CN109703759A - A kind of carrier vehicle - Google Patents
A kind of carrier vehicle Download PDFInfo
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- CN109703759A CN109703759A CN201910123997.2A CN201910123997A CN109703759A CN 109703759 A CN109703759 A CN 109703759A CN 201910123997 A CN201910123997 A CN 201910123997A CN 109703759 A CN109703759 A CN 109703759A
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- aircraft body
- storehouse
- carrier vehicle
- delivery
- docking
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- 238000003032 molecular docking Methods 0.000 claims abstract description 76
- 230000001133 acceleration Effects 0.000 claims description 13
- 230000003247 decreasing effect Effects 0.000 abstract description 3
- 238000010586 diagram Methods 0.000 description 7
- 238000012544 monitoring process Methods 0.000 description 5
- 210000000078 claw Anatomy 0.000 description 4
- 238000013461 design Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000007423 decrease Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005265 energy consumption Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000005484 gravity Effects 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 230000002159 abnormal effect Effects 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000005622 photoelectricity Effects 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 239000004449 solid propellant Substances 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
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Abstract
The invention discloses a kind of carrier vehicles, including for providing the aircraft body of lift, with be connected in the aircraft body and the delivery storehouse of delivery function be provided, wherein, the aircraft body is connected with the delivery storehouse by docking mechanism, when the docking mechanism is in locking state, the delivery storehouse is linked together with the aircraft body；When the docking mechanism is in disengaged condition, the delivery storehouse and the aircraft body are detached from；Parachute is provided on the delivery storehouse.Delivery storehouse in the carrier vehicle may be implemented individually to land, for the case where current aircraft integrally lands, the weight in delivery storehouse is remarkably decreased, the pulling force that parachute and umbrella rope are born also just substantially reduces, this just effectively prevents the damage of parachute and umbrella rope, provides guarantee to deliver the safe falling in storehouse.
Description
Technical field
The present invention relates to Flight Vehicle Design production technical field, more specifically to a kind of carrier vehicle.
Background technique
With the progress of stereo urban traffic technology, have the low flyer (such as hovercar) of delivery function at
For development trend.This low flyer is mainly used in city low latitude environment, in descent with the buffering on ground away from
Short from very, it is one of the focus of current those skilled in the art that how safety and steady, which lands,.
The forced landing that low flyer is realized by parachute is to compare routine at present and be technically relatively easy to reality
Existing mode, in the prior art, either rotary aircraft or culvert type aircraft, the cabin and aircraft of aircraft
It being an integral structure between main body, the two can not separate, and the top of aircraft is arranged in the parachuting mechanism of this aircraft,
Parachute and umbrella rope itself need to bear very big pulling force during aircraft decline, this causes parachute and umbrella rope to hold very much
It easily damages, will lead to aircraft landing failure under serious conditions, cause damages.
Therefore, in carrier vehicle descent, how to reduce the pulling force that parachute and umbrella rope are born is
At present the technical issues of those skilled in the art's urgent need to resolve.
Summary of the invention
In view of this, the invention discloses a kind of carrier vehicles, so as in carrier vehicle forced landing process
In effectively reduce the pulling force that parachute and umbrella rope are born.
In order to achieve the above objectives, disclosed in this invention carrier vehicle, including for providing the aircraft master of lift
Body, and be connected in the aircraft body and the delivery storehouse of delivery function is provided, wherein
The aircraft body is connected with the delivery storehouse by docking mechanism, is in locking state in the docking mechanism
When, the delivery storehouse is linked together with the aircraft body；When the docking mechanism is in disengaged condition, the delivery storehouse
It is detached from the aircraft body；
Parachute is provided on the delivery storehouse.
Preferably, hollow docking cavity, the bottom setting of the aircraft body are provided at the top of the delivery storehouse
There is a dock that can be embedded in the docking cavity, the docking cavity and the dock are provided with active on any one
In addition lock piece is provided with the lock groove being adapted to the active lock piece in one.
Preferably, the bottom of the aircraft body is provided with hollow docking cavity, the top setting in the delivery storehouse
There is a dock that can be embedded in the docking cavity, the docking cavity and the dock are provided with active on any one
In addition lock piece is provided with the lock groove being adapted to the active lock piece in one.
Preferably, the active lock piece is telescopic locking protrusion.
Preferably, the telescopic locking protrusion is the continuous of the circumferentially extending along the docking cavity or the dock
Strip projected parts.
