CN2921855Y - Airplane dynamic position time detector - Google Patents
Airplane dynamic position time detector Download PDFInfo
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- CN2921855Y CN2921855Y CN 200620078962 CN200620078962U CN2921855Y CN 2921855 Y CN2921855 Y CN 2921855Y CN 200620078962 CN200620078962 CN 200620078962 CN 200620078962 U CN200620078962 U CN 200620078962U CN 2921855 Y CN2921855 Y CN 2921855Y
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Abstract
The utility model relates to an airplane dynamic position time detector comprises a wave-shaping circuit, a frequency division circuit, a signal shaping circuit, a control circuit, a data latch, a computer system, wherein, the output of the wave-shaping circuit is connected with the frequency division circuit; the output of the frequency division circuit is connected with the data latch; the output of the data latch is connected with the computer system; the output of the signal shaping circuit is connected with the control circuit; the output of the control circuit is connected with the frequency division circuit and the computer system. The utility model has the advantages of reasonable design, simple structure, small size, light weight, high surveying precision, favorable data accuracy and so forth,and is applicable to the time detection in the dynamic position during airplane flight.
Description
Technical field
The utility model belongs to technical field of radio, is specifically related to the time detection device of aircraft dynamic position.
Background technology
When aircraft aloft flies, the radar that is distributed in two places will detect the aircraft dynamic position respectively over time, require two places to receive the information of flight test simultaneously, data are with 50 groups, every group 20ms output of per second, require the time system precise synchronization of two places receiving equipment, if directly adopt two cover time service type GPS receivers also can meet the demands, still, the receive frequency and the GPS receiver receive frequency of monitoring radar system are very approaching, directly can influence the operate as normal of GPS receiver.The time that will solve the aircraft dynamic position awing is a big technical barrier of flying unit.
Summary of the invention
Technical problem to be solved in the utility model be to provide a kind of reasonable in design, measuring accuracy is high, the data of the surveying time detection device of aircraft dynamic position accurately.
Solving the problems of the technologies described above the technical scheme that is adopted is: it comprises shaping circuit, frequency dividing circuit, signal transformation circuit, control circuit, data latches, computer system, the output termination frequency dividing circuit of shaping circuit, the output termination data latches of frequency dividing circuit, the output termination computer system of data latches, the output terminal connection control circuit of signal transformation circuit, the output termination frequency dividing circuit and the computer system of control circuit.
Control circuit of the present utility model is: 2 pin of integrated circuit U11A connect an end of K switch 1 and connect by R13 that 5V positive source, 5 pin connect 1 pin of integrated circuit U12,3 pin, 1 pin and 4 pin that 6 pin meet integrated circuit U13B connect the 5V positive source, the other end ground connection of K switch 1.13 pin, 5 pin and 15 pin ground connection, 7 pin that 2 pin of integrated circuit U12 meet integrated circuit U5A connect 10 pin of integrated circuit U10B, 1 pin that 4 pin meet integrated circuit U13A.14 pin of integrated circuit U5A connect the end of C2, the other end that 15 pin meet C2 and by R6 connect the 5V positive source, 1 pin connects frequency dividing circuit.6 pin of integrated circuit U10B connect the end of C4, the other end that 7 pin meet C4 and connect by R12 that 5V positive source, 9 pin ground connection, 11 pin connect the 5V positive source, 5 pin connect frequency dividing circuit.Output terminal 4 pin of integrated circuit U13B and output terminal 2 pin of integrated circuit U13A connect computer system.
The utlity model has reasonable in design, simple in structure, volume is little, in light weight, measuring accuracy is high, advantage such as the data of surveying are accurate, can be used for the aircraft time detecting of dynamic position awing.
Description of drawings
Fig. 1 is an electrical principle block scheme of the present utility model.
Fig. 2 is an electronic circuit schematic diagram of the present utility model.
Embodiment
Below in conjunction with drawings and Examples the utility model is further described, but the utility model is not limited to these embodiment.
Fig. 1 is an electrical principle block scheme of the present utility model, referring to Fig. 1.In Fig. 1, the utility model is connected and composed by shaping circuit, frequency dividing circuit, signal transformation circuit, control circuit, data latches, computer system.The output termination frequency dividing circuit of shaping circuit, the output termination data latches of frequency dividing circuit, the output termination computer system of data latches, the output terminal connection control circuit of signal transformation circuit, the output termination frequency dividing circuit and the computer system of control circuit.
