Airborne power system disconnect system and method
First Claim
Patent Images
1. An aircraft comprising a control panel, an electrical system having a primary power source, and an electrical unit selectively electrically connected to the aircraft electrical system, the electrical unit being configured to automatically electrically disconnect system circuits of the electrical unit from the aircraft electrical system and electrically connect the system circuits of the electrical unit to a secondary power source if an emergency event occurs while the aircraft is in flight, the electrical unit further comprising:
- a controller to monitor electrical power associated with the aircraft electrical system so as to determine a first factor; and
a switch to electrically connect the system circuits of the electrical unit to the aircraft electrical system in a first position and to the secondary power source in a second position,wherein the controller compares the first factor to a predetermined second factor;
wherein if the first factor is less than the predetermined second factor, then the controller generates a signal to move the switch from the first position to the second position;
wherein the control panel includes a plurality of systems;
wherein the electrical unit is one of the systems of the control panel;
wherein at least some of the systems of the control panel continue to be powered by the aircraft electrical system when said switch is in the second position; and
wherein said secondary power source is electronically isolated from the aircraft electrical system regardless of which position said switch is in.
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Abstract
An system and method to automatically disconnect a retrofit electrical unit from an electrical system in the event of an emergency situation and maintain power to the retrofit electrical unit.
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Citations
20 Claims
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1. An aircraft comprising a control panel, an electrical system having a primary power source, and an electrical unit selectively electrically connected to the aircraft electrical system, the electrical unit being configured to automatically electrically disconnect system circuits of the electrical unit from the aircraft electrical system and electrically connect the system circuits of the electrical unit to a secondary power source if an emergency event occurs while the aircraft is in flight, the electrical unit further comprising:
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a controller to monitor electrical power associated with the aircraft electrical system so as to determine a first factor; and a switch to electrically connect the system circuits of the electrical unit to the aircraft electrical system in a first position and to the secondary power source in a second position, wherein the controller compares the first factor to a predetermined second factor;
wherein if the first factor is less than the predetermined second factor, then the controller generates a signal to move the switch from the first position to the second position;wherein the control panel includes a plurality of systems; wherein the electrical unit is one of the systems of the control panel; wherein at least some of the systems of the control panel continue to be powered by the aircraft electrical system when said switch is in the second position; and wherein said secondary power source is electronically isolated from the aircraft electrical system regardless of which position said switch is in. - View Dependent Claims (2, 3, 4, 5, 6)
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7. A method to add a retrofit apparatus to an aircraft, the aircraft comprising a control panel and an electrical system having a primary power source, the method comprising:
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installing the retrofit apparatus onto the control panel of the aircraft; electrically connecting a switch of the retrofit apparatus to the electrical system of the aircraft; monitoring electrical power from the aircraft electrical system so as to determine a first factor; comparing the first factor to a predetermined second factor; and generating a signal to move a switch of the retrofit apparatus from a first position to a second position if the first factor is less than the predetermined second factor; wherein system circuits of the retrofit apparatus are electrically connected to the aircraft electrical system when said switch is in the first position; wherein moving said switch from the first position to the second position disconnects said system circuits of the retrofit apparatus from the aircraft electrical system and connects said system circuits to a secondary power source; wherein adding the retrofit apparatus to the aircraft does not require a load analysis;
wherein adding the retrofit apparatus to the aircraft would require a load analysis if the retrofit apparatus did not disconnect said system circuits of the retrofit apparatus from the aircraft electrical system when the first factor is less than the predetermined second factor;wherein the control panel includes a plurality of systems; wherein the installing and the electrically connecting steps cause the retrofit apparatus to become one of the systems of the control panel; wherein at least some of the systems of the control panel continue to be powered by the aircraft electrical system when said switch is in the second position; and wherein said secondary power source is electronically isolated from the aircraft electrical system regardless of which position said switch is in. - View Dependent Claims (8, 9, 10, 11, 12, 13)
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14. A power control system to control power to an electrical component of an aircraft while the aircraft is in flight, the system comprising:
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a first power source to store power; an alternator to generate power, said alternator being connected to said first power source; an electrical bus connected to said first power source; an electrical switch connected to said electrical bus and to said electrical component so as to selectively connect system circuits of said electrical component to said electrical bus when said electrical switch is located at a first position; and a second power source connected to said electrical switch such that said system circuits of said electrical component are connected to said second power source when said electrical switch is located at a second position; wherein the aircraft includes a plurality of systems; wherein the electrical component is one of the systems of the control panel; wherein at least some of the systems of the control panel continue to be powered by the electrical bus when said electrical switch is in the second position; and wherein the secondary power source is electronically isolated from the aircraft electrical system regardless of which position said electrical switch is in. - View Dependent Claims (15, 16, 17, 18, 19, 20)
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Specification