CN109612456B - Low-altitude search positioning system - Google Patents
Low-altitude search positioning system Download PDFInfo
- Publication number
- CN109612456B CN109612456B CN201811623450.0A CN201811623450A CN109612456B CN 109612456 B CN109612456 B CN 109612456B CN 201811623450 A CN201811623450 A CN 201811623450A CN 109612456 B CN109612456 B CN 109612456B
- Authority
- CN
- China
- Prior art keywords
- detection device
- ground
- ejection
- infrared
- aerial
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000001514 detection method Methods 0.000 claims abstract description 194
- 238000004458 analytical method Methods 0.000 claims abstract description 7
- 230000015572 biosynthetic process Effects 0.000 claims abstract description 7
- 238000003786 synthesis reaction Methods 0.000 claims abstract description 7
- 238000012790 confirmation Methods 0.000 claims abstract description 6
- 230000033001 locomotion Effects 0.000 claims description 31
- 238000001931 thermography Methods 0.000 claims description 16
- 238000012544 monitoring process Methods 0.000 claims description 10
- 238000004891 communication Methods 0.000 claims description 9
- 230000007246 mechanism Effects 0.000 claims description 8
- 230000003993 interaction Effects 0.000 claims description 4
- 238000012423 maintenance Methods 0.000 claims description 4
- 230000008439 repair process Effects 0.000 claims description 4
- 238000011084 recovery Methods 0.000 claims description 3
- 238000011840 criminal investigation Methods 0.000 abstract description 2
- 238000000034 method Methods 0.000 description 20
- 238000005192 partition Methods 0.000 description 11
- 238000010586 diagram Methods 0.000 description 10
- 230000008569 process Effects 0.000 description 10
- 238000006073 displacement reaction Methods 0.000 description 8
- 238000006243 chemical reaction Methods 0.000 description 6
- 239000003721 gunpowder Substances 0.000 description 6
- 238000005516 engineering process Methods 0.000 description 5
- 238000004880 explosion Methods 0.000 description 4
- 230000006870 function Effects 0.000 description 4
- 238000004088 simulation Methods 0.000 description 4
- 235000015429 Mirabilis expansa Nutrition 0.000 description 3
- 244000294411 Mirabilis expansa Species 0.000 description 3
- 230000001133 acceleration Effects 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 3
- 235000013536 miso Nutrition 0.000 description 3
- 238000000926 separation method Methods 0.000 description 3
- 230000004888 barrier function Effects 0.000 description 2
- 230000008901 benefit Effects 0.000 description 2
- 238000004422 calculation algorithm Methods 0.000 description 2
- 238000004364 calculation method Methods 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 239000002131 composite material Substances 0.000 description 2
- 230000005674 electromagnetic induction Effects 0.000 description 2
- 230000005484 gravity Effects 0.000 description 2
- 230000002093 peripheral effect Effects 0.000 description 2
- 239000000523 sample Substances 0.000 description 2
- 230000002194 synthesizing effect Effects 0.000 description 2
- 230000001960 triggered effect Effects 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 244000043261 Hevea brasiliensis Species 0.000 description 1
- 230000001174 ascending effect Effects 0.000 description 1
- 230000002238 attenuated effect Effects 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 238000001564 chemical vapour infiltration Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 238000007405 data analysis Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229920003052 natural elastomer Polymers 0.000 description 1
- 229920001194 natural rubber Polymers 0.000 description 1
- 238000012946 outsourcing Methods 0.000 description 1
- 229920001084 poly(chloroprene) Polymers 0.000 description 1
- 239000000843 powder Substances 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 230000035945 sensitivity Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
- 239000013598 vector Substances 0.000 description 1
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C21/00—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00
- G01C21/005—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00 with correlation of navigation data from several sources, e.g. map or contour matching
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
- G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
- G01J5/0066—Radiation pyrometry, e.g. infrared or optical thermometry for hot spots detection
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
- G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
- G01J2005/0077—Imaging
Landscapes
- Engineering & Computer Science (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Spectroscopy & Molecular Physics (AREA)
- Automation & Control Theory (AREA)
- Geophysics And Detection Of Objects (AREA)
Abstract
The invention discloses a low-altitude search positioning system, which comprises: the ground terminal sends an ejection angle signal to the ground ejection device, the ground ejection device drives a driving motor according to the received angle data, and the driving motor rotates the ground ejection device to a set angle; the ground terminal sends the ejection confirmation signal to the ground ejection device, the ground ejection device launches the air detection device, the air detection device collects real-time comprehensive data and sends the real-time comprehensive data to the ground terminal, and the ground terminal receives the comprehensive data, performs dynamic image synthesis and target object identification analysis and pushes target object information. The system quickly lifts off the sensor in a short time, so that the target is prevented from being influenced and accurate ground target positioning is realized; the aerial detection device is small in size, can be carried about, is convenient to recover, can be used for multiple times, and can be applied to scenes such as post-earthquake search and rescue, wild animal protection, criminal investigation, flood rescue and the like.
Description
Technical Field
The invention relates to the technical field of aerial detection, in particular to a low-altitude search positioning system.
Background
The traditional detection device is mainly as follows: acquiring the position information of a target object from the ground through an ultralow frequency electric wave or electromagnetic induction technology, wherein the ultralow frequency electric wave is mainly used for a life detector, the electromagnetic induction is mainly used for a metal detector, but the detection range of a ground detection device is limited and is easily shielded by an obstacle; carry on infrared sensing detection device or airborne radar from aerial through unmanned aerial vehicle and acquire target object positional information, but unmanned aerial vehicle rises to the air the speed slower, and the timeliness is poor, and produces huge noise disturbing target object easily.
The airborne radar has higher cost, is more biased to the military field and is not suitable for short-distance accurate position monitoring; the position information of the underwater target object is acquired from underwater through a sonar positioning technology, but the sound propagation speed is slow, the positioning position deviation is easily generated when the target object is in a motion state, and whether the target object is a living body cannot be detected. In addition, the devices involved in the three methods are large in size and difficult to carry and transport.
Disclosure of Invention
The purpose of the invention is as follows: in order to overcome the defects of the prior art, the invention provides a low-altitude search positioning method which can solve the problems of poor ground obstacle avoidance capability, small detection range, poor timeliness, high noise, high cost, difficulty in carrying and the like.
The technical scheme is as follows: the invention relates to a low-altitude search positioning system, which comprises: the ground terminal sends an ejection angle signal to the ground ejection device, the ground ejection device drives a driving motor according to the received angle data, and the driving motor rotates the ground ejection device to a set angle; the ground terminal sends an ejection confirmation signal to the ground ejection device, the ground ejection device launches an air detection device, the air detection device collects real-time comprehensive data and sends the real-time comprehensive data to the ground terminal, and the ground terminal receives the comprehensive data, performs dynamic image synthesis and target object identification analysis and pushes target object information; the comprehensive data comprises self motion attitude information of the aerial detection device, relative position information of the aerial detection device, a depth map and a thermal imaging map of the periphery of the target object.
