CN110203415A - A kind of unmanned plane launch control unit - Google Patents
A kind of unmanned plane launch control unit Download PDFInfo
- Publication number
- CN110203415A CN110203415A CN201910547710.9A CN201910547710A CN110203415A CN 110203415 A CN110203415 A CN 110203415A CN 201910547710 A CN201910547710 A CN 201910547710A CN 110203415 A CN110203415 A CN 110203415A
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- circuit board
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- unmanned plane
- conducting wire
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- 238000001514 detection method Methods 0.000 claims abstract description 21
- 238000010304 firing Methods 0.000 claims description 35
- 238000012360 testing method Methods 0.000 claims description 26
- 238000006243 chemical reaction Methods 0.000 claims description 19
- 238000009432 framing Methods 0.000 claims description 6
- 238000007689 inspection Methods 0.000 claims description 6
- 238000003466 welding Methods 0.000 claims description 6
- 238000012544 monitoring process Methods 0.000 claims description 3
- 230000003014 reinforcing effect Effects 0.000 claims description 2
- 238000000034 method Methods 0.000 description 7
- 238000010586 diagram Methods 0.000 description 5
- 230000005611 electricity Effects 0.000 description 4
- 238000005259 measurement Methods 0.000 description 4
- 238000012790 confirmation Methods 0.000 description 2
- 239000006185 dispersion Substances 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 230000002159 abnormal effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 210000000232 gallbladder Anatomy 0.000 description 1
- 230000013011 mating Effects 0.000 description 1
- 238000000691 measurement method Methods 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
- 230000000007 visual effect Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/04—Ground or aircraft-carrier-deck installations for launching aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Geophysics And Detection Of Objects (AREA)
Abstract
The present invention relates to a kind of unmanned plane launch control units, the present invention is integrated with the detection of launching circuit, igniting component etc., operator does not need in outdoor, after primary connection, it can be rapidly performed by circuit detection at any time, can light a fire with a key, a people while can detect, light a fire, take off operation, original at least three operator is down to an operator, also without the concern for coordination problem.And the environment manually built has certain risk, interface is all made of aerospace connectors to the present invention everywhere, and safety is significantly promoted.
Description
Technical field
The invention belongs to unmanned emission control technical field, it is related to a kind of unmanned plane launch control unit and emission control side
Method, in particular to a kind of autonomous detection launching circuit of realization, and realize the control device of one key of unmanned plane igniting.
Background technique
Zero length lauuch technology is used when small and medium size unmanned aerial vehicles are taken off, and is completed by pencil rocket boosting.In order to ensure nobody
The transmitting of normally taking off of machine, needs aircraft engine, igniting, operator under the commander of commander, is uniformly coordinated operation, together
When need a certain range of visual transmitter site.If ground controls vehicle and car launcher not in same plane or environment ratio
It is more noisy, it is unfavorable for coordination and the commander of commander.In order to ensure the exception that will not light a fire, staff sends out in each unmanned plane
It has to detect launching circuit, igniting component etc. before penetrating.But it manually carries out detecting measurement every time and requires to build
Environment is measured, special testing staff is needed and detects, needs to tell ground control station operator, ground after the completion of detection
After face control station operator is ready to, ignition operation can be carried out by reinforming survey crew, and ground control station operator is same
Shi Jinhang takes off operation, this sequence of operations requires extremely high cooperation,
Meanwhile in order to ensure the exception that will not light a fire, have to detect launching circuit, igniting component etc..
Prior art shortcoming:
1) need personnel more and very high good teamwork degree；
2) need equipment more, intercom, igniting resistance detection device, igniting power supply unit etc., equipment dispersion, occupied space
Greatly；
3) height is required to transmitter site, cannot achieve any place transmitting；
4) there is certain risk, two ignition leads that car launcher comes out are bare wire or connecting terminal, may be connected to
The place of certain pressure difference, leads to abnormal ignition；
5) detection resistance application method is usually instrument measurement method at present, cannot achieve real-time online detection, measurement accuracy
Easily it is affected by human factors.
