CN115320838A - Earthquake rescue high altitude monitoring unmanned aerial vehicle - Google Patents
Earthquake rescue high altitude monitoring unmanned aerial vehicle Download PDFInfo
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- CN115320838A CN115320838A CN202211251909.5A CN202211251909A CN115320838A CN 115320838 A CN115320838 A CN 115320838A CN 202211251909 A CN202211251909 A CN 202211251909A CN 115320838 A CN115320838 A CN 115320838A
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- 238000012544 monitoring process Methods 0.000 title claims abstract description 68
- 230000005540 biological transmission Effects 0.000 claims abstract description 57
- 230000007246 mechanism Effects 0.000 claims abstract description 21
- 230000000694 effects Effects 0.000 claims description 15
- 238000001514 detection method Methods 0.000 claims description 13
- 230000009471 action Effects 0.000 claims description 10
- 230000008859 change Effects 0.000 abstract description 5
- 238000004891 communication Methods 0.000 description 12
- 238000000034 method Methods 0.000 description 5
- 230000001174 ascending effect Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/52—Tilting of rotor bodily relative to fuselage
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
- B64C39/024—Aircraft not otherwise provided for characterised by special use of the remote controlled vehicle type, i.e. RPV
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Abstract
The invention relates to the technical field of monitoring unmanned aerial vehicle equipment, and discloses an earthquake rescue high-altitude monitoring unmanned aerial vehicle which comprises a machine body framework, wherein four groups of support arms are fixedly arranged on the outer surface of the machine body framework, a group of fixed connecting rods are respectively pin-connected to the end surfaces of the four groups of support arms, a group of rotor wing structures are respectively fixedly arranged at the bottom ends of the four groups of fixed connecting rods, an adjusting mechanism is arranged at the top ends of the fixed connecting rods, and the adjusting mechanism is in transmission connection with the tops of the outer surfaces of the support arms. This earthquake rescue high altitude monitoring unmanned aerial vehicle, to the support arm, fixed connecting rod and guiding mechanism's setting, make this high altitude monitoring unmanned aerial vehicle when receiving the wind-force influence of equidirectional, the accessible adjusts its inclination that corresponds the position and goes up the rotor structure and produce corresponding horizontal component, and then the horizontal force of offsetting wind is to this high altitude monitoring unmanned aerial vehicle's influence, this high altitude monitoring unmanned aerial vehicle's anti-wind performance has effectively been improved, make its position be difficult for receiving the influence of wind-force and change.
Description
Technical Field
The invention relates to the technical field of monitoring unmanned aerial vehicle equipment, in particular to an earthquake rescue high-altitude monitoring unmanned aerial vehicle.
Background
The unmanned aerial vehicle is an aircraft which does not need to be controlled by man-made driving but is controlled by a radio remote control flight or self-contained control program, has wide application range and application prospect in the fields of disaster rescue, surveying and mapping, power inspection or monitoring, greatly expands the application of the unmanned aerial vehicle, can monitor the landform environment of the whole area at a high altitude by using the unmanned aerial vehicle particularly in the aspect of earthquake rescue, provides real-time area landforms for rescue workers under a complex geographic environment, and then timely gives an alarm and provides early warning information when danger occurs, thereby effectively reducing the occurrence of unnecessary casualty conditions.
Wherein, when utilizing the landform environment in the unmanned aerial vehicle monitoring target area territory in the earthquake rescue environment, for guaranteeing the accurate nature of monitoring data, often need hover this unmanned aerial vehicle on a certain point, but current unmanned aerial vehicle is relatively poor at the anti-wind ability when suspending, receive the influence of external environment wind-force, make its position very easily change, and then produce the shake and lead to the image quality that its monitoring was shot relatively poor, and need constantly adjust the position state of this unmanned aerial vehicle self in order to keep its position of hovering, and then greatly influenced this unmanned aerial vehicle's duration, stability and reliability are relatively poor.
Therefore, there is a need for an aerial monitoring unmanned aerial vehicle for earthquake rescue, which can stably hover at a certain specific point during earthquake rescue, thereby accurately providing a geomorphic environment of a target area.
Disclosure of Invention
Technical problem to be solved
The invention provides an earthquake rescue high-altitude monitoring unmanned aerial vehicle, which has the advantages that the unmanned aerial vehicle can be accurately hovered at a certain specific point, the wind resistance is strong, the position of the unmanned aerial vehicle is not easy to change due to the influence of wind power, the cruising ability of the unmanned aerial vehicle is effectively improved, and the stability and the reliability are high.
(II) technical scheme
The invention provides the following technical scheme: the utility model provides an earthquake rescue high altitude monitoring unmanned aerial vehicle, includes the organism framework, the bottom of organism framework is equipped with the monitoring support, the fixed surface of organism framework installs four groups support arms, four groups the terminal surface of support arm is the pin joint respectively has a set of fixed connecting rod, and has a set of rotor structure at the bottom of four groups of fixed connecting rod fixed mounting respectively, the top of fixed connecting rod is equipped with guiding mechanism to form the transmission through between the top of guiding mechanism and support arm surface and be connected, guiding mechanism includes the linkage sleeve, the telescopic outside of linkage is equipped with solenoid, and has cup jointed the transmission connecting rod at the telescopic inside activity of linkage, the middle part of transmission connecting rod surface just is located the fixed transmission piston that has magnetic structure in the top of linkage sleeve inner chamber, the bottom of transmission connecting rod surface just is located the middle part activity of linkage sleeve inner chamber and has cup jointed the control valve block that the bottom has magnetic structure, and the bottom of control valve block forms the transmission and is connected through cup jointing the activity constant voltage spring in the transmission connecting rod surface and the linkage sleeve inner chamber's bottom to be equipped with a set of groove hole respectively in the upper and lower both sides of control valve block surface, one side of linkage sleeve inner chamber and the second through the first through the groove hole intercommunication that the linkage piston communicates the top that the second piston communicates the formation is linked together.
Preferably, a chamber formed by the top end of the transmission piston and the top of the inner cavity of the linkage sleeve and a chamber formed between the transmission piston and the control valve block are filled with hydraulic transmission oil.
Preferably, the elastic force of the constant pressure spring is smaller than the magnetic force of the magnetic field generated when the electromagnetic coil is switched on, and the magnetic field in different directions can be generated on the control valve block when the current on the electromagnetic coil is switched on and the direction of the current on the electromagnetic coil is changed, so that the control valve block is driven to move rightwards or leftwards by overcoming the elastic force of the constant pressure spring.
Preferably, when the electromagnetic coil is connected with current, the magnetic field generated can force the transmission piston on the transmission connecting rod and the control valve block to generate a force moving towards the right side, so that the constant pressure spring is compressed and the control valve block is driven to move towards the right side, and the first communication slotted hole and the second communication slotted hole are connected under the action of the annular groove at the left side of the control valve block, so that the transmission piston moves towards the right side.
Preferably, when the electromagnetic coil is connected with current, the magnetic field generated can force the transmission piston on the transmission connecting rod and the control valve block to generate a force moving towards the left side, so that the constant pressure spring is stretched and the control valve block is driven to move towards the left side, and the first communication slotted hole and the second communication slotted hole are connected under the action of the annular groove at the right side of the control valve block, so that the transmission piston moves towards the left side.
Preferably, four corresponding groups of the four groups of the rotor wing structures form electric feedback connection with a wind power detection system and a control system on the high-altitude monitoring unmanned aerial vehicle respectively.
(III) advantageous effects
The invention has the following beneficial effects:
1. this earthquake rescue high altitude monitoring unmanned aerial vehicle, to the support arm, fixed connecting rod and guiding mechanism's setting, make this high altitude monitoring unmanned aerial vehicle when receiving the wind-force influence of equidirectional, the accessible adjusts its inclination that corresponds the rotor structure in the position and produces corresponding horizontal component, the horizontal force of offsetting wind is to this high altitude monitoring unmanned aerial vehicle's influence, and then effectively improved this high altitude monitoring unmanned aerial vehicle's anti-wind performance, make its position be difficult for receiving the influence of wind-force and change, the precision of monitoring shooting is higher, simultaneously, the vertical component that utilizes wind can produce ascending lift to this high altitude monitoring unmanned aerial vehicle, and then effectively reduce this high altitude monitoring unmanned aerial vehicle's power loss, and improved its self duration.
2. This earthquake rescue high altitude monitoring unmanned aerial vehicle, to the setting of guiding mechanism and structure above that, the produced magnetic field of accessible solenoid and the flexible state of adjusting transmission connecting rod above that, and then adjust its inclination that corresponds the position rotary wing structure, and simultaneously, at control valve piece and the setting of linkage structure above that, can adjust the break-make state between first intercommunication slotted hole and the second intercommunication slotted hole on the control linkage sleeve according to solenoid's circular telegram state, the position state of transmission connecting rod on the effective control, make this high altitude monitoring unmanned aerial vehicle at the in-process of operation, the rotor structure on its corresponding position can not take place the slope change by the influence of wind-force, stability and reliability are higher.
