CN107792374A - Unmanned plane relieving mechanism and fixed-wing unmanned plane - Google Patents
Unmanned plane relieving mechanism and fixed-wing unmanned plane Download PDFInfo
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- CN107792374A CN107792374A CN201711093067.4A CN201711093067A CN107792374A CN 107792374 A CN107792374 A CN 107792374A CN 201711093067 A CN201711093067 A CN 201711093067A CN 107792374 A CN107792374 A CN 107792374A
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- 229920000049 Carbon (fiber) Polymers 0.000 claims description 29
- 239000004917 carbon fiber Substances 0.000 claims description 29
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 28
- 230000005484 gravity Effects 0.000 claims description 11
- ZZUFCTLCJUWOSV-UHFFFAOYSA-N furosemide Chemical compound C1=C(Cl)C(S(=O)(=O)N)=CC(C(O)=O)=C1NCC1=CC=CO1 ZZUFCTLCJUWOSV-UHFFFAOYSA-N 0.000 claims description 2
- 238000000034 method Methods 0.000 description 10
- 238000000926 separation method Methods 0.000 description 8
- 238000007667 floating Methods 0.000 description 4
- 239000007787 solid Substances 0.000 description 3
- 230000006641 stabilisation Effects 0.000 description 3
- 238000011105 stabilization Methods 0.000 description 3
- 238000005265 energy consumption Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000007689 inspection Methods 0.000 description 2
- 239000011435 rock Substances 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
Classifications
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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
- B64D5/00—Aircraft transported by aircraft, e.g. for release or reberthing during flight
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U70/00—Launching, take-off or landing arrangements
- B64U70/20—Launching, take-off or landing arrangements for releasing or capturing UAVs in flight by another aircraft
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Mechanical Engineering (AREA)
- Transportation (AREA)
- Toys (AREA)
Abstract
The present invention provides a kind of unmanned plane relieving mechanism, including, steering wheel：Steering wheel includes output shaft；Rudder arm：Rudder arm one end is fixedly connected on output shaft；Drive link：Connecting rod one end and rudder arm other end hinged latch bar：Bolt rod one end is hinged with the connecting rod other end；Mounting blocks：Mounting blocks are fixedly installed in steering wheel, inserting groove is provided with the middle part of mounting blocks, the horizontal direction of mounting blocks is provided with through hole, the bolt rod other end is extended in inserting groove through through hole, inwall of the inserting groove away from rudder arm side offsets with the bolt rod other end, steering wheel can drive bolt rod in being moved back and forth in through hole, unmanned plane relieving mechanism flight stability of the present invention, cruising time length.
Description
Technical field
The present invention relates to vehicle technology field, and in particular to a kind of unmanned plane relieving mechanism and fixed-wing unmanned plane.
Background technology
Unmanned plane refers to the not manned vehicle being controlled using wireless remote control device and the control device of itself, such as
Depopulated helicopter, fixed-wing unmanned plane, unmanned parasol etc..In recent ten years, unmanned plane be widely used in taking photo by plane photography,
The fields such as electric inspection process, environmental monitoring, forest fire protection, disaster inspection, anti-terrorism lifesaving, military surveillance, battle assessment.
Multiaxis and fixed-wing are complex as a whole by the unmanned wing plate of the fixed-wing for being capable of VTOL common at present
Compound flying wing unmanned plane, but such more rotors are completed machine after taking off and no longer worked, fixed-wing unmanned plane is suitable
Flown in unnecessary more rotors, have a strong impact on cruising time and flight attitude.
Need a kind of flight stability, long-endurance fixed-wing unmanned plane badly.
