CN208141229U - Navigation of Pilotless Aircraft communication integral system - Google Patents
Navigation of Pilotless Aircraft communication integral system Download PDFInfo
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- CN208141229U CN208141229U CN201820766824.3U CN201820766824U CN208141229U CN 208141229 U CN208141229 U CN 208141229U CN 201820766824 U CN201820766824 U CN 201820766824U CN 208141229 U CN208141229 U CN 208141229U
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Abstract
The utility model provides a kind of Navigation of Pilotless Aircraft communication integral system, including satellite navigation flight control system and data image delivering system；The satellite navigation flight control system and data image transfer system encapsulation are in the same housing；Satellite navigation flight control system includes satellite earth antenna, the 1st radio-frequency channel processing circuit, analog-digital converter, the 1st programmable logic chip, the 1st processor, attitude measuring and steering engine.Advantage is：Satellite navigation flight control system and the encapsulation of data image delivering system in the same housing, therefore, can effectively reduce space on the machine of occupancy, simplied system structure.
Description
Technical field
The utility model belongs to airborne land navigation communication reception technique field, and in particular to a kind of Navigation of Pilotless Aircraft communication
Integral system.
Background technique
It is more and more important that modern military theory and the developing direction of war mode play the part of unmanned plane in future war
Role.Unmanned plane has played important function with its distinctive mode of operation and fighting efficiency in war.In following anti-air battle
In, unmanned plane will become a kind of important air-supported threat, bring stern challenge to air defense operation.
With the application of Satellite Navigation Technique, wireless communication technique and imaging technique on unmanned plane, unmanned plane is in war
The effect of middle performance is more and more comprehensive, and unmanned plane is more next in the advantage of the fields of military operations such as target reconnaissance, tactics strike, relay communication
It is more obvious, traditional unmanned plane satellite navigation part, number pass part, inertial navigation part is respectively adopted independent module and is set
Meter, also, modules are loaded on respectively in different shells, cause space on occupancy machine big.In addition, in traditional scheme, nobody
Machine only configures a set of wireless transceiver system, causes the load of wireless transceiver system big, communication efficiency is low.
Utility model content
In view of the defects existing in the prior art, the utility model provides a kind of Navigation of Pilotless Aircraft communication integral system, can
Effectively solve the above problems.
The technical solution adopted in the utility model is as follows：
The utility model provides a kind of Navigation of Pilotless Aircraft communication integral system, including satellite navigation flight control system and data
Image delivering system；The satellite navigation flight control system and data image transfer system encapsulation are in the same housing；
The satellite navigation flight control system include satellite earth antenna, the 1st radio-frequency channel processing circuit, analog-digital converter,
1st programmable logic chip, the 1st processor, attitude measuring and steering engine；Wherein, the output of the satellite earth antenna
After end passes sequentially through the 1st radio-frequency channel processing circuit and the analog-digital converter, it is connected to the 1st programmable logic core
The input terminal of piece；1st programmable logic chip is bi-directionally connected with the 1st processor；The attitude measuring it is defeated
Outlet is connected to the input terminal of the 1st programmable logic chip；The output end of 1st programmable logic chip is connected to institute
State the input terminal of steering engine；
The data image transfer system includes the 1st wireless transceiver system, the 2nd wireless transceiver system, at the 2nd radio-frequency channel
Manage circuit, the 2nd programmable logic chip, the 2nd processor and image acquisition and processing device；1st wireless transceiver system and institute
The 2nd wireless transceiver system is stated to connect with the 2nd radio-frequency channel processing circuit；The 2nd radio-frequency channel processing circuit and institute
The 2nd programmable logic chip is stated to be bi-directionally connected；The output end of described image Acquisition Processor and the 2nd programmable logic chip
Input terminal connection；2nd programmable logic chip is bi-directionally connected with the 2nd processor；
Also, the 1st programmable logic chip and the 2nd programmable logic chip are bi-directionally connected.
