A novel quadcopter power board system
The quadcopter power board system, which integrates battery detection and power supply functions, solves the problem of limited internal space in small drones, achieves a highly integrated and loosely coupled design, and improves the safety and ease of teaching of drones.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- JIACHUANG FEIHANG (SUZHOU) INTELLIGENT TECH CO LTD
- Filing Date
- 2025-08-29
- Publication Date
- 2026-07-31
AI Technical Summary
Existing small drones have limited internal space and low component integration, resulting in complex and inconvenient wiring, which affects system efficiency and safety.
A novel quadcopter power board system is designed, integrating battery detection, ESC power supply, and flight control power supply functions into a single power board. The system adopts a modular design, including a battery interface, fuses, capacitors, ESC power supply circuit, and flight control power supply circuit, with a reserved auxiliary power interface, achieving high integration and low coupling design.
It improves the utilization of internal space in drones, simplifies wiring, increases system safety and reliability, reduces the learning difficulty, and is suitable for drone teaching and commercial applications.
Smart Images
Figure CN224582933U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of power board technology, specifically to a novel quadcopter power board system. Background Technology
[0002] In the field of small unmanned aerial vehicles (UAVs), the design of aircraft often requires balancing various physical constraints and performance indicators. Due to the strong geometric constraints on the internal space of small UAVs, the arrangement and design of their internal components must achieve the optimal solution within a limited space. Attempting to increase the volume of a certain part, such as the power system or the shape of the vehicle, will cause a series of engineering problems.
[0003] First, increasing the size of the drone alters its aerodynamic shape, leading to increased drag. To overcome this increased drag, greater thrust is needed, requiring higher-powered motors. This can increase the overall system load and power consumption, significantly reducing the drone's range, which relies heavily on limited energy storage. Furthermore, the increased power requirements also impact structural and thermal design. Therefore, drone design must comprehensively optimize size, power, and weight while meeting performance requirements to achieve optimal system efficiency. The internal components of a drone primarily include the flight controller and its power supply, the electronic speed controller (ESC) and its power supply, and a battery monitoring module.
[0004] However, most products on the market currently have low integration, and the aforementioned core components are all independent parts, which greatly occupies the internal space of the drone and also brings inconvenience to wiring.
[0005] Therefore, there is a need to provide a novel quadcopter power board system designed to solve the above problems. Utility Model Content
[0006] In view of the shortcomings of the existing technology, the purpose of this utility model embodiment is to provide a novel quadcopter power board system to solve the problems in the background technology mentioned above.
[0007] To achieve the above objectives, this utility model provides the following technical solution:
[0008] A novel quadcopter power board system includes a power board comprising a front arrangement area and a rear arrangement area. One end of the front arrangement area has a battery interface, and the other end has a fuse. Between the battery interface and the fuse, a capacitor, a battery detection circuit, an ESC power supply circuit, and a flight control power supply circuit are sequentially distributed. One end of the rear arrangement area has a power auxiliary interface located near the fuse. The rear arrangement area also includes a flight control power supply interface and a battery detection interface.
[0009] As a further embodiment of this invention, the battery interface is powered by a power battery and connects two XT60s in parallel to the battery.
[0010] As a further embodiment of this invention, the battery detection circuit estimates the flight time of the aircraft and checks the current status of the aircraft by detecting the real-time voltage and discharge current of the battery.
[0011] As a further embodiment of this utility model, the electronically controlled power supply circuit includes four XT60 batteries connected in parallel to the power battery.
[0012] As a further embodiment of this invention, the flight control power supply circuit is used to convert the battery voltage to 5V and control the ripple within 5% of the battery voltage.
[0013] As a further embodiment of this invention, the capacitor is an MLCC capacitor.
[0014] As a further embodiment of this invention, the fuse is a self-resetting fuse with a tripping current of 8A.
[0015] In summary, the embodiments of this utility model have the following beneficial effects compared with the prior art:
[0016] 1. In this utility model, the power distribution board and the step-down circuit required by the flight controller are integrated. In addition to powering the ESC, it also has the functions of detecting the battery status and powering the flight controller. At the same time, it also reserves an auxiliary power interface with overcurrent protection for other peripherals, isolating the power supply of peripherals from the power supply, which greatly increases the safety of flight.
