Battery and unmanned aerial vehicle with the battery

• US 9,592,744 B2
• Filed: 04/25/2014
• Issued: 03/14/2017
• Est. Priority Date: 12/06/2013
• Status: Active Grant

• Current Assignee: SZ DJI Technology Co., Ltd. (d/b/a DJI) (iFlight Technology Company Limited)
• Original Assignee: SZ DJI Technology Co., Ltd. (d/b/a DJI) (iFlight Technology Company Limited)
• Inventors: Zhao, Tao
• Primary Examiner(s): Rodas, Richard Isla
• Assistant Examiner(s): Henze-Gongola, David V
• Application Number:
  US14/262,478
• Publication Number:
  US 20150158392A1
• Time in Patent Office: 1,054 Days
• Field of Search: 320/109, 320/136
• US Class Current: 1/1
• CPC Class Codes: B60L 2200/10 Air crafts
• CPC Class Codes: B60L 2260/32 Auto pilot mode
• CPC Class Codes: B60L 53/80 Exchanging energy storage elements, e.g. removable batteries
• CPC Class Codes: B60L 58/12 responding to state of charge [SoC]
• CPC Class Codes: B60L 58/15 Preventing overcharging
• CPC Class Codes: B60L 58/22 Balancing the charge of battery modules
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64U 2201/20 Remote controls
• CPC Class Codes: B64U 30/20 Rotors; Rotor supports
• CPC Class Codes: B64U 50/19 using electrically powered motors
• CPC Class Codes: H02J 7/00 Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
• CPC Class Codes: Y02T 10/70 Energy storage systems for electromobility, e.g. batteries
• CPC Class Codes: Y02T 10/7072 Electromobility specific charging systems or methods for batteries, ultracapacitors, supercapacitors or double-layer capacitors
• CPC Class Codes: Y02T 90/16 Information or communication technologies improving the operation of electric vehicles

Abstract

The disclosure provides a battery which can include a power supply and power supply circuit, the power supply circuit connected to the power supply. The power supply can discharge through the power supply circuit. An electronic switch can control the power-on or off of the power supply, thereby avoiding the generation of sparks during the power on process and allowing for the normal use of the battery and the safety of the aircraft. The disclosure also provides an aircraft having the battery.

Claims

1. A power supply control assembly, comprising:

a power supply adapted to power an aerial vehicle;

an input device configured to receive at least two types of input from a user of the aerial vehicle; and

a power supply circuit connected to the power supply, wherein the power supply is configured to discharge through the power supply circuit to power the aerial vehicle in response to receipt of a first type of input by the input device, wherein the power supply circuit comprises;

(a) an electronic switch in electrical communication with the power supply for controlling discharge of power from the power supply to the aerial vehicle, wherein the input device is in electrical communication with the electronic switch for controlling a switch-on or a switch-off state of the electronic switch,

(b) a power measurement device in electrical communication with the power supply, and

(c) an indication device in electrical communication with the power measurement device, wherein the indication device is configured to display a level of charge of the power supply in response to receipt of a second type of input by the input device, (1) without requiring the power supply to be connected to the aerial vehicle, and (2) without requiring the power supply to provide power to a propulsion unit of the aerial vehicle to set said propulsion unit in motion.

5. The power supply control assembly of claim 1, wherein the input device is selected from the group consisting of a key switch, mechanical switch, potentiometer, a pressure sensor, and a touch sensor.

6. The power supply control assembly of claim 1, wherein the electronic switch includes one of a power MOSFET, a solid state relay, a power transistor, or an insulated gate bipolar transistor (IGBT).

8. The power supply control assembly of claim 1, wherein the aerial vehicle is an unmanned aerial vehicle (UAV).

9. The power supply control assembly of claim 8, wherein the propulsion unit includes one or more rotors with rotatable blades, and wherein the power supply causes rotation of the one or more rotors including the rotatable blades, thereby generating a lift for the UAV.

10. The power supply control assembly of claim 8, wherein the UAV is capable of flying for at least about 25 minutes without recharging.

11. The power supply control assembly of claim 1, wherein the indication device is configured to be powered on only in response to the receipt of the second type of input by the input device.

12. The power supply control assembly of claim 1, wherein the indication device is configured to display the level of charge of the power supply in response to the receipt of the second type of input by the input device, when the power supply is detached from the aerial vehicle.

13. The power supply control assembly of claim 1, wherein the indication device is configured to display the level of charge of the power supply in response to the receipt of the second type of input by the input device, when (a) the power supply is not providing power to the propulsion unit of the aerial vehicle, and (b) the power supply is detached from the aerial vehicle.

14. The power supply control assembly of claim 1, wherein the first type of input is for powering on the aerial vehicle, and the second type of input is for powering on the indication device.

2. The power supply control assembly of claim wherein the power measurement device further comprises:

a current sampling device configured to detect a current signal during charging or discharging of the power supply, and wherein the power measurement device is configured to calculate the level of charge of the power supply by sampling and integrating the current signal over a period of time at a predetermined frequency.

3. The power supply control assembly of claim wherein the current sampling device is configured to collect current during the discharging of the power supply.

4. The power supply control assembly of claim further comprising:

an interface configured to provide access to the level of charge of the power supply and voltage of the power supply.

7. The power supply control assembly of claim wherein the power supply and power supply circuit weigh less than about 400 grams.

