CN214247558U - System for emergency starting power supply of unmanned aerial vehicle engine - Google Patents

Abstract

The utility model discloses a system of an unmanned aerial vehicle engine emergency starting power supply, which comprises a controller, a charger, a capacitor module, a heat dissipation module, an electric quantity detection module, an input port, an output port 1 and an output port 2; the controller is connected with the charger and the capacitor module; the charger is connected with the capacitor module; the electric quantity detection module is connected with the capacitor module; the controller integrates power conversion, signal processing and power driving; the controller also comprises a charging switch and a discharging switch; when the engine is not ignited, the charging switch is closed, the discharging switch is opened, the capacitor is charged, and the energy output is zero; when the engine is ignited, the charging switch is switched off, the discharging switch is switched on, and energy is output to the engine for ignition. The selected devices and ports have the service temperature of-55 ℃ to +85 ℃, and the heat dissipation module is added, so that the service temperature range of the emergency starting power supply is greatly improved, and the performance is improved.

Description

System for emergency starting power supply of unmanned aerial vehicle engine

Technical Field

The utility model belongs to the technical field of emergent starting power supply, concretely relates to emergent starting power supply's of unmanned aerial vehicle engine system.

Background

Compared with the piloted airplane, the unmanned aerial vehicle can play a great role in executing dangerous tasks such as disaster rescue, material transportation, disaster relief and the like due to the characteristic that the unmanned aerial vehicle does not need people to participate in high-altitude flight; for military use unmanned aerial vehicle has more significant meaning to the air battle, consequently it is very important to ensure unmanned aerial vehicle's safety and stability flight, in abominable airspace environment, when unmanned aerial vehicle engine trouble is flamed out, need an emergency starting power supply to come the restart engine, let unmanned aerial vehicle not receive the trouble influence, still can safety and stability's flight, avoided the aircraft crash to cause ground personnel and property to and the loss of aircraft itself.

Compared with an airplane piloted by a person, the unmanned aerial vehicle is smaller in size, but the unmanned aerial vehicle has various functions of material conveying, investigation, combat and the like, has higher requirements on an emergency starting power supply in terms of power and space, and not only meets the requirement of high power required by engine ignition, but also has smaller size; the unmanned aerial vehicle flies at high altitude, has extremely high requirements on the use temperature, has extremely strict requirements on the temperature in aviation, and can still normally work in the environment of-55 ℃ to +85 ℃. Most of the existing emergency starting power supplies in the market are used for civil use, the problems of small power density ratio, large size and the like exist, and the use temperature range is between-10 ℃ and +50 ℃, so that the use requirements of the unmanned aerial vehicle can not be met completely.

SUMMERY OF THE UTILITY MODEL

In view of the above problems, the present invention provides a system for starting a power supply of an engine of an unmanned aerial vehicle in an emergency, which is characterized by comprising a controller, a charger, a capacitor module, a heat dissipation module, an electric quantity detection module, an input port, an output port 1 and an output port 2; the controller is connected with the charger and the capacitor module; the charger is connected with the capacitor module; the electric quantity detection module is connected with the capacitor module.

Preferably, the controller integrates power conversion, signal processing and power driving; the controller also comprises a charging switch and a discharging switch; the controller can receive and process an external control signal and control whether to ignite the engine according to the control signal; when the engine is not ignited, the capacitor module is in a charging state, the charging switch is closed, the charger works, the discharging switch is disconnected, and the energy output is zero; when the engine is ignited, the capacitor module is in a discharging state, the charging switch is switched off, the charger is switched off, the discharging switch is switched on, and the controller outputs energy to the engine for ignition.

Preferably, the capacitor module is formed by connecting 6 capacitors in series, and can satisfy the power required by ignition of a large-scale unmanned aerial vehicle engine.

Preferably, the controller is installed on the heat dissipation module, and the heat dissipation module can perform good heat dissipation on the controller.

Preferably, the heat dissipation module comprises a heat dissipation sheet and heat conduction silica gel, and the heat conduction silica gel is installed between the controller and the heat dissipation sheet and has the functions of insulation and heat conduction.

Preferably, the electric quantity detection module is connected to the output port 2, and the electric quantity detection module detects the remaining electric quantity in the capacitor, and outputs the remaining electric quantity from the output port 2 after modulation.

Preferably, the input port is connected with the controller, the charger and the electric quantity detection module.