Preferably, the telescopic locking protrusion includes multiple, and the telescopic locking protrusion is along the docking cavity
Or the circumferential intermittent arrangement of the dock.
Preferably, the docking cavity also serves as the umbrella storehouse for accommodating the parachute, and the parachute is built in institute
State the bottom of docking cavity.
Preferably, the cross section of the internal cavities of the docking cavity is in rectangle, and on the inner wall of the docking cavity also
Rotation is provided with the cover board for covering the parachute.
Preferably, the cover board includes two, and two cover boards are symmetricly set on the docking cavity by shaft
On two opposite inner walls.
It preferably, further include being arranged in the aircraft body and upward thrust being provided for the aircraft body
Retro-rocket or gas ejector.
Preferably, further includes:
Setting is stretched in the aircraft body or on the delivery storehouse for controlling the telescopic locking protrusion
Out and retract controller；
Attitude transducer in the aircraft body is set, and detects the aircraft in the attitude transducer
When the inclination angle of main body is more than preset value, the controller control telescopic locking protrusion is retracted so that the delivery storehouse and
The aircraft body is detached from.
Preferably, it is additionally provided with acceleration transducer in the aircraft body, and is detected in the acceleration transducer
When reaching predetermined acceleration to the whereabouts acceleration of the carrier vehicle, the controller controls the locking protrusion and retracts,
So that the delivery storehouse and the aircraft body are detached from.
It preferably, further include energy monitoring module, and in the energy monitoring module monitors to the aircraft body
When energy supply is less than default energy limit value, the controller controls the locking protrusion and retracts, so that the delivery storehouse and institute
State aircraft body disengaging.
Preferably, further include warning device, supplied in the energy of the energy monitoring module monitors to the aircraft body
When should be less than default energy limit value, the controller controls the warning device alarm.
Disclosed in this invention carrier vehicle in, aircraft body is connected with delivery storehouse by docking mechanism, and
When docking mechanism is in locking state, delivery storehouse is linked together with aircraft body；When docking mechanism is in disengaged condition,
It delivers storehouse and aircraft body is detached from；Delivery is provided with parachute on storehouse.
Delivery carries the passenger for needing to transport or cargo in storehouse, right when delivery storehouse needs forced landing in the sky
Connection mechanism is in disengaged condition, so that delivery storehouse will be detached from from aircraft body, delivering parachute set on storehouse will be
Upward pulling force is provided in delivery storehouse descent, guarantees the safe falling in delivery storehouse；Since delivery storehouse is with aircraft body
Separation design, therefore may be implemented individually to land in delivery storehouse, for the case where current aircraft integrally lands, fortune
The weight for carrying storehouse is remarkably decreased, and the pulling force that parachute and umbrella rope are born also just substantially reduces, this just effectively prevents parachute
With the damage of umbrella rope, guarantee is provided to deliver the safe falling in storehouse.
Detailed description of the invention
In order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, to embodiment or will show below
There is attached drawing needed in technical description to be briefly described, it should be apparent that, the accompanying drawings in the following description is only this
Some embodiments of invention for those of ordinary skill in the art without creative efforts, can be with
Other attached drawings are obtained according to these attached drawings.
Fig. 1 is the structural schematic diagram of the aircraft body disclosed in the embodiment of the present invention；
Fig. 2 is the structural schematic diagram in the delivery storehouse disclosed in the embodiment of the present invention；
Fig. 3 is the structural schematic diagram after the delivery storehouse disclosed in the embodiment of the present invention is combined with the Flight main body；
Fig. 4 is the structural schematic diagram of the dock disclosed in the embodiment of the present invention；
Fig. 5 is the structural schematic diagram of the docking cavity disclosed in the embodiment of the present invention；
The card distribution structure schematic diagram Fig. 6 dock disclosed in the embodiment of the present invention and dock cavity；
Fig. 7 is the dropping process schematic diagram in the delivery storehouse disclosed in the embodiment of the present invention.
Wherein, 1 is aircraft body, and 2 be delivery storehouse, and 11 be dock, and 12 be lock groove, and 21 be docking cavity, and 22 are
Cover board, 23 be telescopic locking protrusion, and 24 be landing pack.
Specific embodiment
Core of the invention is to provide a kind of carrier vehicle, so as to have during carrier vehicle forced landing
Effect reduces the pulling force that parachute and umbrella rope are born.