[0017] 2. This utility model adopts a modular design concept, distributing the circuits of each part in a modular manner with low coupling design; it can be applied to the field of UAV teaching, which greatly facilitates students' understanding of the specific composition of each part of the power supply of UAV, reduces the difficulty of understanding and learning, and also provides convenience for the wiring and internal space constraints of UAV; at the same time, it can also be applied to the commercial field.
[0018] To more clearly illustrate the structural features and effects of this utility model, the following detailed description of this utility model is provided in conjunction with the accompanying drawings and specific embodiments. Attached Figure Description
[0019] Figure 1 This is a schematic diagram of the front structure of the power supply board in an embodiment of the utility model.
[0020] Figure 2 This is a schematic diagram of the back structure of the power supply board in an embodiment of the utility model.
[0021] Figure 3 This is a block diagram of the power supply board system in an embodiment of the utility model.
[0022] Figure 4 This is a schematic diagram of the battery detection circuit and the flight control power supply interface in an embodiment of the utility model.
[0023] Figure 5 This is a schematic diagram of the flight controller power supply circuit in an embodiment of the utility model.
[0024] Figure 6 This is a schematic diagram of the power supply circuit, auxiliary power interface, and battery detection circuit (partial) in the embodiment of the utility model.
[0025] Reference numerals in the attached diagram: 1. Battery interface; 2. Capacitor; 3. Battery detection circuit; 4. ESC power supply circuit; 5. Flight controller power supply circuit; 6. Fuse; 7. Power auxiliary interface; 8. Flight controller power supply interface and battery detection interface. Detailed Implementation
[0026] To make the objectives, technical solutions, and advantages of this utility model clearer, the present utility model will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present utility model and are not intended to limit the present utility model.
[0027] The specific implementation of this utility model will be described in detail below with reference to specific embodiments.
[0028] In one embodiment of this utility model, see Figures 1-6 A novel quadcopter power board system includes a power board comprising a front arrangement area and a rear arrangement area. A battery interface 1 is located at one end of the front arrangement area, and a fuse 6 is located at the other end. A capacitor 2, a battery detection circuit 3, an ESC power supply circuit 4, and a flight control power supply circuit 5 are sequentially distributed between the battery interface and the fuse. A power auxiliary interface 7 is located at one end of the rear arrangement area, near the fuse 6. The rear arrangement area also includes a flight control power supply interface and a battery detection interface 8.
[0029] The battery interface 1 is powered by the power battery, and the two XT60s are connected in parallel to the battery. It also has a high current protection function. If a short circuit or overcurrent occurs, it can effectively protect the peripherals connected here.
[0030] Battery detection circuit 3 can detect the real-time battery voltage and discharge current, which can be used to estimate the flight time of the aircraft and check the current status of the aircraft.
[0031] The ESC power supply circuit 4 includes four XT60s connected in parallel to the power battery, which can directly power the ESC, reducing wiring difficulty;
[0032] The flight controller power supply circuit 5 converts the battery voltage to 5V, while keeping the ripple within 5% of the battery voltage, providing a reliable power supply for the flight controller.
[0033] In this embodiment, the battery is inserted into the battery interface of the power supply board. The current first passes through the sampling circuit, which collects the voltage across the sampling resistor, calculates the current, and transmits the data to the battery detection interface through an operational amplifier. The flight controller connects to the battery detection interface to obtain the battery data. Then, through a voltage divider circuit, the battery voltage is transmitted to the flight controller, which then obtains the current complete state of the battery.
[0034] Next, the battery voltage is distributed to the four XT60 connectors to power the four ESCs.
[0035] Afterwards, the current passes through the filter circuit to the DC-DC step-down circuit. Through the step-down chip, the output voltage is reduced to 5V. At the same time, the output through the filter circuit provides reliable power to the flight controller and also provides a power indicator to indicate the current status of the flight controller power supply circuit.
[0036] The entire system has a high degree of integration, combining the power distribution board, step-down module, and battery detection module onto a single board, which reduces the complexity of wiring inside the aircraft and increases the safety of the entire aircraft system.
