Abstract:
A portable hydraulic pump apparatus that is self-powered, wherein an onboard fuel-powered engine is provided to drive the hydraulic pump, the units being mounted onto a wheeled cart such that the apparatus is easily moved to a remote location as needed.

Description:
[0001]    This application claims the benefit of U.S. Provisional Patent Application Ser. No. 62/139,098, filed Mar. 27, 2015, the disclosure of which is incorporated herein by reference. 
     
    
     BACKGROUND OF THE INVENTION 
       [0002]    This invention relates generally to the field of hydraulic pumps, and more particularly to the field of portable hydraulic pumps, and even more particularly to the field of self-powered portable hydraulic pumps. 
         [0003]    There are numerous circumstances where a portable hydraulic pump is needed, such that the hydraulic pump can be easily moved to a position near equipment that requires hydraulic power. For example, frequent testing of the hydraulic systems of aircraft such as helicopters is required by regulation. Known portable hydraulic pumps operated by electric motors require a hard wire connection to the electrical grid, i.e., the power unit must be plugged into a power source in order to operate the hydraulic pump. In many situations however there is no readily accessible electrical outlet or source availability in the near proximity of the helicopter. Thus, the portability range of the hydraulic pump is limited, unless multiple extension/power cords are utilized, which is often impractical and creates safety hazards to personnel. 
         [0004]    It is an object of this invention to provide a portable hydraulic pump apparatus that is self-powered, wherein an onboard fuel-powered (e.g., gasoline) engine is provided to drive the hydraulic pump, the units being mounted onto a wheeled cart such that the apparatus is easily moved to a remote location as needed. 
       SUMMARY OF THE INVENTION 
       [0005]    The invention is in general a portable self-powered hydraulic pump apparatus, the apparatus comprising a hydraulic pump powered by a dedicated fuel-powered, non-electric engine, both units mounted onto a wheeled cart for mobility. The apparatus is structured such that the hydraulic pump and the fuel-powered engine are small enough to be easily transportable, while the engine and pump are sufficiently powerful to deliver hydraulic fluid to a piece of equipment, such as a helicopter for testing operations, at a minimum pressure of approximately 1200 psi, and more preferably able to deliver hydraulic fluid at a minimum pressure of at least approximately 5000 psi, such that the apparatus is suitable for providing hydraulic power for testing the majority of commercial and private helicopters. In general, the apparatus comprises a heavy-duty wheeled cart, a fuel-powered engine, a hydraulic pump, a flow control regulator mechanism, a flow meter, a pressure regulator, a pressure gauge, a temperature gauge, a function control mechanism, a high flow filter and automatic flow cutoff hydraulic hose connector fittings. 
     
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         [0006]      FIG. 1  is a representative schematic of the operational systems and flow paths of the hydraulic pump apparatus. 
           [0007]      FIG. 2  is a representative illustration of the hydraulic pump apparatus. 
           [0008]      FIG. 3  is a representative illustration of the panel portion of the hydraulic pump apparatus. 
       
    
    
