CN209870743U - Integrated comprehensive avionics system for observing and shooting unmanned aerial vehicle - Google Patents
Integrated comprehensive avionics system for observing and shooting unmanned aerial vehicle Download PDFInfo
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- CN209870743U CN209870743U CN201920120507.9U CN201920120507U CN209870743U CN 209870743 U CN209870743 U CN 209870743U CN 201920120507 U CN201920120507 U CN 201920120507U CN 209870743 U CN209870743 U CN 209870743U
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Abstract
The utility model discloses an integrated comprehensive avionics system for a scouting and batting unmanned aerial vehicle, which comprises a task computer, a weapon module, two wireless data transmission modules, an unmanned aerial vehicle flight control module, a nacelle, a combined navigation module and a video switching module; the weapon module and the unmanned aerial vehicle flight control are connected with a task computer CAN bus interface, the combined navigation module is connected with a task computer SPI interface, the pod is connected with a task computer RS422 interface, and the first wireless data transmission module is connected with a task computer RS232 interface; the video switching module is connected with the weapon module, the task computer and the second wireless data transmission module; the second wireless data transmission module is in wireless connection with the unmanned aerial vehicle flight control; the weapon module and pod are suspended from the drone. The realization is to the quick centralized management system of unmanned aerial vehicle multiple task load equipment, regard the task computer as the cross-linking between information transfer station greatly reduction task load and the aerial vehicle platform, makes the task load more independent, reduces the influence of task load to flight platform safety.
Description
Technical Field
The utility model belongs to unmanned aerial vehicle avionics field relates to an integrated comprehensive avionics system of observing and beating unmanned aerial vehicle.
Background
The unmanned aerial vehicle is combatted and beaten based on unmanned aerial vehicle flight platform, through installing airborne avionics system and weapon system additional, makes ordinary unmanned aerial vehicle possess investigation, supervision, target capture and to the real-time strike ability of target, very big shortening from the discovery to destroy the time of target. The small-sized scouting and attacking integrated unmanned aerial vehicle has the characteristics of low life cycle cost, zero casualty and small size, can utilize an airborne accurate guided weapon to execute battle tasks such as 'fixed point clearing', 'head chopping action' and the like, can also realize the hunting and killing effect which is not intended for a sensitive target, and can start a bee colony attack mode to continuously suppress an enemy to a ground target aiming at a large target to be attacked. The development of the unmanned aerial vehicle for the investigation and the combat adapts to the characteristics of the situation of a battlefield in the informationized war of being changeable instantly and the fact that the fighter passes the scene shortly.
However, some unmanned aerial vehicles do not possess in the existing market and observe and beat integrative function, and the demand problem that unmanned aerial vehicle changes to unmanned aerial vehicle of small-size observing and beating integrative unmanned aerial vehicle is urgent to be solved.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to overcome above-mentioned prior art's shortcoming, provide an integrated comprehensive avionics system of observing and beating unmanned aerial vehicle.
In order to achieve the above purpose, the utility model adopts the following technical scheme to realize:
an integrated comprehensive avionics system of a scouting and batting unmanned aerial vehicle comprises a task computer, a weapon module, two wireless data transmission modules, an unmanned aerial vehicle flight control module, a pod, a combined navigation module and a video switching module;
the weapon module and the unmanned aerial vehicle flight control are connected with a task computer CAN bus interface, the combined navigation module is connected with a task computer SPI interface, the pod is connected with a task computer RS422 interface, and the first wireless data transmission module is connected with a task computer RS232 interface;
the video switching module is connected with the weapon module, the task computer and the second wireless data transmission module;
the second wireless data transmission module is in wireless connection with the unmanned aerial vehicle flight control;
the weapon module and pod are both suspended on the drone.
The utility model discloses further improvement lies in:
the task computer is a TMS320F28377D dual-core task computer.
The weapon module comprises a two-way fire control computer, a weapon hanging frame and a guided missile;
the two-way fire control computer is connected with the task computer through a CAN bus interface, the weapon hanging rack is hung on the unmanned aerial vehicle, and the guided missile is arranged on the weapon hanging rack and is connected with the two-way fire control computer and the video switching module.
The wireless data transmission module is a PCI0840 wireless transceiver chip.
The pod is an airborne photoelectric pod.
The integrated navigation module comprises a GNSS receiver and an inertial measurement unit;
the GNSS receiver is connected with the inertial measurement unit through a UART communication interface, and the GNSS receiver is connected with the task computer through an SPI interface.
The GNSS receiver is an OEM718D receiver and the inertial measurement unit is an SNC100A inertial measurement unit.
The video switching module is an ST78262 chip.
The video switching module, the first wireless data transmission module, the combined navigation module and the task computer are all integrated on one PCB.
The unmanned plane flight control, weapon module and pod are all connected with the mission computer through J30J-25ZKP connectors.
Compared with the prior art, the utility model discloses following beneficial effect has:
through the RS422 interface that sets up on the task computer, the RS232 interface, CAN bus interface and SPI interface CAN carry on multiple task load, including weapon module, nacelle, wireless data transmission module and combination navigation module, realize the quick centralized management system to unmanned aerial vehicle multiple task load equipment, regard the task computer as the information transfer station greatly to reduce the cross-linking between task load and the aircraft platform, make the task load more independent, reduce the influence of task load to flight platform safety. The wireless data transmission module is used for sending the control instruction of the ground station to the task load and receiving the data returned by the task load, has the characteristics of low cost, long transmission distance, good reliability and high real-time performance, and meets the requirements of the current unmanned aerial vehicle comprehensive avionics system on information transmission. And simultaneously, the utility model has the characteristics of small, the integrated level is high.
Drawings
FIG. 1 is a schematic block diagram of the system of the present invention;
fig. 2 is a hardware block diagram of the integrated board card of the present invention;
fig. 3 is a schematic diagram of the power supply scheme of the present invention.
Detailed Description
In order to make the technical solution of the present invention better understood, the technical solution of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts shall belong to the protection scope of the present invention.
It should be noted that the terms "first," "second," and the like in the description and claims of the present invention and in the drawings described above are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used is interchangeable under appropriate circumstances such that the embodiments of the invention described herein are capable of operation in sequences other than those illustrated or otherwise described herein. Furthermore, the terms "comprises," "comprising," and "having," and any variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those steps or elements expressly listed, but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus.
The present invention will be described in further detail with reference to the accompanying drawings:
referring to fig. 1 and 2, the utility model relates to a reconnaissance and play unmanned aerial vehicle's integration and synthesize avionics system, including task computer, weapon module, two wireless data transmission modules, unmanned aerial vehicle flight control, nacelle, combination navigation module and video switch module. The weapon module and the unmanned aerial vehicle flight control are connected with a task computer CAN bus interface, the combined navigation module is connected with a task computer SPI interface, the pod is connected with a task computer RS422 interface, and the first wireless data transmission module is connected with a task computer RS232 interface; the unmanned aerial vehicle flight control, weapon module and pod are connected with the mission computer through J30J-25ZKP connectors; the weapon module and pod are suspended from the drone.
The TMS320F28377D task computer can be selected as the task computer, the pod can be selected as the onboard photoelectric pod, the video switching module is realized by a chip ST78262, and the wireless data transmission module can adopt a PCI0840 wireless transceiver chip; the video switching module, the first wireless data transmission module, the combined navigation module and the task computer are all integrated on one PCB.
The weapon module comprises a two-way fire control computer, a weapon hanging frame and a guided missile; the two-way fire control computer is connected with the task computer through a CAN bus interface, the weapon hanging rack is hung on the unmanned aerial vehicle, and the guided missile is arranged on the weapon hanging rack and is connected with the two-way fire control computer and the video switching module.
The integrated navigation module comprises a GNSS receiver and an inertial measurement unit; the GNSS receiver is connected with the inertia measurement unit through a UART communication interface, and the inertia measurement unit receiver is connected with the task computer through an SPI interface; the GNSS receiver may employ an OEM718D receiver and the inertial measurement unit may employ an SNC100A inertial measurement unit.
The video switching module is connected with the weapon module, the task computer and the second wireless data transmission module; the second wireless data transmission module is in wireless connection with the unmanned aerial vehicle.
The task computer is used as the brain of the avionic system, the RS232 interface, the SPI interface, the RS422 interface and the CAN interface which are arranged on the task computer completely meet the information interaction operation of the unmanned aerial vehicle and a plurality of task loads, the task computer is used as an information transfer station, the cross-linking between the task loads and the aerial vehicle platform is greatly reduced, the task loads are more independent, and the influence of the task loads on the safety of the flight platform is reduced.
The unmanned aerial vehicle weapon module is used as a final executor of striking and comprises a double-circuit fire control computer, a weapon hanging frame and a missile, when the unmanned aerial vehicle weapon module is loaded with the television-guided missile, a task load outputs double-circuit PAL video signals, and the task computer switches and selects the double-circuit PAL video signals, outputs one circuit and processes the same. And (4) receiving the self and target longitude and latitude height and launching command information given by the mission machine by using the fire control computer, and returning the optimal launching state and whether the weapon meets the launching state after calculation (the weapon is not ready). One fire control computer (one PCB) can only control one bomb, and two fires can be controlled by one PCB by adopting a two-way fire control computer.
Double-path PAL video flow: two TV guidance missiles output PAL video signals to a mission computer, the mission computer controls and outputs one of the PAL video signals to a wireless data transmission module, the wireless data transmission module transmits the PAL video signals to a ground station for ground personnel to observe things seen by the TV guidance missiles, so that the angle of the TV guidance missiles is adjusted, and accurate strike is realized.
An airborne photoelectric pod can be carried on the unmanned aerial vehicle platform, and a front-view infrared camera, a television camera, a laser indicator/a range finder and other photoelectric sensors are usually arranged on the unmanned aerial vehicle platform. The airborne photoelectric pod is used for searching a designated area and outputting an infrared/visible light image. And carrying out laser ranging on the target, carrying out laser irradiation guidance on the weapon module, measuring target distance information, position information and angle information, and outputting the data to a task computer through an RS422 serial port so as to be used by other task loads.
The remote high-speed data link carried by the unmanned aerial vehicle platform consists of a wireless data link and an automatic tracking antenna. The method mainly completes the control instruction sending of the ground station to the task load and the data receiving of the task load return. The data transmission module has the characteristics of low cost, long transmission distance, good reliability and high real-time performance, and can meet the requirements of the current unmanned aerial vehicle integrated avionics system.
The high-precision combined navigation system comprises a GNSS receiver and an inertial measurement unit, real-time high-precision angular speed, acceleration, speed, position, attitude and course information are provided for a flight platform and a weapon system, the real-time high-precision angular speed, acceleration, speed, position, attitude and course information is performance indexes of the whole unmanned combat platform which are directly influenced by the precision of flight control, target positioning and weapon system transmission alignment of an unmanned aerial vehicle, the requirements of the precision of the unmanned aerial vehicle and the weapon system are fully met by adopting the OEM718D receiver and the SNC100A inertial measurement unit, and the receiver is connected with the inertial measurement unit through a UART communication interface and has the same.
Referring to fig. 3, a system power supply is provided by the unmanned aerial vehicle, and 28V of power supply voltage is converted into 5V through the TPS54560 to supply power to the task computer, the video switching module, and the wireless data transmission module; the 5V voltage is converted into 3.3V by TLV62565 to power the inertial measurement unit, the GNSS receiver and the mission computer.
The airborne photoelectric pod provides target position information to the task computer and receives control instructions of the task computer. The unmanned aerial vehicle flight control sends control instructions and other information to the task computer and receives weapon module state and launching state information fed back by the task computer, and the weapon module, as a striking implementation main body, receives self position and target position provided by the task computer and then resolves the information in real time and feeds back missile state and launching state information to the task computer. When the image bomb is used, the video switching module receives the two paths of video signals and selectively outputs one path of video signals according to the pulse signals of the task computer. The video switching module switches the signal to the pulse signals of the periods 20us and 30 us. The pulse 20us outputs a first path, the pulse 30us outputs a second path, and the pulse signal is output to the video switching module by the task computer. The two wireless data transmission modules can directly interact with information of the ground station, send information required by the ground station to the ground station and receive control instructions of the ground station. The combined navigation module provides position information for the task computer, and the task computer is used as a brain of the system to receive information of the airborne photoelectric pod, the unmanned aerial vehicle flight control, the weapon system, the video switching module, the wireless data transmission module and the combined navigation, integrates and packages the information and sends the information to corresponding equipment. The mission computer is connected with the unmanned plane flight control, weapon module and airborne photoelectric pod through a J30J-25ZKP connector. And two interfaces of RS422 and CAN are reserved for the model task computers with different electrical interfaces.
The above contents are only for explaining the technical idea of the present invention, and the protection scope of the present invention cannot be limited thereby, and any modification made on the basis of the technical solution according to the technical idea of the present invention all fall within the protection scope of the claims of the present invention.
Claims (10)
1. An integrated comprehensive avionics system of a scouting and batting unmanned aerial vehicle is characterized by comprising a task computer, a weapon module, two wireless data transmission modules, an unmanned aerial vehicle flight control module, a pod, a combined navigation module and a video switching module;
the weapon module and the unmanned aerial vehicle flight control are connected with a task computer CAN bus interface, the combined navigation module is connected with a task computer SPI interface, the pod is connected with a task computer RS422 interface, and the first wireless data transmission module is connected with a task computer RS232 interface;
the video switching module is connected with the weapon module, the task computer and the second wireless data transmission module;
the second wireless data transmission module is in wireless connection with the unmanned aerial vehicle flight control;
the weapon module and pod are both suspended on the drone.
2. The integrated avionics system of a research and flight unmanned aerial vehicle of claim 1, wherein the mission computer is a TMS320F28377D dual-core mission computer.
3. The integrated, integrated avionics system of scouting and battling unmanned aerial vehicles according to claim 1, wherein the weapons module includes a two-way fire control computer, a weapons rack, and a missile;
the two-way fire control computer is connected with the task computer through a CAN bus interface, the weapon hanging rack is hung on the unmanned aerial vehicle, and the guided missile is arranged on the weapon hanging rack and is connected with the two-way fire control computer and the video switching module.
4. The integrated avionics system of the scout and combat unmanned aerial vehicle of claim 1, wherein the wireless data transmission module is a PCI0840 wireless transceiver chip.
5. The integrated, integrated avionics system of a scout and taxi flight drone of claim 1, wherein the pod is an airborne photoelectric pod.
6. The integrated avionics system of a scout and dozen drone according to claim 1, characterized in that the combined navigation module comprises a GNSS receiver and an inertial measurement unit;
the GNSS receiver is connected with the inertial measurement unit through a UART communication interface, and the GNSS receiver is connected with the task computer through an SPI interface.
7. The integrated avionics system of the scout and beaten drone of claim 6, wherein the GNSS receiver is an OEM718D receiver and the inertial measurement unit is an SNC100A inertial measurement unit.
8. The integrated avionics system of the scout and taxi flight vehicle of claim 1, wherein the video switching module is an ST78262 chip.
9. The integrated avionics system of the scout and play drone of claim 1, wherein the video switching module, the first wireless data transmission module, the combined navigation module, and the task computer are all integrated on one PCB board.
10. The integrated, integrated avionics system of scouting and printing drones according to claim 1, characterized in that the drone flight controls, weapon modules and pods are all connected to the mission computer by means of J30J-25ZKP connectors.
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| CN201920120507.9U CN209870743U (en) | 2019-01-23 | 2019-01-23 | Integrated comprehensive avionics system for observing and shooting unmanned aerial vehicle |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109774940A (en) * | 2019-01-23 | 2019-05-21 | 西安深瞳智控技术有限公司 | It is a kind of to examine the integrated synthesis avionics system for beating unmanned plane |
| CN112256053A (en) * | 2020-09-27 | 2021-01-22 | 中国航空工业集团公司洛阳电光设备研究所 | Fire control photoelectric system of small-sized scouting and fighting unmanned aerial vehicle |
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2019
- 2019-01-23 CN CN201920120507.9U patent/CN209870743U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109774940A (en) * | 2019-01-23 | 2019-05-21 | 西安深瞳智控技术有限公司 | It is a kind of to examine the integrated synthesis avionics system for beating unmanned plane |
| CN112256053A (en) * | 2020-09-27 | 2021-01-22 | 中国航空工业集团公司洛阳电光设备研究所 | Fire control photoelectric system of small-sized scouting and fighting unmanned aerial vehicle |
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