It is serial code temporal information and the standard second that directly receives GPS that the utility model start is operated in definition status, by information such as Single Chip Microcomputer (SCM) system decoding generation time, date, longitudes and latitudes.And with the time, the minute, second temporal information extracts the inner software clock that is provided with of initialization single-chip microcomputer, thereby when accomplishing this locality, the UTC time synchronized of minute, second and standard.The standard second (1PPS) of utilizing GPS output by shaping obtain width be the pulse per second (PPS) of 1 μ s through interruption 0 (INTO) and the software clock count pulse of control circuit as computer system, computer system sends standard time information from serial ports.Outside 5MHZ frequency obtains μ s, ms and 1HZ signal by shaping circuit, frequency dividing circuit, division chain be that 1PPS by GPS output finishes under definition status by control circuit synchronously, thereby guarantee that local μ s, ms and 1HZ and UTC's is synchronous.When the utility model is operated under the punctual state, the 1HZ signal that control circuit selects frequency marking to produce obtains 1 μ s pulse as singlechip interruption 0 (INT0) and software clock sprocket pulse by shaping.Control circuit cuts off all information of GPS simultaneously, after flight test begins, the flight information receiving equipment that in a single day radar receives aircraft sends pulse signal positive pulse after shaping immediately and send data latches to latch the temporal information of division chain output, negative pulse is as look-at-me (INT1) the requesting computer read time information of computer system, latch the temporal information of time collecting unit simultaneously, single-chip microcomputer reads in internal memory with this moment (being accurate to 1 μ s), and with broadcast type the generation of incident is sent from serial ports every the 50ms time interval constantly.
In Fig. 2, the shaping circuit of present embodiment is connected and composed by triode T1, triode T2, diode D1, R1～R5, C1.The 5MHz standard-frequency signal is by the end input of C1, the other end of C1 connect by R1 triode T1 base stage, diode D1 negative pole and connect the positive pole of 5V power supply by R2, the base stage of the collector connecting transistor T2 of triode T1 also connects the positive pole of 5V power supply by R3, the collector frequency dividing circuit of triode T2 also connects the 5V positive source by R4, and the emitter of triode T1 and triode T2 and the positive pole of diode D1 are by R5 ground connection.
The signal transformation circuit of present embodiment is connected and composed by integrated circuit U10A, triode T3, diode D2, R9～R11, C3, and the model of integrated circuit U10A is 74HC221.The aircraft aloft moment signal of a certain position is imported by the base stage of triode T3, the base stage of triode T3 connects the negative pole of diode D2 and connects 5V positive source, collector by R9 and connects 1 pin of integrated circuit U10A and connect the plus earth of 5V positive source, emitter and diode D2 by R10, and 2 pin of integrated circuit U10A and 3 pin connect a end that 5V positive source, 14 pin meet C3, the other end that 15 pin meet C3 and connect by R11 that 5V positive source, 13 pin connect frequency dividing circuit, 4 pin connect computer system.
The control circuit of present embodiment is connected and composed by integrated circuit U5A, integrated circuit U11A, integrated circuit U12, integrated circuit U10B, integrated circuit U13A, integrated circuit U13B, R6, R12, R13, C2, C4, K switch 1, and the model of integrated circuit U5A is that the model of 74HC221, integrated circuit U11A is that the model of 74HC74A, integrated circuit U12 is that the model of 74HC157A, integrated circuit U10B is that the model of 74HC221, integrated circuit U13A and integrated circuit U13B is 74HC04.Signal second of GPS is imported by 3 pin of integrated circuit U11A and 3,6 pin of integrated circuit U12,2 pin of integrated circuit U11A connect an end of K switch 1 and connect by R13 that 5V positive source, 5 pin connect 1 pin of integrated circuit U12,3 pin, 1 pin and 4 pin that 6 pin meet integrated circuit U13B connect the 5V positive source, the other end ground connection of K switch 1.13 pin, 5 pin and 15 pin ground connection, 7 pin that 2 pin of integrated circuit U12 meet integrated circuit U5A connect 10 pin of integrated circuit U10B, 1 pin that 4 pin meet integrated circuit U13A.14 pin of integrated circuit U5A connect the end of C2, the other end that 15 pin meet C2 and by R6 connect the 5V positive source, 1 pin connects frequency dividing circuit.6 pin of integrated circuit U10B connect the end of C4, the other end that 7 pin meet C4 and connect by R12 that 5V positive source, 9 pin ground connection, 11 pin connect the 5V positive source, 5 pin connect frequency dividing circuit.Output terminal 4 pin of integrated circuit U13B and output terminal 2 pin of integrated circuit U13A connect computer system.