Drawings
FIG. 1 is a schematic view of the structure of the present invention;
FIG. 2 is a schematic view of the internal structure of the adjusting mechanism of the present invention;
FIG. 3 is a schematic view of the adjusting mechanism according to the present invention;
FIG. 4 is a schematic view of the adjusting mechanism according to the present invention;
FIG. 5 is a top view of the structure of the present invention;
FIG. 6 is a schematic structural diagram of a first embodiment of the present invention;
FIG. 7 is a schematic structural view of a second embodiment of the present invention;
FIG. 8 is a schematic structural diagram of a third embodiment of the present invention;
FIG. 9 is a schematic structural diagram of a fourth embodiment of the present invention.
In the figure: 1. a body frame; 2. monitoring the stent; 3. a support arm; 4. fixing the connecting rod; 5. a rotor structure; 6. an adjustment mechanism; 7. a linkage sleeve; 8. an electromagnetic coil; 9. a transmission connecting rod; 10. a drive piston; 11. a control valve block; 12. a constant pressure spring; 13. a first communication slot; 14. a second communicating slot.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be obtained by a person skilled in the art without making any creative effort based on the embodiments in the present invention, belong to the protection scope of the present invention.
Referring to fig. 1, an earthquake rescue high altitude monitoring unmanned aerial vehicle comprises a machine body framework 1, a monitoring support 2 for fixedly mounting monitoring equipment is arranged at the bottom end of the machine body framework 1, four groups of support arms 3 arranged in an annular array are fixedly mounted on the outer surface of the machine body framework 1, a group of fixed connecting rods 4 are respectively pin-connected to the end surfaces of the four groups of support arms 3, a group of rotor wing structures 5 are respectively fixedly mounted at the bottom ends of the four groups of fixed connecting rods 4, the four groups of rotor wing structures 5 are respectively set to be a, B, C and D, an adjusting mechanism 6 is arranged at the top end of the fixed connecting rod 4 and forms transmission connection with the top of the outer surface of the support arm 3 through the adjusting mechanism 6, as shown in fig. 2, the adjusting mechanism 6 comprises a linkage sleeve 7 with one end pin-connected to the top of the outer surface of the support arm 3, an electromagnetic coil 8 is arranged outside the linkage sleeve 7, a transmission connecting rod 9 with one end pin-connected to the top end of the fixed connecting rod 4 is movably sleeved inside the linkage sleeve 7, a transmission piston 10 with the top of the inner cavity of the outer surface of the linkage sleeve 9 and a transmission sleeve with a transmission piston with a magnetic structure with a transmission valve 10 with a magnetic structure, a transmission valve block 11 arranged at the bottom end of the inner cavity of the linkage sleeve 9, a constant pressure control block is arranged in a constant pressure control block arranged in a constant pressure control sleeve 7, a constant pressure control inner cavity of a constant pressure control sleeve 11 arranged in a constant pressure control sleeve 7 arranged on the inner cavity of a constant pressure control block arranged on the inner cavity of a constant pressure control sleeve 11 arranged on one side of a constant pressure control sleeve 7, and is communicated with a chamber formed between the transmission piston 10 and the control valve block 11 through a first communication slotted hole 13, a second communication slotted hole 14 is arranged on the other side in the linkage sleeve 7 and is communicated with a chamber formed between the top end of the transmission piston 10 and the top of the inner cavity of the linkage sleeve 7 through the second communication slotted hole 14, and the first communication slotted hole 13 and the second communication slotted hole 14 are in a mutually blocked state in an initial state.
As shown in fig. 2, in the present embodiment, a chamber formed by the top end of the transmission piston 10 and the top of the inner cavity of the linkage sleeve 7 and a chamber formed between the transmission piston 10 and the control valve block 11 are filled with a full volume of hydraulic transmission oil, so as to control the position state of the transmission piston 10 thereon through the on-off state between the first communication slot hole 13 and the second communication slot hole 14, and adjust the tilt state of the upper rotor structure 5 thereof under the transmission action of the fixed link 4.
As shown in fig. 2, in the present embodiment, the elastic force of the constant pressure spring 12 is smaller than the magnetic force of the magnetic field generated when the electromagnetic coil 8 is switched on, and when the current on the electromagnetic coil 8 is switched on and the direction of the current thereon is changed, magnetic fields in different directions can be generated on the control valve block 11, so as to drive the control valve block 11 to move rightward or leftward against the elastic force of the constant pressure spring 12.
As shown in fig. 3, in the present embodiment, when the electromagnetic coil 8 is energized, the magnetic field generated can force the transmission piston 10 and the control valve block 11 on the transmission connecting rod 9 to generate a force moving to the right, so as to compress the constant pressure spring 12 and drive the control valve block 11 to move to the right, and the first communicating slot 13 and the second communicating slot 14 are communicated under the action of the annular groove on the left side of the control valve block 11, so that the transmission piston 10 moves to the right, so as to adjust the inclination angle of the rotary wing structure 5 on the fixed connecting rod 4.
As shown in fig. 4, in the present embodiment, when the electromagnetic coil 8 is energized, the magnetic field generated can force the transmission piston 10 and the control valve block 11 on the transmission connecting rod 9 to generate a force moving to the left, so as to stretch the constant pressure spring 12 and drive the control valve block 11 to move to the left, and the first communicating slot 13 and the second communicating slot 14 are communicated under the action of the annular groove on the right side of the control valve block 11, so that the transmission piston 10 moves to the left, so as to adjust the inclination angle of the rotary wing structure 5 on the fixed connecting rod 4.
In the technical scheme, four corresponding adjusting mechanisms 6 (A, B, C and D) on the four rotor wing structures 5 are respectively in electric feedback connection with a wind power detection system and a control system on the high-altitude monitoring unmanned aerial vehicle, so that the inclination angles of the four adjusting mechanisms 6 can be respectively regulated and controlled when the high-altitude monitoring unmanned aerial vehicle is influenced by wind power.
Example one
As shown in fig. 5 and 6, when the high-altitude monitoring unmanned aerial vehicle is affected by horizontal wind, the wind detection system on the high-altitude monitoring unmanned aerial vehicle calculates the effect of the high-altitude monitoring unmanned aerial vehicle on the wind detection system, and then adjusts the currents respectively communicated with the four groups of electromagnetic coils 8 on the wind detection system through the control system, and adjusts the magnitude and direction of the current communicated with the electromagnetic coils 8 through the control system, and respectively forces the four groups of rotor structures 5 on the wind detection system to rotate counterclockwise by using the end surfaces of the upper support arms 3 as the rotation center points, and generates a group of component forces horizontally corresponding to the wind direction to counteract the effect of the wind on the high-altitude monitoring unmanned aerial vehicle;
simultaneously, the rotational speed of four rotor structures 5 of accessible increase and keep its component force that makes progress to this high altitude monitoring unmanned aerial vehicle production, ensure that this high altitude monitoring unmanned aerial vehicle is in corresponding position height all the time.
Example two
As shown in fig. 5 and 7, when the left side of the high altitude monitoring unmanned aerial vehicle is affected by wind power obliquely upward, the wind power detection system thereon calculates the effect of the wind power detection system on the high altitude monitoring unmanned aerial vehicle, and then adjusts the currents respectively connected to the four sets of electromagnetic coils 8 thereon through the control system, and adjusts the magnitude and direction of the current connected to the electromagnetic coils 8 through the control system, and respectively forces the four sets of rotor structures 5 thereon to rotate counterclockwise by using the end surface of the upper arm 3 thereof as a rotation center point, and generates a set of component force horizontally corresponding to the wind power direction to counteract the effect of the wind power on the high altitude monitoring unmanned aerial vehicle;
simultaneously, the accessible reduces four group's rotor structure 5's rotational speed and reduces its upwards component to this high altitude monitoring unmanned aerial vehicle to utilize the vertical ascending component of wind and ensure this high altitude monitoring unmanned aerial vehicle's position height, and then effectively reduce this high altitude monitoring unmanned aerial vehicle's power loss, improved its self duration.
EXAMPLE III
As shown in fig. 5 and 8, when the right side of the high altitude monitoring unmanned aerial vehicle is affected by wind power obliquely upward, the wind power detection system thereon calculates the effect of the wind power detection system on the high altitude monitoring unmanned aerial vehicle, and then adjusts the currents respectively communicated with the four sets of electromagnetic coils 8 thereon through the control system, and adjusts the magnitude and direction of the current communicated with the electromagnetic coils 8 through the control system, and respectively forces the four sets of rotor structures 5 thereon to rotate clockwise with the end surface of the upper arm 3 thereof as a rotation center point, and generates a set of component force horizontally corresponding to the wind power direction to counteract the effect of the wind power on the high altitude monitoring unmanned aerial vehicle;
simultaneously, the accessible reduces four group's rotor structure 5's rotational speed and reduces its upwards component to this high altitude monitoring unmanned aerial vehicle to utilize the vertical ascending component of wind and ensure this high altitude monitoring unmanned aerial vehicle's position height, and then effectively reduce this high altitude monitoring unmanned aerial vehicle's power loss, improved its self duration.