The content of the invention
To achieve the above object, the present invention adopts the following technical scheme that：A kind of unmanned plane relieving mechanism, including, a steering wheel,
Steering wheel is discoid, and it has an output shaft, plate face of the output shaft perpendicular to steering wheel；One rudder arm, rudder arm one end are fixedly connected on
Output shaft；One drive link, connecting rod one end and rudder arm other end hinged latch bar：Bolt rod one end is hinged with the connecting rod other end；
One mounting blocks, the horizontal direction of mounting blocks are provided with a through hole, and the one end of bolt rod away from drive link is through through hole and extends to slotting
In access slot, the one end of bolt rod away from drive link is provided with a rubber blanket, inwall of the inserting groove away from rudder arm side and rubber blanket phase
Support, servo driving bolt rod in through hole in moving back and forth.
Unmanned plane relieving mechanism provided by the invention, by servo driving output shaft, output shaft drives rudder arm, so as to drive
Bolt rod in the inserting groove of mounting blocks, bolt rod in through hole in moving back and forth, by controlling the rotating of steering wheel, so as to
Fixed-wing unmanned plane and the fixation and release of unmanned plane release structure are controlled, unmanned plane is awing avoided unnecessary heavy burden,
Extend the cruising time of fixed-wing unmanned plane, ensure the stabilization of fixed-wing unmanned plane during flying posture.
Further, the shape of through hole and the form fit of bolt rod.
The shape of through hole and the form fit of bolt rod, bolt rod during flight is avoided to be shaken in through hole, so as to shadow
Ring the state of flight of fixed-wing unmanned plane.
The present invention also provides a kind of fixed-wing unmanned plane, including the unmanned plane relieving mechanism mentioned by the present invention；Also include
Multi-axis aircraft, fixed-wing handset and connecting rod, connecting rod one end are connected with fixed-wing handset, and the connecting rod other end is provided with link；Rudder arm
It is fixedly connected with Multi-axis aircraft, link is located in inserting groove and is sheathed on bolt rod.
Multi-axis aircraft and fixed-wing handset structure are prior art.
Connected between Multi-axis aircraft and fixed-wing handset by unmanned plane relieving mechanism, fixed-wing handset on connecting rod by setting
The link put, the bolt rod being hung in inserting groove, by the rotation for controlling steering wheel, you can flexibly rapidly realize Multi-axis aircraft
The switching of fixation and release between fixed-wing handset, awing realizes the separation of Multi-axis aircraft and fixed-wing handset, from
And avoid the weight of fixed-wing handset carrying Multi-axis aircraft from being cruised, influence the flight attitude of cruising time and fixed-wing.
Further, in addition to retainer ring and carbon fiber sleeve pipe, retainer ring are fixedly installed in connecting rod one end, carbon fiber sleeve pipe
Fixed-wing handset is symmetrically set in, the axis of carbon fiber sleeve pipe is vertical with the symmetry axis of fixed-wing handset, and retainer ring inwall is fine with carbon
Tie up sleeve outer wall connection.
Carbon fiber sleeve pipe by being arranged at fixed-wing handset is sheathed on the retainer ring for being connected to connecting rod, fixing-stable, no
Easily shake, so as to influence the flight attitude of fixed-wing unmanned plane, in addition, carbon fiber sleeve pipe lighter weight, and be tubulose knot
Structure, while reducing meaningless heavy burden, retainer ring and sleeve pipe connection face are big, and junction bearing capacity is strong, and connection is reliable and stable.
Further, carbon fiber sleeve pipe overlaps with the center of retainer ring junction with the center of gravity of fixed-wing handset.
Carbon fiber sleeve pipe and the center of retainer ring junction and the center superposition of fixed-wing handset, joint face is in all directions
It is equal in magnitude by the gravity from fixed-wing unmanned plane, ensure the flight attitude of unmanned plane；By connecting rod and link and release
When putting the fixed-wing unmanned plane of structure connection with Multi-axis aircraft flight, both are in same vertical, ensure fixed-wing
Unmanned plane takes off vertically.
A kind of method that takes off vertically of fixed-wing unmanned plane, including the fixed-wing unmanned plane mentioned by the present invention, fixed-wing
The method of taking off vertically of unmanned plane comprises the following steps：
S1：Multi-axis aircraft is crossed after unmanned plane relieving mechanism drives the lift-off of fixed-wing handset and keeps floating state；
S2：Detector detects that the air speed of fixed-wing handset reaches takeoff speed；
S3：Servo driving bolt rod exits inserting groove, and link is deviate from from bolt rod；
S4：Fixed-wing handset leaves Multi-axis aircraft, into cruising condition.