Preferably, the attitude measuring includes：Angular velocity measurement device, acceleration measurement device and tachometric survey
Device.
Preferably, the 1st wireless transceiver system includes that number passes transmitting antenna sum number biography receiving antenna；Described 2nd is wireless
Receive-transmit system includes that figure passes transmitting antenna and schemes to pass receiving antenna.
Navigation of Pilotless Aircraft communication integral system provided by the utility model has the following advantages that：
(1) satellite navigation flight control system and the encapsulation of data image delivering system in the same housing, therefore, can effectively drop
Space on the machine of low occupancy, simplied system structure；
(2) therefore two sets of independent wireless transceiver systems of data image transfer system configuration can effectively reduce each wireless
The load of receive-transmit system improves communication efficiency.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of Navigation of Pilotless Aircraft communication integral system provided by the utility model；
Fig. 2 is flight control principle structure chart in satellite navigation flight control system provided by the utility model.
Specific embodiment
The technical issues of in order to keep the utility model solved, technical solution and beneficial effect are more clearly understood, below
In conjunction with accompanying drawings and embodiments, the present invention will be further described in detail.It should be appreciated that specific implementation described herein
Example only to explain the utility model, is not used to limit the utility model.
With reference to Fig. 1, the utility model provides a kind of Navigation of Pilotless Aircraft communication integral system, including satellite navigation flies control system
System and data image delivering system；Satellite navigation flight control system and data image delivering system encapsulation in the same housing, by
In the same housing in satellite navigation flight control system and the encapsulation of data image delivering system, therefore, it can effectively reduce occupancy
Space on machine, simplied system structure.In addition, due to satellite navigation flight control system and data image delivering system be encapsulated in it is same
In shell, to prevent the circuit board between the two systems from interfering, the application also uses a kind of special designing, i.e.,：In shell
Portion, the 1st circuit board of satellite navigation flight control system is supported by support column to be fixed；It is recessed in the surrounding setting the 1st of the 1st circuit board
Slot covers the 1st circuit board using the 1st shielding case, and extend into the 1st shielding case in the 1st groove；Equally, data image transfer
2nd circuit board of system is supported by support column and is fixed；The 2nd groove is set in the surrounding of the 2nd circuit board, using the 2nd shielding case
The 2nd circuit board is covered, and extend into the 2nd shielding case in the 1st groove；It, can using the sealing fit structure of shielding case and groove
To effectively prevent the electromagnetic wave in the 1st circuit board to enter in the 2nd shielding case from the side of circuit board, it is also possible to effectively anti-
Only the electromagnetic wave in the 2nd circuit board enters in the 1st shielding case from the side of circuit board, and therefore, effectively reducing the two is
Circuit board interference between system, guarantees the stability of system work.
Satellite navigation flight control system include satellite earth antenna, the 1st radio-frequency channel processing circuit, analog-digital converter, the 1st can
Programmed logic chip, the 1st processor, attitude measuring and steering engine；Wherein, the output end of satellite earth antenna passes sequentially through
After 1st radio-frequency channel processing circuit and analog-digital converter, it is connected to the input terminal of the 1st programmable logic chip；1st programmable patrols
Chip is collected to be bi-directionally connected with the 1st processor；The output end of attitude measuring is connected to the input of the 1st programmable logic chip
End；The output end of 1st programmable logic chip is connected to the input terminal of steering engine；Wherein, attitude measuring includes：Angular speed is surveyed
Measure device, acceleration measurement device and velocity measuring device.
