CN210555627U - Unmanned aerial vehicle transmission controlling means - Google Patents
Unmanned aerial vehicle transmission controlling means Download PDFInfo
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- CN210555627U CN210555627U CN201920961031.1U CN201920961031U CN210555627U CN 210555627 U CN210555627 U CN 210555627U CN 201920961031 U CN201920961031 U CN 201920961031U CN 210555627 U CN210555627 U CN 210555627U
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Abstract
The utility model relates to an unmanned aerial vehicle transmission controlling means, the utility model discloses integrateed the detection of transmission return circuit, ignition components and parts etc. operating personnel need not be outdoor, once connect the back, just can be quick at any time carry out the return circuit and detect, can ignite by a key, can alone detect simultaneously, ignite, the aircraft operation of taking off, will originally at least three operating personnel fall to an operating personnel, need not consider coordination cooperation problem yet. And the environment of artifical buildding has certain danger, the utility model discloses the interface all adopts the aviation connector everywhere, and the security promotes by a wide margin.
Description
Technical Field
The invention belongs to the technical field of unmanned launch control, relates to an unmanned aerial vehicle launch control device and a launch control method, and particularly relates to a control device for realizing autonomous detection of a launch loop and realizing one-key ignition of an unmanned aerial vehicle.
Background
The small and medium unmanned aerial vehicle adopts a zero-length launching technology when taking off and is completed by the aid of small rocket boosting. In order to ensure normal takeoff and launching of the unmanned aerial vehicle, an aircraft engine, ignition and operation personnel are required to perform unified coordination operation under the command of a commander, and meanwhile, a visible launching site in a certain range is required. If the ground control vehicle and the launching vehicle are not on the same plane or the environment is noisy, the coordination and the command of a commander are not facilitated. In order to ensure that the ignition is not abnormal, the staff must detect a transmitting loop, an ignition component and the like before the unmanned aerial vehicle transmits every time. However, each measurement is manually detected by building a measurement environment, a special detector is needed for detection, the operator of the ground control station needs to be informed after the detection is finished, the operator of the ground control station is informed of the ignition operation after the operator of the ground control station is ready, the operator of the ground control station simultaneously performs the airplane takeoff operation, and the series of operations all need extremely high cooperation,
meanwhile, in order to ensure that ignition abnormality is not caused, the transmitting loop, the ignition component and the like are required to be detected.
The prior art has the following defects:
1) the number of required personnel is large, and the matching default degree is high;
2) the required equipment is many, the interphone, the ignition resistance detection device, the ignition power supply device and the like are dispersed, and the occupied space is large;
3) the requirement on a launching site is high, and the launching of any site cannot be realized;
4) the two ignition wires from the launching vehicle are bare wires or wiring terminals and may be connected to a place with a certain pressure difference, so that abnormal ignition is caused;
5) the existing method for detecting the resistance is generally an instrument measuring method, real-time online detection cannot be realized, and the measuring precision is easily influenced by human factors.
Disclosure of Invention
The technical problem solved by the invention is as follows: in order to avoid the defects in the prior art and overcome the problems of excessive personnel cooperation, equipment dispersion and the like in the takeoff process of the unmanned aerial vehicle, the invention provides the unmanned aerial vehicle launching control device and the launching control method which have the advantages of high reliability, high integration level, few interfaces, simplicity, easiness in use and capability of being completed by one person. The device is used for one-key measurement and uploading of the measurement result, so that the real-time monitoring of the resistance of the ignition head can be realized.
The technical scheme of the invention is as follows: an unmanned aerial vehicle launching control device comprises a reinforced sealing box body, a circuit board and a direct-current power supply module; the circuit board and the direct-current power supply module are positioned at the bottom of the reinforced sealing box body, and an operation option assembly is arranged on a box body panel of the reinforced sealing box body and used for monitoring the resistance value of the ignition head in real time before the unmanned aerial vehicle is launched and judging whether ignition operation can be carried out or not according to the value; the direct current power supply module converts the voltage of an external power supply into the voltage used by the circuit board and then supplies power; the circuit board collects analog quantities at two ends of the ignition head, converts the analog quantities into digital quantities, frames the digital quantities, and operates and implements the digital quantities through the operation option assembly.
