Aircraft emergency and backup secondary power apparatus

1. In combination,

an aircraft having an outer surface,

a rotatively combined electrical motor/generator and hydraulic motor/pump configured to provide either hydraulic power from electrical power, or electrical power from hydraulic power, installed on said aircraft, and having one mode of operation wherein electrical power provided to the electrical motor/generator generates hydraulic power for aircraft hydraulic devices, and a second mode of operation wherein hydraulic power provided to the hydraulic motor/pump generates electrical power for aircraft electrical devices, and wherein said electrical motor/generator and hydraulic motor/pump are directly rotatively connected together free of any intervening disengageable clutch structure, and

a ram air turbine housed inside an air flow duct within said aircraft and provided with inlet and exit openings to direct outside air to the turbine for driving said rotatively combined electrical motor/generator and hydraulic motor/pump to which the turbine is operatively connected,

said air flow duct including an exit flap, wherein the exit flap has at least a first position that is flush with the aircraft outer surface and a second position where the exit flap is deployed away from the aircraft outer surface to induce airflow through the duct,

said combined electrical motor/generator and hydraulic motor/pump housed inside said air flow duct.

2. The combination of claim 1 , wherein said flap extends into sideward proximity to the turbine in all flap positions.

3. The combination of claim 2 , including a variable inlet air flap controlled in concert with said exit flap to control air flow and power to the ram air turbine.

4. An aircraft having a ram air turbine housed inside an airflow duct within said aircraft, the duct provided with air inlet and exit openings to direct outside air to the turbine for driving one of the following installed on the aircraft and within said duct:

a) an electric motor generator,

b) an hydraulic pump,

the electric motor generator and hydraulic pump configured to provide one mode of operation wherein electrical power provided to the electric motor generator generates hydraulic power for aircraft hydraulic devices, and a second mode of operation wherein hydraulic power provided to the hydraulic pump generates electrical power for aircraft electrical devices,

there being a variable exit air flap at and proximate said exit opening to control the power of the ram air turbine, there being a variable inlet air flap controlled in conjunction with said exit flap to control air flow to and power of the ram air turbine, said inlet and outlet flaps each having at least a first position that is flush with an aircraft outer surface and a second position where the flaps are deployed away from the aircraft outer surface to induce airflow through the duct.

5. The combination of claim 4 wherein said ram air turbine, electric motor generator and hydraulic pump are rotatively connected and configured such that hydraulic power supplied from the aircraft to the hydraulic pump is usable to drive the electric motor generator to supply electric power, and alternatively electrical power supplied from the aircraft is usable to drive the hydraulic pump to supply hydraulic power to the aircraft, independent of the ram air turbine.

6. In combination with an aircraft having a body with an outer surface,

a ram air turbine housed inside an airflow duct within said aircraft and provided with inlet and exit openings to direct outside air to the turbine for driving an electrical generator and hydraulic pump in combination, wherein the turbine is operatively connected to the electrical generator and the hydraulic pump, and each of the turbine the electrical generator and the hydraulic pump are within the duct, the electrical generator and hydraulic pump are configured to provide one mode of operation wherein electric power provided to the electrical generator generates hydraulic power for aircraft hydraulic devices, and a second mode of operation wherein hydraulic power provided to the hydraulic pump generates electrical power for aircraft electrical devices,

there being a variably movable exit flap to control the power of the ram air turbine, said exit flap having a trailing edge that can be moved into an airstream adjacent to the aircraft body, said exit flap having at least a first position that is flush with the aircraft outer surface and a second position where the exit flap is deployed away from the aircraft outer surface to induce airflow.

7. The combination of claim 6 wherein said flap defines one side of the duct along the entire length of the flap.