Example four
As shown in fig. 5 and 9, when the opposite corners of the high altitude monitoring unmanned aerial vehicle are affected by horizontal wind, the wind detection system on the high altitude monitoring unmanned aerial vehicle calculates the effect of the wind detection system on the high altitude monitoring unmanned aerial vehicle, and then adjusts the currents respectively connected to the electromagnetic coils 8 on the opposite corners through the control system, and adjusts the magnitude and direction of the current connected to the electromagnetic coils 8 through the control system, and respectively forces the rotor structure 5 (a, C or B, D) in the opposite corners on the rotor structure to rotate counterclockwise by using the end surface of the upper arm 3 as a rotation center point, and generates a group of component forces horizontally corresponding to the wind direction to counteract the effect of the wind on the high altitude monitoring unmanned aerial vehicle;
meanwhile, the rotating speed of the rotor structure 5 (A, C or B, D) in the opposite angle can be increased to keep the upward component force of the high-altitude monitoring unmanned aerial vehicle, so that the position height of the high-altitude monitoring unmanned aerial vehicle is ensured.
When the right side of the opposite corner of the high altitude monitoring unmanned aerial vehicle is influenced by wind which inclines upwards or the left side of the opposite corner of the high altitude monitoring unmanned aerial vehicle is influenced by wind which inclines upwards, the rotating inclination angle of the rotor structure 5 at the corresponding position is the same as that of the second embodiment and the third embodiment, and the specific inclined rotor structure 5 is the same as that of the fourth embodiment.
It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (6)
1. The utility model provides an earthquake rescue high altitude monitoring unmanned aerial vehicle, includes organism framework (1), the bottom of organism framework (1) is equipped with monitoring support (2), the fixed surface of organism framework (1) installs four groups support arm (3), its characterized in that: the end surfaces of the four groups of support arms (3) are respectively in pin joint with a group of fixed connecting rods (4), the bottom ends of the four groups of fixed connecting rods (4) are respectively and fixedly provided with a group of rotor wing structures (5), the top ends of the fixed connecting rods (4) are provided with adjusting mechanisms (6), and the adjusting mechanisms (6) are in transmission connection with the top parts of the outer surfaces of the support arms (3);
adjustment mechanism (6) are including linkage sleeve (7), the outside of linkage sleeve (7) is equipped with solenoid (8), and has cup jointed transmission connecting rod (9) in the inside activity of linkage sleeve (7), the middle part of transmission connecting rod (9) surface and the fixed cover in top that is located linkage sleeve (7) inner chamber have connect transmission piston (10) that have the magnetic structure, the bottom of transmission connecting rod (9) surface and the middle part activity that is located linkage sleeve (7) inner chamber have cup jointed the control valve piece (11) that the bottom has the magnetic structure, and form the transmission and be connected between the bottom of constant voltage spring (12) and linkage sleeve (7) inner chamber that the activity cup jointed in transmission connecting rod (9) surface through the bottom of control valve piece (11) surface to be equipped with a set of ring channel respectively in the upper and lower both sides of control valve piece (11) surface, one side of linkage sleeve (7) inside is equipped with first through linkage slotted hole (13), and is linked together through the cavity that first intercommunication slotted hole (13) and transmission piston (10) and control valve piece (11) formed between, the linkage slotted hole (7) inside is equipped with second slotted hole (14), and second piston top intercommunication (7) and second piston chamber (14) top intercommunication (7) are linked together.
2. The earthquake rescue high altitude monitoring unmanned aerial vehicle of claim 1, characterized in that: and a cavity formed by the top end of the transmission piston (10) and the top of the inner cavity of the linkage sleeve (7) and a cavity formed between the transmission piston (10) and the control valve block (11) are filled with hydraulic transmission oil.
3. The earthquake rescue high altitude monitoring unmanned aerial vehicle of claim 2, characterized in that: the elasticity of the constant-pressure spring (12) is smaller than the magnetic force of a magnetic field generated when the electromagnetic coil (8) is switched on, and the magnetic force of the magnetic field generated when the electromagnetic coil (8) is switched on is larger than the magnetic force of the magnetic field generated when the current on the electromagnetic coil is changed, so that magnetic fields in different directions can be generated on the control valve block (11), and the control valve block (11) is driven to overcome the elasticity of the constant-pressure spring (12) to move rightwards or leftwards.
