Unmanned aerial vehicle igniter

Abstract

The utility model discloses an unmanned aerial vehicle igniter. Comprising a shell, a storage battery, an ignition control panel, a first ignition binding post, a second ignition binding post, a safety pin clamping groove and an airspeed tube cap clamping groove are arranged in the shell, and the safety pin clamping groove and the airspeed tube cap clamping groove are used for clamping a safety pin and an airspeed tube cap of the unmanned aerial vehicle respectively; a safety pin trigger switch and an airspeed tube cap trigger switch are arranged in the safety pin clamping groove and the airspeed tube cap clamping groove respectively and electrically connected between the ignition control panel and the first ignition key and between the ignition control panel and the second ignition key. And the control module is used for controlling the ignition control panel to be communicated with the first ignition key and the second ignition key. Therefore, only when the safety pin and the airspeed tube cap of the unmanned aerial vehicle are inserted into the safety pin clamping groove and the airspeed tube cap clamping groove and the ignition control panel is communicated with the first ignition key and the second ignition key, the igniter can be used for ignition, and the safety pin and the airspeed tube cap of the unmanned aerial vehicle are ensured to be taken down before ignition by the igniter; the takeoff safety of the unmanned aerial vehicle is ensured.

Description

Technical Field

[0001] The present application relates to the technical field of unmanned aerial vehicles, and in particular to an igniter for unmanned aerial vehicles. Background Art

[0002] Drones are devices that fly in the atmosphere. With the continuous development of drone technology, drones have been widely used in military, civil and commercial fields. Drones include fixed-wing drones, which have fixed wings and rely on the wind flowing through the wings to provide lift. Fixed-wing drones need a run-up when taking off and must glide when landing, but these drones have long flight time, high flight efficiency and large payload. These drones take off by running or catapult, and land by parachute or running. Before the drone takes off, it is necessary to pull out the safety pin on the drone and remove the pitot cap, and then ignite and launch it. However, in the prior art, there may be situations where the operator does not pull out the safety pin or remove the pitot cap and directly ignites and launches, resulting in unsafe takeoff of the drone. Utility Model Content

[0003] The main technical problem solved by the present application is to provide a UAV igniter to solve the problem that the operator directly ignites and launches the UAV without pulling out the safety pin or removing the pitot tube cap, thereby causing unsafe take-off of the UAV.

[0004] In order to solve the above technical problems, a technical solution adopted by the present application is to provide a drone igniter, including a shell, a battery, an ignition control board, a first ignition terminal and a second ignition terminal are arranged in the shell, the battery is electrically connected to the ignition control board, the ignition control board is electrically connected to the first ignition terminal and the second ignition terminal, the first ignition terminal and the second ignition terminal are used to electrically connect the drone, and a first ignition button and a second ignition button are arranged on the shell, the first ignition button is electrically connected between the ignition control board and the first ignition terminal, and is used to control the connection between the ignition control board and the first ignition terminal; The second ignition button is electrically connected between the ignition control board and the second ignition terminal, and is used to control the connection between the ignition control board and the second ignition terminal; a safety pin slot and a pitot tube cap slot are provided on the shell, and the safety pin slot and the pitot tube cap slot are used to respectively clamp the safety pin and the pitot tube cap of the drone; a safety pin trigger switch and a pitot tube cap trigger switch are respectively provided in the safety pin slot and the pitot tube cap slot, and the safety pin trigger switch and the pitot tube cap trigger switch are electrically connected between the ignition control board and the first ignition button and the second ignition button, and are used to control the connection between the ignition control board and the first ignition button and the second ignition button.

[0005] In some embodiments, a charging port and a charging switch are provided in the shell, the charging port is electrically connected to the battery, the charging switch is electrically connected between the charging port and the battery, the charging port is used to insert an external charging cable, and the charging switch is used to control the connection between the charging port and the battery.

[0006] In some embodiments, a charging fuse and a battery fuse are provided in the shell. The charging fuse is electrically connected between the charging switch and the battery to protect charging safety. The battery fuse is electrically connected between the ignition control panel and the first ignition button and the second ignition button to protect discharging safety.

[0007] In some embodiments, an aviation plug port and a 220V plug port are provided at the upper end of the shell, and a portable charging cable is inserted between the aviation plug port and the 220v plug port, and the portable charging cable is used to electrically connect the charging port with an external power source.

