CN112009705A - Automatic launching device of unmanned aerial vehicle time domain avionic receiving equipment and application method thereof - Google Patents
Automatic launching device of unmanned aerial vehicle time domain avionic receiving equipment and application method thereof Download PDFInfo
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- CN112009705A CN112009705A CN202010880791.7A CN202010880791A CN112009705A CN 112009705 A CN112009705 A CN 112009705A CN 202010880791 A CN202010880791 A CN 202010880791A CN 112009705 A CN112009705 A CN 112009705A
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- 239000002184 metal Substances 0.000 claims abstract description 51
- 229920000049 Carbon (fiber) Polymers 0.000 claims abstract description 37
- 239000004917 carbon fiber Substances 0.000 claims abstract description 37
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract description 37
- 238000012546 transfer Methods 0.000 claims abstract description 24
- 230000007704 transition Effects 0.000 claims abstract description 16
- 239000007769 metal material Substances 0.000 claims description 8
- 239000003292 glue Substances 0.000 claims description 6
- 238000011084 recovery Methods 0.000 claims description 3
- 230000001360 synchronised effect Effects 0.000 claims description 3
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- 239000002131 composite material Substances 0.000 description 3
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- 238000005259 measurement Methods 0.000 description 3
- 238000009434 installation Methods 0.000 description 2
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- 230000009286 beneficial effect Effects 0.000 description 1
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- 238000001514 detection method Methods 0.000 description 1
- 230000005672 electromagnetic field Effects 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D1/00—Dropping, ejecting, releasing or receiving articles, liquids, or the like, in flight
- B64D1/02—Dropping, ejecting, or releasing articles
- B64D1/08—Dropping, ejecting, or releasing articles the articles being load-carrying devices
- B64D1/12—Releasing
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Abstract
The invention discloses an automatic throwing device for an unmanned aerial vehicle time domain avionics receiving device. The cylindrical adapter beam comprises a metal frame, a carbon fiber frame, a metal beam, a carbon fiber skin and a metal skin, is connected with the main bearing frame of the unmanned aerial vehicle body through bolts and is used as a transition for connecting the load hanging frame with the unmanned aerial vehicle body; the special-shaped structural beam is connected with the time domain avionic receiving equipment through a bolt and used for fixing the time domain avionic receiving equipment; the load hanging frame is connected with the upper surface of the special-shaped structural beam through the bolt and is connected with the metal skin of the cylindrical transfer beam through the hook, and therefore automatic unlocking and releasing of the avionic device in an emergency can be achieved. The invention also discloses an application method of the automatic releasing device. The invention can safely mount the time domain avionics receiving equipment on the unmanned aerial vehicle, effectively reduce the structural weight, have stronger stability and can be widely used in the field of aviation electromagnetic exploration.
Description
Technical Field
The invention relates to an automatic throwing device of a time domain avionic receiving device and an application method thereof, belonging to the field of aviation electromagnetic measurement.
Background
The time domain aviation electromagnetic measurement technology is also called aviation transient electromagnetic method, and is an aviation geophysical prospecting method which utilizes an airborne coil to emit pulse electromagnetic waves and measures a secondary induction electromagnetic field through a receiving coil. The method has the advantages of high speed, low cost, wide detection range and the like, can be used for working in areas where ground personnel and equipment are difficult to enter, and is suitable for large-area general investigation; the method can be widely applied to the fields of geological mapping, mineral exploration, hydrogeology, environmental monitoring and the like.
At present, the time domain aeroelectromagnetic measurement takes a man-machine as a main carrier, and typical fixed wing time domain systems in various foreign stages represent systems such as INPUT, MARK I, MARK II, MARK IV SKYVAN TRISLANDER, CASA, QUESTEM, SPECTREM, SALTMAP, GEOTEMDEEP, MEGATEM, TEMPEST, MEGATEMII, GEOTEM1000 and the like. China developed a first set of pod type time domain helicopter aviation electromagnetic survey system in 2012. However, the time domain airborne electromagnetic survey system based on human-machine mainly faces the problems of high danger, high cost, poor flexibility, low working efficiency and the like.