Summary of the invention
Technical problem solved by the present invention is overcoming in unmanned plane take-off process to avoid the shortcomings of the prior art
The problems such as needing excessive personnel cooperation, equipment dispersion, the present invention propose a kind of high reliablity, integrated level is high, interface is few, it is simple easily
With, can a people complete unmanned plane launch control unit and emission control method.A key measurement and measurement are carried out by the device
As a result the real-time monitoring, it can be achieved that igniter head resistance is uploaded.
The technical scheme is that a kind of unmanned plane launch control unit, including reinforce sealed box body, circuit board, straight
Galvanic electricity source module；The circuit board and DC power supplier, which are located at, reinforces sealed box body bottom, reinforces the box body surface of sealed box body
Can plate be equipped with option of operation component, into according to value judgement for monitoring igniter head resistance value in real time before unmanned plane transmitting
Row ignition operation；DC power supplier is powered after outer power voltage to be converted to the voltage that circuit board uses；Circuit board
Acquire igniter head both ends analog quantity, analog quantity is converted into digital quantity, then framing send, and by option of operation component into
Row operation is implemented.
A further technical solution of the present invention is: the option of operation component includes power supply indicator, power switch, rocket
Ignition switch, rocket firing key, igniting test switch, igniting detection key, the first aerospace connectors, the second aviation connection
Device, third aerospace connectors and trough；The back pin of first aerospace connectors is welded in DC power supplier by conducting wire
Input terminal, the output end and power switch of DC power supplier connect with conducting wire, the energization pins of circuit board, power supply indicator
It is welded respectively with power switch with the enabled switch of rocket firing by conducting wire, the enabled switch of rocket firing passes through conducting wire and rocket point
Fiery key welding；The data pin of instruction key and indicator lamp regions, igniter head check that key passes through conducting wire respectively and circuit board welds
It connects；The back pin and circuit board of second aerospace connectors are welded by conducting wire；The back pin of third aerospace connectors passes through
Conducting wire and igniting test selection switch welding；Igniter head checks that key and rocket firing key pass through conducting wire and igniting test selection
Switch is welded.
A further technical solution of the present invention is: the circuit board includes ignition circuit detection module and serial ports transmitting-receiving mould
Block, wherein ignition circuit detection module includes function conversion circuit and A/D conversion circuit.Function conversion circuit turns resistance signal
For voltage signal, then voltage analog signal is converted to by digital signal by A/D conversion circuit, then framing passes through serial ports and receives and dispatches
Module is sent to the second aerospace connectors.
A further technical solution of the present invention is: the ignition circuit detection module of the circuit board includes A/D converter, quilt
Measuring resistance RX and reference resistance R0；DC voltage is provided to A/D converter, and cooperates reference resistance R0It completes.Measured resistance RXWith
Reference resistance R0Series connection is followed by V+Between COM.V+With VREF+,VREF-With IN+, IN-It is communicated two-by-two with COM.It is converted using A/D
The reference voltage source V of device+, to RXAnd R0Test electric current I is provided.R0On pressure drop VROAlso serve as reference voltage, RXOn pressure drop VRXMake
For input voltage VIN；Measured resistance R is obtained according to Ohm's lawXResistance value, that is, test out the resistance value at igniter head both ends, if
When the value is greater than threshold value, then misfire.
Invention effect
The technical effects of the invention are that: of the invention a kind of unmanned plane launch control unit and emission control method, collection
At the detection of launching circuit, igniting component etc., operator is not needed in outdoor, after primary connection, so that it may at any time
It is rapidly performed by circuit detection, can light a fire with a key, a people while can detect, light a fire, take off operation, it will originally extremely
Few three operators are down to an operator, also without the concern for coordination problem.And the environment manually built has one
Fixed risk, interface is all made of aerospace connectors to the present invention everywhere, and safety is significantly promoted.
Ignition circuit of the invention, i.e. feature capability conversion circuit and A/D converter circuit, detection part are carried out using circuit
Realize, compared with prior art, unmanned plane launch control unit provided by the invention not only high reliablity, integrated level it is high but also
Eliminate security risk, save the cost can both be fixed on that ground control is interior to be used, can also with coupled computer it is in office where
Point uses, and has very high engineering practical value.