The further technical scheme of the invention is as follows: the operation option component comprises a power indicator light, a power switch, a rocket ignition key, an ignition test switch, an ignition detection key, a first aviation connector, a second aviation connector, a third aviation connector and a reserved area; a back pin of the first aviation connector is welded at the input end of the direct-current power supply module through a wire, the output end of the direct-current power supply module is connected with the power switch through a wire, a power supply pin of the circuit board, the power indicator lamp and the rocket ignition enabling switch are respectively welded with the power switch through wires, and the rocket ignition enabling switch is welded with the rocket ignition key through a wire; the instruction key, the data pin of the indicator lamp area and the ignition head inspection key are respectively welded with the circuit board through wires; the back pin of the second aviation connector is welded with the circuit board through a lead; a back pin of the third aviation connector is welded with the ignition test selection switch through a lead; the ignition head check key and the rocket ignition key are welded with the ignition test selection switch through the conducting wire.
The further technical scheme of the invention is as follows: the circuit board comprises an ignition loop detection module and a serial port transceiving module, wherein the ignition loop detection module comprises a function conversion circuit and an A/D conversion circuit. The function conversion circuit converts the resistance signal into a voltage signal, the A/D conversion circuit converts the voltage analog signal into a digital signal, and then framing is sent to the second aviation connector through the serial port receiving and sending module.
The further technical scheme of the invention is as follows: the ignition loop detection module of the circuit board comprises an A/D converter, a detected resistor RX and a reference resistor R0; providing DC voltage to A/D converter in cooperation with reference resistor R0And (4) finishing. Measured resistance RXAnd a reference resistance R0Connected in series and then connected at V+And COM. V+And VREF+,VREF-and IN+，IN-Communicated with COM in pairs. Reference voltage source V using A/D converter+To RXAnd R0A test current I is provided. R0Pressure drop V overROAlso serving as a reference voltage, RXPressure drop V overRXAs an input voltage VIN(ii) a Obtaining the measured resistance R according to ohm lawXThe resistance value of the ignition head is tested, and if the resistance value is larger than the threshold value, the ignition is not started.
Effects of the invention
The invention has the technical effects that: according to the unmanned aerial vehicle launching control device and the launching control method, detection of the launching loop, the ignition component and the like is integrated, operators do not need to be outdoors, loop detection can be performed rapidly at any time after one-time connection, ignition can be performed by one key, detection, ignition and airplane takeoff operation can be performed by one person at the same time, at least three original operators are descended to one operator, and coordination and cooperation problems do not need to be considered. And the environment built manually has certain danger, and each interface of the invention adopts an aviation connector, so that the safety is greatly improved.
Compared with the prior art, the unmanned aerial vehicle launching control device provided by the invention has the advantages that the reliability is high, the integration level is high, the potential safety hazard is eliminated, the cost is saved, the unmanned aerial vehicle launching control device can be fixed in a ground control vehicle for use, can also be matched with a computer for use in any place, and has very high engineering practical value.
The panel of the unmanned aerial vehicle launching control device is provided with the instruction area and the indicator light area, so that the unmanned aerial vehicle can be detected before the unmanned aerial vehicle is ignited and launched, and whether the state of the unmanned aerial vehicle is suitable for taking off or not is determined.
Drawings
FIG. 1 is a schematic view of the inside of the case according to the present invention
FIG. 2 is a layout view of the top panel of the hair-pin container
FIG. 3 is a schematic view of the connection during the use of the present invention
FIG. 4 is a schematic block diagram of a circuit board of the present invention
FIG. 5 shows the operation principle of the A/D conversion circuit of the present invention
FIG. 6 is a schematic diagram of the operation of the present invention
Description of reference numerals: 1. reinforcing the sealed box body; 2. a circuit board; 3. a DC power supply module; 4. a power supply indicator lamp 5, a power supply switch; 6. a rocket firing enable switch; 7. a rocket ignition key; 8. an ignition test selection switch; 9. an ignition head inspection key; 10. a first aeronautical connector; 11. a second aeronautical connector; 12. a third aeronautical connector; 13. a reserved area; 14. a function conversion circuit; an A/D conversion circuit; 16. serial port receiving and transmitting module
Detailed Description
Referring to fig. 1-6, the launch control device for the unmanned aerial vehicle provided by the invention comprises a reinforced sealed box body 1. The bottom of the box body 1 is provided with a circuit board 2 and a direct current power supply module 3; a power indicator lamp 4, a power switch 5, a rocket ignition enabling switch 6, a rocket ignition key 7, an ignition test selection switch 8, an ignition head check key 9 and a reserved area 13 are embedded in a box body panel of the reinforced sealing box body 1; the lateral wall of the box body is provided with 3 external aviation connectors 10-12. Consolidate sealed box body 1 and protect each module to make unmanned aerial vehicle transmission controlling means can adapt to environment such as abominable vibration, impact, temperature.
The unmanned aerial vehicle launch control device adopts 220V alternating current power supply, outputs 24V direct current after the conversion of the direct current power supply module 3, connects the 24V direct current to the pin of the power switch 5, controls the pin at the other end to have or not have voltage by pulling the power switch 5, and when the power switch 5 is pulled to be turned on, the direct current 24V power is supplied to the circuit board 2 and the rocket ignition enabling switch 6.
On one hand, after the circuit board 2 is powered on, if the ignition test selection switch 8 is switched to the test end, and the ignition head check key 9 is pressed at the same time, the ignition loop detection module of the circuit board 2 collects resistance signals at two ends of the ignition head and displays the resistance signals on the display, and at the moment, the manipulator can determine whether to perform ignition operation according to the display value.
On the other hand, whether the direct current 24V is supplied to the rocket ignition key 7 or not is controlled through the connection and disconnection of the rocket ignition enabling switch 6, if the ignition key 7 is pressed down, the direct current 24V can be supplied to the ignition test selection switch 8, if the ignition test selection switch 8 is pulled to the ignition end, the direct current 24V is connected to the two ends of the ignition head, the rocket is ignited at the moment, and the unmanned aerial vehicle launches.
As shown in fig. 4, the circuit board 2 includes an ignition loop detection module and a serial port transceiver module 16, wherein the ignition loop detection module includes a function conversion circuit 14 and an a/D conversion circuit 15. The function conversion circuit 14 converts the resistance signal into a voltage signal, converts the voltage analog signal into a digital signal through the a/D conversion circuit 15, and then frames the digital signal and sends the digital signal to the second aviation connector 11 through the serial port transceiver module 16.
As shown in fig. 5, the ignition loop detection module is implemented by using an a/D converter, and provides a dc voltage to the a/D converter, and is implemented by matching with a reference resistor R0. The measured resistor RX and the reference resistor R0 are connected in series and then connected between V + and COM. V + and VREF +, VREF-and IN +, IN-and COM are communicated IN pairs. The test current I is supplied to RX and R0 using the reference voltage source V + of the a/D converter. The voltage drop VRO across R0 doubles as the reference voltage,
the voltage drop VRX across RX is used as the input voltage VIN, and the formula can be obtained according to ohm's law:
therefore, it is not only easy to use
The emission control operation steps of the device are as follows:
the method comprises the following steps: preparing before transmitting; the method comprises the following substeps:
the first substep: installing an unmanned aerial vehicle launching control device in a ground control vehicle;
and a second substep: connecting a cable;
step two: ignition loop detection comprising the sub-steps of:
the first substep: the rocket ignition enabling switch 6 is pulled to the connection gear,
and a second substep: turning an ignition test selection switch 8 to an ignition head inspection end;
and a third substep: pressing an ignition head check key, checking a resistance value, judging whether the resistance value is within a safe emission threshold value, and if the resistance value is not within the range, checking an ignition loop and searching for problems; if so, executing the next step.
Step three: firing the fire, comprising the steps of:
the first substep: confirming whether the plane-free engine and the engine displayed on the ground control vehicle comprehensive monitoring software are in a dischargeable state or not, and if not, executing corresponding operation to reach the dischargeable state;
and a second substep: confirming that the unmanned aerial vehicle stays within a certain range;
and a third substep: turning an ignition test selection switch 8 to a rocket ignition end;
and a fourth substep: the rocket ignition key is pressed.
Other features of the invention are as follows:
the unmanned aerial vehicle launching control device sealed box body comprises a box body and a box body panel;
the instruction key can comprise an instruction, a flight control instruction and the like required by the trial run of the engine, and the indicator lamp is designed according to actual requirements;
the side wall of the box body is provided with 3 aviation connectors for connecting the device with external equipment;
the unmanned aerial vehicle launching control device needs to be matched with a computer for use, can be arranged in a ground control vehicle, and can also be matched with the computer for use at any place;
when being fixed in the ground control car and using, unmanned aerial vehicle transmission controlling means need design transition aviation connector in signal hole door department.