In order to enable those skilled in the art to better understand the solution of the present invention, below with reference to attached in the embodiment of the present invention
Figure, technical scheme in the embodiment of the invention is clearly and completely described, it is clear that described embodiment is only this
Invention a part of the embodiment, instead of all the embodiments.Based on the embodiments of the present invention, those of ordinary skill in the art exist
Every other embodiment obtained under the premise of creative work is not made, shall fall within the protection scope of the present invention.
Fig. 1 to Fig. 7, the carrier vehicle disclosed in the present embodiment, including aircraft body 1 and delivery storehouse 2 are please referred to,
Wherein the effect of aircraft body 1 is to provide upward lift for entire carrier vehicle to overcome entire carrier vehicle
Gravity, delivery storehouse 2 can be used for transporting goods and materials or passenger, and aircraft body 1 and delivery storehouse for providing delivery function
2 are connected by docking mechanism, and when docking mechanism is in locking state, delivery storehouse 2 is linked together with aircraft body 1, right
When connection mechanism is in disengaged condition, delivery storehouse 2 and aircraft body 1 are detached from, and are delivered and are additionally provided with parachute on storehouse 2.
Delivery carries the passenger for needing to transport or goods and materials in storehouse 2, right when delivery storehouse needs forced landing in the sky
Connection mechanism is in disengaged condition, so that delivery storehouse 2 will be detached from from aircraft body 1, delivering parachute set on storehouse 2 will
To provide upward pulling force in delivery 2 descent of storehouse, guarantee the safe falling in delivery storehouse 2；Due to delivery storehouse 2 and aircraft master
Body 1 is separation design, therefore the case where individually landing, integrally landing compared to current aircraft may be implemented in delivery storehouse 2
For, the weight in delivery storehouse 2 is remarkably decreased, and the pulling force that parachute and umbrella rope are born also just substantially reduces, this is just effectively avoided
The damage of parachute and umbrella rope provides guarantee to deliver the safe falling in storehouse 2.
The carrier vehicle of this type can be used in combination with the transporting cars on ground, thus formed can on land and
Delivery storehouse 2 is arranged on transporting cars in ground handling for the hovercar run in the air；And it blocks up or needs on ground
When quickly arriving at the destination, the delivery storehouse 2 can be made to be connected with aircraft body 1 by docking mechanism, taken by aircraft body 1
Band delivery storehouse 2 arrives at the destination as early as possible.
It needs to be illustrated, the locking of docking mechanism and disengaged condition can be by manually controlling by button, can also
Instruction is received by controller to carry out automatically controlling.
The form of docking mechanism is not limited to one kind, for example, in one embodiment, docking mechanism can be butt hole
With dock the mutually matched form of claw, dock claw and butt hole be separately positioned in aircraft body 1 and delivery storehouse 2, when
The locking of docking mechanism can be realized when in docking claw insertion butt hole, can be realized when docking claw and extracting butt hole pair
The disengagement of connection mechanism, in another embodiment, docking mechanism may be the form that stud is matched with screw hole, stud and spiral shell
Hole is separately positioned in aircraft body 1 and delivery storehouse 2, and the locking of docking mechanism can be realized when stud screws in screw hole,
The disengagement of docking mechanism can be realized when stud is screwed out from screw hole.
A kind of specific implementation form of docking mechanism is additionally provided in the present embodiment, as shown in Fig. 1 to Fig. 6, delivers storehouse 2
Top be provided with hollow docking cavity 21, the bottom of aircraft body 1, which is provided with, can be embedded into inside docking cavity 21
Dock 11, dock and be provided with active lock piece in any one of cavity 21 and dock 11, be in addition provided in one
Lock groove 12 compatible with active lock piece.
So-called active lock piece is exactly the lock piece for referring to driven device driving, can be docking card pawl, stud
Or locking protrusion etc., the active lock piece in the embodiment of the present invention is preferably telescopic locking protrusion 23, in Fig. 5 and Fig. 6
It is shown, telescopic locking protrusion 23 along docking cavity 21 or dock 11 circumferentially, in driving device (such as motor or electronic
Telescopic rod) driving under, telescopic locking protrusion 23 can retraction docking cavity 21 or dock 11 side wall in, thus realize pair
The disengagement of connection mechanism, certainly, under the drive of the drive, telescopic locking protrusion 23 can stretch out docking cavity 21 or docking
The side wall of platform 11, to realize the locking of docking mechanism.