A kind of unmanned plane launch control unit panel of the present invention is equipped with instruction area and indicator lamp regions, can be in unmanned plane point
Unmanned plane is detected before fire transmitting, determines the state of unmanned plane if appropriate for taking off.
Detailed description of the invention
Fig. 1 is tray interior schematic diagram of the present invention
Fig. 2 is this hair gallbladder box body panel layout
Fig. 3 is connection schematic diagram in use process of the present invention
Fig. 4 is circuit board functional block diagram of the present invention
Fig. 5 is A/D conversion circuit working principle of the present invention
Fig. 6 is working principle diagram of the present invention
Description of symbols: 1. reinforce sealed box body；2. circuit board；3. DC power supplier；4. 5. electricity of power supply indicator
Source switch；6. the enabled switch of rocket firing；7. rocket firing key；8. igniting test selection switch；9. igniter head checks key；
10. the first aerospace connectors；11. the second aerospace connectors；12. third aerospace connectors；13. trough；14. power and energy is electric
Road；15.A/D conversion circuit；16. serial ports transceiver module
Specific embodiment
Referring to Fig. 1-Fig. 6, unmanned plane launch control unit provided by the invention, including reinforce sealed box body 1.1 bottom of box body
Portion is equipped with circuit board 2 and DC power supplier 3；It reinforces on the box body panel of sealed box body 1 and is opened embedded with power supply indicator 4, power supply
It closes the enabled switch 6 of 5, rocket firing, rocket firing key 7, igniting test selection switch 8, igniter head and checks key 9, trough
13；3 external aerospace connectors 10~12 are housed on box side wall.It reinforces sealed box body 1 to protect each module, so that institute
Unmanned plane launch control unit is stated to adapt in environment such as severe vibration, impact, temperature.
The unmanned plane launch control unit uses 220V Alternating Current Power Supply, exports 24V after the conversion of DC power supplier 3
24V direct current is connected to 5 pin of power switch by direct current, has no-voltage by pulling the control other end pin of power switch 5,
When power switch 5 pulls "ON", direct current 24V electricity is supplied to circuit board 2 and rocket firing enables switch 6.
On the one hand, after circuit board 2 is powered, if igniting test selection switch 8 pulls test lead, while igniter head inspection is pressed
Key 9, the then resistance signal that the ignition circuit detection module of circuit board 2 acquires igniter head both ends are shown in display, grasp at this time
Vertical hand can decide whether to carry out ignition operation according to show value.
On the other hand, the " on " and "off" of switch 6 are enabled by rocket firing, whether control direct current 24V is supplied to fire
Arrow igniting button 7, if igniting button 7 is pressed, direct current 24V can be supplied to igniting test selection switch 8, if igniting test selection is opened
It closes 8 and pulls firing tip, then direct current 24V is connected to igniter head both ends, at this time rocket firing, and unmanned plane is emitted.
As shown in figure 4, circuit board 2 includes ignition circuit detection module and serial ports transceiver module 16, wherein ignition circuit is examined
Surveying module includes function conversion circuit 14 and A/D conversion circuit 15.Resistance signal is switched to voltage signal by function conversion circuit 14,
Voltage analog signal is converted to by digital signal by A/D conversion circuit 15 again, then framing is sent out by serial ports transceiver module 16
It send to the second aerospace connectors 11.
As shown in figure 5, ignition circuit detection module is realized using A/D converter, DC voltage is provided to A/D converter,
And reference resistance R0 is cooperated to complete.Measured resistance RX connects with reference resistance R0 and is followed by between V+ and COM.V+ and VREF+,
VREF- and IN+, IN- are communicated two-by-two with COM.Using the reference voltage source V+ of A/D converter, test electric current is provided to RX and R0
I.Pressure drop VRO on R0 also serves as reference voltage,
Pressure drop VRX on RX can obtain formula according to Ohm's law as input voltage VIN:
So
Steps are as follows for the launch-control operations of the present apparatus:
Step 1: prepare before transmitting；Including following sub-step:
Sub-step one: it is interior that unmanned plane launch control unit is installed on ground control；
Sub-step two: connecting cable；
Step 2: ignition circuit detection, including following sub-step:
Sub-step one: enabling switch 6 for rocket firing and pull connection shelves,
Sub-step two: selection switch 8 is tested into igniting and pulls igniter head inspection end；
Sub-step three: pressing igniter head and check key, check resistance value, judge whether can in secure transmission threshold value, if
Not in range, checks ignition circuit, search problem；If it is within range, it performs the next step rapid.