The unmanned aerial vehicle aerial geophysical prospecting has the advantages of high efficiency, low cost, small risk, no influence of terrain conditions and human factors and the like, and is an effective way for solving the problems. However, applying the drone to the field of airborne electromagnetic surveying still faces many difficulties, one of which is how to implement the mounting of the time domain avionics reception equipment. The traditional manned machine often puts time domain avionics receiving equipment in the aircraft fuselage at the aviation geophysical prospecting, but because unmanned aerial vehicle is small, can lay load space in the fuselage is not big, and time domain avionics receiving equipment in addition need pull at the during operation, and is big very much to unmanned aerial vehicle flight performance influence, if do not have reliable design and device, unmanned aerial vehicle can't carry time domain avionics receiving equipment safely.
Therefore, before the unmanned aerial vehicle carries out an aviation electromagnetic survey operation task, the time domain avionic receiving equipment is installed on the unmanned aerial vehicle, so that the normal work of the unmanned aerial vehicle is ensured, and the automatic release is realized when the time domain avionic receiving equipment breaks down. At present, no automatic throwing device for unmanned aerial vehicle time domain avionic receiving equipment is successful in China.
Disclosure of Invention
The invention aims to solve the problems and provides an automatic throwing device of unmanned aerial vehicle time domain avionic receiving equipment and an application method thereof.
The above object of the present invention is achieved by the following technical solutions:
an automatic throwing device of an unmanned aerial vehicle time domain avionic receiving device comprises a cylindrical transfer beam, a load hanging frame and a special-shaped structural beam;
the cylindrical transfer beam is connected with a main bearing frame of the unmanned aerial vehicle body through a bolt; the upper surface of the load hanging rack is connected with the cylindrical adapter beam through a hook, the lower surface of the load hanging rack is connected with the upper surface of the special-shaped structural beam through a bolt, and the lower surface of the special-shaped structural beam is connected with the time domain avionic receiving equipment;
during mounting and flying, the time domain avionic receiving equipment is tightened on the lower surface of the special-shaped structural beam, and during release and exploration, a receiver nacelle of the time domain avionic receiving equipment slides and falls.
The special-shaped structural beam is formed by integrally cutting a metal material and comprises a first section, a transition section and a second section, wherein the upper surfaces of the first section, the transition section and the second section are flush, and the widths of the upper surfaces of the first section, the transition section and the second section are equal; the second section is a rectangular flat plate, and the width of the upper surface of the second section is equal to that of the lower surface of the second section;
the first section main body is trapezoidal in section along the wingspan direction, the front end of the main body is semicircular in section along the wingspan direction, the lower surface of the first section is wider than the upper surface of the first section, the thickness of the first section is larger than that of the second section, and the transition section is trapezoidal in section along the wingspan direction and used for connecting the first section and the second section.
The connecting mode of the lower surface of the special-shaped structural beam and the time domain avionic receiving equipment is as follows:
the front part of the lower surface of the first section of the special-shaped structural beam is fixedly connected with an electric winch fairing in the time domain avionic receiving equipment through a bolt, the lower surface of the second section of the special-shaped structural beam is provided with a hanging rack, a receiver pod in the time domain avionic receiving equipment is placed in the hanging rack, and the hanging rack is provided with a longitudinal guide frame; the electric winch is connected with the receiver nacelle through a towing cable;
during hanging and flying, the electric winch tightens the towing cable, the receiver nacelle is fixed in the hanging rack, and during throwing and surveying, the electric winch releases the towing cable, and the receiver nacelle slides and falls along the longitudinal guide frame of the hanging rack.
The cylindrical adapter beam comprises a metal frame, a carbon fiber frame, a metal beam, a carbon fiber beam, a metal skin and a carbon fiber skin;
the cylindrical transfer beam is divided into a front end frame, a rear end frame and a body frame, wherein the body frame is a metal frame, the front end frame and the rear end frame are both carbon fiber frames, a metal skin is fixed on the outer side of the body frame, a carbon fiber skin is fixed on the outer side of the carbon fiber frame, a metal beam is installed in the metal frame, and a carbon fiber beam is installed in the carbon fiber frame;
the upper surface of the metal frame is provided with a metal connecting frame, and the metal connecting frame is connected with a main bearing frame of the unmanned aerial vehicle body through bolts.
