Modular externally accessible batteries for an aircraft

1. An aircraft comprising:

an airframe;

a battery pod comprising a battery unit and a physical connector system wherein the physical connector system comprises a lug extending from the battery pod; and

an engagement system attached to the airframe, the engagement system configured to removably engage the physical connector system to connect the battery pod to the airframe, the engagement system comprising a latch mechanism configured to engage the lug.

2. The aircraft of claim 1 , wherein the latch mechanism comprises:

a hook connected to the airframe via a mechanism that allows remote actuation of the hook to release the lug.

3. The aircraft of claim 2 , wherein the aircraft further comprises:

a second battery pod having a second physical connector system comprising a second lug extending from the second battery pod; and

a second engagement system attached to the airframe, the second engagement system configured to removably engage the second physical connector system to connect the second battery pod to the airframe, the second engagement system comprising a second hook removably secured to the second lug, the second hook connected to the airframe via a second mechanism that allows remote actuation of the second hook to release the second lug.

4. The aircraft of claim 3 , wherein the battery pod, engagement system, second battery pod, and second engagement system all are secured to a single wing of the aircraft.

5. The aircraft of claim 1 , wherein the

battery unit is selected from at least one of a lithium ion battery, a lithium ion polymer battery, a nickel metal hydride battery, and a zinc-bromide flow battery.

6. The aircraft of claim 1 , wherein the engagement system further comprises:

a pylori attached to the airframe of the aircraft.

7. The aircraft of claim 1 , wherein the engagement system further comprises:

a sway brace removably connected between the battery pod and the airframe.

8. The aircraft of claim 1 , wherein the airframe further comprises a wing, wherein the battery pod and the engagement system are integrated with the wing and form part of an operational shape of the wing.

9. The aircraft of claim 1 , wherein the battery pod is integrated with an electric propulsion system within the airframe.

10. The aircraft of claim 9 , wherein the electric propulsion system further comprises an electric propulsor system comprising a number of electric propulsors.

11. The aircraft of claim 1 , wherein the engagement system is configured to jettison the battery pod during flight.

12. The aircraft of claim 1 , wherein the airframe comprises a fuselage, a tail, and a wing.

13. The aircraft of claim 12 , wherein the battery pod is removably connected to at least one of the fuselage, the tail, and the wing by the engagement system.

14. The aircraft of claim 12 , wherein the battery pod has a shape conforming to an outer mold line of the fuselage.

15. The aircraft of claim 12 , wherein the aircraft is selected from one of a fixed wing aircraft and a rotary wing aircraft.

16. The aircraft of claim 12 , wherein the aircraft further comprises a second wing, and wherein the engagement system further comprises:

a plurality of pylons attached to at least one of the fuselage, the first wing, and the second wing; and

a plurality of latch mechanisms attached to corresponding ones of the plurality of pylons, wherein the plurality of latch mechanisms is capable of engaging a corresponding plurality of physical connector systems for a plurality of battery pods.

17. A method comprising:

attaching a battery pod to an airframe, wherein the battery pod comprises a battery unit and a physical connector system wherein the physical connector system comprises a lug extending from the battery pod; and

attaching an engagement system to the physical connector system, the engagement system configured to removably engage the physical connector system to connect the battery pod to the airframe, the engagement system comprising a hook removably secured to the lug, wherein attaching includes engaging the hook to the lug, and wherein attaching further includes attaching the hook to a mechanism that allows remote actuation of the hook to release the lug.

18. The method of claim 17 further comprising:

releasing the hook from the lug.

19. The method of claim 18 , wherein releasing is performed during flight.

20. The method of claim 17 further comprising:

electrically connecting the battery pod to a system, in the airframe, that uses electrical power.