HYDRAULIC/PNEUMATIC CHARGING VALVE WITH INTEGRATED PRESSURE TRANSDUCER
First Claim
1. A charging valve for use in a pressure vessel in an aircraft landing gear comprising:
- a valve stem having a first and second end and a channel extending therebetween;
a pressure-sensing device received within the channel at the first end and operable to measure the pressure of the pressure vessel; and
a receptacle received within the channel between the pressure-sensing device and the second end and operable to be in communication with the pressure-sensing device and configured to allow fluid to flow through the valve.
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Accused Products
Abstract
The present invention is a device that allows the pressure inside an aircraft landing gear shock strut to be measured. A charging valve is modified by integrating a small pressure sensing device into the stem of the part such that the active diaphragm is subjected to the pressure within the charged vessel. The wires from the pressure sensing device are connected to a receptacle or connector in the bore of the stem such that a corresponding electrical receptacle may be mated for the purposes of making a measurement. The internal receptacle is designed such that the flow of air or oil is not excessively impeded and normal servicing tools do not interfere with the receptacle.
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Citations
25 Claims
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1. A charging valve for use in a pressure vessel in an aircraft landing gear comprising:
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a valve stem having a first and second end and a channel extending therebetween; a pressure-sensing device received within the channel at the first end and operable to measure the pressure of the pressure vessel; and a receptacle received within the channel between the pressure-sensing device and the second end and operable to be in communication with the pressure-sensing device and configured to allow fluid to flow through the valve. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16, 17, 18, 19, 20, 21)
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22. A method of modifying a charging valve having a main body including a channel therethrough, to include a pressure measuring device for use in a pressure vessel comprising the steps of:
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(i) placing a pressure-sensing device within the channel at the end of the valve that is in communication with the pressure vessel to allow the pressure-sensing device to measure the pressure within the vessel; (ii) connecting the pressure-sensing device to a receptacle to allow for communication therebetween, the receptacle being located within the channel of the valve at the opposite end of the pressure-sensing device from the measurement end and being operable to allow for fluid to flow through the valve.
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23. A charging valve for use in a pressure vessel in an aircraft landing gear comprising:
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a valve stem having a first and second end and a channel extending therebetween; a pressure reading means connected to the first end of the valve body for reading the pressure in the pressure vessel; and a receptacle received within the channel between the pressure reading means and the second end and operable to be in communication with the pressure reading means and configured to allow fluid to flow through the valve. - View Dependent Claims (24, 25)
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Specification