CN211252976U - Special unmanned aerial vehicle pneumatic layout is visited to horizontal gradient magnetism - Google Patents
Special unmanned aerial vehicle pneumatic layout is visited to horizontal gradient magnetism Download PDFInfo
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- CN211252976U CN211252976U CN201921874165.6U CN201921874165U CN211252976U CN 211252976 U CN211252976 U CN 211252976U CN 201921874165 U CN201921874165 U CN 201921874165U CN 211252976 U CN211252976 U CN 211252976U
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Abstract
The utility model provides a special unmanned aerial vehicle aerodynamic configuration is visited to horizontal gradient magnetism, which comprises a bod, the main wing, wing probe and fin slightly, the fuselage includes the fuselage covering, strengthen the frame, ordinary frame, truss and flap, the fuselage adopts the truss formula overall arrangement, set up ordinary frame along aircraft fuselage axial, be provided with the main wing hookup location and strengthen the frame, fixed connection is realized with ordinary frame and enhancement frame to the truss, the fuselage covering splices in truss and ordinary frame and enhancement frame surface, form fuselage major structure, the wing is probed slightly including wing fairing slightly, probe and support, the probe is fixed in on the support, wing fairing is connected in the support surface slightly, the wing is probed slightly for two probes, symmetrical arrangement is on the same horizontal line of main wing tip department, be used for realizing horizontal gradient aviation geophysical prospecting and doing the industry. The utility model discloses can effectual and carry the horizontal gradient aeromagnetic measuring equipment phase-match, both promote horizontal gradient measuring accuracy, also ensure that the unmanned aerial vehicle after increasing the load can last stable flight.
Description
Technical Field
The utility model belongs to aircraft structural scheme design field, concretely relates to special unmanned aerial vehicle pneumatic layout is visited to horizontal gradient magnetism.
Background
The aeronautical magnetic measurement is a geophysical method for loading an aeronautical wing tip probe and auxiliary equipment matched with the aeronautical wing tip probe on an aircraft and measuring the intensity or gradient of a geomagnetic field according to a preset measuring line and height above a measurement area, and is widely applied to the fields of mineral resource exploration, regional structure mapping, anti-latency and the like.
The aeromagnetic horizontal gradient measurement method is that wing tip probes are respectively arranged on two sides of an aircraft to respectively measure the gradient of the geomagnetic field, and the measurement result of the horizontal gradient is obtained by comparing and analyzing data obtained by the two instruments.
For an unmanned aerial vehicle executing a horizontal gradient aeromagnetic measurement task, in order to reduce the influence of a machine body and onboard equipment on measurement data and ensure good flight performance of the aircraft, the horizontal gradient measurement equipment needs to be mounted at a proper position, and the overall pneumatic layout of the aircraft needs to be redesigned.
When a man-machine is used for carrying out aerial geophysical prospecting operation, in order to meet hanging conditions, a wing tip probe is generally required to be fixed below a composite wing body or in the middle of a wing, the two hanging modes are close to electronic equipment in a cabin, and a stable working environment cannot be provided for the wing tip probe due to electromagnetic interference.
SUMMERY OF THE UTILITY MODEL
The utility model provides a technical problem be: aiming at the defects of the prior art, the invention provides the special unmanned aerial vehicle pneumatic layout for horizontal gradient magnetic detection, which can effectively improve the accuracy of the aeromagnetic gradient detection of the unmanned aerial vehicle and ensure the pneumatic efficiency of the aircraft.
The technical solution of the utility model is that:
a horizontal gradient magnetic detection special unmanned aerial vehicle pneumatic layout comprises a fuselage, a main wing, a wing tip probe and a tail wing, wherein the fuselage comprises a fuselage skin, a reinforcing frame, a common frame, a truss and a covering cover,
the fuselage adopts a truss type layout, a common frame is arranged along the axial direction of the fuselage of the airplane, a reinforcing frame is arranged at the connecting position of the fuselage and the main wing, the truss is fixedly connected with the common frame and the reinforcing frame, and the fuselage skin is glued to the outer surfaces of the truss, the common frame and the reinforcing frame to form a fuselage main body structure;
the main wing comprises a main beam, a main wing skin and a main wing rib, the main wing adopts a double-beam layout, the main wing rib connects and combines the main beam into a main wing framework, and the main wing skin is glued on the main wing rib and the outer surface of the wing rib to form a main wing main body structure;
the tail wing comprises a tail beam, a tail wing skin and a tail wing rib, the tail wing adopts a double-beam layout, the tail beam is connected and combined into a tail wing framework by the tail wing rib, and the tail wing skin is glued to the tail wing rib and the outer surface of the wing rib to form a tail body structure of the tail wing;
the tail wing is fixedly connected to the axial tail end of the fuselage in a V-shaped layout, and the main wing is connected to the axial middle position of the fuselage in a symmetrical layout;
the wing tip probe comprises a wing tip fairing, two probes and a support, wherein the probes are fixed on the support, the wing tip fairing is connected to the outer surface of the support, and the two probes are symmetrically arranged on the same horizontal line at the wing tip of the main wing and used for realizing the horizontal gradient aviation geophysical prospecting operation.