The unmanned aerial vehicle launch control device integrally adopts a reinforced sealing box body 1, and a circuit board 2 and a direct-current power supply module 3 are arranged in the box body 1; a power indicator lamp 4, a power switch 5, a rocket ignition enabling switch 6, a rocket ignition key 7, an ignition test selection switch 8, an ignition head check key 9 and a reserved area 13 are embedded in a box body panel of the reinforced sealing box body 1; the lateral wall of the box body is provided with 3 external aviation connectors 10-12.
As shown in FIG. 3, the insertion surfaces of the 3 aviation connectors 10-12 are respectively connected with an external alternating current 220V power supply, an RS232 serial port of an external computer and an ignition cable.
The functional conversion circuit 14 converts the resistance signal into a voltage signal, the a/D conversion circuit 15 converts the voltage analog signal into a digital signal, and the serial port transceiver module 16 transmits the digital signal to the second aviation connector 11.
The A/D converter circuit shown in FIG. 5 can be realized by using an A/D converter to provide DC voltage for the A/D converter, and matching with a reference resistor R0And (4) finishing. Measured resistance RXAnd a reference resistance R0Connected in series and then connected at V+And COM. V+And VREF+,VREF-And IN+，IN-Communicated with COM in pairs. Reference voltage source V using A/D converter+To RXAnd R0A test current I is provided. R0Pressure drop V overROAlso serving as a reference voltage, RXPressure drop V overRXAs an input voltage VINAccording to ohm
The law can be given by the formula:
therefore, it is not only easy to use
A back pin of the first aviation connector 10 is welded to an input end of the direct-current power supply module 3 through a wire, an output end of the direct-current power supply module 3 is connected with the power switch 5 through a wire, a power supply pin of the circuit board 2, the power indicator lamp 4 and the rocket ignition enabling switch 6 are respectively welded with the power switch 5 through wires, and the rocket ignition enabling switch 6 is welded with the rocket ignition key 7 through a wire; the data pin of the ignition head check key 9 is welded with the circuit board 2 through a lead; the back pin of the second aviation connector 11 is welded with the circuit board 2 through a lead; the back pin of the third aviation connector 12 is welded with the ignition test selection switch 8 through a lead; the ignition head check key 9 and the rocket ignition key 7 are welded with the ignition test selection switch 8 through a lead.
When the power switch 5 is turned on, the power indicator lamp 4 is lit, the DC power module 3 converts the externally input AC220V into DC24V, and then supplies the DC24V voltage to the circuit board 2, the power indicator lamp 4, and the rocket ignition enable switch 6. And meanwhile, the circuit board 2 starts to scan the resistance value at the ignition test selection switch 8 to form a data frame, the data frame is sent to the second aviation connector 11 through the RS232 serial port, the second aviation connector 11 is connected with a computer, and interface display is achieved through programming and decoding. When the power switch 5 is turned from on to off, the device is powered off and stops working.
The rocket ignition and test functions can not be executed simultaneously, selection is carried out through an ignition test selection switch 8, the switch is switched to an ignition head inspection end, an ignition head inspection key 9 is communicated with a third aviation connector 12, and the ignition head inspection key 9 is pressed down to carry out ignition head resistance value and voltage value inspection; and the ignition test selection switch 8 is turned to a rocket ignition end, and when the rocket ignition enabling switch 6 is turned to be turned on, the rocket ignition key 7 is communicated with the third aviation connector 12, and the rocket ignition key 7 is pressed down to execute launching and taking off of the airplane.
In the embodiment of the invention, preferably, the ignition test selection switch 8 adopts a double-pole double-throw lockable switch, the rocket ignition enabling switch 6 adopts a key switch, and on the other hand, the rocket ignition key 7 adopts a color with a warning function for safety.
The present invention is described in the above-mentioned examples, but the present invention is not limited to the above-mentioned specific embodiments.