Telescopic locking protrusion 23 can be uninterruptedly distributed in the circumferential direction of docking cavity 21 or dock 11, to be formed
Continuous strip projected parts, as shown in Figure 5, telescopic locking protrusion 23 are uninterruptedly distributed on the inner wall of docking cavity 21, and
Continuous strip projected parts structure is formd on the inner wall of docking cavity 21, correspondingly, lock groove 12 has just been designed in docking
On platform 11, and lock groove 12 is the continuous annular groove being adapted to telescopic locking protrusion 23, as shown in Figure 4.
Certainly, telescopic locking protrusion 23 can also be distributed in the circumferential direction of docking cavity 21 or dock 11 for discontinuous,
Telescopic locking protrusion 23 should be comprising multiple, correspondingly, lock groove 12 should also be as comprising multiple, and along docking cavity 21 at this time
Or the circumferential intermittent distribution of dock 11.
The docking cavity 21 of the carrier vehicle shown in attached drawing of the present invention is arranged on delivery storehouse 2, dock 11
Be arranged in aircraft body 1, those skilled in the art it is conceivable that flexible mode are as follows: dock 11 setting delivery storehouse
On 2, docking cavity 21 is arranged in aircraft body 1.
The parachuting device of aircraft is to be separately provided in the prior art, other than having the function of auxiliary landing, parachuting
On the one hand device influences the aesthetics of aircraft, on the other hand also to fly without any other auxiliary function, parachuting device
Self weight of the device in normal flight course is larger, and energy consumption is higher.For this purpose, in carrier vehicle disclosed in the present embodiment,
Docking cavity 21 also serves as the umbrella storehouse for accommodating parachute, and as shown in Figure 5, parachute is built in landing pack 24, falls umbrella
Packet 24 is located at the bottom middle position of docking cavity 21, and certainly, its pulling force should cross the weight in delivery storehouse 2 to parachute after deployment
The heart, to guarantee the landing of delivery 2 safety and steady of storehouse.
It is designed so that docking mechanism is combined into one with umbrella storehouse, without other individually designed umbrella chamber structure, not only improves
The overall aesthetics of carrier vehicle, so that the overall weight of carrier vehicle and energy consumption decline.
Since dock 11 needs to be embedded into the inside of docking cavity 21, the shape of dock 11 should be with butt cavity
The cross sectional shape of 21 inner cavity of body is consistent, and in the present embodiment, the cross section for docking the internal cavities of cavity 21 is in rectangle, such as Fig. 1-7
Shown in, therefore the cross section of dock 11 is also in rectangle；Further, also in the inner wall of docking cavity 21 in the present embodiment
Upper rotation is provided with cover board 22, and when parachute is in receiving state, cover board 22 can be covered parachute, is made with playing protection
With, and during parachute flicks, cover board 22 can rotate under the impact force of parachute again, guarantee that parachute can be normal
Expansion.
Cover board 22 may include a fan or more fans, and in one embodiment, cover board 22 specifically includes two, and two lids
Plate 22 is symmetricly set on two opposite inner walls of docking cavity 21 by shaft, so that clamshell doors form is formed, such as Fig. 5 and figure
Shown in 7.
When needing to open, the extractor parachute in parachute starts pop-up, and opens cover board 22, by guiding wire saws main chute to beat
It opens.
Further, (1 bottom of aircraft body is preferably arranged in also in aircraft body 1 in the embodiment of the present invention
The surrounding in portion) it is provided with retro-rocket or gas ejector, liquid or solid fuel can be used in retro-rocket, and gas ejector can
With use nozzle arrangements injection compressed gas, the thrust direction of retro-rocket and gas ejector should be upward, to dock
When disengaging aircraft body 1 and delivery storehouse 2 can be detached from rapidly for mechanism, forms safety between aircraft body 1 and delivery storehouse 2
Parachute-opening distance, realize normal parachute-opening.