4. A earthquake rescue high altitude monitoring unmanned aerial vehicle according to claim 3, characterized in that: when the electromagnetic coil (8) is connected with current, the generated magnetic field can force the transmission piston (10) and the control valve block (11) on the transmission connecting rod (9) to generate force moving towards the right side, so that the constant pressure spring (12) is compressed and the control valve block (11) is driven to move towards the right side, and the first connecting groove hole (13) and the second connecting groove hole (14) are connected under the action of the annular groove at the left side of the control valve block (11), so that the transmission piston (10) moves towards the right side.
5. A earthquake rescue high altitude monitoring unmanned aerial vehicle according to claim 3, characterized in that: when the electromagnetic coil (8) is connected with current, the magnetic field can force the transmission piston (10) and the control valve block (11) on the transmission connecting rod (9) to generate a force moving towards the left side, so that the constant pressure spring (12) is stretched and the control valve block (11) is driven to move towards the left side, and the first connecting groove hole (13) and the second connecting groove hole (14) are connected under the action of the annular groove at the right side of the control valve block (11), so that the transmission piston (10) moves towards the left side.
6. The earthquake rescue high altitude monitoring unmanned aerial vehicle of claim 1, characterized in that: four corresponding groups of the four groups of the adjusting mechanisms (6) on the four groups of the rotor wing structures (5) are respectively connected with a wind power detection system and a control system on the high-altitude monitoring unmanned aerial vehicle in an electric feedback manner.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211251909.5A CN115320838A (en) | 2022-10-13 | 2022-10-13 | Earthquake rescue high altitude monitoring unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211251909.5A CN115320838A (en) | 2022-10-13 | 2022-10-13 | Earthquake rescue high altitude monitoring unmanned aerial vehicle |
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| CN115320838A true CN115320838A (en) | 2022-11-11 |
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| CN202211251909.5A Pending CN115320838A (en) | 2022-10-13 | 2022-10-13 | Earthquake rescue high altitude monitoring unmanned aerial vehicle |
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| CN104802985A (en) * | 2015-04-30 | 2015-07-29 | 江苏数字鹰科技发展有限公司 | Variable axial multi-rotor aircraft and flight attitude adjustment method thereof |
| US20160244157A1 (en) * | 2015-02-19 | 2016-08-25 | Amazon Technologies, Inc. | Vehicle configuration with motors that rotate between a lifting position and a thrusting position |
| CN207150510U (en) * | 2017-06-09 | 2018-03-27 | 周崇秋 | Solar panels angle regulator based on magnetic rheology effect |
| CN110001950A (en) * | 2019-04-06 | 2019-07-12 | 胡永星 | A kind of quadrotor drone keeping flight stability in beam wind |
| CN210083537U (en) * | 2019-03-29 | 2020-02-18 | 厦门天源欧瑞科技有限公司 | High stability I-shaped unmanned aerial vehicle |
| CN111301673A (en) * | 2020-03-04 | 2020-06-19 | 吉林工程技术师范学院 | Six-wing medium-sized unmanned aerial vehicle's rotary device |
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2022
- 2022-10-13 CN CN202211251909.5A patent/CN115320838A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20160244157A1 (en) * | 2015-02-19 | 2016-08-25 | Amazon Technologies, Inc. | Vehicle configuration with motors that rotate between a lifting position and a thrusting position |
| CN104802985A (en) * | 2015-04-30 | 2015-07-29 | 江苏数字鹰科技发展有限公司 | Variable axial multi-rotor aircraft and flight attitude adjustment method thereof |
| CN207150510U (en) * | 2017-06-09 | 2018-03-27 | 周崇秋 | Solar panels angle regulator based on magnetic rheology effect |
| CN210083537U (en) * | 2019-03-29 | 2020-02-18 | 厦门天源欧瑞科技有限公司 | High stability I-shaped unmanned aerial vehicle |
| CN110001950A (en) * | 2019-04-06 | 2019-07-12 | 胡永星 | A kind of quadrotor drone keeping flight stability in beam wind |
| CN111301673A (en) * | 2020-03-04 | 2020-06-19 | 吉林工程技术师范学院 | Six-wing medium-sized unmanned aerial vehicle's rotary device |
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