The frequency dividing circuit of present embodiment is connected and composed by integrated circuit U1A, integrated circuit U1B, integrated circuit U2A, integrated circuit U2B, integrated circuit U3A, integrated circuit U3B, integrated circuit U4A, and the model of integrated circuit U1A, integrated circuit U1B, integrated circuit U2A, integrated circuit U2B, integrated circuit U3A, integrated circuit U3B, integrated circuit U4A is 74HC390.4 pin of integrated circuit U1A connect the collector of triode T2,15 pin that 7 pin meet integrated circuit U1B.12 pin of integrated circuit U1B connect 13 pin, 9～11 and 13 pin by the bus interface data latches, and 1 pin of integrated circuit U2A connects 9 pin of integrated circuit U1B, 4 pin connect 3 pin, 5～7 and 3 pin by the bus interface data latches.7 pin, 12 pin that 15 pin of integrated circuit U2B meet integrated circuit U2A connect 13 pin, 9～11 and 13 pin by the bus interface data latches.9 pin, 4 pin that 1 pin of integrated circuit U3A meets integrated circuit U2B connect 3 pin, 5～7 and 3 pin by the bus interface data latches.7 pin, 12 pin that 15 pin of integrated circuit U3B meet integrated circuit U3A connect 13 pin, 9～11 and 13 pin by the bus interface data latches.9 pin, 4 pin that 1 pin of integrated circuit U4A meets integrated circuit U3B connect 3 pin, 5～7 and 3 pin by the bus interface data latches.5 pin of the integrated circuit U10B of the 2 pin connection control circuits of integrated circuit U1A, integrated circuit U2A, integrated circuit U3A, integrated circuit U4A, 5 pin of the integrated circuit U10B of the 14 pin connection control circuits of integrated circuit U1B, integrated circuit U2B, integrated circuit U3B.
The data latches of present embodiment is made of in succession integrated circuit U6～integrated circuit U8, and the model of integrated circuit U6～integrated circuit U8 is 74HC374.3,4,7,8 pin of integrated circuit U6 connect 13,11,10,9 pin of integrated circuit U1B respectively by bus, and 13,14,17,18 pin of integrated circuit U6 are by 3,5,6,7 pin of bus interface integrated circuit U2A.3,4,7,8 pin of integrated circuit U7 connect 13,11,10,9 pin of integrated circuit U2B respectively by bus, and 13,14,17,18 pin of integrated circuit U7 are by 3,5,6,7 pin of bus interface integrated circuit U3A.3,4,7,8 pin of integrated circuit U8 connect 13,11,10,9 pin of integrated circuit U3B respectively by bus, and 13,14,17,18 pin of integrated circuit U8 are by 3,5,6,7 pin of bus interface integrated circuit U4A.1 pin of integrated circuit U6～integrated circuit U8 connects 13 pin that computer system, 11 pin meet the integrated circuit U10A of signal transformation circuit, and the 1Q of integrated circuit U6～integrated circuit U8～8Q end is by the bus interface computer system.
The computer system of present embodiment is connected and composed by integrated circuit U9, integrated circuit U13C, R14, C5～C7, crystal oscillator JZ, and integrated circuit U9 is that the one-chip computer model is that the model of 89C52, integrated circuit U13C is 74HC04.GPS serial time code signal is through the input end 5 pin input of R13 from integrated circuit U13, and output terminal 6 pin of integrated circuit U13C connect 10 pin of integrated circuit U9.13 pin of integrated circuit U9 connect 4 pin of integrated circuit U10A, 2 pin that 12 pin meet integrated circuit U13A, 4 pin that 23 pin meet integrated circuit U13B, 1 pin that 24 pin meet integrated circuit U8,1 pin that 25 pin meet integrated circuit U7,1 pin that 26 pin meet integrated circuit U6, P00～P07 end respectively 1Q～8Q the end by bus interface integrated circuit U6～integrated circuit U8,18 connect the oscillatory circuit that crystal oscillator JZ and C6 be connected with C7, the end that 9 pin meet C5 with 19 pin, another termination 5V positive source of C5, the 11 pin output aircraft of integrated circuit U9 is the concrete moment of a certain position aloft.