Step 3: igniting transmitting, comprising the following steps:
Sub-step one: whether what is shown on confirmation ground control vehicle comprehensively monitoring software is that can emit without aircraft and engine
State, if it is not, executing corresponding operating, reach can emission state；
Sub-step two: unmanned in confirmation unmanned plane a certain range to stop；
Sub-step three: selection switch 8 is tested into igniting and pulls rocket firing end；
Sub-step four: rocket firing key is pressed.
Other feature of the present invention is as follows:
The unmanned plane launch control unit sealed box body includes box body and box body panel；
The instruction of needs and flight control instruction etc., the indicator light when described instruction key may include engine test
It is designed according to actual needs；
3 aerospace connectors are housed on the box side wall, are connect for the present apparatus with external equipment；
The unmanned plane launch control unit needs coupled computer to use, and can be installed on ground control car, can also
With the use of coupled computer in any place；
If it is interior in use, needing to design at telltale hole door that the unmanned plane launch control unit is fixed on ground control
Transition aerospace connectors.
Unmanned plane launch control unit of the invention, which integrally uses to reinforce, is equipped with circuit board 2 inside 1. box body 1 of sealed box body
With DC power supplier 3；Reinforcing on the box body panel of sealed box body 1 makes embedded with power supply indicator 4, power switch 5, rocket firing
It can switch 6, rocket firing key 7, igniting test selection switch 8, igniter head inspection key 9, trough 13；It is filled on box side wall
There are 3 external aerospace connectors 10~12.
As shown in figure 3, the mating surface of 3 aerospace connectors 10~12 is calculated with external communication 220V power supply, outside respectively
The RS232 serial ports and firing cable of machine are attached.
The functional block diagram of circuit board 2 as shown in figure 4, resistance signal is switched to voltage signal by function conversion circuit 14,
Voltage analog signal is converted to by digital signal by A/D conversion circuit 15 again, then framing is sent out by serial ports transceiver module 16
It send to the second aerospace connectors 11.
A/D converter realization can be used in A/D conversion circuit as shown in Figure 5, provides DC voltage to A/D converter, and match
Close reference resistance R0It completes.Measured resistance RXWith reference resistance R0Series connection is followed by V+Between COM.V+With VREF+,VREF-With IN+,
IN-It is communicated two-by-two with COM.Utilize the reference voltage source V of A/D converter+, to RXAnd R0Test electric current I is provided.R0On pressure drop
VROAlso serve as reference voltage, RXOn pressure drop VRXAs input voltage VIN, according to ohm
Law can obtain formula:
So
The back pin of first aerospace connectors 10 is welded in the input terminal of DC power supplier 3, direct current by conducting wire
The output end of source module 3 is connect with power switch 5 with conducting wire, energization pins, power supply indicator 4 and the rocket firing of circuit board 2
Enabled switch 6 is welded with power switch 5 respectively by conducting wire, and rocket firing enables switch 6 and passes through conducting wire and rocket firing key 7
Welding；Igniter head checks that the data pin of key 9 is welded by conducting wire and circuit board 2；Draw at the back of second aerospace connectors 11
Foot and circuit board 2 are welded by conducting wire；The back pin of third aerospace connectors 12 passes through conducting wire and igniting test selection switch 8
Welding；Igniter head checks that key 9 is tested selection switch 8 with igniting by conducting wire with rocket firing key 7 and welded.
When power switch 5 pulls "ON", when, power supply indicator 4 lights, and DC power supplier 3 is externally input
AC220V is converted to DC24V, and DC24V voltage supply circuit plate 2, power supply indicator 4 and rocket firing are then enabled switch 6.