Preferably, the ratio of the maximum dimensions of the main wing to the fuselage is 2: 1-2.5: 1.
preferably, the aspect ratio is 17-23.
Preferably, the wing area is 12-16 m2。
Preferably, the lift-drag ratio of the airplane is 14-16.
Preferably, both the ailerons and the elevator rudder use split control surfaces.
Preferably, the sweep angle of the leading edge of the main wing ranges from 0.8 degrees to 1 degree.
Preferably, the sweep angle of the trailing edge of the main wing is-4 to 3.5 degrees.
Preferably, the V wing aspect ratio is 3-4.
Preferably, the sweepback angles of the front edge and the rear edge of the tail wing are both 16-17 degrees.
Compared with the prior art, the utility model the advantage lie in:
the utility model discloses can effectual and carry the horizontal gradient aeromagnetic measuring equipment phase-match, both promote horizontal gradient measuring accuracy, also ensure that the unmanned aerial vehicle after increasing the load can last stable flight.
Drawings
Fig. 1 is a top view of the present invention;
fig. 2 is a side view of the present invention.
Detailed Description
The present invention will be further described with reference to the accompanying drawings.
The unmanned aerial vehicle for performing the horizontal gradient aviation magnetic detection task should reduce the interference of the flight of the unmanned aerial vehicle on the measurement result of the wing tip probe as much as possible. The invention provides a novel unmanned aerial vehicle pneumatic layout, which is shown in figures 1 and 2. The wing tip probe is arranged at the wing tip of the airplane, so that the wing tip probe can be far away from the airplane body as far as possible, and the interference of the onboard equipment on the wing tip probe is reduced. And a wing tip fairing is designed outside the wing tip probe mounted on the wing tip to coat the wing tip fairing, so that the aerodynamic performance of the wing tip load position can be greatly improved, and the overall aerodynamic efficiency of the airplane is improved. In addition, the fairing is made of glass fiber reinforced plastic materials, and the influence of the fairing on the measurement data of the wing tip probe is reduced to the maximum extent on the premise of ensuring the structural strength of the fairing.
The concrete structure is shown in figures 1 and 2, and comprises a fuselage 1, a main wing 2, a wing tip probe 3 and a tail wing 4, wherein the fuselage 1 comprises a fuselage skin, a reinforcing frame, a common frame, a truss and a covering cover,
the fuselage 1 adopts a truss type layout, a common frame is arranged along the axial direction of the fuselage 1, a reinforcing frame is arranged at the connecting position of the fuselage and the main wing 2, the truss is fixedly connected with the common frame and the reinforcing frame, and the fuselage skin is glued to the outer surfaces of the truss, the common frame and the reinforcing frame to form a main body structure of the fuselage 1;
the main wing 2 comprises a main beam, a main wing skin and a main wing rib, the main wing 2 adopts a double-beam layout, the main wing rib connects and combines the main beam into a main wing 2 framework, and the main wing skin is glued on the main wing rib and the outer surface of the wing rib to form a main structure of the main wing 2;
the tail wing 4 comprises a tail beam, a tail wing skin and a tail wing rib, the tail wing 4 adopts a double-beam layout, the tail wing rib connects and combines the tail beam into a tail wing 4 framework, and the tail wing skin is glued to the tail wing rib and the outer surface of the wing rib to form a tail body structure of the tail wing 4;
the tail wing 4 is fixedly connected to the axial tail end of the machine body 1 in a V-shaped layout, and the main wing 2 is connected to the axial middle position of the machine body 1 in a symmetrical layout;
the wing tip probe 3 comprises a wing tip fairing, probes and a support, the probes are fixed on the support, the wing tip fairing is connected to the outer surface of the support, the wing tip probes 3 are two probes and are symmetrically arranged on the same horizontal line at the wing tip of the main wing 2, and the horizontal gradient aviation geophysical prospecting operation is achieved.
The specific parameter requirements of the pneumatic layout of the unmanned aerial vehicle are as follows: the maximum size ratio of the main wing 2 to the fuselage 1 is 2: 1-2.5: 1, the aspect ratio is 17-23, and the wing area is 12-16 m2The lift-drag ratio of the airplane is 14-16, the ailerons and the elevator rudder both adopt split control surfaces, the sweepback angle of the front edge of the main wing is 0.8-1 degrees, the sweepback angle of the rear edge of the main wing is-4-3.5 degrees, the span-chord ratio of the V wing is 3-4 degrees, and the sweepback angles of the front edge and the rear edge of the tail wing are 16-17 degrees.