The thickness of metal covering is 5mm, and the carbon fiber covering adopts honeycomb sandwich structure, and thickness is 3 mm.
The carbon fiber skin and the carbon fiber frame are directly glued through mold closing glue; the metal skin is glued with the metal frame through laminating glue, and glue leaking holes are formed in the metal frame and the metal beam to increase the connection strength.
The diameter of the bolt for connecting the metal connecting frame and the main bearing frame of the unmanned aerial vehicle body is less than or equal to 8 mm.
The upper surface of the load hanging rack is connected with the metal skin of the cylindrical transfer beam through a hook.
The couple of load stores pylon passes through power cable and synchronous cable and links to each other with unmanned aerial vehicle.
An application method of an automatic launching device of an unmanned aerial vehicle time domain avionics receiving device comprises the following steps:
(1) installing an electric winch fairing in the time domain avionic receiving equipment on the front part of the lower surface of the first section of the special-shaped structural beam through a bolt, and placing a receiver pod in the time domain avionic receiving equipment in a hanging rack on the lower surface of the second section of the special-shaped structural beam; the electric winch tightens the towing cable and fixes the receiver nacelle in the hanging frame;
(2) the mounting and flying reach a preset working area, when the unmanned aerial vehicle is put into a survey, the unmanned aerial vehicle sends a release instruction to the electric winch, the electric winch loosens the towing cable, and the receiver nacelle slides and falls along the longitudinal guide frame of the hanging rack;
(3) after the receiver nacelle is placed at the preset position, the time domain avionics receiving equipment starts to work, after the work is finished, the unmanned aerial vehicle sends a recovery instruction to the electric winch, the electric winch winds and recovers the towing cable, the receiver nacelle returns to the hanging rack along the longitudinal guide frame of the hanging rack, and the electric winch tightens the towing cable after the receiver nacelle is recovered in place, so that the receiver nacelle is fixed in the hanging rack.
In the releasing or recovering process, if the electric winch fails or the receiver nacelle is accidentally dragged, the unmanned aerial vehicle sends an unlocking instruction to the hook on the upper surface of the load hanger, and after the hook receives the unlocking instruction, the connection between the hook and the cylindrical transfer beam is cut off, so that the load hanger, the special-shaped structural beam and the time-domain avionic receiving device are thrown together.
Compared with the prior art, the invention has the beneficial effects that:
(1) the device can be with time domain avionics receiving equipment on the unmanned aerial vehicle, realizes time domain avionics receiving equipment's automatic input, guarantees that the smooth completion of aviation electromagnetic survey operation.
(2) The cylindrical transfer beam adopts a mixed structure of a metal material and a carbon fiber composite material, the metal material can meet the requirement of installation strength, and the carbon fiber material can effectively reduce the structural weight. 5 diameters that cylindric switching roof beam respectively arranged around are not more than 8mm bolts, can effectively reduce the influence to unmanned aerial vehicle fuselage owner load frame intensity.
(3) The special-shaped structural beam is integrally cut by adopting a metal material, has good structural stability, and can provide mounting positions for an electric winch and a receiver nacelle hanger in the time domain avionics receiving equipment at the same time.
(4) The maximum mounting capacity of the load hanger is 250kg, and the mounting requirements of time domain avionic receiving equipment of different models can be met. The couple of load stores pylon has instruction unblock function, and its and cylindric switching beam's connection and disconnection are realized to the accessible instruction for realize the automatic input under emergency, guarantee the safety of unmanned aerial vehicle flight.
Drawings
Fig. 1 is a schematic diagram of the general structure of an automatic launching device of an unmanned aerial vehicle time domain avionics receiving device.
Fig. 2 is a schematic structural view of a cylindrical transfer beam.
Fig. 3 is a schematic view of a load hanger structure.
Fig. 4 is a schematic structural view of the beam with the special-shaped structure, wherein (a) is a schematic upper surface of the beam with the special-shaped structure, and (b) is a schematic lower surface of the beam with the special-shaped structure.