Preferably, the output port 1 is connected with the controller for outputting energy to the engine of the unmanned aerial vehicle.

Compared with the prior art, the beneficial effects of the utility model are that:

the utility model discloses a system for the emergency starting power supply of the unmanned aerial vehicle engine, the controller integrates power conversion, signal processing and power driving, removes the power converter, relay and driver which are commonly used at present, and greatly reduces the volume of the emergency starting power supply; the controller is provided with a processor chip, so that an external control signal can be intelligently monitored, and whether ignition is needed or not can be quickly judged; the interlocking function is realized, when the engine is not ignited, the charging switch is closed, the discharging switch is opened, the capacitor is charged, and the energy output is zero; when the engine is ignited, the charging switch is switched off, the discharging switch is switched on, and the output energy is ignited, so that the equipment can be prevented from being damaged due to misoperation; the used capacitor is formed by connecting 6 capacitors in series, and can completely meet the energy required by the ignition of an engine of a large unmanned aerial vehicle; the controller is provided with a heat dissipation module through which a high-power signal passes, so that the heating problem of a high-power device can be effectively relieved, and the service performance is improved; the electric quantity detection module is installed, and the electric quantity of the emergency starting power supply can be detected in real time. The use temperature of the selected device and the port reaches the temperature requirement of-55 ℃ to +85 ℃.

Drawings

Fig. 1 is a system connection diagram of an emergency starting power supply of an engine of an unmanned aerial vehicle according to the first embodiment.

Fig. 2 is a system work flow chart of the emergency starting power supply of the engine of the unmanned aerial vehicle according to the first embodiment.

In order to make the technical solution of the present invention better understood, the technical solution of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by a person of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

In the description of this patent, it is noted that, unless expressly stated or limited otherwise, the terms "mounted," "connected," and "communicating" are to be construed broadly, e.g., as meaning fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. It is to be noted that all the figures are exemplary representations. The meaning of the above terms in this patent may be specifically understood by those of ordinary skill in the art.

In the following description, for purposes of explanation and not limitation, specific details are set forth, such as particular system structures, techniques, etc. in order to provide a thorough understanding of the embodiments of the present application. It will be apparent, however, to one skilled in the art that the present application may be practiced in other embodiments that depart from these specific details. In other instances, detailed descriptions of well-known concepts, systems, devices, circuits, and methods are omitted.

The patent is described in further detail below with reference to specific embodiments and with reference to the attached drawings.

Detailed Description

As shown in fig. 1, an unmanned aerial vehicle engine emergency starting power supply control system includes a controller, a charger, a capacitor module, a heat dissipation module, an electric quantity detection module, an input port, an output port 1, and an output port 2; the controller is connected with the charger and the capacitor module; the charger is connected with the capacitor module; the electric quantity detection module is connected with the capacitor module.

Preferably, the controller integrates power conversion, signal processing and power driving, so that the volume of the emergency starting power supply is effectively reduced; the controller also comprises a charging switch and a discharging switch; the controller is provided with a processor, so that the controller can receive and process an external control signal, the control signal is a voltage signal, the controller modulates the voltage signal and transmits the modulated voltage signal to the processor, when the processor detects that the control signal is between 21V and 32V, the engine needs to be ignited, the charging switch is switched off, the discharging switch is switched on, the capacitor module discharges, and the controller outputs energy to the engine for ignition; when the processor detects that the control signal is less than 21V, the engine does not ignite, the charging switch is closed, the discharging switch is disconnected, and the energy output is zero. The capacitor module is charged to store electric quantity for next engine ignition, and the state is that the unmanned aerial vehicle has no fault and the emergency starting power supply is not used; the capacitor module is in an interlocking mode between two states of charging and discharging, and the capacitor module only has one state at the same moment, so that the device can be prevented from being damaged by misoperation, and the use is safer.

Preferably, the electric capacity module is established ties by 6 electric capacity and is formed, can satisfy the power that a large-scale unmanned aerial vehicle engine was igniteed needs.