Its working principle is that：Satellite earth antenna receives the satellite-signal of satellite launch, and satellite-signal is sent to the 1st
Radio-frequency channel processing circuit；1st radio-frequency channel processing circuit amplifies the satellite-signal received, filter and down coversion at
Reason, after radiofrequency signal is converted to intermediate-freuqncy signal, is sent to analog-digital converter；Analog-digital converter turns the analog signal received
After being changed to digital signal, satellite navigation is obtained as a result, satellite navigation result is sent to the 1st programmable logic chip；Posture is surveyed
It measures device and exports unmanned plane current pose information, including：Unmanned plane speed, unmanned plane angular speed and unmanned plane acceleration, and will
Unmanned plane current pose information is sent to the 1st programmable logic chip；1st programmable logic chip believes unmanned plane current pose
Breath and satellite navigation result are compared, and generate the control instruction to steering engine, and be sent to steering engine, thus change adjustment unmanned plane
Posture.Its working principle can refer to Fig. 2.Unmanned plane Installation posture measurement sensor and trajectory measurement sensor；Attitude measurement passes
The output end of sensor is connected to the 1st input terminal of external loop controller；The output end of trajectory measurement sensor passes through guiding control
Device is connected to the 1st input terminal of the 1st comparator；2nd input terminal of the 1st comparator is connect with command receiver；1st comparator
Output end is connected to the 2nd input terminal of external loop controller；The output end of external loop controller is connected to the 1st of the 2nd comparator
Input terminal；2nd input terminal of the 2nd comparator and the output end of attitude-measuring sensor connect；3rd input terminal of the 2nd comparator
It is connect with feedforward controller；After the output end of 2nd comparator passes through positive controller, it is connected to steering engine for unmanned plane.Its work is former
Reason is：1st comparator sends instructions and unmanned plane real-time track under, generates the 1st adjustment control signal；External loop controller root
According to the 1st adjustment control signal and unmanned plane current pose, the 2nd adjustment control signal is generated；2nd comparator is according to feedforward controller
Control stick instruction, the 2nd adjustment control signal and unmanned plane current pose, generate the 3rd adjustment control signal, and act on rudder
Machine changes posture and the track of unmanned plane by steering engine, realizes UAV Attitude and track according to target posture and track operation.
Data image transfer system includes the 1st wireless transceiver system, the 2nd wireless transceiver system, the 2nd radio-frequency channel processing electricity
Road, the 2nd programmable logic chip, the 2nd processor and image acquisition and processing device；1st wireless transceiver system and the 2nd wireless receiving and dispatching
System is connect with the 2nd radio-frequency channel processing circuit；2nd radio-frequency channel processing circuit and the 2nd two-way company of programmable logic chip
It connects；The output end of image acquisition and processing device is connect with the input terminal of the 2nd programmable logic chip；2nd programmable logic chip with
2nd processor is bi-directionally connected；Wherein, the 1st wireless transceiver system includes that number passes transmitting antenna sum number biography receiving antenna；2nd is wireless
Receive-transmit system includes that figure passes transmitting antenna and schemes to pass receiving antenna.Also, the 1st programmable logic chip and the 2nd programmable logic
Chip is bi-directionally connected.
Its working principle is that：1st wireless transceiver system is used to communicate with ground control station, receives ground control station uplink
Command information, make ground handling operator can manual manipulation unmanned plane carry out relevant action, it is lower to pass the position of unmanned plane itself, speed
Degree, state and the image information of shooting；
2nd wireless transceiver system is used to carry out the communication between multiple UAVs, the control of Broadcast Terrestrial tracking telemetry and command station uplink
Instruction and data forwards the image and video data of each unmanned plane shooting；
The camera module of image acquisition and processing device gives the image of shooting or video to the 2nd wireless transceiver system, will
Image data is launched, and unmanned plane photographing module is supported visible light and shot using visible light on infrared camera, daytime,
Night is shot using infrared camera, realizes all weather operations.
Therefore two sets of independent wireless transceiver systems of data image transfer system configuration can effectively reduce each wireless receipts
The load of hair system improves communication efficiency.
Navigation of Pilotless Aircraft communication integral system provided by the utility model has the following advantages that：
(1) satellite navigation flight control system and the encapsulation of data image delivering system in the same housing, therefore, can effectively drop
Space on the machine of low occupancy, simplied system structure；
(2) therefore two sets of independent wireless transceiver systems of data image transfer system configuration can effectively reduce each wireless
The load of receive-transmit system improves communication efficiency.
The above is only the preferred embodiment of the utility model, it is noted that for the common skill of the art
For art personnel, without departing from the principle of this utility model, several improvements and modifications can also be made, these improve and
Retouching should also regard the protection scope of the utility model.
Claims (3)
1. a kind of Navigation of Pilotless Aircraft communication integral system, which is characterized in that including satellite navigation flight control system and data image
Transmission system；The satellite navigation flight control system and data image transfer system encapsulation are in the same housing；
The satellite navigation flight control system include satellite earth antenna, the 1st radio-frequency channel processing circuit, analog-digital converter, the 1st can
Programmed logic chip, the 1st processor, attitude measuring and steering engine；Wherein, the output end of the satellite earth antenna is successively
After the 1st radio-frequency channel processing circuit and the analog-digital converter, it is connected to the defeated of the 1st programmable logic chip
Enter end；1st programmable logic chip is bi-directionally connected with the 1st processor；The output end of the attitude measuring connects
It is connected to the input terminal of the 1st programmable logic chip；The output end of 1st programmable logic chip is connected to the steering engine
Input terminal；
The data image transfer system includes the 1st wireless transceiver system, the 2nd wireless transceiver system, the 2nd radio-frequency channel processing electricity
Road, the 2nd programmable logic chip, the 2nd processor and image acquisition and processing device；1st wireless transceiver system and the described 2nd
Wireless transceiver system is connect with the 2nd radio-frequency channel processing circuit；The 2nd radio-frequency channel processing circuit and the described 2nd
Programmable logic chip is bi-directionally connected；The output end of described image Acquisition Processor is defeated with the 2nd programmable logic chip
Enter end connection；2nd programmable logic chip is bi-directionally connected with the 2nd processor；
Also, the 1st programmable logic chip and the 2nd programmable logic chip are bi-directionally connected.
2. Navigation of Pilotless Aircraft communication integral system according to claim 1, which is characterized in that the attitude measuring
Including：Angular velocity measurement device, acceleration measurement device and velocity measuring device.
3. Navigation of Pilotless Aircraft communication integral system according to claim 1, which is characterized in that the 1st wireless receiving and dispatching
System includes that number passes transmitting antenna sum number biography receiving antenna；2nd wireless transceiver system includes that figure passes transmitting antenna and schemes to pass
Receiving antenna.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820766824.3U CN208141229U (en) | 2018-05-22 | 2018-05-22 | Navigation of Pilotless Aircraft communication integral system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820766824.3U CN208141229U (en) | 2018-05-22 | 2018-05-22 | Navigation of Pilotless Aircraft communication integral system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208141229U true CN208141229U (en) | 2018-11-23 |
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ID=64314127
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
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| CN201820766824.3U Active CN208141229U (en) | 2018-05-22 | 2018-05-22 | Navigation of Pilotless Aircraft communication integral system |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108919819A (en) * | 2018-05-22 | 2018-11-30 | 北京和协导航科技有限公司 | Navigation of Pilotless Aircraft communication integral system and method |
| CN109724480A (en) * | 2018-12-29 | 2019-05-07 | 湖北航天技术研究院总体设计所 | A kind of integrated synthesis control device suitable for aircraft |
-
2018
- 2018-05-22 CN CN201820766824.3U patent/CN208141229U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108919819A (en) * | 2018-05-22 | 2018-11-30 | 北京和协导航科技有限公司 | Navigation of Pilotless Aircraft communication integral system and method |
| CN108919819B (en) * | 2018-05-22 | 2023-10-27 | 北京和协导航科技有限公司 | Unmanned aerial vehicle navigation communication integrated system and method |
| CN109724480A (en) * | 2018-12-29 | 2019-05-07 | 湖北航天技术研究院总体设计所 | A kind of integrated synthesis control device suitable for aircraft |
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