Battery pack for failure safety

1. An electric aircraft with a battery pack for failure safety, the electric aircraft comprising:

a fuselage defining a longitudinal axis of the electric aircraft;

at least a flight control element configured to affect flight of the electric aircraft;

a battery pack, wherein the battery pack comprises:

a pack casing, wherein the pack casing is configured with an inner lining and is mounted to the electric aircraft;

a battery module secured to the pack casing by a battery module connection, wherein the battery module is located along a vertical axis perpendicular to the longitudinal axis of the electric aircraft, and wherein the battery module is electrically connected to the at least a flight control element; and

a crush zone located along the vertical axis perpendicular to the longitudinal axis of the electric aircraft and in a direction beneath the battery module, wherein the crush zone comprises an energy absorbing material configured to compress as a function of the battery module and a crash force, and wherein the battery module connection releases the battery module into the crush zone guided by the inner lining.

2. The electric aircraft of claim 1 , wherein the battery module is secured to an upper wall of the pack casing.

3. The electric aircraft of claim 2 , wherein the upper wall of the pack casing includes a recess located along a central longitudinal axis.

4. The electric aircraft of claim 1 , wherein the pack casing includes an external shell.

5. The electric aircraft of claim 1 , wherein the pack casing includes at least a side wall configured with a high compression strength element.

6. The electric aircraft of claim 5 , wherein the side wall is configured to secure the inner lining that guides the battery module.

7. The electric aircraft of claim 6 , wherein the inner lining guides the battery module in a downward vertical direction towards the energy absorbing material.

8. The electric aircraft of claim 1 , wherein the battery module connection is configured to release the battery module as a function of the crash force exceeding a breakaway force.

9. The electric aircraft of claim 8 , wherein the breakaway force is configured as a function of a predetermined amount of force.

10. The electric aircraft of claim 8 , wherein the breakaway force is configured as a function of a predetermined direction of force.

11. The electric aircraft of claim 8 , wherein the battery module further comprises a frangible buswork.

12. The electric aircraft of claim 1 , wherein the energy absorbing material includes polyether ether ketone.

13. The electric aircraft of claim 1 , wherein the energy absorbing material includes polymer foam.

14. The electric aircraft of claim 1 , wherein the energy absorbing material is configured to absorb a predetermined amount of force.

15. The electric aircraft of claim 1 , wherein the energy absorbing material is configured to absorb a predetermined direction of force.

16. The electric aircraft of claim 1 , wherein the crush zone is configured to reduce an impact force.

17. The electric aircraft of claim 1 , wherein the crush zone is configured to prevent a thermal runaway of the battery module.

18. The electric aircraft of claim 1 , wherein the battery pack further comprises a secondary crush zone located between an upper wall of the pack casing and the battery module.

19. The electric aircraft of claim 18 , wherein the secondary crush zone increases in thickness as the battery module compresses the energy absorbing material.

20. The electric aircraft of claim 18 , wherein the secondary crush zone protects the battery module from debris.