Sealed float with batteries

Patent metadata

Field	Value
Publication number	US-10059436-B1
Application number	US-201715783898-A
Country	US
Kind code	B1
Filing date	Oct 13, 2017
Priority date	Jul 13, 2017
Publication date	Aug 28, 2018
Grant date	Aug 28, 2018

Abstract

A float has a front-to-back length, a width, and a height where the front-to-back length of the float is strictly greater than the height of the float which in turn is strictly greater than the width of the float. At least a bottom portion of the float is watertight. The float includes an access panel to access the inside of the float. A battery is inside the float and is accessible via the access panel.

First claim

What is claimed is:

1. A system, comprising:
a float which has a front-to-back length, a width, and a height, wherein:
the float is included in an aircraft;
the front-to-back length of the float is strictly greater than the height of the float which in turn is strictly greater than the width of the float;
at least a bottom portion of the float is watertight;
the float includes an access panel to access the inside of the float;
the float includes a removable and interchangeable float bottom adapted for at least one of: water and land, the land float bottom including a wheel; and

a battery, wherein the battery is inside the float and is accessible via the access panel.

2. The system recited in claim 1 , wherein the aircraft includes a plurality of rotors which are attached to the aircraft at a fixed roll angle and a fixed pitch angle.

3. The system recited in claim 1 , wherein:
the aircraft includes a plurality of rotors which are attached to the aircraft at a fixed roll angle and a fixed pitch angle; and
the plurality of rotors include:
a right inner front rotor which is configured to rotate in a first direction;
a right outer front rotor which is configured to rotate in the first direction;
a right inner middle rotor which is configured to rotate in a second direction;
a right outer back rotor which is configured to rotate in the second direction;
a right inner back rotor which is configured to rotate in the first direction;
a left inner back rotor which is configured to rotate in the second direction;
a left outer back rotor which is configured to rotate in the first direction;
a left inner middle rotor which is configured to rotate in the first direction;
a left outer front rotor which is configured to rotate in the second direction; and
a left inner front rotor which is configured to rotate in the second direction.

4. The system recited in claim 1 , wherein:
the aircraft includes a plurality of rotors which are attached to the aircraft at a fixed roll angle and a fixed pitch angle;
the plurality of rotors include:
a right outer front rotor which is attached to the aircraft at a negative roll angle and a negative pitch angle;
a right inner middle rotor which is attached to the aircraft at a negative roll angle and a negative pitch angle;
a right outer back rotor which is attached to the aircraft at a negative roll angle and a negative pitch angle;
a right inner back rotor which is attached to the aircraft at a negative roll angle and a negative pitch angle;
a left inner back rotor which is attached to the aircraft at a positive roll angle and a negative pitch angle;
a left outer back rotor which is attached to the aircraft at a positive roll angle and a negative pitch angle;
a left inner middle rotor which is attached to the aircraft at a positive roll angle and a negative pitch angle; and
a left outer front rotor which is attached to the aircraft at a positive roll angle and a negative pitch angle; and

the plurality of rotors are attached to the aircraft at roll angles and pitch angles with magnitudes in the range of 0 degrees and 10 degrees.

5. The system recited in claim 1 further including at least one of a gore vent and a drain.

6. The system recited in claim 1 further including a heat sink, wherein a view of the heat sink is at least partially obstructed by a blocking object when viewed from above.

7. The system recited in claim 1 further including a heat sink, wherein a view of the heat sink is at least partially obstructed by a blocking object when viewed from above, wherein the blocking object includes one or more of the following: a boom or a rotor.

8. The system recited in claim 1 , wherein the float further includes a sidewall with sandwich-structure composite.

9. The system recited in claim 1 , wherein:
the aircraft further includes a parachute and a fuselage, where the parachute is attached to an anchor point in a back half of the fuselage; and
the float includes energy absorbing material inside the float at a front portion.

10. The system recited in claim 1 further including a crush structure inside the float which supports the battery.

Assignees

• Kitty Hawk Corp

Inventors

• Robertson Cameron
• Reichert Todd

Classifications

• B64D27/24

  using steam or spring force (jet aircraft B64D27/16) · CPC title

• B64C2025/325

  specially adapted for helicopters · CPC title

• B64C27/08 Primary

  with two or more rotors · CPC title

• B64C25/36

  Arrangements or adaptations of wheels, tyres or axles in general · CPC title

• B64C31/028

  Hang-glider-type aircraft; Microlight-type aircraft · CPC title