Preferably, aerial detection device is for including the spherical shell that upper hemispherical shell and lower hemispherical shell constitute, set up a plurality of detectors on the spherical shell and accomodate the hole and set up the parachute along the circumference and accomodate the groove at the top of upper hemispherical shell, arrange infrared detection system, motion sensing system, major control system and power supply system in the spherical shell, infrared detection system, motion sensing system and power supply system all with major control system links to each other, infrared detection system includes a plurality of infrared detector, infrared detector passes through the detector is accomodate the hole and is fixed on the spherical shell.
Preferably, the plurality of infrared detectors comprise a plurality of infrared detectors A which are arranged along the circumference of the spherical shell in a layered manner and an infrared detector B which is arranged at the lower vertex of the spherical shell, the infrared detectors A are M layers except the upper vertex and the lower vertex of the spherical shell, and N infrared detectors are arranged on each layer, wherein M is more than or equal to 3 and less than or equal to 6, and N is more than or equal to 9 and less than or equal to 15.
Preferably, the infrared detection system is used for capturing the thermal imaging image and the depth image, and further comprises an infrared signal memory and a first a/D acquisition circuit, the infrared detector and the first a/D acquisition circuit are both electrically connected with the infrared signal memory, and the infrared signal memory transmits the thermal imaging image and the depth image to the main control system.
Preferably, motion sensing system for continuously catch aerial detection device's motion state, it includes automatically controlled parachute, automatically controlled motor, inertial sensor and second AD acquisition circuit, automatically controlled parachute upper end is passed through outside the spherical shell is arranged in to the parachute storage tank, the drive of automatically controlled motor the opening/the recovery of automatically controlled parachute, second AD acquisition circuit with inertial sensor links to each other, automatically controlled motor and major control system electric connection.
Preferably, the master control system comprises a first master controller and a first WIFI module, the first WIFI module is responsible for returning information collected by the infrared detector and the inertial sensor, and the first WIFI module is electrically connected with the first master controller.
Preferably, the unlocking module comprises a photoelectric sensor, a second main controller, a second WIFI module and a safety device, and the photoelectric sensor, the second WIFI module and the safety device are electrically connected with the second main controller; the photoelectric sensor is fixed at the outlet of the ejection gun barrel and used for detecting whether foreign matters exist in the fixed range of the outlet of the gun barrel, the second main controller acquires signals of whether foreign matters exist and detected by the photoelectric sensor, controls the safety device to be locked/unlocked, and sends the signals of whether foreign matters exist to the ground terminal through the second WIFI module.
Preferably, the ground terminal includes:
the ground ejection device initialization module is used for setting relevant parameters of the ground ejection device, checking whether the external environment is suitable for ejection or not, and performing information interaction with the ground ejection device through a WIFI module in the ground terminal;
the target monitoring module is used for checking specific target information on a full time axis in a monitoring range after the aerial detection device is ejected, and communicating information with the aerial detection device through the first WIFI module;
and the state checking module of the aerial detection device is used for confirming the working state and the device loss condition of the aerial detection device so as to provide convenience for maintenance and repair, and the information intercommunication is carried out between the first WIFI module and the aerial detection device.
Has the advantages that: compared with the prior art, the invention has the following remarkable advantages: 1. the invention realizes a low-altitude search positioning system by utilizing an aerial detection device, the system quickly lifts off a sensor in a short time, can be used for emergencies, avoids influencing a target object and simultaneously realizes accurate ground target positioning; 2. the aerial detection device used by the invention has small volume, can be carried about, is convenient to recover, can be used for multiple times, and can be applied to scenes such as post-earthquake search and rescue, wild animal protection, criminal investigation, flood rescue and the like; 3. the aerial detection device avoids the barrier of the obstacle during ground ranging through aerial ranging; 4. the searching and positioning system is simple and easy to operate, the method is high in accuracy, and real-time information of the target object can be obtained.
Drawings
FIG. 1 is a schematic diagram of the general structure of an aerial detection device according to the present invention;
FIG. 2 is a schematic view of the internal structure of the aerial detection device 1 according to the present invention;
FIG. 3 is a schematic diagram of the internal structure of the aerial detection device of the present invention shown in FIG. 2;
FIG. 4 is a schematic diagram of an infrared detection system according to the present invention;
FIG. 5 is a flow chart of the operation of the aerial detection unit of the present invention;
fig. 6 is a schematic structural view of a ground ejection device according to the present invention;
fig. 7 is a flow chart of a working method of the ground ejection device according to the invention;
fig. 8 is a schematic structural diagram of a low-altitude positioning search system according to the present invention;
fig. 9 is a flowchart of a method of operating a ground terminal according to the present invention;
fig. 10 is a schematic diagram of a simulation structure of a ground ejection device according to an embodiment of the present invention;
FIG. 11 is a diagram illustrating the relationship between the air resistance F and the centroid velocity V of the aerial detection device when the aerial detection device is ejected according to an embodiment of the present invention;
FIG. 12 is a graph of the relationship between the height of the center of mass and time when the aerial detection device is ejected according to one embodiment of the present invention;
FIG. 13 is a graph showing X-direction displacement versus time for an airborne detection apparatus according to an embodiment of the present invention;
FIG. 14 is a Y-X relationship diagram illustrating the vertical and horizontal components of the center of mass of an airborne detection apparatus according to an embodiment of the present invention;
FIG. 15 is a graph of centroid velocity versus time for an airborne detection apparatus in accordance with an embodiment of the present invention;
FIG. 16 is a schematic diagram illustrating the relative position of an object to a user according to an embodiment of the present invention;
FIG. 17 is a schematic diagram of a polar coordinate transformation of a target relative to a ground terminal in accordance with an embodiment of the present invention;
fig. 18 is a flowchart of a method for calculating a relative position of a target object to a ground terminal according to an embodiment of the present invention;
fig. 19 is a schematic diagram of interface design and interaction of a ground terminal according to the present invention.
The figure includes: an aerial detection device 100, a spherical shell 101, a detector accommodating hole 102, a parachute accommodating groove 103, a first partition plate 104, a second partition plate 105, a third partition plate 106 and a fourth partition plate 107, an infrared detection system 1, an infrared detector 11, an infrared detector A111, an infrared detector B112, an infrared signal memory 12, a first A/D acquisition circuit 13, a motion sensing system 2, an electronic control parachute 21, an electronic control motor 22, an inertial sensor 23, a second A/D acquisition circuit 24, a main control system 3, a first main controller 31, a first WIFI module 32, a sequential circuit 33, a D/A conversion circuit 34, a power supply system 4, a power supply circuit 41 and a protection circuit 42,
the device comprises an ejector 200, an ejection barrel 201, a trigger mechanism 202, a trigger 2021, a trigger 2022, an unlocking module 203, a second WIFI module 2031, a second main controller 2032, a safety device 2033, a photoelectric sensor 2034, a communication module 204, a third A/D acquisition circuit 2041, a second D/A conversion circuit 2042, a power supply module 205 and a driving motor 206.