[0008] In some embodiments, an ignition preparation switch is provided in the shell, and the ignition preparation switch is electrically connected between the ignition control board and the first ignition button and the second ignition button, and is used to control the connection between the ignition control board and the first ignition button and the second ignition button.

[0009] In some embodiments, the safety pin trigger switch is electrically connected to a first indicator light, which is used to determine whether the safety pin trigger switch is closed, and the pitot tube cap trigger switch is electrically connected to a second indicator light, which is used to determine whether the pitot tube cap trigger switch is closed.

[0010] In some embodiments, a boost circuit is also provided between the charging switch and the battery, the boost circuit comprising an inductor and a boost transformer, the first end of the boost transformer is electrically connected to the inductor, and the fourth end of the boost transformer and the inductor are electrically connected to the charging switch.

[0011] In some embodiments, the boost circuit is also electrically connected to a rectifier and voltage-doubling energy storage circuit, which includes a first diode, a second diode, a current limiting resistor, a first voltage-doubling capacitor, a second voltage-doubling capacitor and an energy storage capacitor. The first diode and the second diode are both electrically connected to the second end of the boost transformer, the first voltage-doubling capacitor and the second voltage-doubling capacitor are both electrically connected to the third end of the boost transformer, the other end of the first diode is electrically connected to the first voltage-doubling capacitor and the energy storage capacitor, the other end of the second diode is electrically connected to the current limiting resistor, and the other ends of the current limiting resistor are respectively electrically connected to the second voltage-doubling capacitor and the energy storage capacitor.

[0012] In some embodiments, the ignition control board includes a discharge circuit, which includes a discharge resistor, a gas discharge tube, a high-frequency oscillation capacitor and a high-frequency transformer. The discharge resistor is connected in parallel with a battery and an energy storage capacitor, respectively. The first end of the discharge resistor is also electrically connected to the gas discharge tube and the high-frequency oscillation capacitor, respectively. The gas discharge tube and the high-frequency oscillation capacitor are both electrically connected to the high-frequency transformer.

[0013] The beneficial effect of the present application is as follows: by arranging a safety pin slot and a pitot tube cap slot on the shell of the drone, a safety pin trigger switch and a pitot tube cap trigger switch are respectively arranged in the safety pin slot and the pitot tube cap slot, and the safety pin trigger switch and the pitot tube cap trigger switch are electrically connected between the ignition control board and the first ignition button and the second ignition button. Only when the safety pin and the pitot tube cap of the drone are inserted into the safety pin slot and the pitot tube cap slot, and the ignition control board and the first ignition button and the second ignition button are connected, can the igniter be used for ignition, ensuring that the safety pin and the pitot tube cap of the drone have been removed before the igniter is used for ignition, thereby ensuring the safety of the drone's takeoff. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 is a structural schematic diagram according to an embodiment of the present application;

[0015] Figure 2 is a circuit connection diagram according to an embodiment of the present application;

[0016] Figure 3 is a connection diagram of a boost circuit and a rectifier voltage doubler energy storage circuit according to an embodiment of the present application;

[0017] Figure 4 4 is a connection diagram of a discharge circuit according to an embodiment of the present application. DETAILED DESCRIPTION

[0018] In order to facilitate the understanding of the present application, the present application is described in more detail below in conjunction with the accompanying drawings and specific embodiments. The preferred embodiments of the present application are provided in the accompanying drawings. However, the present application can be implemented in many different forms and is not limited to the embodiments described in this specification. On the contrary, the purpose of providing these embodiments is to make the understanding of the disclosure of the present application more thorough and comprehensive.

[0019] It should be noted that, unless otherwise defined, all technical and scientific terms used in this specification have the same meaning as those commonly understood by those skilled in the art of the present application. The terms used in the specification of this application are only for the purpose of describing specific embodiments and are not intended to limit this application. The term "and / or" used in this specification includes any and all combinations of one or more related listed items.