Multi-axis aircraft drives, and after the lift-off of fixed-wing handset, the air speed of fixed-wing handset reaches takeoff speed, by releasing
The rudder arm driving bolt rod of laying mechanism exits inserting groove, so as to realize the separation of fixed-wing handset and Multi-axis aircraft, has reached
The fixed-wing handset rapidly spent is while Multi-axis aircraft weight is shed, you can into cruising condition, so as to realize fixed-wing
Take off vertically, and while shed Multi-axis aircraft species, flight attitude is stable, cruise time length.
Further, step S1The height of middle lift-off is 200m.
Lift-off height is 200m, and after ensureing that Multi-axis aircraft separates with fixed-wing handset, Multi-axis aircraft is easy to drop to
Starting point, in addition 200m height ensure fixed-wing handset switch to setting aside some time for cruising condition, prevent highly too low, bottom of dropping
Face.
The present invention also provides a kind of method that takes off vertically of fixed-wing unmanned plane, fixed-wing provided by the present invention nobody
Machine, the method for taking off vertically of fixed-wing unmanned plane comprise the following steps：
S1：Multi-axis aircraft is crossed after unmanned plane relieving mechanism drives the lift-off of fixed-wing handset and keeps floating state；
S2：Servo driving bolt rod exits inserting groove, and link is deviate from from bolt rod；
S3：Fixed-wing handset leaves Multi-axis aircraft, and controller control fixed-wing handset, which bows to dive, to be accelerated；
S4：Fixed-wing handset leaves Multi-axis aircraft, into cruising condition.
Multi-axis aircraft drives, after the lift-off of fixed-wing handset, admittedly drive bolt rod to exit by the rudder arm of relieving mechanism
Inserting groove, so as to realize the separation of fixed-wing handset and Multi-axis aircraft, the fixed-wing handset for underriding of bowing is accelerated by gravity
Reach takeoff speed, then switch to cruising condition, so as to realize taking off vertically for fixed-wing, and shed Multi-axis aircraft species
Meanwhile flight attitude is stable, cruise time length, is accelerated using gravity, reduce energy consumption, extend cruising time.Step S1Middle lift-off
Height be 250m.
250m lift-off height ensures that fixed-wing handset is dived and accelerates to setting aside some time for cruising condition, prevents height from spending
It is low, bottom surface of dropping.
Beneficial effects of the present invention：
1. unmanned plane relieving mechanism provided by the invention, by servo driving output shaft, output shaft drives rudder arm, set so as to drive
Bolt rod in the inserting groove of mounting blocks, bolt rod in through hole in moving back and forth, by controlling the rotating of steering wheel, so as to control
Fixed-wing unmanned plane processed and the fixation and release of unmanned plane release structure, so as to awing avoid unnecessary heavy burden, extend solid
Determine the cruising time of wing unmanned plane, ensure the stabilization of fixed-wing unmanned plane during flying posture.
2. unmanned plane relieving mechanism provided by the invention, the shape of through hole and the form fit of bolt rod, when avoiding flight
Bolt rod shakes in through hole, so as to influence the state of flight of fixed-wing unmanned plane.
3. fixed-wing unmanned plane provided by the present invention, passes through unmanned plane machine for releasing between Multi-axis aircraft and fixed-wing handset
Structure connects, and fixed-wing handset is by the link set on connecting rod, the bolt rod being hung in inserting groove, by the rotation for controlling steering wheel
Turn, you can flexibly rapidly realize the switching of the fixation and release between Multi-axis aircraft and fixed-wing handset, awing realize
Multi-axis aircraft and the separation of fixed-wing handset, so as to avoid the weight of fixed-wing handset carrying Multi-axis aircraft from being cruised,
Influence the flight attitude of cruising time and fixed-wing.
4. fixed-wing unmanned plane provided by the present invention, company is sheathed on by the carbon fiber sleeve pipe for being arranged at fixed-wing handset
The retainer ring of connecting rod is connected on, fixing-stable, is not susceptible to rock, so as to influence the flight attitude of fixed-wing unmanned plane, in addition, carbon
Fiber sleeve lighter weight, and be tubular structure, while reducing meaningless heavy burden, retainer ring and sleeve pipe connection face are big, junction
Bearing capacity is strong, and connection is reliable and stable.
5. fixed-wing unmanned plane provided by the present invention, center and fixed-wing of the carbon fiber sleeve pipe with retainer ring junction
The center superposition of machine, joint face is equal in magnitude by the gravity from fixed-wing unmanned plane in all directions, ensures unmanned plane
Flight attitude；When the fixed-wing unmanned plane being connected by connecting rod with link and release structure is with Multi-axis aircraft flight, both
In same vertical, ensure taking off vertically for fixed-wing unmanned plane.
The method 6. fixed-wing unmanned plane provided by the present invention takes off vertically, Multi-axis aircraft drive, fixed-wing handset liter
After sky, directly accelerate or dive using gravity to accelerate, drive bolt rod to exit inserting groove by the rudder arm of relieving mechanism, from
And the separation of fixed-wing handset and Multi-axis aircraft is realized, the fixed-wing handset for reaching takeoff speed is shedding Multi-axis aircraft weight
Amount, i.e., so as to realize taking off vertically for fixed-wing, and while shed Multi-axis aircraft species, flight attitude is stable, cruise
Time is grown, in addition, also having preset lifting height, ensures that fixed-wing unmanned plane enters cruising flight.
Brief description of the drawings
Fig. 1 is the unmanned plane relieving mechanism structural representation of embodiment 1.
Fig. 2 is the fixed-wing handset structural representation of embodiment 2.
Fig. 3 is the retainer ring and carbon fiber casing-pipe connection structure schematic diagram of embodiment 3.
Wherein：101- steering wheels；102- rudder arms；20- drive links；30- bolt rods；40- mounting blocks；401- inserting grooves；402-
Through hole；50- fixed-wing handsets；60- connecting rods；70- links；80- retainer rings；90- carbon fiber sleeve pipes.
Embodiment one：
As shown in figure 1, the present embodiment provides a kind of unmanned plane relieving mechanism, including：Steering wheel 101：Steering wheel 101 includes output shaft；
Rudder arm 102：The one end of rudder arm 102 is fixedly connected on output shaft；Drive link 20：The one end of connecting rod 60 is be hinged slotting with the other end of rudder arm 102
Pin rod 30：The one end of bolt rod 30 is hinged with the connecting rod other end；Mounting blocks 40：Mounting blocks 40 are fixedly installed in steering wheel 101, installation
The middle part of block 40 is provided with inserting groove 401, and the horizontal direction of mounting blocks 40 is provided with through hole 402, and the other end of bolt rod 30 runs through through hole 402
Extend in inserting groove 401, inwall of the inserting groove 401 away from the side of rudder arm 102 offsets with the other end of bolt rod 30, steering wheel 101
Bolt rod 30 can be driven in reciprocating motion in through hole 402.
Output shaft is driven by steering wheel 101, output shaft drives rudder arm 102, so as to drive the inserting groove located at mounting blocks 40
Bolt rod 30 in 401, bolt rod 30 in through hole 402 in moving back and forth, by controlling the rotating of steering wheel 101, so as to control
Fixed-wing unmanned plane and the fixation and release of unmanned plane release structure, make unmanned plane awing avoid unnecessary heavy burden, extend
In the cruising time of fixed-wing unmanned plane, ensure the stabilization of fixed-wing unmanned plane during flying posture.
Further, the shape of through hole 402 and the form fit of bolt rod 30.
The shape of through hole 402 and the form fit of bolt rod 30, bolt rod 30 during flight is avoided to be shaken in through hole 402
It is dynamic, so as to influence the state of flight of fixed-wing unmanned plane.