As described above, the present invention is only the best embodiment, but the protection scope of the present invention is not limited thereto, and any person skilled in the art can easily deduce or replace the present invention within the technical scope of the present invention.
The details of the present invention not described in detail in the specification are well known to those skilled in the art.
Claims (10)
1. The utility model provides a special unmanned aerial vehicle pneumatic layout is visited to horizontal gradient magnetism which characterized in that: comprises a fuselage (1), a main wing (2), a wing tip probe (3) and a tail wing (4), wherein the fuselage (1) comprises a fuselage skin, a reinforcing frame, a common frame, a truss and a covering cover,
the fuselage (1) adopts a truss type layout, a common frame is axially arranged along the fuselage (1) of the airplane, a reinforcing frame is arranged at the connecting position of the fuselage and the main wing (2), the truss is fixedly connected with the common frame and the reinforcing frame, and the fuselage skin is glued to the outer surfaces of the truss, the common frame and the reinforcing frame to form a main body structure of the fuselage (1);
the main wing (2) comprises a main beam, a main wing skin and main wing ribs, the main wing (2) adopts a double-beam layout, the main wing ribs connect and combine the main beam into a main wing (2) framework, and the main wing skin is glued on the main wing ribs and the outer surfaces of the wing ribs to form a main structure of the main wing (2);
the tail wing (4) comprises a tail beam, a tail wing skin and a tail wing rib, the tail wing (4) adopts a double-beam layout, the tail beam is connected and combined into a tail wing (4) framework by the tail wing rib, and the tail wing skin is glued to the tail wing rib and the outer surface of the wing rib to form a tail body structure of the tail wing (4);
the tail wing (4) is fixedly connected to the axial tail end of the machine body (1) in a V-shaped layout, and the main wing (2) is connected to the axial middle position of the machine body (1) in a symmetrical layout;
the wing tip probe (3) comprises a wing tip fairing, probes and a support, the probes are fixed on the support, the wing tip fairing is connected to the outer surface of the support, the wing tip probe (3) comprises two probes, and the two probes are symmetrically arranged on the same horizontal line at the wing tip of the main wing (2) and used for achieving horizontal gradient air geophysical prospecting operation.
2. The horizontal gradient magnetic detection special unmanned aerial vehicle pneumatic layout of claim 1, characterized in that: the maximum size ratio of the main wing (2) to the fuselage (1) is 2: 1-2.5: 1.
3. the horizontal gradient magnetic detection special unmanned aerial vehicle pneumatic layout of claim 1, characterized in that: the aspect ratio is 17-23.
4. The horizontal gradient magnetic detection special unmanned aerial vehicle pneumatic system according to claim 1The layout is characterized in that: the wing area is 12-16 m2。
5. The pneumatic layout of unmanned aerial vehicle special for horizontal gradient magnetic detection according to claim 3, characterized in that: the lift-drag ratio of the airplane is 14-16.
6. The horizontal gradient magnetic detection special unmanned aerial vehicle pneumatic layout of claim 1, characterized in that: the ailerons and the elevator rudder both adopt split control surfaces.
7. The horizontal gradient magnetic detection special unmanned aerial vehicle pneumatic layout of claim 1, characterized in that: the sweepback angle of the leading edge of the main wing is 0.8-1 deg.
8. The horizontal gradient magnetic detection special unmanned aerial vehicle pneumatic layout of claim 1, characterized in that: the sweep angle of the trailing edge of the main wing is-4 to 3.5 degrees.
9. The horizontal gradient magnetic detection special unmanned aerial vehicle pneumatic layout of claim 1, characterized in that: the V wing aspect ratio is 3-4.
10. The horizontal gradient magnetic detection special unmanned aerial vehicle pneumatic layout of claim 1, characterized in that: the sweepback angles of the front edge and the rear edge of the tail wing are both 16-17 degrees.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921874165.6U CN211252976U (en) | 2019-10-31 | 2019-10-31 | Special unmanned aerial vehicle pneumatic layout is visited to horizontal gradient magnetism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921874165.6U CN211252976U (en) | 2019-10-31 | 2019-10-31 | Special unmanned aerial vehicle pneumatic layout is visited to horizontal gradient magnetism |
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| CN211252976U true CN211252976U (en) | 2020-08-14 |
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| CN201921874165.6U Active CN211252976U (en) | 2019-10-31 | 2019-10-31 | Special unmanned aerial vehicle pneumatic layout is visited to horizontal gradient magnetism |
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