Detailed Description
The technical solution of the present invention will be described in detail below with reference to the accompanying drawings.
The time domain avionic receiving device can be installed on the unmanned aerial vehicle, and when an electric winch in the time domain avionic receiving device fails or a receiver nacelle is accidentally dragged, the device can integrally throw the time domain avionic receiving device according to instructions, so that the flight safety of the unmanned aerial vehicle is ensured.
Fig. 1 is an automatic device structure sketch map of puting in of unmanned aerial vehicle time domain avionics receiving arrangement, structurally includes cylindric switching roof beam 1, special-shaped structure roof beam 3 and load stores pylon 2. The cylindrical transfer beam 1 is used as a transition for connecting the load hanger 2 with the unmanned aerial vehicle body, so that a main bearing structure of the unmanned aerial vehicle body is further protected; the load hanging frame 2 is used for realizing automatic throwing of avionic equipment; the special-shaped structural beam 3 provides a mounting position for the electric winch and the receiver nacelle hanger.
Specifically, the cylindrical transfer beam 1 is connected with a main bearing frame of the unmanned aerial vehicle body through bolts and is used as a transition for connecting the load hanging rack with the unmanned aerial vehicle body; the upper surface of the load hanging rack 2 is connected with the cylindrical transfer beam 1 through a hook, the lower surface of the load hanging rack 2 is connected with the upper surface of the special-shaped structural beam 3 through a bolt, the lower surface of the first section of the special-shaped structural beam 3 is fixedly connected with an electric winch fairing in the time domain avionic receiving device through a bolt, the lower surface of the second section is provided with a hanging rack, and a receiver pod in the time domain avionic receiving device is placed in the hanging rack. The hanging rack is provided with a longitudinal guide rack. The electric winch is connected with the receiver nacelle through a towing cable.
During mounting and flying, the electric winch fixes the receiver nacelle in the hanger by tightening the towing cable, and during throwing and surveying, the electric winch releases the towing cable, and the receiver nacelle slides and falls along the longitudinal guide frame of the hanger.
Fig. 2 is a schematic structural diagram of a cylindrical transfer beam, the weight of the cylindrical transfer beam is 40kg, a mixed structure of a metal material and a carbon fiber composite material is adopted, the metal material can meet the installation strength requirement, and the carbon fiber material can effectively reduce the structural weight. The cylindric transfer beam includes: the composite material comprises a metal frame 1-1, a carbon fiber frame 1-2, a metal skin 1-3, a carbon fiber skin 1-4, a metal beam 1-5 and a carbon fiber beam 1-6. The cylindrical transfer beam 1 is divided into a front end frame, a rear end frame and a body frame, wherein the body frame is a metal frame 1-1, and the metal frame 1-1 is connected with a main bearing frame of the unmanned aerial vehicle body through bolts. The front end frame and the rear end frame are both carbon fiber frames 1-2, metal skins 1-3 are fixed on the outer sides of the body frames, and carbon fiber skins 1-4 are fixed on the outer sides of the carbon fiber frames 1-2. The metal frame 1-1 is internally provided with a metal beam 1-5, and the carbon fiber frame 1-2 is internally provided with a carbon fiber beam 1-6.
The barrel-shaped transfer beam has the barrel length of 1180mm, the body frame diameter of 100mm and the barrel deepest depth of 100 mm. A metal connecting frame 1-7 is respectively processed in front of and behind a cylindrical adapter beam metal frame 1-1, 5 bolt holes are arranged on each metal connecting frame and used for being connected with a main bearing frame of an unmanned aerial vehicle body through bolts, the diameter of each bolt is less than or equal to 8mm, and the influence on the strength of the main bearing frame of the unmanned aerial vehicle body is reduced. .