Extending and retracting for telescopic locking protrusion 23 can be carried out automatically controlling by controller, for example, controller can root
Judge that aircraft body is in normal flight according to information detected by the detection devices such as attitude transducer, acceleration transducer
State, controller makes docking mechanism be in locking state at this time, after carrier vehicle lands safely, can pass through automatic or manual
Mode controls telescopic locking protrusion 23 and retracts；When the state of flight of carrier vehicle is abnormal, the either energy that accelerates to fall supplies
When insufficient, energy resource system being answered to collapse, controller controls telescopic locking protrusion 23 and retracts, so that docking mechanism is in disengagement shape
State；It is, of course, also possible to control button be designed in delivery storehouse 2 or aircraft body 1, in emergency situations, to pass through control
The telescopic locking protrusion 23 of button manual control retracts, and makes to deliver storehouse 2 and aircraft body 23 is detached from, and guarantees 2 safety of delivery storehouse
Landing.
In the present embodiment, it is additionally provided with attitude transducer in aircraft body 1, the attitude transducer is for detecting flight
Angle between device main body 1 and horizontal plane, the angle are known as inclination angle, when the inclination angle is more than preset value, then show delivery flight
There are falling risks for device, can control telescopic locking protrusion 23 by controller at this time and retract, so that delivery storehouse 2 and aircraft master
Body 1 is detached from, and guarantees the safe falling in delivery storehouse.
Further, it is additionally provided with acceleration transducer in aircraft body 1, in the delivery that acceleration transducer detects
The whereabouts acceleration of aircraft is close to or up to predetermined acceleration (usually using acceleration of gravity as a threshold value model of reference
Enclose) when, controller controls telescopic locking protrusion 23 and retracts, so that delivery storehouse 2 and aircraft body 1 are detached from.
In addition to this, also settable energy monitoring module, so that the energy supply situation to aircraft body 1 is supervised
It surveys, when energy monitoring module detects that energy supply reaches default energy limit value, controller controls locking protrusion and retracts, so that
It delivers storehouse and aircraft body 1 is detached from, if being provided with warning device in delivery storehouse, controller also controls warning device progress at this time
The signals such as sound, photoelectricity are alarmed, and to prompt the personnel in delivery storehouse to carry out emergency operation, realize delivery storehouse and aircraft master
The disengaging of body 1.
In carrier vehicle disclosed in above-described embodiment, aircraft body 1 includes but is not limited to propeller type flight
Device and culvert type aircraft.
Each embodiment in this specification is described in a progressive manner, the highlights of each of the examples are with it is other
The difference of embodiment, the same or similar parts in each embodiment may refer to each other.
The foregoing description of the disclosed embodiments enables those skilled in the art to implement or use the present invention.
Various modifications to these embodiments will be readily apparent to those skilled in the art, as defined herein
General Principle can be realized in other embodiments without departing from the spirit or scope of the present invention.Therefore, of the invention
It is not intended to be limited to the embodiments shown herein, and is to fit to and the principles and novel features disclosed herein phase one
The widest scope of cause.
Claims (12)
1. a kind of carrier vehicle, which is characterized in that including the aircraft body (1) for providing lift, and be connected to described
In aircraft body (1) and provide the delivery storehouse (2) of delivery function, wherein
The aircraft body (1) is connected with the delivery storehouse (2) by docking mechanism, is in locking shape in the docking mechanism
When state, the delivery storehouse (2) is linked together with the aircraft body (1)；When the docking mechanism is in disengaged condition, institute
It states delivery storehouse (2) and the aircraft body (1) is detached from；
Parachute is provided on the delivery storehouse (2).
2. carrier vehicle as described in claim 1, which is characterized in that be provided at the top of the delivery storehouse (2) hollow
It docks cavity (21), the bottom of the aircraft body (1) is provided with the dock that can be embedded in docking cavity (21)
(11), the docking cavity (21) and the dock (11) are provided with active lock piece on any one, in addition set in one
It is equipped with the lock groove (12) being adapted to the active lock piece.
3. carrier vehicle as described in claim 1, which is characterized in that during the bottom of the aircraft body (1) is provided with
Empty docking cavity (21), it is described to deliver the dock for being provided with and being embedded in docking cavity (21) at the top of storehouse (2)
(11), the docking cavity (21) and the dock (11) are provided with active lock piece on any one, in addition set in one
It is equipped with the lock groove (12) being adapted to the active lock piece.
4. carrier vehicle as claimed in claim 2 or claim 3, which is characterized in that the active lock piece is that telescopic locking is convex
It rises (23).
5. carrier vehicle as claimed in claim 4, which is characterized in that the telescopic locking raised (23) is along described right
Connect the continuous strip projected parts of the circumferentially extending of cavity (21) or the dock (11).
