but not limited to, use in multiple engine aircrafts. Reference numbers are repeated for elements ofFIG. 3 which are the same or similar to those ofFIG. 2 . Elements inFIG. 3 depicting additional iterations of the same or similar elements as depicted inFIG. 2 are shown using the same reference numbers with the addition of a letter, for example, “A” or “B.” According to various embodiments ofsystem 300, during normal operation,master switch 2 is activated allowing battery power to flow frommain battery 1 tomain power bus 3. During a normal ignition sequence, current flows frommain power bus 3 throughelectrical connection 67 and starter breaker 4, then throughelectrical connection 52 to the normally closedcontacts 20 ofsecurity relay 11. In various embodiments, the current continues to flow throughelectrical connections electrical connections 53C and 53D to the normally open contacts ofstarter switches starter switches - In one embodiment, starter switches 5A and 5B are operated by separate means. In one embodiment, starter switches 5A and 5B may be operated at separate times. When
starter switch 5A is activated, current flows through its closed contacts andelectrical connection 54A to the associatedstarter relay 6A, energizing the control coil ofstarter relay 6A, andclosing contacts 22A. Withcontacts 22A closed, current fromstarter bus 23A flows throughelectrical connection 55A,contacts 22A, andelectrical connection 56A topower starter motor 7A. Thus, the starting of the aircraft's engine associated withstarter motor 7A is enabled. - When the
starter switch 5B is activated, current flows through its closed contacts andelectrical connection 54B to the associatedengine starter relay 6B, energizing the control coil ofstarter relay 6B, andclosing contacts 22B. Withcontacts 22B closed, current fromstarter bus 23B flows throughelectrical connection 55B,contacts 22B, andelectrical connection 56B to power starter motor 7B. Thus, the starting of the aircraft's engine associated with starter motor 7B is enabled. - As discussed above, various embodiments of
security system 300 include additionalelectrical connections 53C and 53D that are coupled tostarter switches - In various embodiments, the function and location of the
security switch 9 is known only to authorized operators of the aircraft. When the owner/operator desires security,security switch 9 is activated (closed). In an embodiment, whensecurity switch 9 is activated and an unauthorized start is attempted, current flows frommain power bus 3, throughelectrical connection 57 and the now closedsecurity switch 9, throughelectrical connection 60, and to the control coil ofsecurity relay 11, thus activatingsecurity relay 11. In one embodiment,electrical connection 60 is coupled tosecurity switch 9 throughelectrical connection 59 anddiode 10B. - When
security relay 11 is activated, various events occur. In an embodiment, the normally closedcontacts 20 of thesecurity relay 11 open, removing power from the starter switches 5A and 5B, and preventing either of the engines from being started, even if starter switches 5A or 5B are actuated. In an embodiment, whensecurity relay 11 is activated, the normallyopen contacts 21 ofsecurity relay 11 close, allowing power to flow from theremote battery 14 through theremote switch 12 andelectrical connections open contacts 21, and throughelectrical connection 63 to theaudio alarm 13. Current also flows fromelectrical connection 63 throughdiode 10A to keep thesecurity relay 11 activated (latched) even if the starter breaker 4 is reopened or when the aircraft's primary power is removed from themain power bus 3 by re-opening the aircraft'smaster switch 2. In one embodiment, oncesecurity switch 9 is opened (unarmed), theaudible alarm 13 is turned off by openingremote switch 12. This removes power from thealarm 13 as well as from the control coil of thesecurity relay 11, unlatchingsecurity relay 11. Unlatchingsecurity relay 11 causes normallyopen contacts 21 to open, and normally closedcontacts 20 to close. -
FIG. 4 illustrates an embodiment of thesecurity system 400 enhanced to provide security against unauthorized entry and unauthorized removal of installed devices. The embodiment is shown for single engine aircraft, but is equally applicable to multi-engine aircraft as shown inFIG. 5 . Reference numbers are repeated for elements ofFIG. 4 that are the same or similar to those ofFIG. 2 . Elements inFIG. 5 depicting additional iterations of the same or similar elements as depicted inFIG. 4 are shown using the same reference numbers with the addition of a letter, for example, “A” or “B.” - Various embodiments of
security system 400 are enhanced to includesecurity switch 9 coupled tomain power bus 3 throughelectrical connection 57 and a circuit protection device, for example, an in-line fuse 26, is included betweenelectrical connections Electrical connection 58couples circuit 24 ofsecurity switch 9 throughdiode 10B toelectrical connection 60, which then is coupled to the coil (the control portion) ofsecurity relay 11. Whensecurity switch 9 is closed (armed) andmaster switch 2 is activated, power frommain battery 1 flows frommain battery 1 throughmaster switch 2 andmain power bus 3, and further throughcircuit 24 ofsecurity switch 9 to energize the coil ofsecurity relay 11. - Once activated,
security relay 11 opens normally closedcontacts 20 and closes normallyopen contacts 21, latchingsecurity relay 11 throughremote battery 14 andremote switch 12 while preventing the powering ofstarter relay 6, as described above. Further, in various embodiments,alarm 13 is activated whensecurity relay 11 is energized. - As illustrated in