Detailed Description
As shown in fig. 8, the present invention utilizes an aerial detection device and a corresponding ejection device to implement a low-altitude search positioning system, which includes: the ground terminal sends an ejection angle signal to the ground ejection device, the ground ejection device drives a driving motor according to the received angle data, and the driving motor rotates the ground ejection device to a set angle; the ground terminal sends an ejection confirmation signal to the ground ejection device, the ground ejection device launches an air detection device, the air detection device collects real-time comprehensive data and sends the real-time comprehensive data to the ground terminal, and the ground terminal receives the comprehensive data, performs dynamic image synthesis and target object identification analysis and pushes target object information; the comprehensive data comprises self motion attitude information of the aerial detection device, relative position information of the aerial detection device, a depth map and a thermal imaging map of the periphery of the target object.
As shown in FIG. 1, the aerial detection device 100 of the present invention comprises a spherical shell 101 composed of an upper hemispherical shell and a lower hemispherical shell, and the sphere has a small volume, can be carried about, and can be designed to be 15 cm. The device 200 shell adopts bilayer structure, at first mainly adopts the carbon-fibre composite that tensile strength is high, density is little, corrosion resistance, durability are good, wraps up the natural rubber or the chloroprene rubber that stickness is high, elasticity is high in its outsourcing, can play effectual vibrations isolation, the internal circuit of protection aerial detection device.
Set up a plurality of detectors on the spherical shell 101 and accomodate hole 102 and set up the parachute along the circumference and accomodate groove 103 at the top of last hemisphere shell, set up infrared detection system 1, motion sensing system 2, major control system 3 and power supply system 4 in the spherical shell 101, infrared detection system 1, motion sensing system 2 and power supply system 4 all with major control system 3 links to each other, infrared detection system 1 includes a plurality of infrared detector 11, infrared detector 11 passes through detector is accomodate hole 102 and is fixed on the spherical shell 101.
As shown in fig. 2 and 3, a first partition plate 104, a second partition plate 105, a third partition plate 106 and a fourth partition plate 107 are sequentially installed in the spherical shell 101 from bottom to top along the circumference, the fourth partition plate 107 is used for placing an electronic control parachute 21 in the motion sensing system 2 and an electronic control motor 22 for driving the electronic control parachute 21 to open and recover, the upper end of the electronic control parachute 21 penetrates through the parachute storage groove 103 and is placed outside the spherical shell 1, in one embodiment, the electronic control motor 22 is a stepping motor, the stepping motor can control the rotating speed and the stopping position of the motor through pulse signals, the electronic control parachute 21 has a risk of being stuck in an aerial detection device, and the parachute can be effectively taken out and unfolded by adjusting the state of the stepping motor.
The third diaphragm 106 houses the inertial sensor 23 in the motion sensing system 2 and the second a/D acquisition circuit 24 connected to the inertial sensor 23. The inertial sensor 23 is responsible for collecting the motion state of the detection device itself, and includes: the speed, the acceleration, the angular acceleration, the spatial rotation angle and the like are detected and then sent to the master control system 3. When the inertial sensor 23 detects that the aerial detection device 100 rises to the highest point (when the vertical speed is reduced to 0), the main control system 3 drives the electric control motor 22 at the top end of the detection device 100 to open the electric control parachute 21, and the first WIFI module 32 continuously transmits back data in the process.
Preferably, the inertial sensor 23 parameters are as follows: the model is as follows: SI-11.s1.c-30, sensitivity 10 hz <0.0015 °, repeated measurement deviation ± 0.0030 °, temperature coefficient deviation ± 0.0025 °/K, output data rate: 1600 hertz, bandwidth: 400 Hz, digital interface: SPI, working temperature-40 to 85 degrees.
The second partition 105 is used for placing related components of the main control system 3 and related components of the power supply system 4, and specifically placing the first main controller 31, the first WIFI module 32 for receiving and transmitting signals, the sequential circuit 33, the D/a conversion circuit 34, the power circuit 41 for providing power and the protection circuit 42 connected with the power circuit 41, wherein the D/a conversion circuit is connected with the first WIFI module 32, and the sequential circuit 33, the power circuit 41 and the first WIFI module 32 are connected with the first main controller 31.
The first WIFI module 32 includes a sub-module WIFI RFID module, and the WIFI RFID module is responsible for returning information collected by each sensor, and is also responsible for returning the position information of the detection device to the ground terminal. The Wifi RFID module is a submodule of the Wifi module, and the specific relative position of the detection device is mainly determined through a WIFI RFID technology. The WIFI main module is mainly responsible for transmission work of all data, and the data comprise relative positions of the detection devices acquired through a WIFI RFID technology. The system carries a high-power wifi module with the model number of SKW77, the farthest communication distance is 1.5 kilometers, signals of the module are not attenuated in a short-distance communication range, and the condition that the signals cannot be received does not exist.
As shown in fig. 4, the first partition 104 is used to place the infrared signal storage 12 in the infrared detection system 1 and the first a/D acquisition circuit 13 connected to the infrared signal storage 12, in one embodiment, the infrared signal storage 11 is preferably an uncooled focal plane infrared signal storage, and all the infrared detectors 11 are electrically connected to the infrared signal storage 12. The infrared detector 11 is connected with the uncooled focal plane infrared signal memory at the lowest layer through a data line arranged along the inner wall of the detection device.
The spherical shell of the aerial detection device is made of a carbon fiber composite material with the thickness of 2.5cm, the density of the material is larger than the average density of internal electronic elements, the weight of the shell accounts for more than 90% of the weight of the whole detection device, the center of mass of the aerial detection device is basically located at the center of a sphere, and the influence of the mass distribution of the electronic elements in the aerial detection device on the balance of the device is negligible.
The data interfaces of the first master controller 31 are all Serial Peripheral Interfaces (SPI), wherein the first master controller 31 and the sequential circuit 33 are connected by a Serial Clock Line (SCLK), and all the other modules are connected by a data line MISO.