Embodiment two：
As shown in Fig. 2 the present embodiment provides a kind of fixed-wing unmanned plane, include the unmanned plane relieving mechanism of embodiment 1；Also include
Multi-axis aircraft, fixed-wing handset 50 and connecting rod 60, the one end of connecting rod 60 are connected with fixed-wing handset 50, and the other end of connecting rod 60 is provided with
Link 70；Rudder arm 102 is fixedly connected with Multi-axis aircraft, and link 70 is located in inserting groove 401 and is sheathed on bolt rod 30.
Multi-axis aircraft and the structure of fixed-wing handset 50 are prior art.
Connected between Multi-axis aircraft and fixed-wing handset 50 by unmanned plane relieving mechanism, fixed-wing handset 50 passes through connecting rod
The link 70 set on 60, the bolt rod 30 being hung in inserting groove 401, by the rotation for controlling steering wheel 101, you can flexibly quick
The switching of the fixation and release between Multi-axis aircraft and fixed-wing handset 50 is realized on ground, awing realizes Multi-axis aircraft with consolidating
Determine the separation of wing handset 50, cruised so as to avoid fixed-wing handset 50 from carrying the weight of Multi-axis aircraft, when influenceing continuation of the journey
Between flight attitude with fixed-wing.
Embodiment three：
As shown in figure 3, the present embodiment provides a kind of fixed-wing unmanned plane, include the unmanned plane relieving mechanism of embodiment 1；Also include
Multi-axis aircraft, fixed-wing handset 50 and connecting rod 60, the one end of connecting rod 60 are connected with fixed-wing handset 50, and the other end of connecting rod 60 is provided with
Link 70；Rudder arm 102 is fixedly connected with Multi-axis aircraft, and link 70 is located in inserting groove 401 and is sheathed on bolt rod 30；Also wrap
Retainer ring 80 and carbon fiber sleeve pipe 90 are included, retainer ring 80 is fixedly installed in the one end of connecting rod 60, and carbon fiber sleeve pipe 90 is symmetrically set in solid
Determine wing handset 50, the axis of carbon fiber sleeve pipe 90 is vertical with the symmetry axis of fixed-wing handset 50, the inwall of retainer ring 80 and carbon fiber
The outer wall of sleeve pipe 90 connects.
Carbon fiber sleeve pipe 90 by being arranged at fixed-wing handset 50 is sheathed on the retainer ring 80 for being connected to connecting rod 60, fixed
It is stable, it is not susceptible to rock, so as to influence the flight attitude of fixed-wing unmanned plane, in addition, the lighter weight of carbon fiber sleeve pipe 90, and
For tubular structure, while reducing meaningless heavy burden, retainer ring 80 and sleeve pipe connection face are big, and junction bearing capacity is strong, and connection is reliable
It is stable.
Example IV：
The present embodiment provides a kind of fixed-wing unmanned plane, includes the unmanned plane relieving mechanism of the embodiment of the present invention 1；Also include multiaxis
Aircraft, fixed-wing handset 50 and connecting rod 60, the one end of connecting rod 60 are connected with fixed-wing handset 50, and the other end of connecting rod 60 is provided with link
70；Rudder arm 102 is fixedly connected with Multi-axis aircraft, and link 70 is located in inserting groove 401 and is sheathed on bolt rod 30；Also include solid
Determine ring 80 and carbon fiber sleeve pipe 90, retainer ring 80 is fixedly installed in the one end of connecting rod 60, and carbon fiber sleeve pipe 90 is symmetrically set in fixed-wing
Handset 50, the axis of carbon fiber sleeve pipe 90 is vertical with the symmetry axis of fixed-wing handset 50, the inwall of retainer ring 80 and carbon fiber sleeve pipe
90 outer walls connect；Carbon fiber sleeve pipe 90 overlaps with the center of the junction of retainer ring 80 with the center of gravity of fixed-wing handset 50.