FIG. 4 , in various embodiments ofsystem 400, aircraft doors and removable equipment are protected withswitches FIG. 4 , switches 15 and 16 are shown as magnetic switches. However, switches 15 and 16 are not limited to being magnetic switches. In one embodiment, switches 15 and 16 are motion activated. In an embodiment, switches 15 and 16 are proximity switches. In various embodiments, other type switches are possible, including, but not limited to, optical, Hall effect, pressure, or other types of switches, such as proximity or motion activated switches. In various embodiments, additional switches are included. In various embodiments, switches 15 and 16 will not be the same type of switch. It will be recognized that various type switches, and various combinations of types of switches, may be used in a variety of applications and in various combinations. In various embodiments, switches 15 and 16 are in communication withsystem 400 using a wireless form of coupling. - In various embodiments, switches 15 and 16 are arranged so that when a door or a hatch of the aircraft is opened, or in the case of installed equipment, the equipment is tampered with or removed from its housing, the associated
switch remote battery 14 throughelectrical connection 61 andremote switch 12, on throughelectrical connection 64 and the now actuated contacts ofswitches electrical connection 65 to thecircuit 25 of thesecurity switch 9. If the security system is set on (armed), thecircuit 25 ofsecurity switch 9 will be closed, allowing current to flow throughelectrical connection 66 anddiode 10C to activate and latchsecurity relay 11, as discussed above. In various embodiments,alarm 13 is also activated whensecurity relay 11 is activated or latched. In various embodiments,alarm 13 includes an audible alarm. In various embodiments, the alarm is a silent alarm. In various embodiments,alarm 13 includes notification of the activation of the alarm to one or more various parties, including but not limited to, the aircraft owner, the aircraft operator, airport security officials, and law enforcement officials. - In one embodiment, activation of
security relay 11 will cause normally closedcontacts 20 to open, and thus prevent starting of the engine associated withstarter motor 7, even ifstarter switch 5 is tampered with as discussed above. In an embodiment,alarm 13 is turned off by openingremote switch 12 as discussed above. -
FIG. 5 illustrates an embodiment where thesecurity system 500 is useful in applications, including, but not limited to, use in multiple engine aircrafts. Reference numbers are repeated for elements ofFIG. 5 which are the same or similar to those ofFIG. 4 . Elements inFIG. 5 depicting additional iterations of the same or similar elements as depicted inFIG. 4 are shown using the same reference numbers with the addition of a letter, for example, “A” or “B.” - As illustrated in
FIG. 5 , in various embodiments ofsystem 500, aircraft doors and removable equipment are protected withswitches switch system 500 through a wireless coupling. In various embodiments, if either ofswitches security switch 9 is activated (armed),security relay 11 will be energized, and normally closedcontacts 20 will open. With normally closedcontacts 20 open, power is disconnected fromstarter switches starter switches starter relays starter switches - In various embodiments of
system 500, activation ofsecurity relay 11 will latchrelay 11. In various embodiments,alarm 13 is also activated whensecurity relay 11 is activated or latched. In an embodiment,alarm 13 is turned off by openingremote switch 12 as discussed above. - This description has set forth numerous characteristics and advantages of various embodiments and details of structure and function of an aircraft security system, but is intended to be illustrative and not intended in an exclusive or exhaustive sense. Changes in detail, material and management of parts, order of process and design may occur without departing from the scope of the appended claims and their legal equivalents.
Claims (22)
1. A system for securing an aircraft having a starter, a starter switch, and a master switch to connect, in an on position, a first power source to a main power bus, the system comprising:
a security system connected to control power to the starter, the security system including:
a security switch adapted to arm the security system in an armed state and to disarm the security system in a disarmed state;
a second power source to provide backup power to the security system;
a controllable switch adapted to complete a starter circuit for powering the starter in a first mode and to break the starter circuit in a second mode, the controllable switch adapted to be controlled by sensing states of at least the security switch and the main power bus,
and wherein in the armed state the security system is configured to prevent activation of the starter upon detection of attempted use of the aircraft before disarming the security system.
2. The system of claim 1 , wherein attempted use of the aircraft before disarming the security system includes the master switch being in the on position.
3. The system of claim 1 , wherein the second power source is connected to the controllable switch and is adapted to maintain the controllable switch in the second mode once the controllable switch has entered the second mode.