Claims (4)
1. An unmanned aerial vehicle emission control device is characterized by comprising a reinforced sealing box body (1), a circuit board (2) and a direct-current power supply module (3); the circuit board (2) and the direct-current power supply module (3) are positioned at the bottom of the reinforced sealing box body (1), and an operation option assembly is arranged on a box body panel of the reinforced sealing box body (1) and used for monitoring the resistance value of an ignition head in real time before the unmanned aerial vehicle is launched, and judging whether ignition operation can be carried out or not according to the value; the direct current power supply module (3) converts the external power supply voltage into the voltage used by the circuit board (2) and then supplies power; the circuit board (2) collects analog quantities at two ends of the ignition head, converts the analog quantities into digital quantities, frames the digital quantities, and operates and implements the digital quantities through the operation option assembly.
2. The unmanned aerial vehicle launch control apparatus of claim 1, wherein the operational option components comprise a power indicator (4), a power switch (5), a rocket ignition enable switch (6), a rocket ignition key (7), an ignition test selection switch (8), an ignition head check key (9), a first aerial connector (10), a second aerial connector (11), a third aerial connector (12), and a reserved area (13); a back pin of the first aviation connector (10) is welded to an input end of the direct-current power supply module (3) through a wire, an output end of the direct-current power supply module (3) is connected with the power switch (5) through a wire, a power supply pin of the circuit board (2), the power indicator lamp (4) and the rocket ignition enabling switch (6) are respectively welded with the power switch (5) through wires, and the rocket ignition enabling switch (6) is welded with the rocket ignition key (7) through a wire; the data pin of the instruction key and the reserved area (13) and the ignition head check key (9) are respectively welded with the circuit board (2) through leads; the back pin of the second aviation connector (11) is welded with the circuit board (2) through a lead; the back pin of the third aviation connector (12) is welded with the ignition test selection switch (8) through a lead; the ignition head check key (9) and the rocket ignition key (7) are welded with the ignition test selection switch (8) through a lead.
3. An unmanned aerial vehicle launch control apparatus according to claim 1, characterised in that the circuit board (2) comprises an ignition loop detection module and a serial port transceiver module (16), wherein the ignition loop detection module comprises a function conversion circuit (14) and an a/D conversion circuit (15); the function conversion circuit (14) converts the resistance signal into a voltage signal, the A/D conversion circuit (15) converts the voltage analog signal into a digital signal, and then the digital signal is framed and sent to the second aviation connector (11) through the serial port transceiving module (16).
4. An unmanned aerial vehicle launch control apparatus according to claim 1, characterised in that the firing loop detection module of the circuit board (2) comprises an a/D converter, a measured resistor RX and a reference resistor R0; providing DC voltage to A/D converter in cooperation with reference resistor R0Completing the process; measured resistance RXAnd a reference resistance R0Connected in series and then connected at V+And COM; v+And VREF+,VREF-And IN+IN-and COM are communicated pairwise; reference voltage source V using A/D converter+To RXAnd R0Providing a test current I; r0Pressure drop V overROAlso serving as a reference voltage, RXPressure drop V overRXAsInput voltage VIN；Obtaining the measured resistance R according to ohm lawXThe resistance value of the ignition head is tested, and if the resistance value is larger than the threshold value, the ignition is not started.
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| CN201920961031.1U CN210555627U (en) | 2019-06-24 | 2019-06-24 | Unmanned aerial vehicle transmission controlling means |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110203415A (en) * | 2019-06-24 | 2019-09-06 | 西安爱生技术集团公司 | A kind of unmanned plane launch control unit |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110203415A (en) * | 2019-06-24 | 2019-09-06 | 西安爱生技术集团公司 | A kind of unmanned plane launch control unit |
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Address after: No.34, Fenghui South Road, Xi'an, Shaanxi 710065 Patentee after: Xi'an Aisheng Technology Group Co.,Ltd. Patentee after: Northwestern Polytechnical University Address before: No.34, Fenghui South Road, Xi'an, Shaanxi 710065 Patentee before: XI'AN AISHENG TECHNOLOGY GROUP Co.,Ltd. Patentee before: Northwestern Polytechnical University |
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Effective date of registration: 20221130 Address after: No.34, Fenghui South Road, Xi'an, Shaanxi 710065 Patentee after: Xi'an Aisheng Technology Group Co.,Ltd. Address before: No.34, Fenghui South Road, Xi'an, Shaanxi 710065 Patentee before: Xi'an Aisheng Technology Group Co.,Ltd. Patentee before: Northwestern Polytechnical University |