15. A power supply control assembly, comprising:

a power supply adapted to power an aerial vehicle;

a microcontroller unit (MCU) in electrical communication with the power supply and capable of at least one of;

(i) controlling discharge of the power supply, (ii) protecting against a short circuit of the power supply, (iii) protecting against over-charge of the power supply, (iv) protecting against over-discharge of the power supply, (v) balancing a level of charge amongst one or more batteries comprising the power supply, (vi) preventing charging of the power supply at temperatures outside of a predefined temperature range, or (vii) communicating information with an external device;

an input device configured to receive at least two types of input from a user of the aerial vehicle; and

a power supply circuit in electrical communication with the power supply, wherein the power supply is configured to discharge through the power supply circuit to power the aerial vehicle in response to receipt of a first type of input by the input device, wherein the power supply circuit comprises;

(a) an electronic switch in electrical communication with the power supply for controlling discharge of power from the power supply to the aerial vehicle, wherein the input device is in electrical communication with the electronic switch for controlling a switch-on or a switch-off state of the electronic switch, and

(b) an indication device configured to display the level of charge of the power supply in response to receipt of a second type of input by the input device, (1) without requiring the power supply to be connected to the aerial vehicle, and (2) without requiring the power supply to provide power to a propulsion unit of the aerial vehicle to set said propulsion unit in motion.

16. The power supply control assembly of claim 15, wherein the microcontroller unit is capable of communicating with the external device by providing state information associated with the power supply to the external device.

17. The power supply control assembly of claim 15, wherein the microcontroller unit is capable of communicating with the external device by receiving information from the external device.

18. The power supply control assembly of claim 15, wherein the electronic switch includes one of a power MOSFET, a solid state relay, a power transistor, or an insulated gate bipolar transistor (IGBT).

19. The power supply control assembly of claim 15, further comprising:

a power supply housing, wherein the power supply housing comprises a bottom member having an opening at a first end and a cover member, the cover member sealing the opening of the bottom member, wherein the power supply is disposed in the bottom member, and wherein the electronic switch, the input device, a power measurement device, and the indication device are all disposed on a circuit board.

20. The power supply control assembly of claim 15, wherein the aerial vehicle is an unmanned aerial vehicle (UAV).

21. The power supply control assembly of claim 20, wherein the propulsion unit includes one or more rotors with rotatable blades, and wherein the power supply causes rotation of the one or more rotors including the rotatable blades, thereby generating a lift for the UAV.

22. The power supply control assembly of claim 15, wherein the indication device is configured to be powered on only in response to the receipt of the second type of input by the input device.

23. The power supply control assembly of claim 15, wherein the microcontroller is further capable of detecting a current signal during charging or discharging of the power supply, and calculating the level of charge of the power supply by sampling and integrating the current signal over a period of time at a predetermined frequency.

24. A power supply control assembly, comprising:

a power supply adapted to power an aerial vehicle; and

an input device configured to;

(1) receive at least two types of input from a user of the aerial vehicle, (2) generate a first input signal based on a first type of input for powering on an indication device, or a second input signal based on a second type of input for powering on or off the aerial vehicle, and (3) enable switching between a plurality of operational modes comprising of a first operational mode associated with the first input signal and a second operational mode associated with the second input signal, said operational modes including at least;

(i) activating display of a level of charge of the power supply on the indication device when the power supply control assembly is in the first operational mode, and (ii) connecting or disconnecting the power supply from the aerial vehicle by turning on or off an electronic switch in electrical communication with the power supply when the power supply control assembly is in the second operational mode,

wherein the indication device is configured to display the level of charge of the power supply in response to receipt of the first type of input by the input device, (1) without requiring the power supply to be connected to the aerial vehicle, and (2) without requiring the power supply to provide power to a propulsion unit of the aerial vehicle to set said propulsion unit in motion.

25. The power supply control assembly of claim 24, wherein the aerial vehicle is an unmanned aerial vehicle (UAV).

26. The power supply control assembly of claim 24, wherein the plurality of operational modes further include communicating with an external device.

27. The power supply control assembly of claim 26, wherein communicating with the external device comprises providing state information associated with the power supply to the external device.

28. The power supply control assembly of claim 24, wherein the input device is selected from the group consisting of a key switch, mechanical switch, potentiometer, a pressure sensor, and a touch sensor.

29. A method for managing a power supply control assembly, the method comprising:

receiving, by an input device, at least two types of input from a user of an aerial vehicle;

generating a first input signal based on a first type of input for powering on an indication device, or a second input signal based on a second type of input for powering on or off the aerial vehicle; and

selecting an operational mode from a plurality of operational modes comprising of a first operational mode associated with the first input signal and a second operational mode associated with the second input signal, said operational modes including at least;

(i) activating display of a level of charge of a power supply on the indication device when the first operational mode is selected, and (ii) connecting or disconnecting the power supply from the aerial vehicle by turning on or off an electronic switch in electrical communication with the power supply when the second operational mode is selected,

wherein the indication device is configured to display the level of charge of the power supply in response to receipt of the first type of input by the input device, (1) without requiring the power supply to be connected to the aerial vehicle, and (2) without requiring the power supply to provide power to a propulsion unit of the aerial vehicle to set said propulsion unit in motion.

30. The method of claim 29, wherein the selecting of the first operational mode or the second operational mode is based on a length of time of each of the first and second types of input received by the input device.

31. The method of claim 29, wherein the indication device is configured to display the level of charge of the power supply when the power supply is detached from the aerial vehicle.

32. The method of claim 29, wherein the indication device is configured to display the level of charge of the power supply, when (a) the power supply is not providing power to the propulsion unit of the aerial vehicle, and (b) the power supply is detached from the aerial vehicle.

33. The method of claim 29, wherein the first type of input is provided by the user pressing the input device at a first instance, and wherein the second type of input is provided by the user pressing the input device at a second instance within a threshold time period before or after the first instance.

34. The method of claim 30, wherein the first type of input is provided by the user pressing the input device for at least a first time duration, wherein the second type of input is provided by the user pressing the input device for at least a second time duration, and wherein the first time duration is different from the second time duration.

35. The method of claim 34, wherein the second time duration is longer than the first time duration.