The plurality of infrared detectors 11 on the outer surface of the spherical shell 101 comprise a plurality of infrared detectors a111 arranged in the detector accommodating holes 102 on the spherical shell in a layered manner along the circumference of the spherical shell and an infrared detector B112 arranged in a detector accommodating hole (not shown in the figure) arranged at the lower vertex of the spherical shell, preferably, the infrared detectors 11 are uncooled infrared focal plane sensors which are responsible for collecting an infrared thermal imaging image and a depth image of an external environment; the dry infrared detectors A111 are M layers except the upper vertex and the lower vertex of the spherical shell, and N infrared detectors are arranged on each layer, wherein M is more than or equal to 3 and less than or equal to 6, and N is more than or equal to 9 and less than or equal to 15. The upper vertex of the spherical shell is not provided with the infrared detector because the electric control parachute 21 needs to be placed.
Preferably, there are 61 infrared detectors, wherein the infrared detectors a111 of the detection device are distributed in five layers, each layer has 12 infrared detectors, and there are 60 infrared detectors in total, and there is one infrared detector B112 at the bottom. The detection space angle of each infrared detector is 45 degrees, the number of the infrared detectors can be set to 8 within a space range of 360 degrees, and the number of the infrared detectors can be set to 4 within a space range of 180 degrees. In order to enhance the signal intensity of infrared rays in a detection angle, the space angle of two adjacent sensors is set to be 30 degrees, on one hand, the detection range can be covered in all aspects, and on the other hand, data acquisition can be achieved without omission. Through aerial range finding, obstacle barrier when avoiding ground range finding.
The infrared detector parameters were as follows: the model is as follows: LA3110(384 × 28817 μm) uncooled infrared movement assembly; noise equivalent temperature difference: at the temperature of less than or equal to 60mK @25 ℃, and f/1.0 (optional less than or equal to 50 mK); frame frequency: 50 Hz; working voltage: 4V; power consumption: less than or equal to 1.7W; working temperature: minus 40 ℃ to plus 60 ℃.
As shown in fig. 5, which is a flow chart of the working principle of each module in the aerial detection device, when the first main controller operates, the inertial sensor continuously captures the motion state of the detection device; firstly, when the inertial sensor detects that the detection device rises to the highest point, the electric control motor drives the electric control parachute to release; the infrared sensor continuously captures the thermal imaging image and the depth image, the sub-module WIFI RFID of the first WIFI module continuously captures the relative position of the detection device, when the first WIFI module continuously returns data to the ground terminal, whether the detection device falls to the ground or not is detected, when the detection is finished and the detection device falls to the ground, all sensors are closed, and the rear WIFI RFID module continuously returns the relative position of the detection device.
As shown in fig. 6, the present invention further discloses a ground ejection device, which can be directly fixed on the ground, and comprises the above-mentioned aerial detection device 100 and an ejector 200, wherein the ejector 200 comprises an ejection barrel 201 matched with the sphere of the aerial detection device 100, and the aerial detection device 100 is placed in the ejection barrel 201.
The catapult 200 comprises a catapult barrel 201 matched with the aerial detection device sphere, a triggering mechanism 202, a communication module 204, an unlocking module 203 and a power supply module 205, wherein the communication module 204 is used for acquiring and transmitting and receiving signals, the power supply module 205 is used for supplying energy, the aerial detection device 100 is arranged in the catapult barrel 201, the unlocking module 203 is used for controlling whether the aerial detection device 100 is launched or not, and when the unlocking module 203 is locked, the triggering mechanism 202 does not work, and the aerial detection device 100 does not launch; when the unlocking module 203 is unlocked, the trigger mechanism 202 can be ignited, and the aerial detection device 100 is launched from the ejection barrel 101.
The trigger mechanism 202 includes a trigger 2021 and a trigger 2022, both disposed at the bottom of the catapult barrel 201, the trigger 2021 is a gunpowder-triggered fuse, and after the trigger 2022 is pulled, the fuse can be ignited to generate explosion in the catapult barrel 201, so that the aerial detection device 100 flies out.
The unlocking module 203 includes a photoelectric sensor 2034, a second main controller 2032, a second WIFI module 2031 and a safety device 2033, the photoelectric sensor 2034, the second WIFI module 2031 and the safety device 2033 are electrically connected to the second main controller 2032.
The photoelectric sensor 2034 is ring-shaped and is nested on the outer wall of the mouth of the catapult gun barrel 201 to detect whether foreign matter exists in the fixed range of the outlet of the gun barrel, the photoelectric sensor 2034 can monitor a space angle of 45 degrees and a distance of 1m, the third a/D acquisition circuit 2041 converts an analog signal detected by the photoelectric sensor 2034 into digital signals 1 and 0, wherein when the signal is 1, the signal represents that no foreign matter exists around the emission mouth of the ground catapult device, when the signal is 0, the signal represents that foreign matter exists around the emission mouth of the ground catapult device, and transmits the converted digital signal to the second main controller 2032, if the second main controller 2032 receives the digital signal 1, the ground catapult device is unlocked, and if the second main controller 2032 receives the digital signal 0, the unlocking device is in a locked state.
The second main controller 2032 in the ejection device is configured to store a feedback signal without a foreign object, and send the signal to the ground terminal through the second WIFI module 2031. Meanwhile, the second main controller 2032 drives the driving motor 206 and the ejection device to operate, and the driving motor 206 is preferably a stepping motor. The state information of the device obtained after being processed by the second main controller 2032 is converted into an analog signal by the second D/a conversion circuit 2042, and the analog signal is transmitted back to the ground terminal by the second WIFI module 2031. Therefore, the sensor can be quickly lifted off in a short time in an ejection mode, and the sensor can be used for emergency events, so that accurate ground target positioning is realized while the target object is prevented from being influenced.
The data Interface connected to the second host controller 2032 is SPI (Serial Peripheral Interface), and all data lines use MISO data lines.
As shown in fig. 6, a safety device 2033 is located at the periphery of the trigger 2022 of the ground ejection device, the device 2033 is used for locking or unlocking the trigger 2022, the device 2033 can clamp the trigger 2022 by a clamp when in a locked state, so that an operator cannot pull the trigger 2022 to ignite a fuse, the safety device 2033 is controlled to be unlocked or locked by the second main controller 2032, the second main controller 2032 receives a signal sent by the photoelectric sensor 2034 and then performs data processing, and sends an instruction to the safety device 2033 through a MISO data line, and when the photoelectric sensor 2034 detects that no foreign object exists within 1m of the periphery of the emission opening of the emission device, the locked state is automatically released.
Fig. 7 shows a flow chart of the ejector.
Firstly, the ejector 200 is fixed on the ground, it is confirmed that the emission environment of the detection device is good, the photoelectric sensor 2034 detects whether foreign matters exist within a range of 1m of the emission port of the ground ejection device, the third a/D acquisition circuit 2041 converts an analog signal detected by the photoelectric sensor 2034 into digital signals 1 and 0, wherein when the signal is 1, the signal represents that no foreign matters exist around the emission port of the ground ejection device, when the signal is 0, the signal represents that foreign matters exist around the emission port of the ground ejection device, and transmits the converted digital signal to the second main controller 2032, if the second main controller 2032 receives the digital signal 1, the safety 2033 is unlocked, and if the second main controller 2032 receives the digital signal 0, the safety 2033 is locked.