Carbon fiber sleeve pipe 90 and the center of the junction of retainer ring 80 and the center superposition of fixed-wing handset 50, joint face is in institute
There is direction equal in magnitude by the gravity from fixed-wing unmanned plane, ensure the flight attitude of unmanned plane；By connecting rod 60 with hanging
When ring 70 and the fixed-wing unmanned plane of release structure connection are with Multi-axis aircraft flight, both are in same vertical,
Ensure taking off vertically for fixed-wing unmanned plane.
Embodiment five：
The present embodiment provides a kind of method that takes off vertically of fixed-wing unmanned plane, includes the fixed-wing unmanned plane of embodiment 2, fixed
The method of taking off vertically of wing unmanned plane comprises the following steps：
S1：Multi-axis aircraft is crossed after unmanned plane relieving mechanism drives the lift-off of fixed-wing handset 50 200m and keeps floating state；
S2：Detector detects that the air speed of fixed-wing handset 50 reaches takeoff speed；
S3：Steering wheel 101 drives bolt rod 30 to exit inserting groove 401, and link 70 is deviate from from bolt rod 30；
S4：Fixed-wing handset 50 leaves Multi-axis aircraft, into cruising condition.
Multi-axis aircraft drives, and after fixed-wing handset 50 is gone up to the air, the air speed of fixed-wing handset 50 reaches takeoff speed, leads to
The rudder arm 102 for crossing relieving mechanism drives bolt rod 30 to exit inserting groove 401, so as to realize fixed-wing handset 50 and Multi-axis aircraft
Separation, reach the fixed-wing handset 50 of takeoff speed while Multi-axis aircraft weight is shed, you can into cruising condition,
So as to realize taking off vertically for fixed-wing, and while shed Multi-axis aircraft species, flight attitude is stable, cruise time length.
Lift-off height is 200m, and after ensureing that Multi-axis aircraft separates with fixed-wing handset 50, Multi-axis aircraft is easy to drop to starting point, separately
Outer 200m height ensures that fixed-wing handset 50 switches to setting aside some time for cruising condition, prevents highly too low, bottom surface of dropping.
Embodiment six
The present embodiment provides a kind of method that takes off vertically of fixed-wing unmanned plane, includes the fixed-wing unmanned plane of embodiment 3, fixed
The method of taking off vertically of wing unmanned plane comprises the following steps：
S1：Multi-axis aircraft is crossed after unmanned plane relieving mechanism drives the lift-off of fixed-wing handset 50 250m and keeps floating state；
S2：Steering wheel 101 drives bolt rod 30 to exit inserting groove 401, and link 70 is deviate from from bolt rod 30；
S3：Fixed-wing handset 50 leaves Multi-axis aircraft, and controller control fixed-wing handset 50, which bows to dive, to be accelerated；
S4：Fixed-wing handset 50 leaves Multi-axis aircraft, into cruising condition.
Multi-axis aircraft drives, after fixed-wing handset 50 is gone up to the air, admittedly bolt rod is driven by the rudder arm 102 of relieving mechanism
30 exit inserting groove 401, so as to realize the separation of fixed-wing handset 50 and Multi-axis aircraft, the fixed-wing handset 50 for underriding of bowing
Accelerate to reach takeoff speed by gravity, then switch to cruising condition, so as to realize taking off vertically for fixed-wing, and shed multiaxis
While aircraft species, flight attitude is stable, cruise time length, is accelerated using gravity, reduces energy consumption, extend cruising time.
250m lift-off height ensures that fixed-wing handset 50 is dived and accelerates to setting aside some time for cruising condition, prevents highly too low, drops
Bottom surface.
It is the wherein specific implementation of the present invention above, its description is more specific and detailed, but can not therefore manage
Solve as the limitation to the scope of the claims of the present invention.For the person of ordinary skill of the art, present inventive concept is not being departed from
Under the premise of, various modifications and improvements can be made, these obvious alternative forms belong to protection scope of the present invention.