Principle of work of the present utility model is as follows:
High stability crystal oscillator 5MHz signal produces the 1Hz frequency signal and outputs to integrated circuit U12 after the whole T1 of triode, the whole T2 amplification of triode output to frequency dividing circuit and the monostable integer of integrated circuit U5A, integrated circuit U1A～integrated circuit U4A output terminal send the integrated circuit U6～integrated circuit U8 input end 1D～8D of data latches respectively simultaneously.The incident collection outputs to integrated circuit U10A through triode T3 amplification constantly, positive pulse is as the hour hands pulse of integrated circuit U6～integrated circuit U8 after the monostable integer, negative pulse is as the interruption 0 of integrated circuit U9, at this moment the P2.3 of integrated circuit U9～P2.5 output timing pulse is respectively that the gating pulse of integrated circuit U6～integrated circuit U8 of engaging in this profession is read in the moment .GPS serial constantly timecode information of incident, outputs to 10 pin of integrated circuit U9 after integrated circuit U13C is anti-phase.The 1PPS signal of GPS is through control circuit, K switch 1 disconnects at ordinary times, 2 pin of integrated circuit U11A are that high level, Q end are high level, integrated circuit U12 B data are selected, GPS 1PPS output signal is as the look-at-me of integrated circuit U9, and the high level of integrated circuit U11A (Q is non-) after integrated circuit U13B is anti-phase outputs to the P2.2 position control end single-chip microcomputer inside of integrated circuit U9 and walk the software clock.After flight test begins, K switch 1 is connected, the Q end step-down level of integrated circuit U11A, the selected frequency dividing circuit 1PPS of integrated circuit U12A data is as the look-at-me of integrated circuit U9, the low level of integrated circuit U11A end of oppisite phase after integrated circuit U13B is anti-phase outputs to the P2.2 position control end of integrated circuit U9 simultaneously, integrated circuit U9 stops decoding and walks the software clock, and at this moment the utility model can utilize inner oscillating circuit to keep time and finish data collection task.
Claims (2)
1, a kind of time detection device of aircraft dynamic position, it is characterized in that: it comprises shaping circuit, frequency dividing circuit, signal transformation circuit, control circuit, data latches, computer system, the output termination frequency dividing circuit of shaping circuit, the output termination data latches of frequency dividing circuit, the output termination computer system of data latches, the output terminal connection control circuit of signal transformation circuit, the output termination frequency dividing circuit and the computer system of control circuit.
2, according to the time detection device of the described aircraft dynamic position of claim 1, it is characterized in that said control circuit is: 2 pin of integrated circuit U11A connect an end of K switch 1 and connect by R13 that 5V positive source, 5 pin connect 1 pin of integrated circuit U12,3 pin, 1 pin and 4 pin that 6 pin meet integrated circuit U13B connect the 5V positive source, the other end ground connection of K switch 1; 13 pin, 5 pin and 15 pin ground connection, 7 pin that 2 pin of integrated circuit U12 meet integrated circuit U5A connect 10 pin of integrated circuit U10B, 1 pin that 4 pin meet integrated circuit U13A; 14 pin of integrated circuit U5A connect the end of C2, the other end that 15 pin meet C2 and by R6 connect the 5V positive source, 1 pin connects frequency dividing circuit; 6 pin of integrated circuit U10B connect the end of C4, the other end that 7 pin meet C4 and connect by R12 that 5V positive source, 9 pin ground connection, 11 pin connect the 5V positive source, 5 pin connect frequency dividing circuit; Output terminal 4 pin of integrated circuit U13B and output terminal 2 pin of integrated circuit U13A connect computer system.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200620078962 CN2921855Y (en) | 2006-05-12 | 2006-05-12 | Airplane dynamic position time detector |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200620078962 CN2921855Y (en) | 2006-05-12 | 2006-05-12 | Airplane dynamic position time detector |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN2921855Y true CN2921855Y (en) | 2007-07-11 |
Family
ID=38254335
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 200620078962 Expired - Fee Related CN2921855Y (en) | 2006-05-12 | 2006-05-12 | Airplane dynamic position time detector |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN2921855Y (en) |
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2006
- 2006-05-12 CN CN 200620078962 patent/CN2921855Y/en not_active Expired - Fee Related
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C19 | Lapse of patent right due to non-payment of the annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |