Sealed float with batteries

• US 10,059,436 B1
• Filed: 10/13/2017
• Issued: 08/28/2018
• Est. Priority Date: 07/13/2017
• Status: Active Grant

• Current Assignee: Kitty Hawk Corporation
• Original Assignee: Kitty Hawk Corporation
• Inventors: Robertson, Cameron, Reichert, Todd
• Primary Examiner(s): Ellis, Christopher P
• Application Number:
  US15/783,898
• Time in Patent Office: 319 Days
• CPC Class Codes: B64C 2025/325 specially adapted for helicopters
• CPC Class Codes: B64C 25/36 Arrangements or adaptations of wheels, tyres or axles in general
• CPC Class Codes: B64C 25/54 Floats
• CPC Class Codes: B64C 27/001 Vibration damping devices
• CPC Class Codes: B64C 27/08 with two or more rotors
• CPC Class Codes: B64C 31/028 Hang-glider-type aircraft; Microlight-type aircraft
• CPC Class Codes: B64C 35/00 Flying-boats; Seaplanes
• CPC Class Codes: B64C 35/008 Amphibious sea planes
• CPC Class Codes: B64D 17/80 in association with aircraft, e.g. for braking thereof
• CPC Class Codes: B64D 27/24 using steam or spring force jet aircraft B64D27/16
• CPC Class Codes: Y02T 50/40 Weight reduction
• CPC Class Codes: Y02T 50/50 On board measures aiming to increase energy efficiency
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

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.

Claims

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.