4. The system of claim 1 , further including a remote switch to reset the security system when the security system is activated.
5. The system of claim 1 , further including the controllable switch being adapted to be controlled by sensing states of one or more switches connected to the second power source.
6. The system of claim 5 , wherein one or more switches connected to the second power source includes a switch associated with a door of the aircraft.
7. The system of claim 5 , wherein one or more switches connected to the second power source includes a switch associated with an installed device of the aircraft.
8. The system of claim 1 , further including an alarm coupled to the security system.
9. The system of claim 1 , wherein the second power source is coupled to the alarm and is adapted to power the alarm until disconnected using a remote switch to reset the security system once the security system is activated.
10. The system of claim 1 , wherein in the armed state the security system is configured to prevent activation of a second starter upon detection of attempted use of the aircraft before disarming the security system.
11. An aircraft electrical system comprising:
a master switch connected to a battery;
a starter relay having a starter switch interconnecting the main switch to the starter relay;
a security switch connected to the main switch; and
a security relay having a coil connected to the security switch;
wherein the security relay interconnects the main switch and the starter relay in a coil unpowered state of operation, and further disconnects the main switch and the starter relay and interconnects a remote battery and the coil in a coil powered state of operation.
12. The system of claim 11 , wherein a normally closed set of contacts of the security relay interconnects the main switch and the starter relay in the coil unpowered state of operation.
13. The system of claim 11 , wherein a normally open set of contacts of the security relay interconnects the remote battery and the coil in the coil powered state of operation.
14. The system of claim 13 , wherein a remote switch interconnects the remote battery and the normally open set of contacts of the security relay.
15. The system of claim 11 , further including an alarm, wherein the alarm interconnects to the remote battery in the coil powered state of operation.
16. The system of claim 11 , further including a switch, wherein the switch interconnects the remote battery through the security switch to the coil.
17. The system of claim 16 , wherein the switch is adapted to interconnect the remote battery through the security switch to the coil when a door associated with the switch is opened.
18. The system of claim 16 , wherein the switch is adapted to interconnect the remote battery through the security switch to the coil when an installed device associated with the switch is removed.
19. The system of claim 11 , wherein the security relay interconnects the main switch and a plurality of starter relays in the coil unpowered state of operation.
20. An apparatus for securing an aircraft, comprising:
a first power supply;
a starter and starter relay for use in starting an engine of the aircraft;
a main power bus and master switch providing power to the starter relay and starter; and
switch means for controllably disconnecting the first power supply from the starter relay and starter upon detection of an attempted intrusion while in an armed state.
21. The apparatus of claim 20 , further comprising alarm means.
22. The apparatus of claim 20 , further comprising a second starter and a second starter relay for use in starting a second engine of the aircraft.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/036,630 US20110148192A1 (en) | 2004-06-02 | 2011-02-28 | Aircraft security system |
Applications Claiming Priority (4)
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US57626204P | 2004-06-02 | 2004-06-02 | |
US11/138,652 US7423554B2 (en) | 2004-06-02 | 2005-05-26 | Aircraft security system |
US12/197,538 US7898399B2 (en) | 2004-06-02 | 2008-08-25 | Aircraft security system |
US13/036,630 US20110148192A1 (en) | 2004-06-02 | 2011-02-28 | Aircraft security system |
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US12/197,538 Continuation US7898399B2 (en) | 2004-06-02 | 2008-08-25 | Aircraft security system |
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US12/197,538 Expired - Fee Related US7898399B2 (en) | 2004-06-02 | 2008-08-25 | Aircraft security system |
US13/036,630 Abandoned US20110148192A1 (en) | 2004-06-02 | 2011-02-28 | Aircraft security system |
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US12/197,538 Expired - Fee Related US7898399B2 (en) | 2004-06-02 | 2008-08-25 | Aircraft security system |
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US9454678B2 (en) | 2011-12-22 | 2016-09-27 | Intel Corporation | Always-available embedded theft reaction subsystem |
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US9507918B2 (en) | 2011-12-22 | 2016-11-29 | Intel Corporation | Always-available embedded theft reaction subsystem |
FR3067877B1 (en) * | 2017-06-14 | 2022-05-20 | Zodiac Aero Electric | POWER SUPPLY ASSEMBLY FOR AN AIRCRAFT |
CN113365884B (en) * | 2019-01-31 | 2023-04-28 | 本田技研工业株式会社 | Control device, saddle-ride type vehicle, control method for saddle-ride type vehicle, and vehicle management system |
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Also Published As
Publication number | Publication date |
---|---|
US7423554B2 (en) | 2008-09-09 |
US7898399B2 (en) | 2011-03-01 |
US20090140573A1 (en) | 2009-06-04 |
US20060131958A1 (en) | 2006-06-22 |
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