The thickness of the metal skin 1-3 is 5mm, and the thickness of the carbon fiber skin 1-4 is 3mm by adopting a honeycomb sandwich structure. Fig. 3 is a schematic view of a load hanger structure. The weight of the load hanging rack is 25kg, the load hanging rack comprises a hook and a bolt, and the maximum hanging capacity is 250 kg. The couple of load stores pylon passes through power cable and synchronous cable and links to each other with unmanned aerial vehicle, and the load stores pylon is invertd, is connected through the metal covering of couple and cylindric switching roof beam, through the upper surface connection of 4 bolts and special-shaped structure roof beams. The couple has instruction unblock function, and unmanned aerial vehicle accessible instruction unblock couple is connected with cylindric switching roof beam.
Fig. 4 is a structural diagram of a beam with a special-shaped structure. The special-shaped structure beam is 40kg in weight, is integrally cut by adopting a metal material and comprises a first section, a transition section and a second section, wherein the total length of the special-shaped structure beam is 1915mm, the upper surfaces of the first section, the transition section and the second section are parallel and level, and the widths of the upper surfaces of the first section, the transition section and the second section are equal; the first section main body is of a trapezoidal flat plate-shaped structure (namely the section along the wingspan direction is trapezoidal), the width of the upper surface of the first section is 75mm, the width of the lower surface of the first section is 185mm, the thickness of the first section is 300mm, and the front end of the trapezoidal flat plate-shaped structure is of a semicircular plate-shaped structure; the transition section is in a trapezoidal structure (namely, the cross section along the wingspan direction is trapezoidal), and the transition section is used for transitioning the lower surface of the first section and the lower surface of the second section. The connecting width of the trapezoid structure and the lower surface of the first section is 185mm, and the connecting width of the trapezoid structure and the lower surface of the second section is 75 mm; the second section is a rectangular flat plate, the widths of the upper surface and the lower surface of the rectangular flat plate are both 75mm, and the thickness of the rectangular flat plate is 125 mm; the lower surface width of first section is greater than the upper surface width, and the lower surface width of first section is greater than the lower surface width of second section, and the upper surface of first section is on the coplanar with the upper surface of second section, and the thickness of first section is greater than the thickness of second section. 4 bolt holes are formed in the upper surface of the first section and used for being connected with a load hanging rack; the front part of the lower surface of the first section is provided with 3 bolt holes for connecting with an electric winch in the time domain avionic receiving equipment; the lower surface of the second section is provided with 4 bolt holes for connecting with a receiver nacelle hanger in the time domain avionics receiving equipment. Fig. 4 (a) is a schematic view of the upper surface of the beam with the special-shaped structure, and (b) is a schematic view of the lower surface of the beam with the special-shaped structure.
The invention can safely mount the time domain avionics receiving equipment on the unmanned aerial vehicle, effectively reduce the structural weight, have stronger stability and can be widely used in the field of aviation electromagnetic exploration.
The invention relates to an application method of an automatic launching device of an unmanned aerial vehicle time domain avionics receiving device, which comprises the following steps:
(1) installing an electric winch fairing in the time domain avionic receiving equipment on the front part of the lower surface of the first section of the special-shaped structural beam 3 through bolts, and placing a receiver pod in the time domain avionic receiving equipment in a hanging rack at the rear part of the lower surface of the second section of the special-shaped structural beam 3; the electric winch winds and tightens the towing cable, and the receiver nacelle is fixed in the hanging frame;
(2) the mounting and flying reach a preset working area, when the unmanned aerial vehicle is put into a survey, the unmanned aerial vehicle sends a release instruction to the electric winch, the electric winch loosens the towing cable, and the receiver nacelle slides and falls along the longitudinal guide frame of the hanging rack;
(3) after the receiver nacelle is placed at the preset position, the time domain avionics receiving equipment starts to work, after the work is finished, the unmanned aerial vehicle sends a recovery instruction to the electric winch, the electric winch winds and recovers the towing cable, the receiver nacelle returns to the hanging rack along the longitudinal guide frame of the hanging rack, and the electric winch tightens the towing cable after the receiver nacelle is recovered in place, so that the receiver nacelle is fixed in the hanging rack.
In the releasing or recovering process, if the electric winch fails or the receiver nacelle is accidentally dragged, the unmanned aerial vehicle sends an unlocking instruction to the hook on the upper surface of the load hanging rack 2, and after the hook receives the unlocking instruction, the connection between the hook and the cylindrical transfer beam 1 is cut off, so that the load hanging rack 2, the special-shaped structural beam 3 and the time domain avionic receiving device are thrown together.
