US-12623791-B2 - Ejecting energy module from an aircraft

Abstract

An aircraft system that includes an aircraft airframe, a drive unit, a mechanical load, an energy module and an ejection system. The aircraft airframe has an internal compartment. The drive unit is mounted with the aircraft airframe. The mechanical load includes a mechanical load rotor. The drive unit is coupled to and configured to drive rotation of the mechanical load rotor. The energy module is disposed within the internal compartment. The energy module includes an energy source configured to power or fuel operation of the drive unit. The ejection system is configured to eject the energy module out of the internal compartment and away from the aircraft airframe

Inventors

• Adam Rosenkrantz

Assignees

• RAYTHEON TECHNOLOGIES CORPORATION

Dates

Publication Date

20260512

Application Date

20230504

Claims (18)

1. 1 . An aircraft system, comprising: an aircraft airframe with an internal compartment; a drive unit mounted with the aircraft airframe; a mechanical load comprising a mechanical load rotor, the drive unit coupled to and configured to drive rotation of the mechanical load rotor; an energy module disposed within the internal compartment, the energy module comprising an energy source configured to power or fuel operation of the drive unit, and the energy source fluidly coupled to the drive unit by a fluid line extending between the drive unit and the energy source; and an ejection system configured to eject the energy module out of the internal compartment and away from the aircraft airframe, and the ejection system configured to shear the fluid line prior to or during ejection of the energy module out of the internal compartment; wherein the energy source is directly coupled to the drive unit.
2. 2 . The aircraft system of claim 1 , wherein the energy source comprises a fuel reservoir configured to contain a fluid fuel; and the fluid line comprises a fuel line.
3. 3 . The aircraft system of claim 1 , wherein the energy source comprises a fluid power source configured to contain a heat exchange working fluid; and the fluid line is configured to transfer the heat exchange working fluid between the energy source and the drive unit.
4. 4 . The aircraft system of claim 1 , wherein the energy source is electrically coupled to the drive unit by an electric line; and the ejection system is configured to sever the electric line prior to or during ejection of the energy module out of the internal compartment.
5. 5 . The aircraft system of claim 1 , wherein the aircraft airframe includes a wall, a cover and an opening through the wall to the internal compartment, and the cover is configured to close the opening; and the ejection system is configured to move the cover and open the opening to facilitate ejection of the energy module out of the internal compartment through the opening.
6. 6 . The aircraft system of claim 1 , wherein the aircraft airframe includes a wall adjacent the internal compartment; and the ejection system is configured to form an opening through the wall to facilitate ejection of the energy module out of the internal compartment through the opening.
7. 7 . The aircraft system of claim 1 , wherein the ejection system comprises a propulsion device configured to propel the energy module at least one of out of the internal compartment; or away from the aircraft airframe.
8. 8 . The aircraft system of claim 1 , further comprising: a descent control device arranged with the energy module; the descent control device configured to control descent of the energy module following ejection away from the aircraft airframe.
9. 9 . The aircraft system of claim 1 , wherein the energy module further comprises a housing configured to contain and seal off the energy source from an external environment before, during or after ejection of the energy module out of the internal compartment and away from the aircraft airframe.
10. 10 . The aircraft system of claim 1 , wherein the energy module further comprises a tracking device which is activated during or after ejection of the energy module out of the internal compartment and away from the aircraft airframe.
11. 11 . The aircraft system of claim 1 , wherein the aircraft airframe comprises a fuselage; and the internal compartment is disposed in the fuselage.
12. 12 . The aircraft system of claim 1 , wherein the aircraft airframe comprises a nacelle for an aircraft propulsion system; and the internal compartment is disposed in the nacelle.
13. 13 . The aircraft system of claim 1 , wherein the drive unit comprises an internal combustion engine; and the internal combustion engine comprises a rotating structure coupled to the mechanical load rotor.
14. 14 . The aircraft system of claim 1 , wherein the drive unit comprises a fluid turbine coupled to the mechanical load rotor.
15. 15 . The aircraft system of claim 1 , wherein the drive unit comprises an electric motor.
16. 16 . The aircraft system of claim 1 , wherein the mechanical load rotor comprises a thrust rotor; and the mechanical load is configured to generate aircraft thrust with the thrust rotor.
17. 17 . An aircraft system, comprising: an aircraft airframe; a drive unit mounted with the aircraft airframe; a mechanical load comprising a mechanical load rotor, the drive unit coupled to and configured to drive rotation of the mechanical load rotor; a power module arranged with the aircraft airframe, the power module comprising a power source configured to power operation of the drive unit, and the power module coupled to the drive unit by a line projecting out of the power module and to the drive unit; and an ejection system configured to eject the power module away from the aircraft airframe, the ejection system configured to destructively sever the line prior to or during ejection of the power module away from the aircraft airframe.
18. 18 . An aircraft system, comprising: an aircraft airframe; a drive unit mounted with the aircraft airframe; a mechanical load comprising a mechanical load rotor, the drive unit coupled to and configured to drive rotation of the mechanical load rotor; an energy module arranged with the aircraft airframe, the energy module including an energy source and a housing, the energy source configured to power or fuel operation of the drive unit, the housing configured to contain and seal off the energy source from an external environment during or after ejection of the energy module away from the aircraft airframe, the energy source fluidly coupled to the drive unit by a fluid line projecting out of the housing to the drive unit; and an ejection system configured to destructively sever the fluid line and eject the energy module away from the aircraft airframe; wherein the energy module further comprises a tracking device which is activated during or after ejection of the energy module away from the aircraft airframe.

Description

BACKGROUND OF THE DISCLOSURE 1. Technical Field This disclosure relates generally to an aircraft and, more particularly, to preparing an energy source for an emergency. 2. Background Information Various methods and systems are known in the art for preparing aircraft systems and components for an emergency. While these known preparation systems and methods have various benefits, there is still room in the art for improvement. SUMMARY OF THE DISCLOSURE According to an aspect of the present disclosure, an aircraft system is provided that includes an aircraft airframe, a drive unit, a mechanical load, an energy module and an ejection system. The aircraft airframe has an internal compartment. The drive unit is mounted with the aircraft airframe. The mechanical load includes a mechanical load rotor. The drive unit is coupled to and configured to drive rotation of the mechanical load rotor. The energy module is disposed within the internal compartment. The energy module includes an energy source configured to power or fuel operation of the drive unit. The ejection system is configured to eject the energy module out of the internal compartment and away from the aircraft airframe. According to another aspect of the present disclosure, another aircraft system is provided that includes an aircraft airframe, a drive unit, a mechanical load, a power module and an ejection system. The drive unit is mounted with the aircraft airframe. The mechanical load includes a mechanical load rotor. The drive unit is coupled to and configured to drive rotation of the mechanical load rotor. The power module is arranged with the aircraft airframe. The power module includes a power source configured to power operation of the drive unit. The ejection system is configured to eject the power module away from the aircraft airframe. According to still another aspect of the present disclosure, another aircraft system is provided that includes an aircraft airframe, a drive unit, a mechanical load, an energy module and an ejection system. The drive unit is mounted with the aircraft airframe. The mechanical load includes a mechanical load rotor. The drive unit is coupled to and configured to drive rotation of the mechanical load rotor. The energy module is arranged with the aircraft airframe. The energy module includes an energy source and a housing. The energy source is configured to power or fuel operation of the drive unit. The housing is configured to contain and seal off the energy source from an external environment during or after ejection of the energy module away from the aircraft airframe. The ejection system is configured to eject the energy module away from the aircraft airframe. The power module may be coupled to the drive unit by a line. The ejection system may be configured to sever the line prior to or during ejection of the power module away from the aircraft airframe. The energy source may be fluidly coupled to the drive unit by a fluid line. The ejection system may be configured to sever the fluid line prior to or during ejection of the energy module out of the internal compartment. The energy source may include a fuel reservoir configured to contain a fluid fuel. The fluid line may be a fuel line. The fluid line may be configured to transfer a heat exchange working fluid between the energy source and the drive unit. The energy source may be electrically coupled to the drive unit by an electric line. The ejection system may be configured to sever the electric line prior to or during ejection of the energy module out of the internal compartment. The aircraft airframe may include a wall, a cover and an opening through the wall to the internal compartment. The cover may be configured to close the opening. The ejection system may be configured to move the cover and open the opening to facilitate ejection of the energy module out of the internal compartment through the opening. The aircraft airframe may include a wall adjacent the internal compartment. The ejection system may be configured to form an opening through the wall to facilitate ejection of the energy module out of the internal compartment through the opening. The ejection system may include a propulsion device configured to propel the energy module: out of the internal compartment; and/or away from the aircraft airframe. The aircraft system may also include a descent control device arranged with the energy module. The descent control device may be configured to control descent of the energy module following ejection away from the aircraft airframe. The energy module may also include a housing configured to contain and seal off the energy source from an external environment before, during or after ejection of the energy module out of the internal compartment and away from the aircraft airframe. The energy module may also include a tracking device which is activated during or after ejection of the energy module out of the internal compartment and away from the aircraft air