     DETAILED DESCRIPTION OF THE INVENTION 
       [0009]    The invention is in general a portable, self-powered hydraulic pump apparatus comprising a non-electric, fuel-powered (e.g., gasoline) engine and a hydraulic pump, both mounted onto a wheeled cart, the apparatus especially suited for providing hydraulic fluid to aircraft, and in particular helicopters, for testing operations. In general, the apparatus comprises a heavy-duty wheeled cart, a fuel-powered engine, a hydraulic pump, a flow control regulator mechanism, a flow meter, a pressure regulator, a pressure gauge, a temperature gauge, a function control mechanism, a high flow filter and automatic flow cutoff hydraulic hose connector fittings. 
         [0010]    With reference to the  FIGS. 1 and 2 , the hydraulic pump apparatus will now be described in greater detail. A heavy-duty multi-wheeled cart  10  is provided, the cart  10  having a base area  101  adapted to support the non-electric, fuel-powered engine or motor  11  and the hydraulic pump  12 . As shown in  FIG. 2 , a cart  10  having two pneumatic tires  102  and an upstanding frame  103  retaining a panel  104  to receive various controls, gauges and the like is suitable. The invention is not limited to this embodiment, as carts with 3 or 4 wheels or with varying structures will also be suitable. 
         [0011]    The engine  11  must be of a size sufficient to power the hydraulic pump  12 , and an 8 hp gasoline engine has been found to be acceptable. In a preferred embodiment, the engine  11  has an electric starter, in which case a DC battery  20  may be provided, the battery  20  being recharged by the alternator of the alternator of the engine  11 . 
         [0012]    The hydraulic pump  12  should be capable of delivering hydraulic fluid at a minimum of approximately 1200 psi at up to approximately 7 gpm (gallons per minute). Hydraulic pumps  12  of varying sizes may be utilized. For example, a 26 hp hydraulic pump  12  capable of producing up to approximately 5000 psi at a flow rate of up to approximately 14 gpm is preferred to cover the full range of helicopter hydraulic systems. Commercially it may be advisable to offer three separate apparatuses, a base model providing approximately 1200-1500 psi at up to approximately 7 gpm, a midline model providing up to approximately 3000 psi at up to approximately 10 gpm, and a topline model providing up to approximately 5000 psi at up to approximately 14 gpm. 
         [0013]    Various equipment, controls and gauges are mounted or attached to the panel  104  on the cart  10  in a manner that provides for easy access and visibility, with such equipment, controls and gauges being in fluid communication for delivery and return of the hydraulic fluid under desired pressure and flow rate. A function control mechanism  13  controls the operational mode of the apparatus, such that the apparatus is either operations and delivering hydraulic fluid at high pressure and suitable flow to and returned from the helicopter  200 , or in nonoperational or idle mode wherein hydraulic fluid is recirculated within the apparatus and not delivered to the helicopter  200 . The function control mechanism  13  also acts as an emergency cutoff if such is needed. The function control mechanism  13  may comprise a ball valve operated by a lever. A flow control or regulator mechanism  14  is provided such that the flow rate is adjustable to a desired gpm. A flow meter  18  provides a visual indication of the flow rate to the operator. A pressure regulator mechanism  15  is provided to adjust the delivery pressure of the hydraulic fluid, with a pressure gauge  16  to provide a visual indication of the pressure to the operator. A temperature gauge  17  is also provided to provide a visual indication of the fluid temperature to the operator. 
         [0014]    A set of hose connector fittings  21  are provided for connecting a delivery hydraulic hose to provide hydraulic fluid under proper pressure and flow to the helicopter  200  and a return hydraulic hose to return the hydraulic fluid from the helicopter  200  to the apparatus. Most preferably quick connect fittings are utilized, and the connector fittings  21  on the apparatus are of the type that automatically close when the connection is broken, i.e., a hose is disconnected, in order to prevent accidental loss of hydraulic fluid. Preferably, interchangeable fittings having different pitches are provided so as to be compatible to the fittings of helicopters  20  of different types and origin. 
         [0015]    A high flow rate filter  19  is provided to filter hydraulic fluid returned from helicopter  200  prior to its return into the hydraulic pump  12  to remove any trach or debris. A 125 micro stainless steel filter is suitable. Because the hydraulic pump apparatus utilizes hydraulic fluid from the helicopter  200  itself, there is no need to provide a storage or auxiliary fluid tank. 
         [0016]    The hydraulic pump apparatus is utilized to provide hydraulic power to a helicopter&#39;s, or other type of equipment&#39;s, hydraulic systems by wheeling the apparatus to a location adjacent the helicopter  200 . The hoses are then connected to the helicopter&#39;s hydraulic system to be tested and the flow control mechanism  14  is adjusted to produce the desired flow rate. The power and hydraulic switches of the helicopter  200  are then initiated and the fuel-powered engine  11  is started to power the hydraulic pump  12  to deliver in a recirculating manner hydraulic fluid to the helicopter systems. The proper testing procedures relative to the helicopter  200  are then followed. Once the test is completed, the hydraulic pump apparatus is turned off and disconnected. 
         [0017]    It is understood that equivalents and substitutions for certain elements set forth above may be obvious to those of skill in the art, and therefore the true scope and definition of the invention is to be as set forth in the following claims.