[0020] Figure 1 , Figure 2An embodiment of an unmanned aerial vehicle igniter of the present application is shown, including a shell 001, in which a battery 71, an ignition control board, a first ignition terminal 1 and a second ignition terminal 2 are arranged, and the battery 71 is electrically connected to the ignition control board. In this embodiment, the battery 71 includes two groups of cadmium nickel batteries G1 and G2, and the two groups of cadmium nickel batteries are connected in series, the ignition control board is electrically connected to the first ignition terminal 1 and the second ignition terminal 2, and the first ignition terminal 1 and the second ignition terminal 2 are used to electrically connect the unmanned aerial vehicle, and a first ignition button 3 and a second ignition button 4 are arranged on the shell 001, and the first ignition button 3 is electrically connected between the ignition control board and the first ignition terminal 1, and is used to control the connection between the ignition control board and the first ignition terminal 1; the second ignition button 4 is electrically connected between the ignition control board and the second ignition terminal 2, and is used to control the connection between the ignition control board and the second ignition terminal 2.

[0021] The housing 001 is provided with a safety pin slot 5 and a pitot tube cap slot 6, which are used to respectively clamp the safety pin and the pitot tube cap of the drone; the safety pin slot 5 and the pitot tube cap slot 6 are respectively provided with a safety pin trigger switch 51 and a pitot tube cap trigger switch 61, which are electrically connected between the ignition control board and the first ignition button 3 and the second ignition button 4. When the safety pin and the pitot tube cap are respectively inserted into the safety pin slot 5 and the pitot tube cap slot 6, the safety pin trigger switch 51 and the pitot tube cap trigger switch 61 will connect the ignition control board and the first ignition button 3 and the second ignition button 4, and then the ignition can be controlled by the first ignition button 3 and the second ignition button 4, ensuring that the safety pin and the pitot tube cap have been removed from the drone before ignition.

[0022] Accordingly, the UAV igniter is provided with a safety pin slot 5 and a pitot tube cap slot 6 on the UAV housing 001, and a safety pin trigger switch 51 and a pitot tube cap trigger switch 61 are provided in the safety pin slot 5 and the pitot tube cap slot 6, respectively. The safety pin trigger switch 51 and the pitot tube cap trigger switch 61 can be a contact switch, a micro switch, a normally open switch, etc. The safety pin trigger switch 51 and the pitot tube cap trigger switch 61 are electrically connected between the ignition control board and the first ignition button 3 and the second ignition button 4. Only when the safety pin and the pitot tube cap of the UAV are inserted into the safety pin slot 5 and the pitot tube cap slot 6, the ignition control board and the first ignition button 3 and the second ignition button 4 are connected, and then the igniter can be used for ignition, ensuring that the safety pin and the pitot tube cap of the UAV have been removed before the igniter is used for ignition, so as to ensure the safety of the UAV's take-off.

[0023] In some embodiments, a charging port 7 and a charging switch 8 are provided in the housing 001. The charging port 7 is electrically connected to the battery 71. The charging switch 8 is electrically connected between the charging port 7 and the battery 71. The charging port 7 is used to insert an external charging line to charge the battery 71. The charging switch 8 is used to control the connection between the charging port 7 and the battery 71. Figure 2 As shown, in this embodiment, the charging switch 8 can also be electrically connected to a charging switch indicator light to determine whether the charging switch is closed.

[0024] In addition, when an overload or short circuit occurs in the circuit, the current will increase dramatically. Excessive current flowing through the circuit may cause circuit damage, fire, or threaten personal safety.

[0025] In view of the above problems, in some embodiments, a charging fuse 9 and a battery fuse 10 are provided in the housing 001. The charging fuse 9 is electrically connected between the charging switch 8 and the battery 71 to protect charging safety, and the battery fuse 10 is electrically connected between the ignition control board and the first ignition button 3 and the second ignition button 4 to protect discharging safety. Specifically, when an overload or short circuit occurs in the circuit, the heat generated by the excessive current will exceed the tolerance of the charging fuse 9 and the battery fuse 10. At this time, the temperature of the charging fuse 9 and the battery fuse 10 rises and reaches the melting point, and the charging fuse 9 and the battery fuse 10 will break, cutting off the circuit to protect the circuit safety.

