CN105468018A - Unmanned aerial vehicle target characteristic simulation system - Google Patents
Unmanned aerial vehicle target characteristic simulation system Download PDFInfo
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- CN105468018A CN105468018A CN201510845430.8A CN201510845430A CN105468018A CN 105468018 A CN105468018 A CN 105468018A CN 201510845430 A CN201510845430 A CN 201510845430A CN 105468018 A CN105468018 A CN 105468018A
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Abstract
The invention provides an unmanned aerial vehicle target characteristic simulation system. The system includes a ground transmitting-and-receiving control platform as well as an electromagnetic characteristic simulation device, an infrared characteristic simulation device and a motion characteristic simulation device which are in communication connection with the ground transmitting-and-receiving control platform. According to the unmanned aerial vehicle target characteristic simulation system of the invention, the electromagnetic characteristics, infrared characteristics and motion characteristics of unmanned aerial vehicles are adjusted in real time through the electromagnetic characteristic simulation device, the infrared characteristic simulation device, the motion characteristic simulation device and the ground transmitting-and-receiving control platform. With the unmanned aerial vehicle target characteristic simulation system adopted, target characteristic simulation of different types of flight targets can be carried out simultaneously, and at the same time, the actual flight parameters and tracks of the plurality of targets can corrected and adjusted, and therefore, accurate control on the flight parameters and tracks can be realized, and the similarity of unmanned aerial vehicle target characteristic simulation and actual flight targets can be effectively enhanced, and the safety of the flight of the unmanned aerial vehicles can be improved.
Description
Technical field
The present invention relates to unmanned vehicle analog control technique field, particularly relate to a kind of unmanned plane target system for simulating feature.
Background technology
Current, along with improving constantly of scientific and technological level, the application of unmanned plane is more and more extensive.Unmanned plane relies on its good maneuverability and disguise becoming indispensable weapon in modern high technology war, be provided to army of various countries more and more, unmanned plane is carrying out military scouting, performing combat duty or can reduce labour intensity in communication, weather monitoring, disaster monitoring, geological mapping, reducing casualties, meanwhile, unmanned plane surveying and drawing, take photo by plane, the application of the civil area such as search also constantly expands.
Unmanned plane target system for simulating feature comprises electromagnetic property simulation, infrared characteristic simulation and kinetic characteristic simulation.
The simplest method of electromagnetic property simulation is the RCS value size changing unmanned plane, at present by the RCS value installing corner reflector additional on unmanned plane, the rich mode such as lens reflector, dielectric reflector of dragon expands unmanned plane, but the RCS value obtained of said method is fixed value, cannot meet and carry out electromagnetic property simulation to polymorphic type target.
The build of current unmanned plane is usually less, its size and quality are all less than Live Flying target, in addition because the engine of unmanned plane is much smaller than Live Flying target, therefore the infrared characteristic of unmanned plane is more much smaller than real airbound target, therefore usually need to carry infrared augmentation equipment on unmanned plane, infrared augmentation equipment of the prior art only can carry out infrared characteristic simulation for single airbound target, and that cannot shoot the arrow at the target carries out infrared characteristic simulation to dissimilar airbound target.
The type of air-supported threat target is many, can not be completed simulate its kinetic characteristic by single unmanned plane.The type kind of unmanned plane can be utilized at present many, the feature that performance index are different, by the method for trajectory planning, make the threat target of unmanned plane in the time domain specified, spatial domain and speed territory needed for simulation with Different Dynamic performance, and then form the simulation to multiple goal air-supported threat.Coordinate by multimachine the flight path that trajectory planning establishes each frame unmanned plane, also need preventing outside midair collision accident, ensure that each unmanned plane arrives predetermined spatial domain simultaneously on time.But existing kinetic characteristic analogue means cannot precise coordination multimachine flight path, and unmanned plane cannot arrive predetermined spatial domain, and midair collision accident happens occasionally especially on time.
Therefore, how inventing a kind of unmanned plane target system for simulating feature is that those skilled in the art have technical barrier to be solved.
Summary of the invention
Target property simulation accurately cannot be carried out to dissimilar airbound target for solving prior art, the invention provides a kind of unmanned plane target system for simulating feature, electromagnetic property simulation and infrared characteristic simulation can be carried out to polymorphic type target, by course deviation check and correction and parameter check and correction precise coordination multimachine flight path in kinetic characteristic simulation, make unmanned plane can arrive predetermined spatial domain according to the course line of planning on time, and the ratio of midair collision accident can be effectively reduced, reduce unmanned plane and Live Flying target in electromagnetic property simultaneously, the difference of infrared characteristic and kinetic characteristic aspect.
For solving the problems of the technologies described above, the present invention includes following technical scheme:
A kind of unmanned plane target system for simulating feature, this system comprises ground transmitting-receiving parametric controller, receives and dispatches with ground electromagnetic property analogue means, infrared characteristic analogue means and the kinetic characteristic analogue means that parametric controller communicates to connect, wherein,
Described electromagnetic property analogue means comprises single chip microcontroller, signal distributor and RCS variable angle reverberator, described single chip microcontroller is received and dispatched parametric controller by signal distributor and described ground and is communicated to connect, described signal distributor is for receiving the control signal of ground transmitting-receiving parametric controller transmission and carrying out transfer and reallocation, the control signal that described single chip microcontroller is reallocated by Received signal strength divider is to regulate the RCS value of described RCS variable angle reverberator, described RCS variable angle reverberator is by scalable connecting framework and some four three right angle reflection spaces being fixed on the scalable frame mattress reflector blade face being connected bone and being formed, the RCS value changing RCS variable angle reverberator is successively peeled off by autogenous shrinkage in described mattress reflector blade face by described scalable connecting framework,
Described infrared characteristic analogue means comprises processor, signal converter and suspension trigger mechanism, described processor is received and dispatched parametric controller by signal converter and described ground and is communicated to connect, described signal converter is for the control signal that receives ground transmitting-receiving parametric controller and send and be converted into the signal that processor can identify, described suspension trigger mechanism comprises some hangers being mounted with flame tracer, flame tracer on different hanger has different fills out dose, hangs trigger mechanism and determines to launch the flame tracer on corresponding hanger by the signal of receiving processor;
Described kinetic characteristic analogue means comprises data transmission module, parameters measurement module, track insmods, data processing module, course deviation checking module, parameter checking module and power train control module, described data transmission module receives simulated flight track and the simulated flight parameter of being received and dispatched parametric controller setting by ground, described track insmods and receives Live Flying parameter and real-time coordinates that described parameters measurement module sends and be forwarded in described data processing module, the Live Flying parameter received and real-time coordinates process are formed Live Flying track and Live Flying parameter by described data processing module, described course deviation checking module is for detecting the error of Live Flying track and simulated flight track, error exceedes setting threshold value, then by described power train control module, Live Flying track is adjusted, described parameter checking module is for detecting the error of Live Flying parameter and simulated flight parameter, error exceedes setting threshold value, then adjusted Live Flying parameter by described power train control module,
Described ground transmitting-receiving parametric controller is used for sending control command to electromagnetic property analogue means, infrared characteristic analogue means and kinetic characteristic analogue means, receives and shows the analog result of electromagnetic property, infrared characteristic and kinetic characteristic.
As preferably, described ground transmitting-receiving parametric controller comprises electromagnetic property control module, infrared characteristic control module, kinetic characteristic control module, data transmit-receive module, display module and processor, described electromagnetic property control module is for setting simulation RCS parameter, described electromagnetic property control module is for setting simulation infrared radiation parameter, described kinetic characteristic control module is for setting simulated flight parameter and simulated flight track, described simulation RCS parameter, simulation infrared radiation parameter, simulated flight parameter and simulated flight track are treated to after control command through described processor and are forwarded to corresponding analogue means by described data transmit-receive module, described data transmit-receive module receives electromagnetic property, the analog result of infrared characteristic and kinetic characteristic, and be presented on described display module.
As preferably, described kinetic characteristic analogue means also comprises make a return voyage judge module and landing buffer module, described in make a return voyage judge module for judging whether to exceed the correcting range of course deviation checking module, generate falling signal according to exceeding correcting range result; Described landing buffer module activates drop buffer for receiving falling signal.
As preferably, described ground transmitting-receiving parametric controller also comprises alarm module, and the falling signal that described alarm module generates for the judge module that makes a return voyage receiving described kinetic characteristic analogue means also carries out automatic alarm.
As preferably, described parameters measurement module comprises treating apparatus, the Digital Magnetic Compass be electrically connected with described treating apparatus, laser ranging system, inertial sensor, GPS locating module, image taking module, elevation carrection module and flying speed detection module.
As preferably, described laser ranging system for judging whether to be between unmanned plane and other targets in the secure threshold that presets, and generates break-in signal according to negative decision, and described power train control module receives break-in signal and carries out pressure break-in.
As preferably, described scalable connecting framework be five isometric and can the electric pushrod of synchronous, described mattress reflector blade face is the isosceles right triangle be spliced into by some cotyledon faces, and described cotyledon face is provided with the set collar for being set on electric pushrod.
As preferably, described electric pushrod inside is provided with control circuit, and the signal that described control circuit receives single chip microcontroller realizes beginning that scalable connecting framework shrinks and stopping by the break-make of circuit.
Further preferably, described hanger for launching hanger, described in launch hanger both sides be provided with anti-sway retainer.
Beneficial effect of the present invention is as follows:
Unmanned plane target system for simulating feature of the present invention is by surface em characteristic simulation device, infrared characteristic analogue means, the electromagnetic property of parametric controller to unmanned plane is received and dispatched on kinetic characteristic analogue means and ground, infrared characteristic and kinetic characteristic adjust in real time, target property simulation can be carried out to number of different types airbound target simultaneously, can also the Live Flying parameter of multiple target and flight path be proofreaded and be adjusted simultaneously, achieve the accurate control of flight parameter and flight path, effectively enhance the similarity of unmanned plane target simulated behavior and Live Flying target, and improve the security of unmanned plane during flying.
Accompanying drawing explanation
Fig. 1 is the structural representation of the unmanned plane target system for simulating feature of the embodiment of the present invention 1;
Fig. 2 is the structural representation of the electromagnetic property analogue means of the embodiment of the present invention 1;
Fig. 3 is the structural representation of the infrared characteristic analogue means of the embodiment of the present invention 1;
Fig. 4 is the structural representation of the kinetic characteristic analogue means of the embodiment of the present invention 1;
Fig. 5 is the structural representation of the ground transmitting-receiving parametric controller of the embodiment of the present invention 1;
Fig. 6 is the structural representation of the parameters measurement module of the embodiment of the present invention 2;
Fig. 7 is the structural representation of the RCS variable angle reverberator of the embodiment of the present invention 3.
Embodiment
For enabling above-mentioned purpose of the present invention, feature and advantage become apparent more, are described in detail the specific embodiment of the present invention below in conjunction with accompanying drawing.
Embodiment 1
As shown in Figure 1, a kind of unmanned plane target system for simulating feature that the embodiment of the present invention provides, this system comprises ground transmitting-receiving parametric controller, electromagnetic property analogue means, infrared characteristic analogue means and kinetic characteristic analogue means, and wherein transmitting-receiving parametric controller in ground realizes signal and data communication by wireless communication apparatus and electromagnetic property analogue means, infrared characteristic analogue means and kinetic characteristic analogue means; Wherein electromagnetic property analogue means, infrared characteristic analogue means and kinetic characteristic analogue means receive the control command that ground transmitting-receiving parametric controller sends, correspondingly, ground is received and dispatched parametric controller real-time reception and is shown electromagnetic property analogue means, infrared characteristic analogue means and kinetic characteristic analogue means and makes various data feedback to control command.