Secondly, the ground terminal sends the ejection angle signal to the second main controller 2032 through the second WIFI module 2031, and the second main controller 2032 drives the stepping motor 206 according to the received angle data to rotate the ejection barrel 201 to a set angle.
Finally, the ground terminal sends the ejection confirmation signal to the second main controller 2032 through the second WIFI module 2031, and launches the aerial detection device.
The first main controller and the second main controller are both MCU (micro controller unit) with the model of STM32F103C8T6, the first WIFI module and the second WIFI module are mainly responsible for transmission of all data, and the data comprise relative positions of detection devices acquired through WIFI RFID technology. The system carries a high-power wifi module with the model number of SKW77, and the farthest communication distance is 1.5 kilometers.
The following discusses the motion model of the aerial detection device, and in the present invention, the motion model of the aerial detection device 100 is as follows:
when the air resistance is in direct proportion to the square of the speed, a motion trail equation of the air detection device can be written by a kinematic formula and a Newton's second law, and the following equation is shown in an O-xy coordinate in the rising process:
the x direction:
the y direction:
will be replaced by
Substituted type
Is provided with
The variables are separated and integrated simultaneously for the above formula and an initial boundary condition v is appliedx|t＝0＝v0x
Continuing to adopt separation variable method and using initial condition x-t＝00, available
Will be replaced by
In the formula (2) is
Can obtain the product
By substitution
Continue to separate the variable integrals and add the initial condition y tint t＝00, available
In the above formula when vyWhen y is 0, y takes a maximum value of ymax，t1At the moment when the air detection device reaches the highest point, the descending process will be
Substituting into formula (3), and adding initial conditions by separation variable method
Can obtain the product
The same can be obtained
Wherein
Wherein x is1Is the horizontal displacement, x, of the aerial detection device during the ascent process2Is the horizontal displacement of the parachute in the descending process, y is the vertical displacement of the aerial detection device in the ascending process, vx1Is the velocity, v, in the horizontal direction of the airborne probe during ascentx2Is the velocity in the horizontal direction, v, of the parachute during descenty1Is the velocity, v, in the vertical direction of the airborne probe during ascenty2Is the velocity in the vertical direction of the descent of the parachute, CVIs the coefficient of resistance of an object in air, m1Is the mass of the aerial sounding device, m2Is the mass of the parachute, g is the acceleration of gravity, v0Is the initial velocity of the aerial detection device. k is a radical of1＝0.5ρ0S1C1，,ροIs the density of air, S1C is the maximum cross-sectional area of the aerial detection device, C1Is the air resistance coefficient of the aerial detection device; k is a radical of2＝0.5ρ0S2C2，S2Is the maximum cross-sectional area of the parachute, C2Is the air resistance coefficient of the parachute.
Based on the aerial detection device and the ground ejection device, the work flow of the search system comprises the following steps:
s1, after confirming the environment detected by the aerial detection device and adjusting the launching angle of the ground launching gun barrel, launching the aerial detection device to the air by the launcher;
firstly, opening a ground terminal application interface, sending an ejection angle signal to a ground ejection device by the ground terminal through a second WIFI module, driving a stepping motor 208 by the ground ejection device according to the received angle data, and rotating the ejection device to a set angle;
then, the ground terminal sends an ejection confirmation signal to the ground ejection device through the second WIFI module 203, the ground ejection device launches the aerial detection device, an ejection angle is set, an ejection height is confirmed, and a trigger of the ejector is triggered after no error is confirmed, wherein the ejection impulse is generated by ignition of gunpowder and is a fixed value;
in one embodiment, in step (1), the relationship between the angle θ of the ground ejection device and the height h of the ejection air detection device is as follows:
wherein P is impulse generated by gunpowder explosion, m1Is the mass of the aerial sounding device, m2Is the quality of the electric control parachute.
And finally, the catapult launches the aerial detection device through the driving force generated after the powder ignites the fuse.
S2, acquiring current comprehensive data of the aerial detection device, wherein the comprehensive data comprises self motion attitude information of the aerial detection device, relative position information of the aerial detection device, a depth map and a thermal imaging map of the periphery of the target object;
after the aerial detection device leaves the ground ejection device, the infrared detector enters a working state to continuously capture a depth map and a thermal imaging map of the periphery of a target object, a sub-module WIFI RFID module in the first WIFI module continuously captures relative position information of the aerial detection device, and the inertial sensor continuously captures motion posture information of the aerial detection device and sends the information to the first main controller.
And S3, the ground terminal receives the comprehensive data, performs dynamic image synthesis and target object identification analysis, and pushes target object information. Fig. 9 is a flowchart illustrating the operation of the ground terminal.
Analog signals captured by the infrared detector 11 and the inertial sensor 23 are converted into digital signals through the A/D converter 13 and input into the first main controller 31, the digital signals are converted into the analog signals through the D/A converter 34 after the first main controller 31 is processed, and the analog signals are sent to the ground terminal through the first WIFI module 32. The ground terminal device receives the infrared thermal imaging image and the depth map sent by the aerial detection device 100, 2 frames per second, the motion attitude information of the detection device itself, and the position information of the detection device.
In one embodiment, in the step (3), the performing dynamic image synthesis and target object recognition analysis and pushing target object information specifically includes:
(31) the ground terminal synthesizes the images transmitted by each frame of the infrared detector into an HDR scene map in a UV map mode; each infrared detector outputs a corresponding transmission image.
(32) Identifying characteristic points in the infrared thermal imaging image through an image identification algorithm, wherein the points with the temperature higher than the surface temperature of the living body are defaulted to be about 30 ℃, and distinguishing a boundary between a target object and the external environment through the characteristic points so as to calculate the position of the mass center of the target object and obtain the relative position coordinate of the target object relative to the aerial detection device;
(33) synthesizing the position coordinates of the target object relative to the aerial detection device, including distance, azimuth angle and pitch angle, and calculating the position coordinates of the target object relative to the user through the position coordinates of the aerial detection device relative to the user;
(34) and pushing the position coordinates of the target object and the aerial detection device relative to the user through a target detection interface of the ground terminal.
Therefore, the low-altitude positioning method can deal with emergency events, is high in accuracy, and can position real-time information of the target object.