[0026] In some embodiments, an aviation plug port 111 and a 220V plug port 112 are provided at the upper end of the shell 001, and a portable charging cable 11 is inserted between the aviation plug port 111 and the 220V plug port 112. The portable charging cable 11 is adapted to the charging port 7. When not in use, the portable charging cable 11 is inserted into the aviation plug port 111 and the 220V plug port 112 at the upper end of the shell 001. When in use, the portable charging cable 11 is directly unplugged, and then the charging port 7 is connected to an external power source for charging. There is no need to find an adapted charging cable for charging. This is convenient to carry and can achieve fast charging.

[0027] In some embodiments, an ignition preparation switch 12 is provided in the shell 001. The ignition preparation switch 12 is electrically connected between the ignition control board and the first ignition button 3 and the second ignition button 4, and is used to control the connection between the ignition control board and the first ignition button 3 and the second ignition button 4. The ignition preparation switch 12 can further prompt the staff to confirm whether the preliminary preparation work is completed.

[0028] In some embodiments, the safety pin trigger switch 51 is electrically connected to a first indicator light 13, and the first indicator light 13 is used to determine whether the safety pin trigger switch 51 is closed. In other words, it is used to determine whether the safety pin is removed from the drone and inserted intact into the safety pin slot 5. The pitot tube cap trigger switch 61 is electrically connected to a second indicator light 14, and the second indicator light 14 is used to determine whether the pitot tube cap trigger switch 61 is closed. In other words, it is used to determine whether the pitot tube cap is removed from the drone and inserted intact into the pitot tube cap slot 6. The first indicator light 13 and the second indicator light 14 can visually give the staff verification prompts to improve work efficiency.

[0029] Combination Figure 3 As shown, in some embodiments, a boost circuit 16 is further provided between the charging switch 8 and the battery 71. The boost circuit 16 boosts the charging voltage. The boost circuit 16 includes an inductor L3 and a boost transformer T1. The boost transformer T2 can increase the AC voltage of 220V to about 2900V. The first end of the boost transformer T1 is electrically connected to the inductor L3. The fourth end of the boost transformer T1 and the inductor L3 are electrically connected to the charging switch 8. The inductor L3 can not only play a role in current regulation and control of input power, but also play a role in filtering to prevent the high-frequency signal of the igniter from interfering with the drone.

[0030] like Figure 3 As shown, in some embodiments, the boost circuit 16 is also electrically connected to a rectifier and voltage-doubling energy storage circuit 17, which can convert the charging voltage into a DC voltage. The rectifier and voltage-doubling energy storage circuit 17 includes a first diode D1, a second diode D2, a current limiting resistor R1, a first voltage-doubling capacitor C1, a second voltage-doubling capacitor C2 and an energy storage capacitor C3. The positive electrode of the first diode D1 and the negative electrode of the second diode D2 are both electrically connected to the second end of the boost transformer T1, wherein the first diode D1 and the second diode D2 are used to rectify and double the voltage of the AC signal, the first voltage-doubling capacitor C1 and the second voltage-doubling capacitor C2 are both electrically connected to the third end of the boost transformer T1, the negative electrode of the first diode D1 is electrically connected to the first voltage-doubling capacitor C1 and the energy storage capacitor C3, the positive electrode of the second diode D2 is electrically connected to the current limiting resistor R1, and the other end of the current limiting resistor R1 is electrically connected to the second voltage-doubling capacitor C2 and the energy storage capacitor C3, wherein the current limiting resistor R1 is used to limit the charging current of the second voltage-doubling capacitor C2.

[0031] Combination Figure 4As shown, in some embodiments, the ignition control board includes a discharge circuit 15, and the discharge circuit 15 includes a discharge resistor R2, a safety resistor R3, a gas discharge tube SG, a high-frequency oscillation capacitor C4 and a high-frequency transformer T2. The discharge resistor R2 is connected in parallel to the battery 71 and the energy storage capacitor C3 respectively. The first end of the discharge resistor R2 is also electrically connected to the gas discharge tube SG and the high-frequency oscillation capacitor C4 respectively. The gas discharge tube SG and the high-frequency oscillation capacitor C4 are both electrically connected to the high-frequency transformer T2. Among them, the gas discharge tube SG is a sealed gas tube, which works stably and is not affected by changes in external air pressure, and can ensure accurate breakdown voltage. The safety resistor R3 is a resistor of the order of kiloohms, and its function is to make the gas discharge tube SG directly feel the voltage on the energy storage capacitor C3; in addition, the safety resistor R3 can also provide a discharge channel for the energy storage capacitor C3 when the high-frequency transformer T2 and the second voltage doubling capacitor C2 fall off, so as to avoid breakdown of the energy storage capacitor C3.