6. carrier vehicle as claimed in claim 4, which is characterized in that the telescopic locking raised (23) include it is multiple,
And the telescopic locking raised (23) is along docking cavity (21) or the circumferential intermittent arrangement of the dock (11).
7. carrier vehicle as claimed in claim 2, which is characterized in that the docking cavity (21) also serves as described for accommodating
The umbrella storehouse of parachute, and the parachute is built in the bottom of docking cavity (21).
8. carrier vehicle as claimed in claim 7, which is characterized in that it is described docking cavity (21) internal cavities it is transversal
Face is in rectangle, and also rotation is provided with the cover board (22) for covering the parachute on the inner wall of docking cavity (21).
9. carrier vehicle as claimed in claim 8, which is characterized in that the cover board (22) includes two, and described in two
Cover board (22) is symmetricly set on two opposite inner walls of docking cavity (21) by shaft.
10. carrier vehicle as described in any one of claims 1-9, which is characterized in that further include being arranged in the flight
The retro-rocket or gas ejector of upward thrust are provided in device main body (1) and for the aircraft body (1).
11. the carrier vehicle as described in claim 4-9 any one, which is characterized in that further include:
Setting is used to control the telescopic locking protrusion on the aircraft body (1) or on the delivery storehouse (2)
(23) controller extended and retracted；
Attitude transducer in the aircraft body (1) is set, and detects the aircraft in the attitude transducer
When the inclination angle of main body (1) is more than preset value, the controller control telescopic locking raised (23) is retracted, so that the fortune
Storehouse (2) and the aircraft body (1) are carried to be detached from.
12. carrier vehicle as claimed in claim 11, which is characterized in that be additionally provided with and add in the aircraft body (1)
Velocity sensor, and detect that the whereabouts acceleration of the carrier vehicle reaches predetermined acceleration in the acceleration transducer
When, the controller control telescopic locking raised (23) retracts, so that the delivery storehouse (2) and the aircraft body
(1) it is detached from.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910123997.2A CN109703759A (en) | 2019-02-19 | 2019-02-19 | A kind of carrier vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910123997.2A CN109703759A (en) | 2019-02-19 | 2019-02-19 | A kind of carrier vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109703759A true CN109703759A (en) | 2019-05-03 |
Family
ID=66264688
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910123997.2A Pending CN109703759A (en) | 2019-02-19 | 2019-02-19 | A kind of carrier vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109703759A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111891373A (en) * | 2020-07-27 | 2020-11-06 | 淮阴工学院 | Multi-position split type land air-berthing unmanned aerial vehicle |
| CN114072334A (en) * | 2019-07-09 | 2022-02-18 | 杰姆·卡拉科 | Bearing device |
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| CN206654190U (en) * | 2017-03-17 | 2017-11-21 | 河南科技大学 | City distribution pattern multi-rotor aerocraft with self-protecting device |
| CN108313313A (en) * | 2018-01-26 | 2018-07-24 | 重庆邮电大学 | Unmanned plane failure response system |
| CN109229352A (en) * | 2018-10-30 | 2019-01-18 | 佛山市神风航空科技有限公司 | A kind of more rotor manned aircraft |
| CN209795831U (en) * | 2019-02-19 | 2019-12-17 | 酷黑科技（北京）有限公司 | Carrying aircraft |
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2019
- 2019-02-19 CN CN201910123997.2A patent/CN109703759A/en active Pending
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6682017B1 (en) * | 2000-03-31 | 2004-01-27 | Pavlos Giannakopoulos | Aircraft with a detachable passenger escape cabin and an aircraft with airbags |
| CN107108038A (en) * | 2016-12-01 | 2017-08-29 | 深圳市大疆创新科技有限公司 | A kind of device for controlling forced landing, method, equipment |
| CN206654190U (en) * | 2017-03-17 | 2017-11-21 | 河南科技大学 | City distribution pattern multi-rotor aerocraft with self-protecting device |
| CN108313313A (en) * | 2018-01-26 | 2018-07-24 | 重庆邮电大学 | Unmanned plane failure response system |
| CN109229352A (en) * | 2018-10-30 | 2019-01-18 | 佛山市神风航空科技有限公司 | A kind of more rotor manned aircraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114072334A (en) * | 2019-07-09 | 2022-02-18 | 杰姆·卡拉科 | Bearing device |
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