The ground terminal is mobile terminal, communication equipment such as cell-phone, computer, ipad, and it includes WIFI module and compass on the hardware, includes data analysis module on the software, includes on the application human-computer interface:
the ground ejection device initialization module is used for setting relevant parameters of the ground ejection device, checking whether the external environment is suitable for ejection or not, and performing information interaction with the ground ejection device through a WIFI module in the ground ejection device;
the target monitoring module is used for checking specific target information on a full time axis in a monitoring range after the aerial detection device is ejected, a user can traverse the whole work flow through a sliding bar, can expand a thermal imaging graph and a depth graph of a target after clicking the target, and is in information intercommunication with the aerial detection device through the first WIFI module;
and the state checking module of the aerial detection device is used for confirming the working state and the device loss condition of the aerial detection device so as to provide convenience for maintenance and repair, and the information intercommunication is carried out between the first WIFI module and the aerial detection device.
A specific embodiment of the motion simulation process is given below:
the following is the detector motion process simulated by Adams software under the condition that the emergence angle is 45 degrees, namely the set angle of the ejection gun barrel is 45 degrees:
(1) adams software is introduced into the model file, the position of the center of mass of the detection device is used as a coordinate origin, and the direction of the catapult is 45 degrees along the XY axis, as shown in FIG. 10.
Wherein the diameter of the aerial detection device 200 is 15cm, and the average density of the aerial detection device and the parachute is 1000kg/m3In the flying process of the detection device, the direction of the air resistance F is always opposite to the direction of the mass center speed of the detection device, and the direction of the mass center speed of the detection device is always changed along with the time. Therefore, when a force is applied to the model, the air resistance needs to be divided into two force components F in the positive axial direction and the negative axial directionxAnd FyApplication was performed as shown in fig. 11.
Air resistance F ═ 0.5 rho V in flying process of detection device2SmCwThe direction is opposite to the direction of the mass center speed of the detection device; where ρ is∞Is the density of air, V∞For detecting the centroid velocity, S, of the devicem＝0.25πD2m is the maximum cross-sectional area of the detection device, and Cw is the air resistance coefficient. The air resistance coefficient of the detection device is 0.5, and the air resistance coefficient of the parachute is 1.4. Adding 9.8m/s of negative direction of Y axis in G direction of gravity into Adams2The resistance F to the detecting deviceX1，FY1Resistance F to the parachuteX2，FY2。
Considering the casting direction of 45 degrees, setting the initial speed VX＝28.7m/s，VY28.7 m/s. According to the formula of resistance F ═ 0.5 rho V2SmCWChecking the data to obtain the air density of 1.288Kg/m3Diameter of the detecting device is 15cm, and air resistance coefficient of the detecting device is CW0.5, parachute air resistance coefficient CW1.4, the total average density of the detector and parachute is 1000kg/m3The diameter of the Y axis of the parachute is 1.190m, the diameter of the X axis of the parachute is 0.2m, and 61 infrared detectors are used in the detection device.
Selecting an icon in a Function column in Adams, and entering a Function editor; entering in a function editor text box:
the resistance of the detecting device
FX1＝0.5*1.288*(.shell.danwan_V**2)*(3.1415/4)*(0.15**2)*0.5*sin(atan(.shell.danwan_VX/(0-.shell.danwan_VY)))*IF(.shell.danwan_VY-0:0,0,-1)
FY1＝0.5*1.288*(.shell.danwan_V**2)*(3.1415/4)*(0.15**2)*0.5*cos(atan(.shell.danwan_VX/(0-.shell.danwan_VY)))*IF(.shell.danwan_VY-0:0,0,-1)
Resistance to parachute
FX2＝0.5*1.288*(.shell.danwan_V**2)*(3.1415/4)*(0.200**2)*1.4*sin(atan(.shell.danwan_VX/(0-.shell.danwan_VY)))*IF(.shell.danwan_VY-0:1,0,0)
FY2＝0.5*1.288*(.shell.danwan_V**2)*(3.1415/4)*(1.190**2)*1.4*cos(atan(.shell.danwan_VX/(0-.shell.danwan_VY)))*IF(.shell.danwan_VY-0:1,0,0)
The above is an Adams function editor resistance expression, in the Adams experiment of this embodiment, the name of the aerial detection device is danwan, shell is a geometric body, and in Adams, a part or a model is referred to,. shell.
Considering that the 45-degree oblique-shooting maximum height of the aerial detection device is 40m, the lift-off height of the aerial detection device depends on the charge of gunpowder in the ground ejection device, the fixed amount of gunpowder explosion can only generate a fixed impulse to push the aerial detection device, the emission impulse of the ground ejection device acting on the aerial detection device is a fixed value 71Ns, and the impulse can maximally oblique-shoot the aerial detection device to the 40m high altitude, and the calculation formula is as follows:
wherein, P is the impulse generated by the explosion of gunpowder, the impulse is 71Ns in the embodiment, theta is the included angle between the gun barrel of the ground ejection device and the ground, the oblique firing angle is 45 degrees in the embodiment, and m is1Is the mass of the aerial sounding device, m2Is the mass of the parachute, which in this example is 1.77kg in total mass.
In the simulation experiment of the embodiment, the names of danwan, CM _ position, x and danwan, CM _ position, y are used to represent displacement changes of the aerial detection device in x and y directions, and CM represents the center of mass. Fig. 12 shows the relationship between the height (Length) of the centroid of the detection device and the Time (Time), fig. 13 shows the relationship between the X-directional displacement (. danwan. cm _ position. X) of the detection device in the air and the Time (Time), and fig. 14 shows the relationship between the vertical component and the horizontal component Y-X height of the centroid of the detection device; fig. 15 is a graph of the centroid velocity (velcro) versus Time (Time) for an aerial detection device.
Taking 21 points of the detection device X, Y direction movement process for quantitative description, the specific correspondence is as the following table 1:
the 21 points are 0.9 second in the time dimension as one step, the number of the collected points can be adjusted according to the size of the step, and can also be set as other steps according to specific requirements to carry out quantitative description. The meaning of describing these points is to describe the displacement change of the aerial detection device in the current relative position, i.e. in the x and y directions. According to the motion simulation experiment of the detection device, the short time required for positioning and the feasibility of the detection device can be seen.
TABLE 1 Displacement Change of aerial sonde at Current relative position, i.e. in x and y directions
(2) Obtaining the current relative position coordinates of the aerial detection device, the depth map and the thermal imaging map of the periphery of the target object
The infrared detector is activated to enter a working state after the detection device leaves the ejector, the first main controller and the inertial sensor are in a continuous working state, the inertial sensor sends a signal to the first main controller after detecting external impact, and the first main controller controls the infrared detector to enter the working state.
(3) Ground terminal receiving sensor comprehensive data
Analog signals captured by the infrared detector and the inertial sensor are converted into digital signals through the second A/D acquisition circuit and input into the first main controller, the digital signals are converted into the analog signals through the D/A conversion circuit after the first main controller is processed, and the analog signals are sent to the ground terminal through the first WIFI module. And the ground terminal receives the infrared thermal imaging image and the depth map sent by the aerial detection device, the self motion attitude information of the detection device and the position information of the detection device.