As shown in Figure 2-5, the architectural feature of ground transmitting-receiving parametric controller, electromagnetic property analogue means, infrared characteristic analogue means and kinetic characteristic analogue means is further defined in the technical program, and describe the technical matters of effect that structure realizes and solution, specific as follows:
As shown in Figure 2, electromagnetic property analogue means comprises single chip microcontroller 11, signal distributor 12 and RCS variable angle reverberator 13.Wherein, single chip microcontroller 11 is received and dispatched parametric controller by signal distributor and 12 ground and is communicated to connect, signal distributor 12 is for receiving the control signal of ground transmitting-receiving parametric controller transmission and carrying out transfer and reallocation, the control signal that single chip microcontroller 11 is reallocated by Received signal strength divider is to regulate the RCS value of described RCS variable angle reverberator 13, RCS variable angle reverberator 13 is by scalable connecting framework and some four three right angle reflection spaces being fixed on the scalable frame mattress reflector blade face being connected bone and being formed, the RCS value changing RCS variable angle reverberator 13 is successively peeled off by autogenous shrinkage in described mattress reflector blade face by scalable connecting framework.By the RCS value installing corner reflector additional on unmanned plane, the rich mode such as lens reflector, dielectric reflector of dragon can only expand unmanned plane with a certain fixed proportion in prior art, by the blade face layer-stepping design of RCS variable angle reverberator in the present embodiment, make the RCS value of unmanned plane reach by successively peeling off mattress reflector blade face the object that noncontinuity regulates RCS value, the destination number of simulation depends on the number of plies on mattress reflector blade face.
As shown in Figure 3, infrared characteristic analogue means comprises processor 21, signal converter 22 and suspension trigger mechanism 23, processor 21 is received and dispatched parametric controller by signal converter 22 and described ground and is communicated to connect, signal converter 22 is for the control signal that receives ground transmitting-receiving parametric controller and send and be converted into the signal that processor 21 can identify, described suspension transmitting 23 mechanism comprises some hangers being mounted with flame tracer, flame tracer on different hanger has different fills out dose, hang trigger mechanism to determine to launch the flame tracer on corresponding hanger by the signal of receiving processor, described hanger is for launching hanger, the both sides of launching hanger are provided with anti-sway retainer.Infrared intensity is strengthened by carrying infrared augmentation equipment (as flame tracer or infrared bullet) on unmanned plane with a certain fixed proportion in prior art, the present embodiment is by carrying the different flame tracers filling out dose, reach by throwing in corresponding flame tracer the object that noncontinuity regulates unmanned plane infrared intensity, the destination number of simulation depends on that UAV flight's difference fills out the flame tracer quantity of dose.Meanwhile, the present embodiment also increases the carry stability of flame tracer by the anti-sway retainer arranged in the both sides of launching hanger.
As shown in Figure 4, kinetic characteristic analogue means comprises data transmission module 31, parameters measurement module 32, track insmod 33, data processing module 34, course deviation checking module 35, parameter checking module 36, power train control module 37, make a return voyage judge module 38 and landing buffer module 39, data transmission module 31 receives simulated flight track and the simulated flight parameter of being received and dispatched parametric controller setting by ground, track insmods the Live Flying parameter and real-time coordinates be forwarded in described data processing module that 33 reception described parameters measurement module 32 send, the Live Flying parameter received and real-time coordinates process are formed Live Flying track and Live Flying parameter by data processing module 34, course deviation checking module 35 is for detecting the error of Live Flying track and simulated flight track, error exceedes setting threshold value, then adjusted by described power train control module 37 pairs of Live Flying tracks, parameter checking module 36 is for detecting the error of Live Flying parameter and simulated flight parameter, error exceedes setting threshold value, then adjusted by power train control module 37 pairs of Live Flying parameters, make a return voyage judge module 38 for judging whether to exceed the correcting range of course deviation checking module, falling signal is generated according to exceeding correcting range result, landing buffer module 39 activates drop buffer for receiving falling signal.The kinetic characteristic analogue means of the present embodiment can carry out kinetic characteristic simulation to number of different types airbound target simultaneously, can also the Live Flying parameter of multiple target and flight path be proofreaded and be adjusted simultaneously, achieve the accurate control of flight parameter and flight path, effectively enhance the similarity of unmanned plane target simulated behavior and Live Flying target, and improve the security of unmanned plane during flying.
As shown in Figure 5, transmitting-receiving parametric controller in ground comprises electromagnetic property control module 41, infrared characteristic control module 42, kinetic characteristic control module 43, data transmit-receive module 44, alarm module 45, display module 46 and processor 47, electromagnetic property control module is for setting simulation RCS parameter, electromagnetic property control module is for setting simulation infrared radiation parameter, kinetic characteristic control module is for setting simulated flight parameter and simulated flight track, the simulation RCS parameter of setting, simulation infrared radiation parameter, simulated flight parameter and simulated flight track are treated to after control command through described processor and are forwarded to corresponding analogue means by described data transmit-receive module, data transmit-receive module receives electromagnetic property, the analog result of infrared characteristic and kinetic characteristic, and be presented on display module, alarm module is for receiving the falling signal of the judge module generation of making a return voyage of kinetic characteristic analogue means and carrying out automatic alarm.
Embodiment 2
The present embodiment 2 provides a kind of unmanned plane target system for simulating feature, and this embodiment 2 further defines described parameters measurement module on the basis of embodiment 1.
Specifically as shown in Figure 6, parameters measurement module 32 comprises treating apparatus 321, Digital Magnetic Compass 322, laser ranging system 333, inertial sensor 334, GPS locating module 335, image taking module 336, elevation carrection module 337 and flying speed detection module 338.Digital Magnetic Compass 322, laser ranging system 333, inertial sensor 334 measure unmanned plane position angle, the angle of pitch, flying height transfer to described treating apparatus 321 respectively, GPS locating module 335 is for providing navigation for unmanned plane, image taking module 336 is for taking the photo of environment residing for unmanned plane, elevation carrection module 337 uses the height value of fixing frequency detecting unmanned plane, and flying speed detecting unit 338 utilizes the flying speed of the velocity estimated unmanned plane of optical flow field.In addition, whether laser ranging system 333 also can be used for judging being between unmanned plane and other targets in the secure threshold that presets, and generates break-in signal according to negative decision, and described power train control module 37 receives break-in signal and carries out pressure break-in.
Embodiment 3
The present embodiment 3 provides a kind of unmanned plane target system for simulating feature, and this embodiment 1 further defines the structure of described RCS variable angle reverberator on the basis of embodiment 1.
Specifically as shown in Figure 7, RCS variable angle reverberator is four three the right angle reflection spaces formed with some mattress reflector blade faces 2 being fixed on scalable connecting framework 1 by scalable connecting framework 1, wherein only shows the schematic diagram of an angle of RCS variable angle reverberator in Fig. 7.Scalable connecting framework 1 be five isometric and can the electric pushrod 10 of synchronous, mattress reflector blade face 2 is the isosceles right triangles be spliced into by some cotyledon faces 20, and cotyledon face 20 is provided with the set collar 200 for being set on electric pushrod 10.Electric pushrod 10 inside is provided with control circuit, and the signal of control circuit reception single chip microcontroller 11 realizes beginning and the stopping of the contraction of scalable connecting framework 1 by the break-make of circuit.
The control circuit of electric pushrod 10 inside receive start shrink control command after five electric pushrod synchronous, until receive stop shrink control command after stop shrink.The set collar 200 that electric pushrod 10 progressively departs from corresponding cotyledon face 20 fetters, and the cotyledon face 20 simultaneously contacting constraint is discharged by RCS variable angle reverberator.The scalable connecting framework 1 of the present embodiment makes the RCS value of unmanned plane reach by successively peeling off mattress reflector blade face 2 object that noncontinuity regulates RCS value by autogenous shrinkage, and total adjustment number of times of RCS value depends on the number of plies on mattress reflector blade face 2.
In sum, unmanned plane target system for simulating feature of the present invention is by surface em characteristic simulation device, infrared characteristic analogue means, the electromagnetic property of parametric controller to unmanned plane is received and dispatched on kinetic characteristic analogue means and ground, infrared characteristic and kinetic characteristic adjust in real time, target property simulation can be carried out to number of different types airbound target simultaneously, can also the Live Flying parameter of multiple target and flight path be proofreaded and be adjusted simultaneously, achieve the accurate control of flight parameter and flight path, effectively enhance the similarity of unmanned plane target simulated behavior and Live Flying target, and improve the security of unmanned plane during flying.
The above embodiment is only that the preferred embodiment of the present invention is described; not scope of the present invention is limited; under not departing from the present invention and designing the prerequisite of spirit; the various distortion that those of ordinary skill in the art make technical scheme of the present invention and improvement, all should fall in protection domain that claims of the present invention determine.
Claims (9)
1. a unmanned plane target system for simulating feature, is characterized in that, this system comprises ground transmitting-receiving parametric controller, receives and dispatches with ground electromagnetic property analogue means, infrared characteristic analogue means and the kinetic characteristic analogue means that parametric controller communicates to connect, wherein,
Described electromagnetic property analogue means comprises single chip microcontroller (11), signal distributor (12) and RCS variable angle reverberator (13), described single chip microcontroller (11) is received and dispatched parametric controller by signal distributor (12) and described ground and is communicated to connect, described signal distributor (12) is for receiving the control signal of ground transmitting-receiving parametric controller transmission and carrying out transfer and reallocation, the control signal that described single chip microcontroller (11) is reallocated by Received signal strength divider (12) is to regulate the RCS value of described RCS variable angle reverberator (13), described RCS variable angle reverberator (13) is four three the right angle reflection spaces formed by scalable connecting framework (1) and some mattress reflector blade faces (2) being fixed on scalable connecting framework (1), described mattress reflector blade face (2) is successively peeled off the RCS value changing RCS variable angle reverberator by autogenous shrinkage by described scalable connecting framework (1),
Described infrared characteristic analogue means comprises processor (21), signal converter (22) and suspension trigger mechanism (23), described processor (21) is received and dispatched parametric controller by signal converter (22) and described ground and is communicated to connect, described signal converter (22) is for the control signal that receives ground transmitting-receiving parametric controller and send and be converted into the signal that processor (21) can identify, described suspension trigger mechanism (23) comprises some hangers being mounted with flame tracer, hang trigger mechanism (23) to determine to launch the flame tracer on corresponding hanger by the signal of receiving processor (21),
Described kinetic characteristic analogue means comprises data transmission module (31), parameters measurement module (32), track insmods (33), data processing module (34), course deviation checking module (35), parameter checking module (36) and power train control module (37), described data transmission module (31) receives simulated flight track and the simulated flight parameter of being received and dispatched parametric controller setting by ground, described track insmod (33) receive real-time flight parameter and real-time coordinates that described parameters measurement module (32) sends and be forwarded in described data processing module (34), the real-time flight parameter received and real-time coordinates process are formed Live Flying track and Live Flying parameter by described data processing module (34), described course deviation checking module (35) is for detecting the error of Live Flying track and simulated flight track, error exceedes setting threshold value, then by described power train control module (37), Live Flying track is adjusted, described parameter checking module (36) is for detecting the error of Live Flying parameter and simulated flight parameter, error exceedes setting threshold value, then adjusted Live Flying parameter by described power train control module (37),
Described ground transmitting-receiving parametric controller is used for sending control command to electromagnetic property analogue means, infrared characteristic analogue means and kinetic characteristic analogue means, receives and shows the analog result of electromagnetic property, infrared characteristic and kinetic characteristic.
2. unmanned plane target system for simulating feature as claimed in claim 1, it is characterized in that, described ground transmitting-receiving parametric controller comprises electromagnetic property control module (41), infrared characteristic control module (42), kinetic characteristic control module (43), data transmit-receive module (44), display module (46) and processor (47), described electromagnetic property control module (41) is for setting simulation RCS parameter, described infrared characteristic control module (42) is for setting simulation infrared radiation parameter, described kinetic characteristic control module (43) is for setting simulated flight parameter and simulated flight track, described simulation RCS parameter, simulation infrared radiation parameter, simulated flight parameter and simulated flight track are forwarded to corresponding analogue means by described data transmit-receive module (44) after described processor (47) is treated to control command, described data transmit-receive module (44) receives electromagnetic property, the analog result of infrared characteristic and kinetic characteristic, and be presented on described display module (46).
3. unmanned plane target system for simulating feature as claimed in claim 1, it is characterized in that, described kinetic characteristic analogue means also comprises the judge module that makes a return voyage (38) and landing buffer module (39), the described judge module that makes a return voyage (38), for judging whether the correcting range exceeding course deviation checking module, generates falling signal according to exceeding correcting range result; Described landing buffer module (39) activates drop buffer for receiving falling signal.
4. unmanned plane target system for simulating feature as claimed in claim 2 or claim 3, it is characterized in that, described ground transmitting-receiving parametric controller also comprises alarm module (45), and the falling signal that described alarm module (45) generates for the judge module that makes a return voyage (38) receiving described kinetic characteristic analogue means also carries out automatic alarm.
5. unmanned plane target system for simulating feature as claimed in claim 1, it is characterized in that, described parameters measurement module (32) comprises treating apparatus (321), the Digital Magnetic Compass (322) be electrically connected with described treating apparatus (321), laser ranging system (323), inertial sensor (324), GPS locating module (325), image taking module (326), elevation carrection module (327) and flying speed detection module (328).
6. the unmanned plane target system for simulating feature as described in claim 1 or 5, it is characterized in that, whether described laser ranging system (323) is for judging to be between unmanned plane and other targets in the secure threshold that presets, and generating break-in signal according to negative decision, described power train control module (37) receives break-in signal and carries out pressure break-in.
7. unmanned plane target system for simulating feature as claimed in claim 1, it is characterized in that, described scalable connecting framework (1) be five isometric and can the electric pushrod (10) of synchronous, described mattress reflector blade face (2) is the isosceles right triangle be spliced into by some cotyledon faces (20), and described cotyledon face (20) is provided with the set collar (200) for being set on electric pushrod (10).
8. unmanned plane target system for simulating feature as claimed in claim 7, it is characterized in that, described electric pushrod (10) inside is provided with control circuit, and the signal that described control circuit receives single chip microcontroller (11) realizes beginning that scalable connecting framework (1) shrinks and stopping by the break-make of circuit.
9. unmanned plane target system for simulating feature as claimed in claim 1, is characterized in that, described hanger for launching hanger, described in launch hanger both sides be provided with anti-sway retainer.
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| CN106774365A (en) * | 2016-12-20 | 2017-05-31 | 华中科技大学 | A kind of unmanned plane debugging system based on external view positioning |
| CN108528749A (en) * | 2018-06-06 | 2018-09-14 | 吉林大学 | The vehicle-mounted unmanned aerial vehicle retracting device and method of technology are attracted based on electromagnetism |
| CN108528749B (en) * | 2018-06-06 | 2023-10-20 | 吉林大学 | Vehicle-mounted unmanned aerial vehicle recycling device and method based on electromagnetic attraction technology |
| CN109870910A (en) * | 2019-03-02 | 2019-06-11 | 哈尔滨理工大学 | A kind of flying vehicles control method based on synovial membrane control |
| CN109991994A (en) * | 2019-05-10 | 2019-07-09 | 重庆邮电大学 | A kind of small drone track and attitude rectification method based on flight simulator |
| CN109991994B (en) * | 2019-05-10 | 2022-02-11 | 重庆邮电大学 | Flight simulator-based small unmanned aerial vehicle track and attitude correction method |
| CN110320508A (en) * | 2019-07-04 | 2019-10-11 | 上海航天测控通信研究所 | A kind of analogy method of airborne answering machine to high dynamic target property |
| CN110320508B (en) * | 2019-07-04 | 2022-11-29 | 上海航天测控通信研究所 | Method for simulating high dynamic target characteristics by airborne responder |
| CN111007465A (en) * | 2019-11-21 | 2020-04-14 | 北京烜翊科技有限公司 | System, method and storage medium for dynamically changing radar scattering sectional area |
| CN113359847A (en) * | 2021-07-06 | 2021-09-07 | 中交遥感天域科技江苏有限公司 | Unmanned aerial vehicle counter-braking method and system based on radio remote sensing technology and storage medium |
| CN113359847B (en) * | 2021-07-06 | 2022-03-11 | 中交遥感天域科技江苏有限公司 | Unmanned aerial vehicle counter-braking method and system based on radio remote sensing technology and storage medium |
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