Claims (5)
- A kind of 1. unmanned plane relieving mechanism, it is characterised in that：Including：One steering wheel, steering wheel are discoid, and it has an output shaft, plate face of the output shaft perpendicular to steering wheel；Output shaft is fixed in one rudder arm, one end of rudder arm；One drive link, one end of drive link and the other end of rudder arm are hinged；One bolt rod, one end and the one end of drive link away from rudder arm of bolt rod are hinged；One mounting blocks, mounting blocks are fixedly installed in steering wheel, are provided with an inserting groove in the middle part of mounting blocks, the horizontal direction of mounting blocks is provided with One through hole, the one end of bolt rod away from drive link is through through hole and extends in inserting groove, the one end of bolt rod away from drive link Provided with a rubber blanket, inwall of the inserting groove away from rudder arm side offsets with rubber blanket, and servo driving bolt rod is in reciprocal in through hole Motion.
- 2. unmanned plane relieving mechanism according to claim 1, it is characterised in that：The shape of through hole and the shape of bolt rod are matched somebody with somebody Close.
- A kind of 3. fixed-wing unmanned plane, it is characterised in that：Including relieving mechanism as claimed in claim 1；Also include multiaxis to fly Device, fixed-wing handset and connecting rod, connecting rod one end are connected with fixed-wing handset, and the connecting rod other end is provided with link；Rudder arm flies with multiaxis Row device is fixedly connected, and link is located in inserting groove and is sheathed on bolt rod.
- 4. fixed-wing unmanned plane according to claim 3, it is characterised in that：Also include retainer ring and carbon fiber sleeve pipe, Gu Determine ring and be fixedly installed in connecting rod one end, carbon fiber sleeve pipe is symmetrically set in fixed-wing handset, the axis and fixed-wing of carbon fiber sleeve pipe The symmetry axis of handset is vertical, and retainer ring inwall is connected with carbon fiber sleeve outer wall.
- 5. fixed-wing unmanned plane according to claim 4, it is characterised in that：In carbon fiber sleeve pipe and retainer ring junction The heart overlaps with the center of gravity of fixed-wing handset.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711093067.4A CN107792374A (en) | 2017-11-08 | 2017-11-08 | Unmanned plane relieving mechanism and fixed-wing unmanned plane |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711093067.4A CN107792374A (en) | 2017-11-08 | 2017-11-08 | Unmanned plane relieving mechanism and fixed-wing unmanned plane |
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| Publication Number | Publication Date |
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| CN107792374A true CN107792374A (en) | 2018-03-13 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2019080180A1 (en) * | 2017-10-27 | 2019-05-02 | 罗伟 | Vertical takeoff method for fixed-wing unmanned aerial vehicle |
| CN110588987A (en) * | 2019-10-09 | 2019-12-20 | 北京中航智科技有限公司 | Mounted unmanned aerial vehicle and reconnaissance method thereof |
| CN117141757A (en) * | 2023-07-14 | 2023-12-01 | 北京科技大学 | Miniature flapping wing aircraft capable of carrying load, ejection device and throwing device |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107298178A (en) * | 2017-07-17 | 2017-10-27 | 广东泰高新技术发展有限公司 | Unmanned plane relieving mechanism and fixed-wing unmanned plane and its method that takes off vertically |
-
2017
- 2017-11-08 CN CN201711093067.4A patent/CN107792374A/en active Pending
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107298178A (en) * | 2017-07-17 | 2017-10-27 | 广东泰高新技术发展有限公司 | Unmanned plane relieving mechanism and fixed-wing unmanned plane and its method that takes off vertically |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2019080180A1 (en) * | 2017-10-27 | 2019-05-02 | 罗伟 | Vertical takeoff method for fixed-wing unmanned aerial vehicle |
| CN110588987A (en) * | 2019-10-09 | 2019-12-20 | 北京中航智科技有限公司 | Mounted unmanned aerial vehicle and reconnaissance method thereof |
| CN117141757A (en) * | 2023-07-14 | 2023-12-01 | 北京科技大学 | Miniature flapping wing aircraft capable of carrying load, ejection device and throwing device |
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