[0037] Specifically, the power battery is connected to the power supply board via the XT60 interface. First, it passes through a 0.5mΩ sampling resistor, which is then connected to the IN- and IN+ pins of the INA199 chip. The INA199 series voltage output and current shunt monitor (also known as a current sensing amplifier) are commonly used for overcurrent protection, precision current measurement optimized for the system, or closed-loop feedback circuits. This series of devices can sense the voltage drop across the shunt resistor at common-mode voltages from –0.3V to 26V, independent of the supply voltage, and offers three fixed gains: 50V / V, 100V / V, and 200V / V. The low offset of the zero-drift architecture allows the device to sense current with a maximum voltage drop across the shunt down to 10mV (full scale). The sixth pin of the INA199 outputs a signal to the battery detection interface, while a series voltage divider circuit consisting of 1.5kΩ and 30kΩ pins is connected to the IN- network to transmit the battery voltage to the battery detection interface.
[0038] Following the sampling circuit is the ESC power supply circuit, which is equivalent to four XT60 interfaces connected in parallel to the battery network, and can simultaneously provide power of the same voltage as the battery to the four XT60 interfaces.
[0039] Next is the flight controller power supply circuit, which uses the TI LMR51420YDDCR chip. It employs a buck topology, converting a maximum input voltage of 36V to 600mV-34.2V. A 169kΩ and 22.1kΩ resistor are connected in series as a feedback resistor. The voltage divided by the voltage divider is connected to the chip's FB pin to ensure a stable output of 5V. Pin 5 of the chip is pulled up to the power input interface, automatically enabling it upon power-up without manual intervention. Four MLCC capacitors are connected in parallel to the LMR51420YDDCR power input pin to ensure stable input voltage and stable operation of the voltage regulator circuit. The regulated output pin uses an LC circuit to reduce output ripple, improve power supply stability, and achieve a smooth and stable output voltage. A power indicator light is also added to the output of the LMR51420YDDCR chip to indicate the working status of the buck module.
[0040] The power supply board system's current loop ends at the auxiliary power interface, which is equivalent to being connected in parallel to the battery. It is connected in series with a self-resetting fuse with a tripping current of 8A to ensure the safety of connected peripherals.
[0041] This invention integrates the power distribution board and the step-down circuit required for flight control. In addition to powering the ESC, it also has the functions of detecting battery status and powering the flight control. Furthermore, it reserves an auxiliary power interface with overcurrent protection for other peripherals, isolating the power supply for peripherals from the power supply for the mains, which greatly increases flight safety.
[0042] Furthermore, this utility model adopts a modular design concept, distributing the circuit components in a modular manner with low coupling; it can be applied to the field of UAV teaching, greatly facilitating students' understanding of the specific composition of each part of the UAV power supply, reducing the difficulty of understanding and learning, and also providing convenience for UAV wiring and internal space constraints; it can also be applied to the commercial field.
[0043] The above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present utility model should be included within the protection scope of the present utility model.
Claims
1. A novel quadcopter power board system characterized by, The power board includes a front arrangement area and a back arrangement area. One end of the front arrangement area is provided with a battery interface (1), and the other end of the front arrangement area is provided with a fuse (6). Between the battery interface (1) and the fuse (6), there are distributed a capacitor (2), a battery detection circuit (3), an ESC power supply circuit (4), and a flight control power supply circuit (5). One end of the back arrangement area is provided with a power auxiliary interface (7), which is located at the end of the power board near the fuse (6). The back arrangement area is also provided with a flight control power supply interface and a battery detection interface (8).
2. The novel quadcopter power board system according to claim 1, wherein, The battery interface (1) is powered by the power battery and connects the two XT60s in parallel to the battery.
3. The novel quadcopter power board system according to claim 1, wherein, The battery detection circuit (3) estimates the flight time of the aircraft and checks the current status of the aircraft by detecting the real-time voltage and discharge current of the battery.
4. The novel quadcopter power board system according to claim 1, wherein, The power supply circuit (4) includes four XT60 batteries connected in parallel to the power battery.
5. The novel quadcopter power board system according to claim 1, wherein, The flight control power supply circuit (5) is used to convert the battery voltage to 5V and control the ripple within 5% of the battery voltage.
6. The novel quadcopter power board system according to claim 1, wherein, The capacitor (2) is an MLCC capacitor.
7. The novel quadcopter power board system according to claim 1, wherein, The fuse (6) is a self-resetting fuse with a tripping current of 8A.