Circuit board 2 starts the resistance value at scanning igniting test selection switch 8 simultaneously, forms data frame, is sent to by RS232 serial ports
Second aerospace connectors 11, the second aerospace connectors 11 are attached with computer, are decoded by programming and are realized interface display.Electricity
When source switch 5 is pulled from "ON" to "Off", device power-off stops working.
Rocket firing and test function are unable to simultaneously perform, and are needed to test selection switch 8 by igniting and are selected, are switched
" igniter head inspection " end is pulled, igniter head checks that key 9 is connected to with third aerospace connectors 12, presses igniter head and checks key
9 carry out igniter head resistance value and voltage value inspection；Igniting test selection switch 8 pulls " rocket firing " end, while rocket firing
When enabled switch 6 gets to " on ", rocket firing key 7 is connected to third aerospace connectors 12, is pressed rocket firing key 7 and is held
Row aircraft launch.
In the embodiment of the present invention, it may be preferable that igniting test selection switch 8 is switched using double-pole double throw lockable, rocket point
The enabled switch 6 of fire uses key switch, and on the other hand, for safety, rocket firing key 7 is using the face with warning function
Color.
Present invention is described for embodiments described above, but the invention is not limited to above-mentioned specific embodiment parties
Formula.
Claims (4)
1. a kind of unmanned plane launch control unit, which is characterized in that including reinforcing sealed box body (1), circuit board (2), direct current
Source module (3)；The circuit board (2) and DC power supplier (3), which are located at, reinforces sealed box body (1) bottom, reinforces sealed box body
(1) box body panel is equipped with option of operation component, for monitoring igniter head resistance value in real time before unmanned plane transmitting, according to the value
Can judgement carry out ignition operation；After outer power voltage is converted to the voltage that circuit board (2) uses by DC power supplier (3)
It is powered；Circuit board (2) acquires the analog quantity at igniter head both ends, and analog quantity is converted to digital quantity, and then framing is sent, and
Operation implementation is carried out by option of operation component.
2. a kind of unmanned plane launch control unit as described in claim 1, which is characterized in that the option of operation component includes
Power supply indicator (4), power switch (5), rocket firing switch (6), rocket firing key (7), igniting test switch (8), point
Fire detects key (9), the first aerospace connectors (10), the second aerospace connectors (11), third aerospace connectors (12) and reserves
Area (13)；The back pin of first aerospace connectors (10) is welded in DC power supplier (3 input terminal, direct current by conducting wire
The output end of power module (3) is connect with power switch (5) with conducting wire, the energization pins of circuit board (2), power supply indicator (4)
It is welded respectively with power switch (5) with the enabled switch (6) of rocket firing by conducting wire, the enabled switch (6) of rocket firing is by leading
Line and rocket firing key (7) are welded；The data pin of key and indicator lamp regions (13), igniter head is instructed to check key (9) point
It Tong Guo not conducting wire and circuit board (2) welding；The back pin of second aerospace connectors (11) and circuit board (2) are welded by conducting wire
It connects；The back pin of third aerospace connectors (12) passes through conducting wire and igniting test selection switch (8) welding；Igniter head inspection is pressed
Key (9) is tested selection switch (8) with igniting by conducting wire with rocket firing key (7) and is welded.
