Avionics system and unmanned aerial vehicle

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, and discloses an avionics system and an unmanned aerial vehicle, and the avionics system comprises an isolation type step-down unit, a non-isolation type step-down unit, a plurality of circuit fluctuation low-sensitive loads and a plurality of circuit fluctuation high-sensitive loads. The input end of the isolation type step-down unit and the input end of the non-isolation type step-down unit are both electrically connected with the power input end, the circuit fluctuation low-sensitive load is electrically connected with the output end of the isolation type step-down unit, and the circuit fluctuation high-sensitive load is electrically connected with the output end of the non-isolation type step-down unit. The isolation type voltage reduction unit can isolate bottom noise generated by the circuit fluctuation low-sensitive load. According to the avionics system, the bottom noise generated by the circuit fluctuation low-sensitive load is isolated outside the power supply bus through the isolation type step-down unit, the reliability of the avionics system is improved, meanwhile, the circuit fluctuation high-sensitive load can be supplied with power through a common non-isolation type step-down unit, and the cost of the avionics system is reduced.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, and in particular to an avionics system and an unmanned aerial vehicle. Background Art

[0002] With the development of science and technology, the application of drones is becoming more and more popular. The load of the drone's avionics system includes some dynamic loads, such as servos, which are prone to generate background noise during operation and have low sensitivity to circuit fluctuations. The background noise generated will not affect their own work, but will be transmitted to more sensitive loads along the power supply bus, which is easy to affect the reliability of electronic modules such as flight control electronic modules and data link electronic modules, thereby affecting the reliability of the entire avionics system. In order to solve the above technical problems, existing avionics systems often add filters and other devices that can isolate and block circuit fluctuations at the input end of these loads that are more sensitive to circuit fluctuations, but this will increase the cost of the avionics system. To this end, it is necessary to design an avionics system with low cost and high reliability. Utility Model Content

[0003] In order to overcome the deficiencies of the prior art, the purpose of the present invention is to provide an avionics system that can solve the impact of background noise generated by dynamic loads on loads with high circuit fluctuation sensitivity, improve the reliability of the avionics system, and at the same time do not increase the implementation cost of the avionics system.

[0004] In order to solve the above problems, the technical solution adopted by the utility model is as follows: an avionics system, including an isolated buck unit, a non-isolated buck unit, a plurality of circuit fluctuation low-sensitive loads and a plurality of circuit fluctuation high-sensitive loads, the input ends of the isolated buck unit and the non-isolated buck unit are electrically connected to the power input end, the circuit fluctuation low-sensitive load is electrically connected to the output end of the isolated buck unit, the circuit fluctuation high-sensitive load is electrically connected to the output end of the non-isolated buck unit, and the isolated buck unit can isolate the background noise generated by the circuit fluctuation low-sensitive load.

[0005] Compared with the prior art, the beneficial effect of the utility model is that: by dividing the circuit fluctuation-sensitive load and the circuit fluctuation-sensitive load into two power supply paths, and supplying power to the circuit fluctuation-sensitive load through an isolated step-down unit that can isolate the background noise, the background noise generated by the circuit fluctuation-sensitive load can be isolated outside the input power supply bus, thereby preventing the generated background noise from being transmitted to other loads along the bus. Since the background noise generated by the circuit fluctuation-sensitive load is isolated outside the bus, the power supply of the circuit fluctuation-sensitive load can work reliably and stably even if an ordinary non-isolated step-down unit is used, thereby reducing the power supply requirements of the circuit fluctuation-sensitive load and reducing the implementation cost of the entire avionics system.

[0006] In the above-mentioned avionics system, the circuit fluctuation low-sensitive load includes a steering gear.

[0007] In the above-mentioned avionics system, the circuit fluctuation highly sensitive loads include a flight control electronic module, a communication electronic module and a GPS positioning module.

[0008] In the above-mentioned avionics system, the isolated buck unit includes an isolated switching power supply and its peripheral circuits, the input pin of the isolated switching power supply is electrically connected to the power input terminal, and the circuit fluctuation low-sensitive load is electrically connected to the output pin of the isolated switching power supply.

[0009] In the above-mentioned avionics system, the non-isolated buck unit includes a first DC-DC buck module and its peripheral circuit and a second DC-DC buck module and its peripheral circuit, the input pin of the first DC-DC buck module is electrically connected to the power input end, and the input end of the second DC-DC buck module is electrically connected to the output pin of the first DC-DC buck module.

[0010] An unmanned aerial vehicle comprises the above-mentioned avionics system.

[0011] The utility model is further described in detail below in conjunction with the accompanying drawings and specific implementation methods. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] Figure 1 This is a functional block diagram of an avionics system according to an embodiment of the utility model;

[0013] Figure 2 This is a circuit schematic diagram of an isolated voltage reduction unit of an avionics system according to an embodiment of the utility model;

[0014] Figure 3 This is a schematic diagram of a first DC-DC buck module and its peripheral circuits according to an embodiment of the present utility model;

[0015] Figure 4 This is a schematic diagram of a second DC-DC buck module and its peripheral circuits according to an embodiment of the present utility model. DETAILED DESCRIPTION

[0016] The embodiments of the present invention are described in detail below. Figure 1An embodiment of the utility model provides an avionics system, including an isolated buck unit, a non-isolated buck unit, a number of circuit fluctuation-sensitive loads, and a number of circuit fluctuation-sensitive loads. The input ends of the isolated buck unit and the non-isolated buck unit are both electrically connected to the power input end, the circuit fluctuation-sensitive load is electrically connected to the output end of the isolated buck unit, and the circuit fluctuation-sensitive load is electrically connected to the output end of the non-isolated buck unit. The isolated buck unit can isolate the background noise generated by the circuit fluctuation-sensitive load. The avionics system of the embodiment of the utility model adopts an isolated buck unit with background noise isolation capability to supply power to the circuit fluctuation-sensitive load that is prone to generate background noise, and can isolate the background noise generated by the circuit fluctuation-sensitive load outside the power supply bus to prevent the background noise from being transmitted to other load devices connected to the power supply bus. Since the background noise generated by loads with low sensitivity to circuit fluctuations will not be transmitted to the power supply bus, loads with high sensitivity to circuit fluctuations that are easily affected by the background noise can be powered by ordinary non-isolated step-down units, reducing the demand for step-down units for loads with high sensitivity to circuit fluctuations, ensuring the reliability of the entire avionics system while reducing the implementation cost of the entire avionics system.

[0017] It is understandable that loads with low sensitivity to circuit fluctuations are mainly dynamic loads, such as loads containing motors such as servos. Loads with high sensitivity to circuit fluctuations are mainly loads that require communication, such as flight control electronic modules, communication electronic modules, and GPS positioning modules.

[0018] Reference Figure 2 In this embodiment, the isolated step-down unit includes isolated switching power supplies U38 and U39 and their peripheral circuits. The input pin of the isolated switching power supply is electrically connected to the power input terminal. After converting the 24V DC power input from the power input terminal into 12V DC power, it is supplied to the circuit fluctuation low-sensitive load through the output pin. The output pin of the isolated switching power supply is connected to a voltage regulator diode D81 to clamp the output voltage to prevent the output voltage from being too high and damaging the load. The output pin of the isolated switching power supply is also connected to a light-emitting diode LED10 to indicate the power supply status of the isolated switching power supply. Figure 2 In this embodiment, two isolated switching power supplies U38 and U39 are connected in parallel to ensure stable power supply to dynamic loads such as steering gears, further improving the reliability of the avionics system.

[0019] Reference Figure 3 and Figure 4Since loads that are highly sensitive to circuit fluctuations usually require a variety of different power supply voltages, in this embodiment, the non-isolated buck unit includes a first DC-DC buck module U37, a second DC-DC buck module U31, and their peripheral circuits. The input pin of the first DC-DC buck module U37 is connected to the power output end, and after converting the 24V DC power input from the power input end into 5V DC power, it is output through the output pin to the circuit fluctuation-sensitive load that requires 5V DC power and the input pin of the second DC-DC buck module U31. The second DC-DC buck module U31 converts the 5V DC power input from the input pin into 3.3V DC power, and then outputs it through the output pin to the circuit fluctuation-sensitive load that requires 3.3V DC power. The output pin of the first DC-DC buck module U37 is also connected to a Zener diode D114 for protecting the buck module and the load, and a light-emitting diode LED11 for indicating the power supply status.

[0020] The drone of the utility model embodiment includes the above-mentioned avionics system, which can ensure that both the circuit fluctuation highly sensitive load and the circuit fluctuation low sensitive load on the drone can work reliably at a relatively low cost, thereby improving the reliability of the drone during flight and reducing the probability of crashing.

[0021] It should be noted that in the description of the present invention, if there are any orientation descriptions, such as up, down, front, back, left, right, etc., the orientations or positional relationships indicated are all based on the orientations or positional relationships shown in the drawings. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed or operated in a specific orientation, and cannot be understood as a limitation on the present invention.

[0022] In the description of the present utility model, "several" means one or more, "more" means two or more, "greater than", "less than", "exceed" etc. are understood to exclude the number itself, and "above", "below", "within" etc. are understood to include the number itself. If there is a description of "first" or "second", it is only used to distinguish the technical features, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features or implicitly indicating the order of the indicated technical features.

[0023] In the description of the present invention, unless otherwise clearly defined, terms such as setting, installing, connecting, etc. should be understood in a broad sense, and technicians in the relevant technical field can reasonably determine the specific meanings of the above terms in the present invention based on the specific content of the technical solution.

[0024] The above-mentioned implementation modes are only preferred implementation modes of the present invention, and cannot be used to limit the protection scope of the present invention. Any non-substantial changes and substitutions made by technicians in this field on the basis of the present invention shall fall within the scope of protection required by the present invention.

Claims

1. An avionics system, characterized in that: It includes an isolated buck unit, a non-isolated buck unit, a plurality of circuit fluctuation-sensitive loads and a plurality of circuit fluctuation-sensitive loads. The input ends of the isolated buck unit and the non-isolated buck unit are both electrically connected to the power input end, the circuit fluctuation-sensitive load is electrically connected to the output end of the isolated buck unit, and the circuit fluctuation-sensitive load is electrically connected to the output end of the non-isolated buck unit. The isolated buck unit can isolate the background noise generated by the circuit fluctuation-sensitive load.

2. The avionics system according to claim 1, characterized in that: The circuit fluctuations are low sensitive to loads including servos.

3. The avionics system according to claim 1, characterized in that: The circuit fluctuation highly sensitive loads include a flight control electronic module, a communication electronic module and a GPS positioning module.

4. The avionics system according to claim 1, characterized in that: The isolated buck unit comprises an isolated switching power supply and its peripheral circuits, the input pin of the isolated switching power supply is electrically connected to the power input terminal, and the circuit fluctuation low-sensitive load is electrically connected to the output pin of the isolated switching power supply.

5. The avionics system according to claim 1, characterized in that: The non-isolated buck unit includes a first DC-DC buck module and its peripheral circuit and a second DC-DC buck module and its peripheral circuit, the input pin of the first DC-DC buck module is electrically connected to the power input end, and the input end of the second DC-DC buck module is electrically connected to the output pin of the first DC-DC buck module.

6. A drone, characterized in that: Comprising an avionics system according to any one of claims 1-5.

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