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Method for producing a galvanized steel drain pan of rectangular or square configuration for use in refrigerators, freezers, and air conditioners to collect condensate water, the method includes the steps of: cutting a blank galvanized steel plate to the desired size; folding sides portions of the b

Method for producing a galvanized steel drain pan of rectangular or square configuration for use in refrigerators, freezers, and air conditioners to collect condensate water, the method includes the steps of: cutting a blank galvanized steel plate to the desired size; folding sides portions of the blank to a degree of 60 to 90 to form side portions of the drain pan; corrugating the corners formed by the side portions; and installing a drain fitting along with a pipe to drain the condensate water from the drain pan. Also disclosed is the drain pan made by the method.

대표청구항 ▼

Method for producing a galvanized steel drain pan of rectangular or square configuration for use in refrigerators, freezers, and air conditioners to collect condensate water, the method includes the steps of: cutting a blank galvanized steel plate to the desired size; folding sides portions of the b

Method for producing a galvanized steel drain pan of rectangular or square configuration for use in refrigerators, freezers, and air conditioners to collect condensate water, the method includes the steps of: cutting a blank galvanized steel plate to the desired size; folding sides portions of the blank to a degree of 60 to 90 to form side portions of the drain pan; corrugating the corners formed by the side portions; and installing a drain fitting along with a pipe to drain the condensate water from the drain pan. Also disclosed is the drain pan made by the method. a primary hydraulic drive. 8. A spacecraft hydraulic power assembly as described in claim 1, wherein said hydraulic system comprises landing gear. 9. A spacecraft hydraulic power assembly comprising: at least one primary hydraulic power unit supplying hydraulic fluid to a hydraulic system; at least one contingency power unit in communication with said hydraulic system, said at least one contingency power unit powered by at least one helium storage tank and capable of providing additional flow of hydraulic fluid to said hydraulic system; and at least one control valve controlling communication between said contingency power unit and said at least one primary hydraulic power unit. 10. A spacecraft hydraulic power assembly comprising: at least one primary hydraulic power unit supplying hydraulic fluid to a hydraulic system; at least one contingency power unit in communication with said hydraulic system, said at least one contingency power unit powered by at least one helium storage tank and capable of providing additional flow of hydraulic fluid to said hydraulic system, said contingency power unit in communication with each of said at least one primary hydraulic power units. 11. A spacecraft hydraulic power assembly comprising: a first primary hydraulic power unit, including a first hydraulic fluid reserve and a first primary hydraulic drive, said first primary hydraulic power unit supplying hydraulic fluid from said first hydraulic fluid reserve to a hydraulic system; a second primary hydraulic power unit, including a second hydraulic fluid reserve and a second primary hydraulic drive, said second primary hydraulic power unit supplying hydraulic fluid from said second hydraulic fluid reserve to said hydraulic system; and a contingency power unit in communication with said hydraulic system, said at least one contingency power unit including a helium storage tank, a contingency hydraulic power drive, and a contingency hydraulic fluid reserve, said helium storage tank powering said contingency hydraulic power drive to supply hydraulic fluid from said contingency hydraulic fluid reserve to said hydraulic system upon failure of one of said primary hydraulic power units, said contingency hydraulic power drive comprising a gas turbine. 12. A spacecraft hydraulic power assembly as described in claim 11, further comprising: at least one hydraulic interconnect line connecting said contingency power unit to said first primary hydraulic power unit. 13. A spacecraft hydraulic power assembly as described in claim 11, further comprising: at least one hydraulic interconnect line connecting said contingency power unit to said first primary hydraulic power unit; and at least one hydraulic interconnect line connecting said contingency power unit to said second primary hydraulic power unit. 14. A spacecraft hydraulic power assembly as described in claim 11, wherein in response to failure of said first primary hydraulic power unit, said contingency power unit boosts flow from said second primary hydraulic power unit during increased flow requirements. 15. A spacecraft hydraulic power assembly as described in claim 11, wherein in response to failure of said first primary hydraulic power unit, said contingency power unit replaces flow from said first primary hydraulic power unit during increased flow requirements. 16. A spacecraft hydraulic power assembly as described in claim 11, wherein said contingency power unit further comprises: a helium valve; and a regulator, said helium valve and regulator controlling the flow of helium out of said helium storage tank. 17. A spacecraft hydraulic power assembly as described in claim 11, wherein said first primary hydraulic power unit is an electro-hydraulic power unit. 18. A spacecraft hydraulic power assembly comprising: a first primary hydraulic power unit, including a first hydraulic fluid reserve and a first primary hydraulic drive, said first primary hydraulic p