[0032] Specifically, when the 220V charging voltage is boosted through the inductor L3 by the step-up transformer T1, when the induced voltage on the secondary winding L2 of the step-up transformer T1 is positive at the upper end and negative at the lower end, before the voltage peak arrives, the first diode D1 is turned on and the second diode D2 is turned off, and the branch consisting of the first voltage doubling capacitor C1 branch, the energy storage capacitor C3 and the second voltage doubling capacitor C2 in series is charged; when at a certain moment after the voltage crosses the peak, the voltage on the second voltage doubling capacitor C2 is greater than the secondary output voltage of the step-up transformer T1, the second diode D2 is turned on and the first diode D1 is turned off. At this time, the second voltage doubling capacitor C2 discharges through the energy storage capacitor C3 through the secondary coil of the step-up transformer T1, and the first voltage doubling capacitor C1 continues to charge the energy storage capacitor C3.

[0033] When the induced voltage on the secondary winding L2 of the step-up transformer T1 is positive at the lower end and negative at the upper end, before the voltage peak arrives, the second diode D2 is turned on to charge the branch consisting of the second voltage doubling capacitor C2 branch, the first voltage doubling capacitor C1 and the energy storage capacitor C3 in series; at a certain moment after the voltage passes the peak, when the voltage on the first voltage doubling capacitor C1 is greater than the secondary voltage of the step-up transformer T1, the first diode D1 is turned on and the second diode D2 is turned off. At this time, the first voltage doubling capacitor C1 is discharged through the first diode D1 via the secondary coil of the step-up transformer T1, and the second voltage doubling capacitor C2 continues to charge the energy storage capacitor C3; the secondary induced voltage of the step-up transformer T1 alternates between positive and negative half cycles. No matter how the induced voltage changes in direction, the voltage of the energy storage capacitor C3 is always in a charging state, and its voltage shows an intermittent upward trend. After a certain period, the sum of the voltages on the first voltage doubling capacitor C1 and the second voltage doubling capacitor C2 is close to twice the induced voltage of the secondary winding L2 of the step-up transformer T1. During this process, if the voltage on the energy storage capacitor C3 rises to the threshold voltage of the gas discharge tube SG, the discharge tube will be broken down and enter the discharge link.

[0034] Furthermore, when the voltage across the gas discharge tube SG reaches its threshold, the gas discharge tube SG is immediately ionized and broken down to conduct. After that, an initial current will flow in the loop formed by the high-frequency capacitor C4, the primary winding L4 of the high-frequency transformer T2 and the gas discharge tube SG, forming a high-frequency oscillation, inducing a high-frequency voltage on the secondary winding L5 of the high-frequency transformer T2, causing the pre-ionization discharge of the igniter's nozzle gap, and the energy storage capacitor C3 will discharge through the discharge tube SG, the secondary winding L5 of the high-frequency transformer T2, the ignition wire and the ignition nozzle that has been broken down and ionized, converting the electrical energy stored in the capacitor C3 into spark heat energy to ignite the fuel for ignition.

[0035] It can be seen that the present application discloses an igniter for a UAV, which provides a safety pin slot and a pitot tube cap slot on the shell of the UAV, and a safety pin trigger switch and a pitot tube cap trigger switch are provided in the safety pin slot and the pitot tube cap slot respectively, and the safety pin trigger switch and the pitot tube cap trigger switch are electrically connected between the ignition control board and the first ignition button and the second ignition button. Only when the safety pin and the pitot tube cap of the UAV are inserted into the safety pin slot and the pitot tube cap slot, and the ignition control board and the first ignition button and the second ignition button are connected, can the igniter be used for ignition, ensuring that the safety pin and the pitot tube cap of the UAV have been removed before the igniter is used for ignition, thereby ensuring the safety of the UAV's takeoff.

[0036] The above are merely embodiments of the present application, and are not intended to limit the patent scope of the present application. Any equivalent structural transformations made using the contents of the present application specification and drawings, or directly or indirectly applied in other related technical fields, are also included in the patent protection scope of the present application.