3. a kind of unmanned plane launch control unit as described in claim 1, which is characterized in that the circuit board (2) includes a little
Fiery loop detection module and serial ports transceiver module (16), wherein ignition circuit detection module includes function conversion circuit (14) and A/
D conversion circuit (15).Resistance signal is switched to voltage signal by function conversion circuit (14), then passing through A/D conversion circuit (15) will
Voltage analog signal is converted to digital signal, and then framing is sent to the second aerospace connectors by serial ports transceiver module (16)
(11)。
4. a kind of unmanned plane launch control unit as described in claim 1, which is characterized in that the igniting of the circuit board (2)
Loop detection module includes A/D converter (16), measured resistance RX and reference resistance R0；DC voltage is provided to A/D converter,
And cooperate reference resistance R0It completes.Measured resistance RXWith reference resistance R0Series connection is followed by V+Between COM.V+With VREF+,VREF-
With IN+, IN-It is communicated two-by-two with COM.Utilize the reference voltage source V of A/D converter+, to RXAnd R0Test electric current I is provided.R0On
Pressure drop VROAlso serve as reference voltage, RXOn pressure drop VRXAs input voltage VIN；Measured resistance R is obtained according to Ohm's lawXResistance
Value, that is, test out the resistance value at igniter head both ends, if the value is greater than threshold value, misfires.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910547710.9A CN110203415A (en) | 2019-06-24 | 2019-06-24 | A kind of unmanned plane launch control unit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910547710.9A CN110203415A (en) | 2019-06-24 | 2019-06-24 | A kind of unmanned plane launch control unit |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110203415A true CN110203415A (en) | 2019-09-06 |
Family
ID=67794272
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910547710.9A Pending CN110203415A (en) | 2019-06-24 | 2019-06-24 | A kind of unmanned plane launch control unit |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110203415A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112012851A (en) * | 2020-08-31 | 2020-12-01 | 中国人民解放军总参谋部第六十研究所 | Unmanned aerial vehicle cluster boosting rocket ignition control system and working method thereof |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4827397A (en) * | 1987-07-10 | 1989-05-02 | Emerson Electric Co. | Microcomputer-based spark ignition gas burner control system |
| RU2191987C2 (en) * | 2000-12-26 | 2002-10-27 | Государственное унитарное предприятие "Научно-производственный центр ЦНИИточмаш-1" | Device for ignition of electric detonators |
| US20070125256A1 (en) * | 2005-12-07 | 2007-06-07 | Battelle Energy Alliance, Llc | Electronic firing systems and methods for firing a device |
| CN203414022U (en) * | 2013-08-06 | 2014-01-29 | 江西洪都航空工业集团有限责任公司 | Unmanned aerial vehicle rocket launching control box |
| CN104049555A (en) * | 2013-10-22 | 2014-09-17 | 北京理工大学 | Intelligent control device for model rockets |
| CN106523189A (en) * | 2016-10-20 | 2017-03-22 | 南京理工大学 | Rocket firing control system |
| CN107525442A (en) * | 2016-06-21 | 2017-12-29 | 李福霞 | A kind of rocket bomb transmitting circuit |
| CN210555627U (en) * | 2019-06-24 | 2020-05-19 | 西安爱生技术集团公司 | Unmanned aerial vehicle transmission controlling means |
-
2019
- 2019-06-24 CN CN201910547710.9A patent/CN110203415A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4827397A (en) * | 1987-07-10 | 1989-05-02 | Emerson Electric Co. | Microcomputer-based spark ignition gas burner control system |
| RU2191987C2 (en) * | 2000-12-26 | 2002-10-27 | Государственное унитарное предприятие "Научно-производственный центр ЦНИИточмаш-1" | Device for ignition of electric detonators |
| US20070125256A1 (en) * | 2005-12-07 | 2007-06-07 | Battelle Energy Alliance, Llc | Electronic firing systems and methods for firing a device |
| CN203414022U (en) * | 2013-08-06 | 2014-01-29 | 江西洪都航空工业集团有限责任公司 | Unmanned aerial vehicle rocket launching control box |
| CN104049555A (en) * | 2013-10-22 | 2014-09-17 | 北京理工大学 | Intelligent control device for model rockets |
| CN107525442A (en) * | 2016-06-21 | 2017-12-29 | 李福霞 | A kind of rocket bomb transmitting circuit |
| CN106523189A (en) * | 2016-10-20 | 2017-03-22 | 南京理工大学 | Rocket firing control system |
| CN210555627U (en) * | 2019-06-24 | 2020-05-19 | 西安爱生技术集团公司 | Unmanned aerial vehicle transmission controlling means |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112012851A (en) * | 2020-08-31 | 2020-12-01 | 中国人民解放军总参谋部第六十研究所 | Unmanned aerial vehicle cluster boosting rocket ignition control system and working method thereof |
| CN112012851B (en) * | 2020-08-31 | 2023-05-16 | 中国人民解放军总参谋部第六十研究所 | Unmanned aerial vehicle cluster boosting rocket ignition control system and working method thereof |
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