The above data of the present invention is only a preferred embodiment of the present invention, and is not a limitation to the embodiments of the present invention. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. Not all embodiments are exhaustive. All obvious changes and modifications of the present invention are within the scope of the present invention.
Claims (11)
1. The utility model provides an automatic device of puting in of unmanned aerial vehicle time domain avionics receiving equipment which characterized in that: comprises a cylindrical transfer beam (1), a load hanger (2) and a special-shaped structural beam (3);
the cylindrical transfer beam (1) is connected with a main bearing frame of the unmanned aerial vehicle body through a bolt; the upper surface of the load hanging rack (2) is connected with the cylindrical transfer beam (1) through a hook, the lower surface of the load hanging rack (2) is connected with the upper surface of the special-shaped structural beam (3) through a bolt, and the lower surface of the special-shaped structural beam (3) is connected with the time domain avionic receiving device;
during mounting and flying, the time domain avionic receiving equipment is tightened on the lower surface of the special-shaped structural beam (3), and during release and exploration, a receiver nacelle of the time domain avionic receiving equipment slides and falls.
2. The automatic launching device of unmanned aerial vehicle time domain avionics receiving equipment according to claim 1, characterized in that: the special-shaped structural beam is formed by integrally cutting a metal material and comprises a first section, a transition section and a second section, wherein the upper surfaces of the first section, the transition section and the second section are flush, and the widths of the upper surfaces of the first section, the transition section and the second section are equal; the second section is a rectangular flat plate, and the width of the upper surface of the second section is equal to that of the lower surface of the second section;
the first section main body is trapezoidal in section along the wingspan direction, the front end of the main body is semicircular in section along the wingspan direction, the lower surface of the first section is wider than the upper surface of the first section, the thickness of the first section is larger than that of the second section, and the transition section is trapezoidal in section along the wingspan direction and used for connecting the first section and the second section.
3. The automatic launching device of unmanned aerial vehicle time domain avionics receiving equipment according to claim 2, characterized in that: the connecting mode of the lower surface of the special-shaped structural beam (3) and the time domain avionic receiving equipment is as follows:
the front part of the lower surface of the first section of the special-shaped structural beam (3) is fixedly connected with an electric winch fairing in the time domain avionic receiving equipment through a bolt, the lower surface of the second section of the special-shaped structural beam (3) is provided with a hanging rack, a receiver pod in the time domain avionic receiving equipment is placed in the hanging rack, and the hanging rack is provided with a longitudinal guide frame; the electric winch is connected with the receiver nacelle through a towing cable;
during hanging and flying, the electric winch tightens the towing cable, the receiver nacelle is fixed in the hanging rack, and during throwing and surveying, the electric winch releases the towing cable, and the receiver nacelle slides and falls along the longitudinal guide frame of the hanging rack.
4. The automatic launching device of unmanned aerial vehicle time domain avionics receiving equipment according to claim 1, characterized in that: the cylindrical transfer beam 1 comprises a metal frame (1-1), a carbon fiber frame (1-2), a metal beam (1-5), a carbon fiber beam (1-6), a metal skin (1-3) and a carbon fiber skin (1-4);
the cylindrical transfer beam (1) is divided into a front end frame, a rear end frame and a body frame, wherein the body frame is a metal frame (1-1), the front end frame and the rear end frame are carbon fiber frames (1-2), a metal skin (1-3) is fixed on the outer side of the body frame, a carbon fiber skin (1-4) is fixed on the outer side of the carbon fiber frame (1-2), the metal beam (1-5) is installed inside the metal frame (1-1), and a carbon fiber beam (1-6) is installed inside the carbon fiber frame (1-2);
the upper surface of the metal frame (1-1) is provided with a metal connecting frame (1-7), and the metal connecting frame (1-7) is connected with a main bearing frame of the unmanned aerial vehicle body through bolts.