Claims

1. A drone igniter, characterized in that: The invention comprises a shell, in which a storage battery, an ignition control board, a first ignition terminal and a second ignition terminal are arranged, the storage battery is electrically connected to the ignition control board, the ignition control board is electrically connected to the first ignition terminal and the second ignition terminal, the first ignition terminal and the second ignition terminal are used to electrically connect the drone, and the shell is provided with a first ignition button and a second ignition button, the first ignition button is electrically connected between the ignition control board and the first ignition terminal, and is used to control the connection between the ignition control board and the first ignition terminal; the second ignition button is electrically connected to the ignition control board and the second ignition terminal, for controlling the connection between the ignition control board and the second ignition terminal; a safety pin slot and a pitot tube cap slot are provided on the shell, and the safety pin slot and the pitot tube cap slot are respectively used to clamp the safety pin and the pitot tube cap of the UAV; a safety pin trigger switch and a pitot tube cap trigger switch are respectively provided in the safety pin slot and the pitot tube cap slot, and the safety pin trigger switch and the pitot tube cap trigger switch are electrically connected between the ignition control board and the first ignition button and the second ignition button, for controlling the connection between the ignition control board and the first ignition button and the second ignition button.

2. The drone igniter according to claim 1, characterized in that: A charging port and a charging switch are provided in the shell, the charging port is electrically connected to the battery, the charging switch is electrically connected between the charging port and the battery, the charging port is used to insert an external charging line, and the charging switch is used to control the connection between the charging port and the battery.

3. The drone igniter according to claim 2, characterized in that: A charging fuse and a battery fuse are arranged in the shell. The charging fuse is electrically connected between the charging switch and the battery to protect charging safety. The battery fuse is electrically connected between the ignition control board and the first ignition button and the second ignition button to protect discharging safety.

4. The drone igniter according to claim 3, characterized in that: An aviation plug port and a 220V plug port are provided at the upper end of the shell, a portable charging cable is inserted between the aviation plug port and the 220V plug port, and the portable charging cable is used to electrically connect the charging port with an external power source.

5. The drone igniter according to claim 4, characterized in that: An ignition preparation switch is provided in the housing, and the ignition preparation switch is electrically connected between the ignition control board and the first ignition key and the second ignition key, and is used to control the connection between the ignition control board and the first ignition key and the second ignition key.

6. The drone igniter according to claim 5, characterized in that: The safety pin trigger switch is electrically connected to a first indicator light, and the first indicator light is used to determine whether the safety pin trigger switch is closed. The pitot tube cap trigger switch is electrically connected to a second indicator light, and the second indicator light is used to determine whether the pitot tube cap trigger switch is closed.

7. The drone igniter according to claim 6, characterized in that: A boost circuit is also provided between the charging switch and the battery. The boost circuit includes an inductor and a boost transformer. The first end of the boost transformer is electrically connected to the inductor, and the fourth end of the boost transformer and the inductor are electrically connected to the charging switch.

8. The drone igniter according to claim 7, characterized in that: The boost circuit is also electrically connected to a rectifier and voltage-doubling energy storage circuit, which includes a first diode, a second diode, a current limiting resistor, a first voltage-doubling capacitor, a second voltage-doubling capacitor and an energy storage capacitor. The first diode and the second diode are both electrically connected to the second end of the boost transformer, the first voltage-doubling capacitor and the second voltage-doubling capacitor are both electrically connected to the third end of the boost transformer, the other end of the first diode is electrically connected to the first voltage-doubling capacitor and the energy storage capacitor, the other end of the second diode is electrically connected to the current limiting resistor, and the other ends of the current limiting resistor are respectively electrically connected to the second voltage-doubling capacitor and the energy storage capacitor.

9. The drone igniter according to claim 8, characterized in that: The ignition control board includes a discharge circuit, which includes a discharge resistor, a gas discharge tube, a high-frequency oscillation capacitor and a high-frequency transformer. The discharge resistor is connected in parallel to the battery and the energy storage capacitor respectively. The first end of the discharge resistor is also electrically connected to the gas discharge tube and the high-frequency oscillation capacitor respectively. The gas discharge tube and the high-frequency oscillation capacitor are both electrically connected to the high-frequency transformer.

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