(4) The ground terminal carries out dynamic image synthesis and target object identification analysis and pushes target object information
After receiving the information sent by the aerial detection device, the ground terminal device combines the images transmitted by each frame by the infrared detectors, in this embodiment, 61 infrared detectors are shared, the 61 transmitted images are combined into an HDR scene map in a UV map mode, and feature points in the infrared thermal imaging map are identified by an image identification algorithm, wherein a point with a temperature higher than the body surface temperature of a living body is about 30 ℃ by default, and a boundary between a target object and an external environment is distinguished by the feature points, so that the centroid position of the target object is calculated, and a relative position coordinate of the target object relative to the aerial detection device is obtained.
And synthesizing the position coordinates of the target relative to the aerial detection device, wherein the position coordinates comprise two groups of vectors of distance, azimuth angle, pitch angle and the position coordinates of the aerial detection device relative to the user, and the position coordinates of the target relative to the user are calculated. And pushing the position coordinates of the target and the aerial detection device relative to the user by applying a target detection interface through the ground terminal.
The relative position of the target to the user is calculated as follows:
as shown in fig. 16, a is the location of the user, B is the location of the aerial detection device, and C is the location of the target; d1For the user-aerial detection device relative distance, d2For the aerial sonde-target relative distance, d3Is the user-target relative distance; as shown in fig. 17, θ1For the user-airborne sonde azimuth angle, θ2For airborne detection apparatus-target azimuth, theta3A user-target azimuth;
for the user-the pitch angle of the aerial detection unit,
for an aerial sonde-target pitch angle,
user-target pitch angle.
As shown in fig. 18, the relative position of the object to the ground terminal is calculated as follows:
polar coordinates of target relative to aerial detection device
Polar coordinates of aerial detection device relative to ground terminal
Directly obtained by a sensor of the aerial detection device, and converted into a space rectangular coordinate formula through a polar coordinate:
converting the two polar coordinates into space rectangular relative coordinates, and directly adding the two space rectangular relative coordinates to obtain a space rectangular relative coordinate (x) of the target relative to the ground terminal3,y3,z3)＝(x1+x2,y1+y2,z1+z2) And finally, converting the space rectangular relative coordinate into a polar coordinate formula through the space rectangular relative coordinate:
converted into polar coordinates of the target relative to the ground terminal
The coordinate information can be pushed to the user in the ground terminal through the human-computer interface.
In this embodiment, as shown in fig. 19, the ground terminal includes 3 interfaces: the ejection initialization interface, the target monitoring interface and the detection device state viewing interface can be switched among the three interfaces through left-right sliding operation. Wherein: the ejection initialization interface is used for setting relevant parameters of the ground ejection device.
The ejection angle is freely set by a user, the set angle is 45 degrees in the embodiment, and after the ejection angle is set, the ground terminal automatically calculates the ejection height which can be reached under the ejection angle according to the calculation formula and displays the ejection height on the interface.
Checking whether the external environment is suitable for ejection; the target monitoring interface is used for checking specific target information on a full time axis in a monitoring range after the detection device is ejected, a user can traverse the whole work flow through a sliding slide bar, and specific information of a target, namely a thermal imaging graph and a depth graph, can be expanded after clicking the target; the detection device state viewing interface is used for confirming the working state of the detection device and the loss condition of the device, so that convenience is provided for maintenance and repair.
(5) Recovery of aerial detection device after landing
And after the air detection device falls to the ground, the user recovers the position information of the air detection device according to the received position information of the air detection device to finish detection.
The above-mentioned embodiments are only preferred embodiments of the present invention, and do not limit the technical scope of the present invention, so that the changes and modifications made by the claims and the specification of the present invention should fall within the scope of the present invention.
Claims (8)
1. A low-altitude search positioning system, comprising: the ground terminal sends an ejection angle signal to the ground ejection device, the ground ejection device drives a driving motor according to the received angle data, and the driving motor rotates the ground ejection device to a set angle; the ground terminal sends an ejection confirmation signal to the ground ejection device, the ground ejection device launches an air detection device, the air detection device collects real-time comprehensive data and sends the real-time comprehensive data to the ground terminal, and the ground terminal receives the comprehensive data, performs dynamic image synthesis and target object identification analysis and pushes target object information; the comprehensive data comprises self motion attitude information of the aerial detection device, relative position information of the aerial detection device, a depth map and a thermal imaging map of the periphery of the target object;
aerial detection device is for including the spherical shell that upper hemisphere shell and lower hemisphere shell are constituteed, set up a plurality of detectors on the spherical shell and accomodate the hole and set up the parachute along the circumference and accomodate the groove at the top of upper hemisphere shell, set up infrared detection system, motion sensing system, major control system and power supply system in the spherical shell, infrared detection system, motion sensing system and power supply system all with major control system links to each other, infrared detection system includes a plurality of infrared detector, infrared detector passes through the detector is accomodate the hole and is fixed on the spherical shell.
2. The low-altitude search positioning system according to claim 1, wherein the plurality of infrared detectors comprise a plurality of infrared detectors A arranged in layers along the circumference of the spherical shell and an infrared detector B arranged at the lower vertex of the spherical shell, the plurality of infrared detectors A are arranged in M layers except the upper vertex and the lower vertex of the spherical shell, and N infrared detectors are arranged in each layer, wherein M is greater than or equal to 3 and less than or equal to 6, and N is greater than or equal to 9 and less than or equal to 15.
3. The low-altitude search positioning system according to claim 1, wherein the infrared detection system is configured to capture the thermal image and the depth map, and further comprises an infrared signal memory and a first a/D acquisition circuit, the infrared detector and the first a/D acquisition circuit are both electrically connected to the infrared signal memory, and the infrared signal memory transmits the thermal image and the depth map to the main control system.
4. The low altitude search positioning system according to claim 1, wherein the motion sensing system is configured to continuously capture a motion state of the aerial detection device, and comprises an electrically controlled parachute, an electrically controlled motor, an inertial sensor, and a second a/D acquisition circuit, wherein an upper end of the electrically controlled parachute is placed outside the spherical shell through the parachute storage slot, the electrically controlled motor drives the opening/recovery of the electrically controlled parachute, the second a/D acquisition circuit is connected to the inertial sensor, and the electrically controlled motor is electrically connected to the main control system.
5. The low-altitude search positioning system according to claim 4, wherein the main control system comprises a first main controller and a first WIFI module, the first WIFI module is responsible for returning information collected by the infrared detector and the inertial sensor, and the first WIFI module is electrically connected with the first main controller.