5. The automatic launching device of unmanned aerial vehicle time domain avionics receiving equipment according to claim 4, characterized in that: the thickness of the metal skin (1-3) is 5mm, and the thickness of the carbon fiber skin (1-4) is 3mm by adopting a honeycomb sandwich structure.
6. The automatic launching device of unmanned aerial vehicle time domain avionics receiving equipment according to claim 5, characterized in that: the carbon fiber skin and the carbon fiber frame are directly glued through mold closing glue; the metal skin is glued with the metal frame through laminating glue, and glue leaking holes are formed in the metal frame and the metal beam to increase the connection strength.
7. The automatic launching device of unmanned aerial vehicle time domain avionics receiving equipment according to claim 4, characterized in that: the diameter of the bolt for connecting the metal connecting frame (1-7) with the main bearing frame of the unmanned aerial vehicle body is less than or equal to 8 mm.
8. The automatic launching device of unmanned aerial vehicle time domain avionics receiving equipment according to claim 4, characterized in that: the upper surface of the load hanging rack (2) is connected with the metal skin (1-3) of the cylindrical transfer beam (1) through a hook.
9. The automatic launching device of unmanned aerial vehicle time domain avionics receiving equipment according to claim 1, characterized in that: the couple of load stores pylon passes through power cable and synchronous cable and links to each other with unmanned aerial vehicle.
10. An application method of an automatic launching device of an unmanned aerial vehicle time domain avionics receiving device is characterized by comprising the following steps:
(1) installing an electric winch fairing in the time domain avionic receiving equipment on the front part of the lower surface of the first section of the special-shaped structural beam (3) through bolts, and placing a receiver nacelle in the time domain avionic receiving equipment in a hanging rack on the lower surface of the second section of the special-shaped structural beam (3); the electric winch tightens the towing cable and fixes the receiver nacelle in the hanging frame;
(2) the mounting and flying reach a preset working area, when the unmanned aerial vehicle is put into a survey, the unmanned aerial vehicle sends a release instruction to the electric winch, the electric winch loosens the towing cable, and the receiver nacelle slides and falls along the longitudinal guide frame of the hanging rack;
(3) after the receiver nacelle is placed at the preset position, the time domain avionics receiving equipment starts to work, after the work is finished, the unmanned aerial vehicle sends a recovery instruction to the electric winch, the electric winch winds and recovers the towing cable, the receiver nacelle returns to the hanging rack along the longitudinal guide frame of the hanging rack, and the electric winch tightens the towing cable after the receiver nacelle is recovered in place, so that the receiver nacelle is fixed in the hanging rack.
11. The application method of the automatic launching device of the unmanned aerial vehicle time domain avionics receiving device according to claim 10, characterized in that: in the releasing or recovering process, if the electric winch fails or the receiver nacelle is accidentally dragged, the unmanned aerial vehicle sends an unlocking instruction to the hook on the upper surface of the load hanging rack (2), and after the hook receives the unlocking instruction, the connection with the cylindrical transfer beam (1) is cut off, so that the load hanging rack (2), the special-shaped structure beam (3) and the time domain avionic receiving equipment are put in together.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN102137741A (en) * | 2008-08-25 | 2011-07-27 | 罗尔斯-罗依斯海运有限公司 | Apparatus and method for immediate emergency disconnection of a load |
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| CN212501076U (en) * | 2020-08-27 | 2021-02-09 | 彩虹无人机科技有限公司 | Automatic throwing device of unmanned aerial vehicle time domain avionics receiving equipment |
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| US20200010193A1 (en) * | 2018-07-04 | 2020-01-09 | Dwight Darwin Alexander | Method and Apparatus for Unmanned Aerial Maritime Float Vehicle That Sense and Report Relevant Data from Physical and Operational Environment |
| CN210653645U (en) * | 2019-09-30 | 2020-06-02 | 广东梵亚科技有限公司 | Unmanned aerial vehicle long-range input system and unmanned aerial vehicle that slowly falls |
| CN212501076U (en) * | 2020-08-27 | 2021-02-09 | 彩虹无人机科技有限公司 | Automatic throwing device of unmanned aerial vehicle time domain avionics receiving equipment |
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