Preferably, the controller is installed on the heat dissipation module, and the heat dissipation module can perform good heat dissipation on the controller; the heat dissipation module comprises a heat dissipation sheet and heat conduction silica gel, and the heat conduction silica gel is arranged between the controller and the heat dissipation sheet and has the functions of insulation and heat conduction. Except the weak current part of treater on the controller, there are a lot of powerful devices in addition, the energy that generator ignition needs passes through from the controller, this can lead to the temperature of controller very high, consequently, the high-power device on the controller must hug closely the fin, the material of fin is the metal, be connected with the shell of emergency starting power supply, good radiating effect has, but there is voltage signal on these high-power devices, if directly paste with the fin, can lead the voltage to the casing, the shell is electrified promptly, it is very dangerous, so selected for use heat conductivity and insulating nature all fabulous thermal silica gel, separate high-power device and fin, do not influence the heat dissipation again, the heat dissipation has been done and can improve the service temperature range of equipment greatly, the lifting performance.

Preferably, the electric quantity detection module is connected to the output port 2, and the electric quantity detection module detects the electric quantity in the capacitor, and outputs the electric quantity from the output port 2 after modulation. After the emergency starting power supply is installed, the technician can not use instruments such as universal meters to measure whether current voltage is enough to ignite for the engine, so the host computer needs to gather the current electric quantity of capacitance module, shows on the control page, monitors at any time, and the host computer can only receive little voltage, electric quantity detection module's effect: and collecting the voltage of the emergency starting power supply in real time, and modulating the voltage into a voltage range which can be received by the host.

Preferably, the input port is electrically connected with the controller, the charger and the electric quantity detection module; the input port comprises 4 signal pins which are respectively used for transmitting a power supply anode, a power supply ground, a control signal anode and a control signal cathode, the power supply anode and the power supply ground are connected to the power supply anode and the power supply cathode of the controller, the charger and the electric quantity detection module, and the control signal anode and the control signal cathode are connected to the controller.

Preferably, output port 1 is connected with the controller for output generator required energy, and output port 1 is just the power output port, and is internally connected with the power positive pole, the negative pole of controller, externally is connected with unmanned aerial vehicle's engine positive pole, negative pole.

As shown in fig. 2, a system for emergency starting power supply of an engine of an unmanned aerial vehicle, the work flow is: when an engine of the unmanned aerial vehicle is flamed out in the air, the on-board flight control computer sends a control signal from 21V to 32V to the emergency starting power supply, and after the controller detects a high level greater than 21V, the charging switch is disconnected, the charger is closed, the discharging switch is closed, and the capacitor module releases energy to start the generator; after the engine is started, the on-board flight control computer sends a control signal smaller than 21V to the emergency starting power supply, the controller disconnects the discharging switch and closes the charging switch, and the charger starts to work to charge the capacitor module, so that the electric quantity is sufficient when the on-board flight control computer needs to be used again.

Claims (7)

1. A system for starting a power supply of an unmanned aerial vehicle engine in an emergency is characterized by comprising a controller, a charger, a capacitor module, a heat dissipation module, an electric quantity detection module, an input port, an output port 1 and an output port 2; the controller is connected with the charger and the capacitor module; the charger is connected with the capacitor module; the electric quantity detection module is connected with the capacitor module;

the controller integrates power conversion, signal processing and power driving; the controller also comprises a charging switch and a discharging switch; the controller can receive and process an external control signal and control whether to ignite the engine according to the control signal; when the engine is not ignited, the capacitor module is in a charging state, the charging switch is closed, the charger works, the discharging switch is disconnected, and the energy output is zero; when the engine is ignited, the capacitor module is in a discharging state, the charging switch is switched off, the charger is switched off, the discharging switch is switched on, and the controller outputs energy to the engine for ignition.

2. The system of claim 1, wherein the capacitor module is formed by connecting 6 capacitors in series, and can satisfy a power requirement for ignition of a large-sized unmanned aerial vehicle engine.

3. The system of claim 1, wherein the controller is mounted on the heat dissipation module, and the heat dissipation module dissipates heat well to the controller.

4. The system of claim 1, wherein the heat dissipation module comprises a heat sink and a heat conductive silicone, and the heat conductive silicone is installed between the controller and the heat sink, and has an insulating and heat conducting function.

5. The system of claim 1, wherein the electric quantity detection module is connected to the output port 2, and detects the remaining electric quantity in the capacitor, and the remaining electric quantity is modulated and then output from the output port 2.

6. The system of claim 1, wherein the input port is connected to the controller, the charger, and the power detection module.

7. The system of claim 1, wherein the output port 1 is connected to the controller for outputting energy to the drone engine.

Images