6. The low altitude search positioning system according to claim 1, wherein the ground ejection device comprises an ejection barrel matched with the air detection device sphere, a triggering mechanism, a communication module, an unlocking module and a power module, wherein the communication module is used for collecting and transmitting and receiving signals, the power module is used for supplying energy, the air detection device is arranged in the ejection barrel, the unlocking module is used for controlling whether the air detection device is launched or not, and when the unlocking module is locked, the triggering mechanism does not work, and the air detection device does not launch; when the unlocking module is unlocked, the trigger mechanism is ignited, and the aerial detection device is launched out from the ejection gun barrel.
7. The low-altitude search positioning system according to claim 6, wherein the unlocking module comprises a photoelectric sensor, a second main controller, a second WIFI module and a safety device, and the photoelectric sensor, the second WIFI module and the safety device are electrically connected with the second main controller; the photoelectric sensor is fixed at the outlet of the ejection gun barrel and used for detecting whether foreign matters exist in the fixed range of the outlet of the gun barrel, the second main controller acquires signals of whether foreign matters exist and detected by the photoelectric sensor, controls the safety device to be locked/unlocked, and sends the signals of whether foreign matters exist to the ground terminal through the second WIFI module.
8. The low-altitude search positioning system according to claim 7, wherein the ground terminal comprises:
the ground ejection device initialization module is used for setting relevant parameters of the ground ejection device, checking whether the external environment is suitable for ejection or not, and performing information interaction with the ground ejection device through a WIFI module in the ground terminal;
the target monitoring module is used for checking specific target information on a full time axis in a monitoring range after the aerial detection device is ejected, and communicating information with the aerial detection device through the first WIFI module;
and the state checking module of the aerial detection device is used for confirming the working state and the device loss condition of the aerial detection device so as to provide convenience for maintenance and repair, and the information intercommunication is carried out between the first WIFI module and the aerial detection device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811623450.0A CN109612456B (en) | 2018-12-28 | 2018-12-28 | Low-altitude search positioning system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811623450.0A CN109612456B (en) | 2018-12-28 | 2018-12-28 | Low-altitude search positioning system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109612456A CN109612456A (en) | 2019-04-12 |
| CN109612456B true CN109612456B (en) | 2022-04-29 |
Family
ID=66013051
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811623450.0A Active CN109612456B (en) | 2018-12-28 | 2018-12-28 | Low-altitude search positioning system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109612456B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111731486B (en) * | 2020-06-04 | 2023-12-19 | 上海机电工程研究所 | parachute ejection device |
| CN113091513B (en) * | 2021-03-03 | 2023-02-28 | 上海机电工程研究所 | Real-time dynamic calibration method, system and medium for ship-based missile weapon system |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4025913A (en) * | 1975-12-22 | 1977-05-24 | The United States Of America As Represented By The Secretary Of The Navy | Electrical field sensing and transmitting apparatus |
| CN1140261A (en) * | 1995-12-22 | 1997-01-15 | 中国科学院空间科学与应用研究中心 | Ejection space electric field detecting method and apparatus |
| WO2005010842A1 (en) * | 2003-07-25 | 2005-02-03 | Wei Chen | Method and device for detecting infrared sources |
| CN105137421A (en) * | 2015-06-25 | 2015-12-09 | 苏州途视电子科技有限公司 | Photoelectric composite low-altitude early warning detection system |
| WO2017199273A1 (en) * | 2016-05-19 | 2017-11-23 | 株式会社 スカイロボット | Search system |
| CN108957445A (en) * | 2018-07-30 | 2018-12-07 | 四川九洲空管科技有限责任公司 | A kind of low-altitude low-velocity small targets detection system and its detection method |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103493112B (en) * | 2011-02-22 | 2016-09-21 | 菲力尔***公司 | infrared sensor system and method |
-
2018
- 2018-12-28 CN CN201811623450.0A patent/CN109612456B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4025913A (en) * | 1975-12-22 | 1977-05-24 | The United States Of America As Represented By The Secretary Of The Navy | Electrical field sensing and transmitting apparatus |
| CN1140261A (en) * | 1995-12-22 | 1997-01-15 | 中国科学院空间科学与应用研究中心 | Ejection space electric field detecting method and apparatus |
| WO2005010842A1 (en) * | 2003-07-25 | 2005-02-03 | Wei Chen | Method and device for detecting infrared sources |
| CN105137421A (en) * | 2015-06-25 | 2015-12-09 | 苏州途视电子科技有限公司 | Photoelectric composite low-altitude early warning detection system |
| WO2017199273A1 (en) * | 2016-05-19 | 2017-11-23 | 株式会社 スカイロボット | Search system |
| CN108957445A (en) * | 2018-07-30 | 2018-12-07 | 四川九洲空管科技有限责任公司 | A kind of low-altitude low-velocity small targets detection system and its detection method |
Non-Patent Citations (1)
| Title |
|---|
| 单兵小型无人机侦察***发展与分析;贺成龙等;《飞航导弹》;20130115(第01期);第27-31页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109612456A (en) | 2019-04-12 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107087427B (en) | Control method, device and the equipment and aircraft of aircraft | |
| Andraši et al. | Night-time detection of uavs using thermal infrared camera | |
| CN105980950B (en) | The speed control of unmanned vehicle | |
| US9237317B2 (en) | Throwable camera and network for operating the same | |
| US11486346B1 (en) | Autonomous underwater beacon locator | |
| JP2022504284A (en) | Deployable aviation measures to neutralize and capture target aircraft | |
| JP5567805B2 (en) | Flying object detection method, system, and program | |
| CN108521812A (en) | Control method, unmanned plane and the machine readable storage medium of unmanned plane | |
| CN108139758A (en) | Apparatus of transport positioning based on significant characteristics | |
| CN107850436A (en) | Merged using the sensor of inertial sensor and imaging sensor | |
| CN107850901A (en) | Merged using the sensor of inertial sensor and imaging sensor | |
| CN107615211A (en) | Merged using the sensor of inertial sensor and imaging sensor | |
| US6933965B2 (en) | Panoramic aerial imaging device | |
| CN106274617B (en) | Ship, machine combination monitoring method and monitoring system | |
| CN106471337A (en) | Interchangeable mounting platform | |
| CN107850899A (en) | Merged using the sensor of inertial sensor and imaging sensor | |
| CN104029825A (en) | Unmanned aerial vehicle system with in-site virtual-actual coupling | |
| CN109947122A (en) | For controlling the equipment and its operating method of flight | |
| CN109612456B (en) | Low-altitude search positioning system | |
| CN207950388U (en) | Precise fire extinguishing system based on unmanned plane and intelligent fire robot | |
| CN109649654B (en) | Low-altitude search positioning method | |
| CN106586009A (en) | Unmanned aerial vehicle | |
| CN109683205B (en) | Aerial detection device and ground ejection system | |
| CN109279017B (en) | Foldable nano unmanned aerial vehicle for verification | |
| CN115202376A (en) | Unmanned aerial vehicle patrols and examines electric power grid management and control platform based on individual soldier removes |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |