CN107600393A - The collapsible undercarriage and its foldable structure of balloon borne near space solar energy unmanned plane - Google Patents

The collapsible undercarriage and its foldable structure of balloon borne near space solar energy unmanned plane Download PDF

Info

Publication number
CN107600393A
CN107600393A CN201710849958.1A CN201710849958A CN107600393A CN 107600393 A CN107600393 A CN 107600393A CN 201710849958 A CN201710849958 A CN 201710849958A CN 107600393 A CN107600393 A CN 107600393A
Authority
CN
China
Prior art keywords
sleeve
undercarriage
wheel
spring
attachment structure
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN201710849958.1A
Other languages
Chinese (zh)
Inventor
赵帅
马晓平
周礼洋
沈思颖
刘冠宇
王立新
凡洪林
尚柏荣
应培
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Institute of Engineering Thermophysics of CAS
Original Assignee
Institute of Engineering Thermophysics of CAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Institute of Engineering Thermophysics of CAS filed Critical Institute of Engineering Thermophysics of CAS
Priority to CN201710849958.1A priority Critical patent/CN107600393A/en
Publication of CN107600393A publication Critical patent/CN107600393A/en
Pending legal-status Critical Current

Links

Landscapes

  • Tents Or Canopies (AREA)

Abstract

The invention discloses a kind of collapsible undercarriage of lightweight of balloon borne near space solar energy unmanned plane and its foldable structure, collapsible undercarriage includes the parts such as top and bottom branch sleeve, sliding sleeve, support bar, connecting spring, wheel branch sleeve, wheel mounting bracket, wheel.Before balloon borne lift-off, undercarriage can be folded into by the position for adjusting sliding sleeve in fuselage, wheel is then fixed on by fuselage interior by high-strength connecting rope.High-strength connecting rope is cut off with cutter when landing, undercarriage is rotated to vertical direction in the presence of self gravitation.Then in the presence of connecting spring and self gravitation, sliding sleeve can slide into ad-hoc location, and now undercarriage is locked, can be landed.The present invention solves the problems, such as resistance increase caused by solar energy unmanned plane fixed landing gear, while has the advantages that simple in construction, manufacturing cost is low, in light weight, working service is convenient relative to traditional retractable undercarriage again.

Description

The collapsible undercarriage and its foldable structure of balloon borne near space solar energy unmanned plane
Technical field
The present invention relates near space solar energy unmanned air vehicle technique field, and in particular to a kind of balloon borne near space solar energy The collapsible undercarriage of lightweight and its foldable structure of unmanned plane.
Background technology
Near space solar energy unmanned plane typically uses more than 90% composite to be used simultaneously to mitigate construction weight High aspect ratio wing structure increases the laying area of solar panel.At present due to the limitation of energy resource system, near space The difficulty that solar energy unmanned plane directly flies near space is larger.It can use and near space is arrived into the balloon borne lift-off of unmanned plane, so An automatic turn flat winged mode of launching makes unmanned plane adjacent to space and autonomous flight afterwards.
Due near space solar energy unmanned plane typically using distributed propeller as power, and near space region The density of interior air is extremely low, and this causes the less efficient of propeller, and the thrust provided is limited, therefore resistance when reducing its flight Power is particularly significant.Current near space solar energy unmanned plane mainly uses fixed landing gear structure, the landing gear structure meeting Cause the resistance of full machine to increase by 5% or so, this can cause larger burden to the energy and dynamical system of unmanned plane.And conventional Retractable landing gear is complicated, manufacturing cost is high, working service is inconvenient and can greatly increase the construction weight of aircraft.
The content of the invention
(1) technical problems to be solved
In view of this, a kind of lightweight of the near space solar energy unmanned plane of balloon borne lift-off of present invention offer is collapsible rises and falls Frame and its foldable structure, to solve the above problems.
(2) technical scheme
A kind of foldable structure of balloon borne near space solar energy unmanned plane undercarriage, the foldable structure can be in locking shapes Changed between state and folded state, including fold unit and sliding sleeve;It is described folding unit include the first attachment structure and With the second attachment structure of the first attachment structure rotation connection, rotatable connecting portion between the two is rotation space;Slip cap Jacket casing, which is located at, to be folded outside unit, and can be slided up and down along unit is folded;When in a locked condition, the first attachment structure, Second attachment structure is coaxial with sliding sleeve, and sliding sleeve is located at rotation space, is connected with limiting the first attachment structure and second Mutual rotation between binding structure;When positioned in the folded position, the first attachment structure has angle with the second attachment structure shape, sliding Moving sleeve is located above rotation space.
In some exemplary embodiments of the present invention, in addition to spring;The outer surface of second attachment structure is set There are the first spring mountings;The outer surface of the sliding sleeve is provided with second spring fixture;The spring is connected to first Between spring mountings and second spring fixture, for pulling sliding sleeve slide downward, when in a locked condition, spring In extended state, for preventing the undercarriage instantaneous sliding motion sleeve that contacts to earth from popping up and cause lockout failure.
In some exemplary embodiments of the present invention, in addition to supporting construction and spring;Supporting construction connection the Two attachment structures, the outer surface of supporting construction are provided with the first spring mountings;The outer surface of the sliding sleeve is provided with Two spring mountings;The spring is connected between the first spring mountings and second spring fixture, for pulling slip cap Cylinder slide downward;When in a locked condition, spring is in extended state, for prevent undercarriage contact to earth instantaneous sliding motion sleeve to On upspring and cause lockout failure.
In some exemplary embodiments of the present invention, the second attachment structure outer surface is provided with positive stop lug boss, uses In limit slippage sleeve slide downward, when foldable structure is in the lock state, sliding sleeve is resisted against on positive stop lug boss.
In some exemplary embodiments of the present invention, first attachment structure includes the first sleeve, the first set Cylinder one end is provided with the first rotating connector, and the other end is fixedly connected with unmanned aerial vehicle body;Second attachment structure includes the Two sleeves, described second sleeve one end are provided with the second rotating connector;First rotating connector and the second rotation connection Part is hinged.
In some exemplary embodiments of the present invention, the supporting construction outer surface is provided with snap ring, and the first spring is consolidated Determine part to be arranged on snap ring;The quantity of first spring mountings and second spring fixture is two, and first spring is consolidated Determine part and second spring fixture is oppositely arranged two-by-two.
A kind of collapsible undercarriage of lightweight of balloon borne near space solar energy unmanned plane, the collapsible undercarriage can be Changed between lock-out state and folded state, including above-mentioned foldable structure;Also include wheel structure, knot is connected with described second Structure is fixedly connected.
In some exemplary embodiments of the present invention, the wheel structure includes wheel, wheel mounting bracket and wheel Branch sleeve;The wheel connects wheel mounting bracket;Described wheel branch sleeve one end connects wheel mounting bracket, the other end Second attachment structure is connected by supporting construction;The wheel branch sleeve outer surface is provided with interface, and interface is connected with connection Rope, for wheel structure to be connected with the unmanned aerial vehicle body;Cutter is provided with the connecting rope, for cutting off connection Rope.
In some exemplary embodiments of the present invention, when the collapsible undercarriage is in folded state, the folding Stack structure is in folded state, and wheel structure is connected by connecting rope with unmanned aerial vehicle body;At the collapsible undercarriage When lock-out state, the foldable structure is in the lock state, and vertical direction is dropped down onto under the wheel structure.
The present invention some exemplary embodiments in, the wheel branch sleeve, supporting construction, the first attachment structure, Second attachment structure and sliding sleeve use thin-wall construction;The support bar uses full carbon fibre composite;The wheel Mounting bracket digs lightening hole.
(3) beneficial effect
The present invention solves the problems, such as resistance increase caused by solar energy unmanned plane fixed landing gear, at the same again relative to Traditional retractable undercarriage has the advantages that simple in construction, manufacturing cost is low, in light weight, working service is convenient.
Brief description of the drawings
Fig. 1 is that the foldable structure of the embodiment of the present invention is in the structural representation of folded state.
Fig. 2 is the structural representation that the foldable structure of the embodiment of the present invention is in the lock state.
Fig. 3 is the sliding sleeve structural representation of the embodiment of the present invention.
Fig. 4 is the structural representation of the floor structure of the embodiment of the present invention.
Fig. 5 is the structural representation of the top attachment structure of the embodiment of the present invention.
Fig. 6 is that the structure that the balloon borne near space solar energy unmanned plane undercarriage of the embodiment of the present invention is in folded state is shown It is intended to.
Fig. 7 is that the structure that the balloon borne near space solar energy unmanned plane undercarriage of the embodiment of the present invention is in the lock state is shown It is intended to.
Fig. 8 is the structural representation of the turbine branch sleeve of the embodiment of the present invention.
Embodiment
For the object, technical solutions and advantages of the present invention are more clearly understood, below in conjunction with specific embodiment, and reference Accompanying drawing, the present invention is described in further detail.
One embodiment of the invention provides a kind of foldable structure of balloon borne near space solar energy unmanned plane undercarriage, folds knot Structure can be changed between lock-out state and folded state, if Fig. 1 is that foldable structure be in the structural representation of folded state, scheme 2 be the structural representation that foldable structure is in the lock state, and as depicted in figs. 1 and 2, foldable structure includes folding unit and slip Sleeve 12.
Folding unit includes top attachment structure 11 (the first attachment structure) and is rotatablely connected with top attachment structure 11 Floor structure 15 (the second attachment structure), coupling part between the two is rotation space, and sliding sleeve 12 is set in Fold outside unit, and can be slided up and down along unit is folded.
When foldable structure is in folded state, as shown in figure 1, top attachment structure 11 is formed with floor structure 15 One angle, sliding sleeve 12 are located above rotation space;When foldable structure is in the lock state, as shown in Fig. 2 top connects Structure 11, floor structure 15 are coaxial with sliding sleeve 12, and sliding sleeve 12 is located at rotation space, is enclosed on outside rotation space Portion, with the mutual rotation between limitation top attachment structure 11 and floor structure 15.
In certain embodiments, foldable structure also includes support bar 17 (supporting construction) and spring 14, and support bar 17 connects Floor structure 15, the outer surface of support bar 17 are provided with snap ring 16, and sliding sleeve 12 is carried out with snap ring 16 by spring 14 Connection, snap ring both sides are provided with two snap ring auricles (the first spring mountings).It is illustrated in figure 3 sliding sleeve structural representation Figure, the outer surface both sides of sliding sleeve 12 are provided with two sliding sleeve auricles (second spring fixture), two spring connections point Not between two snap ring auricles and two sliding sleeve auricles, for pulling sliding sleeve slide downward.At foldable structure When lock-out state, spring tension is larger, in extended state, for preventing the undercarriage instantaneous sliding motion sleeve that contacts to earth from popping up Cause lockout failure.When foldable structure is in folded state, the pulling force of spring is smaller.
In certain embodiments, snap ring and the first spring mountings may also be arranged on the outer surface of the second attachment structure 15.
As shown in figure 4, including circular sleeve part, sleeve one end is connected floor structure 15 with support bar 17, another End is provided with the second rotating connector, and in bottom, the circular sleeve outer surface of branch sleeve 15 is additionally provided with annular stop boss.
Top branch sleeve 11 is as shown in figure 5, including circular sleeve part, sleeve one end is provided with the first rotation connection Part, the other end are fixed by screw with the spare interface on unmanned aerial vehicle body reinforcing frame and are attached.
Top branch sleeve 11 is attached with bottom branch sleeve 15 in a manner of it can mutually rotate, and is logical in this implementation Cross pin 13 to be hinged the first rotating connector and the second rotating connector, turn when pin 13 folds as undercarriage Axle, bottom branch sleeve 15 can be rotated centered on pin 13 relative to top branch sleeve 11, in the present embodiment, The rotating range of bottom branch sleeve 15 is only limitted to the side of top branch sleeve 11, be provided with the top of the second rotating connector flat End face, rotated for limiting bottom branch sleeve 15 towards opposite side.Top branch sleeve 11 and the composition folding of bottom branch sleeve 15 Folded unit, coupling part (the first rotating connector, the second rotating connector and pin 13) composition rotation space between the two.
Sliding sleeve 12, which is set in, to be folded outside unit, and can be slided in the specific lower regions for folding unit, is slided Sleeve 12 plays a part of locked foldable structure.The annular stop boss that wherein outer surface of bottom branch sleeve 15 is set is used to limit The slide downward of sliding sleeve 12 processed.Sliding sleeve is downwards slidably at the annular stop boss of bottom branch sleeve 15, now Rotation space is located inside sliding sleeve 12, with the relative rotation of limitation top branch sleeve 11 and bottom branch sleeve 15;It is sliding Moving sleeve slidably to rotation space top, is enclosed on the outside of top attachment structure 11, exposes rotation space, connect bottom upwards Female connector cylinder 15 can be rotated relative to top branch sleeve 11.
Another embodiment of the present invention provides a kind of collapsible undercarriage knot of lightweight of balloon borne near space solar energy unmanned plane Structure, collapsible landing gear structure mainly has two states, folded state and lock-out state, and can turn between the two states Changing, the landing gear structure sets balloon borne near space below the fuselage of solar energy unmanned plane, when solar energy unmanned plane goes up to the air, Landing gear structure is in folded state, and in solar energy UAV Landing, landing gear structure is in the lock state, if Fig. 6 is this The structural representation of the collapsible undercarriage folded state of lightweight of the balloon borne near space solar energy unmanned plane of inventive embodiments, such as Fig. 7 be the embodiment of the present invention undercarriage lock-out state structural representation, balloon borne near space solar energy unmanned plane it is light The collapsible landing gear structure of matter includes wheel structure and above-mentioned foldable structure, specifically includes:Top attachment structure 21, bottom Attachment structure 25, sliding sleeve 22, support bar 27, snap ring 26, connecting spring 24, wheel structure, high-strength connecting rope 212 and cutting Device 211;
The one end of support bar 27 connects wheel structure, other end connection floor structure 25, and the appearance face ring of support bar 27 is set There is snap ring 26, snap ring 26 is fixed on support bar by way of splicing.Wheel structure includes wheel 210, wheel mounting bracket 29 and wheel branch sleeve 28, wheel 210 be connected with wheel mounting bracket 29, wheel mounting bracket 29 and wheel branch sleeve 28 Connection, the structure of wheel branch sleeve 28 is as shown in figure 8, including circular sleeve, and sleeve one end is connected with support bar 27, the other end Connecting plate is provided with, connecting plate is fixedly connected by bolt with wheel mounting bracket 29, is additionally provided with sleeve outer surface Auricle interface, before balloon borne lift-off, wheel branch sleeve 28 is connect with being reserved in unmanned aerial vehicle body by high-strength connecting rope 212 Mouth is attached fixation, the high-strength one end attachment lug interface of connecting rope 12, one end connection unmanned aerial vehicle body, high-strength connecting rope 212 On be additionally provided with cutter 211, for cutting off high-strength connecting rope 212.Support bar 27 and floor structure 21, snap ring 26, wheel An entirety is fixedly connected into order to install and change by way of splicing between machine branch sleeve 28.Support bar 7 supports Bar uses thin-wall circular tube structure, and shaping is processed using full carbon fibre composite.
Top attachment structure is fixed by screw with the spare interface on unmanned aerial vehicle body reinforcing frame and is attached.
Top attachment structure 21 is attached with floor structure 25 in a manner of it can mutually rotate, and is logical in this implementation Cross pin 23 to be attached, pin 23 serves as rotating shaft when undercarriage folds, during floor structure 25 can be with pin 23 The heart is rotated relative to top attachment structure 21, so as to drive support bar and wheel structure while be rotated.
When undercarriage is in the lock state, as shown in fig. 7, foldable structure is also at lock-out state, sliding sleeve 22 and top Portion connecting structure 21 and floor structure 25 are coaxial, and sliding sleeve is snapped down at annular stop boss, the drawing of connecting spring 24 Power is larger, in extended state, so as to prevent the undercarriage instantaneous sliding motion sleeve 22 that contacts to earth from popping up and cause its locked failure. Vertical direction is dropped down onto under wheel structure.
When undercarriage is in folded state, as shown in fig. 6, foldable structure is also at folded state, slided on sliding sleeve Above folding space, floor structure 25 and the axis shape of top attachment structure 21 have angle, the pulling force of connecting spring 24 It is smaller.Wheel structure is connected by connecting rope with unmanned aerial vehicle body.
Before balloon borne lift-off, sliding sleeve 22 is reserved along the upward sliding of top attachment structure 21 folding space with Afterwards, undercarriage can be folded into fuselage;Folding can be by high-strength connecting rope 212 by wheel branch sleeve 28 after undercarriage Reserved auricle interface and unmanned aerial vehicle body spare interface be attached fixation.
In the front opening hatch door of solar energy UAV Landing, then cutter 211 is powered so as to by high-strength connecting rope 212 Cut-out, undercarriage wheel is carried out release under self gravitation effect and fall until rotating to vertical direction.
After undercarriage rotates to vertical direction, set at the top of first rotating connector of the one end of floor structure 25 Planar end surface be used to carrying out undercarriage spacing, prevent it from further rotating, the support bar 27 of undercarriage and top attachment structure Point-blank, sliding sleeve 22 understands the slide downward in the presence of its own gravity and connecting spring 24 to 21 axis, It will stop sliding when it slides into the positive stop lug boss opening position of polycrystalline substance 25, now undercarriage is in the lock state, can be with Landed.
The present invention uses main force support structure of the full carbon fibre composite thin-wall construction support bar as undercarriage, remaining Connector also all uses thin-wall construction, under conditions of intensity requirement is met, make undercarriage construction weight reduce 50% with On.
The wheel mounting bracket of the present invention is carrying out loss of weight under conditions of meeting intensity requirement by the way of lightening hole is dug.
There is above-described embodiment to understand that resistance caused by the present invention solves solar energy unmanned plane fixed landing gear is increased Problem, while have relative to traditional retractable undercarriage that simple in construction, manufacturing cost is low, in light weight, working service is convenient again The advantages that.
It should also be noted that, the direction term mentioned in embodiment, for example, " on ", " under ", "front", "rear", " left side ", " right side " etc., only it is the direction of refer to the attached drawing, is not used for limiting the scope of the invention.Through accompanying drawing, identical element by Same or like reference represents.When the understanding of the present invention may be caused to cause to obscure, conventional structure will be omitted Or construction.
And the shape and size of each part do not reflect actual size and ratio in figure, and only illustrate the embodiment of the present invention Content.In addition, in the claims, any reference symbol between bracket should not be configured to the limit to claim System.
Furthermore word "comprising" does not exclude the presence of element or step not listed in the claims.Before element Word "a" or "an" does not exclude the presence of multiple such elements.
In addition, unless specifically described or the step of must sequentially occur, the order of above-mentioned steps, which has no, is limited to above institute Row, and can change or rearrange according to required design.And above-described embodiment can based on design and reliability consideration, that This mix and match uses using or with other embodiment mix and match, i.e., the technical characteristic in different embodiments can be with independent assortment Form more embodiments.
Similarly, it will be appreciated that in order to simplify the present invention and help to understand one or more of each inventive aspect, Above in the description to the exemplary embodiment of the present invention, each feature of the invention is grouped together into single implementation sometimes In example, figure or descriptions thereof.However, the method for the invention should be construed to reflect following intention:I.e. required guarantor The application claims of shield features more more than the feature being expressly recited in each claim.It is more precisely, such as following Claims reflect as, inventive aspect is less than all features of single embodiment above invented.Therefore, Thus the claims for following embodiment are expressly incorporated in the embodiment, wherein each claim is in itself Separate embodiments all as the present invention.
Particular embodiments described above, the purpose of the present invention, technical scheme and beneficial effect are carried out further in detail Describe in detail bright, it should be understood that the foregoing is only the present invention specific embodiment, be not intended to limit the invention, it is all Within the spirit and principles in the present invention, any modification, equivalent substitution and improvements done etc., the protection of the present invention should be included in Within the scope of.

Claims (10)

1. a kind of foldable structure of balloon borne near space solar energy unmanned plane undercarriage, the foldable structure can be in lock-out state Changed between folded state, including fold unit and sliding sleeve;
The unit that folds includes the first attachment structure and the second attachment structure with the rotation connection of the first attachment structure, both Between rotatable connecting portion be rotation space;
Sliding sleeve, which is set in, to be folded outside unit, and can be slided up and down along unit is folded;
When in a locked condition, the first attachment structure, the second attachment structure are coaxial with sliding sleeve, and sliding sleeve is positioned at rotation At space, to limit the mutual rotation between the first attachment structure and the second attachment structure;
When positioned in the folded position, the first attachment structure has angle with the second attachment structure shape, and sliding sleeve is empty positioned at rotating Between top.
2. foldable structure as claimed in claim 1, wherein, in addition to spring;
The outer surface of second attachment structure is provided with the first spring mountings;
The outer surface of the sliding sleeve is provided with second spring fixture;
The spring is connected between the first spring mountings and second spring fixture, for pulling sliding sleeve to downslide Dynamic, when in a locked condition, spring is in extended state, for preventing the undercarriage instantaneous sliding motion sleeve that contacts to earth from popping up and make Into lockout failure.
3. foldable structure as claimed in claim 1, wherein, in addition to supporting construction and spring;
The supporting construction connects the second attachment structure, and the outer surface of supporting construction is provided with the first spring mountings;
The outer surface of the sliding sleeve is provided with second spring fixture;
The spring is connected between the first spring mountings and second spring fixture, for pulling sliding sleeve to downslide It is dynamic;
When in a locked condition, spring is in extended state, for preventing the undercarriage instantaneous sliding motion sleeve that contacts to earth from popping up Cause lockout failure.
4. foldable structure as claimed any one in claims 1 to 3, wherein, the second attachment structure outer surface is provided with Positive stop lug boss, for limit slippage sleeve slide downward, when foldable structure is in the lock state, sliding sleeve is resisted against spacing On boss.
5. foldable structure as claimed any one in claims 1 to 3, wherein,
First attachment structure includes the first sleeve, and described first sleeve one end is provided with the first rotating connector, the other end It is fixedly connected with unmanned aerial vehicle body;
Second attachment structure includes second sleeve, and described second sleeve one end is provided with the second rotating connector;
First rotating connector and the second rotating connector are hinged.
6. foldable structure as claimed in claim 3, wherein,
The supporting construction outer surface is provided with snap ring, and the first spring mountings are arranged on snap ring;
The quantity of first spring mountings and second spring fixture is two, first spring mountings and second spring Fixture is oppositely arranged two-by-two.
7. a kind of collapsible undercarriage of lightweight of balloon borne near space solar energy unmanned plane, the collapsible undercarriage can locked Determine to change between state and folded state, including the foldable structure as any one of claim 1-6;
Also include wheel structure, be fixedly connected with second attachment structure.
8. collapsible undercarriage as claimed in claim 7, wherein, the wheel structure include wheel, wheel mounting bracket and Wheel branch sleeve;
The wheel connects wheel mounting bracket;
Described wheel branch sleeve one end connects wheel mounting bracket, and the other end connects the second attachment structure by supporting construction;
The wheel branch sleeve outer surface is provided with interface, and interface is connected with connecting rope, for by wheel structure and the nothing Man-machine fuselage connection;
Cutter is provided with the connecting rope, for cutting off connecting rope.
9. collapsible undercarriage as claimed in claim 7 or 8, wherein,
When the collapsible undercarriage is in folded state, the foldable structure is in folded state, and wheel structure passes through Connecting rope is connected with unmanned aerial vehicle body;
When the collapsible undercarriage is in the lock state, the foldable structure is in the lock state, under the wheel structure Drop down onto vertical direction.
10. collapsible undercarriage as claimed in claim 7 or 8, wherein,
The wheel branch sleeve, supporting construction, the first attachment structure, the second attachment structure and sliding sleeve use thin-walled knot Structure;
The support bar uses full carbon fibre composite;
The wheel mounting bracket digs lightening hole.
CN201710849958.1A 2017-09-19 2017-09-19 The collapsible undercarriage and its foldable structure of balloon borne near space solar energy unmanned plane Pending CN107600393A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201710849958.1A CN107600393A (en) 2017-09-19 2017-09-19 The collapsible undercarriage and its foldable structure of balloon borne near space solar energy unmanned plane

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201710849958.1A CN107600393A (en) 2017-09-19 2017-09-19 The collapsible undercarriage and its foldable structure of balloon borne near space solar energy unmanned plane

Publications (1)

Publication Number Publication Date
CN107600393A true CN107600393A (en) 2018-01-19

Family

ID=61061289

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201710849958.1A Pending CN107600393A (en) 2017-09-19 2017-09-19 The collapsible undercarriage and its foldable structure of balloon borne near space solar energy unmanned plane

Country Status (1)

Country Link
CN (1) CN107600393A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108482699A (en) * 2018-05-31 2018-09-04 深圳市易飞方达科技有限公司 Unmanned plane launching tube
CN110001935A (en) * 2019-05-07 2019-07-12 广州中国科学院沈阳自动化研究所分所 A kind of unmanned plane is from active platform landing auxiliary device
CN110844051A (en) * 2019-11-29 2020-02-28 夏国富 Unmanned aerial vehicle system of rising and falling
CN112606971A (en) * 2020-12-11 2021-04-06 上海海事大学 Unmanned on-board sensor carrying device capable of being automatically retracted and released

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2075448A (en) * 1980-04-30 1981-11-18 British Aerospace Aircraft undercarriage unit
CN2402596Y (en) * 1999-09-01 2000-10-25 张新民 Mechanical landing gear control device
DE102009046117A1 (en) * 2009-10-28 2011-05-19 Thomas Fischer Retractable landing gear for airplane, has actuating device including retractable-pull rope for retracting landing gear legs, where pull rope is locked in extending position of legs and retracted in retracting position of legs
CN203876981U (en) * 2014-05-16 2014-10-15 杜秀堂 Folding and unfolding device for aircraft landing gear
CN205311894U (en) * 2015-12-02 2016-06-15 上海云犀智能系统有限公司 Unmanned aerial vehicle undercarriage
CN205770129U (en) * 2016-06-07 2016-12-07 比亚迪股份有限公司 Unmanned plane undercarriage fold mechanism and unmanned plane
CN205872447U (en) * 2016-08-10 2017-01-11 湖南博瑞通航航空技术有限公司 Many rotor unmanned aerial vehicle's undercarriage that can receive and release automatically
CN207466961U (en) * 2017-09-19 2018-06-08 中国科学院工程热物理研究所 The collapsible undercarriage and its foldable structure of balloon borne near space solar energy unmanned plane

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2075448A (en) * 1980-04-30 1981-11-18 British Aerospace Aircraft undercarriage unit
CN2402596Y (en) * 1999-09-01 2000-10-25 张新民 Mechanical landing gear control device
DE102009046117A1 (en) * 2009-10-28 2011-05-19 Thomas Fischer Retractable landing gear for airplane, has actuating device including retractable-pull rope for retracting landing gear legs, where pull rope is locked in extending position of legs and retracted in retracting position of legs
CN203876981U (en) * 2014-05-16 2014-10-15 杜秀堂 Folding and unfolding device for aircraft landing gear
CN205311894U (en) * 2015-12-02 2016-06-15 上海云犀智能系统有限公司 Unmanned aerial vehicle undercarriage
CN205770129U (en) * 2016-06-07 2016-12-07 比亚迪股份有限公司 Unmanned plane undercarriage fold mechanism and unmanned plane
CN205872447U (en) * 2016-08-10 2017-01-11 湖南博瑞通航航空技术有限公司 Many rotor unmanned aerial vehicle's undercarriage that can receive and release automatically
CN207466961U (en) * 2017-09-19 2018-06-08 中国科学院工程热物理研究所 The collapsible undercarriage and its foldable structure of balloon borne near space solar energy unmanned plane

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108482699A (en) * 2018-05-31 2018-09-04 深圳市易飞方达科技有限公司 Unmanned plane launching tube
CN108482699B (en) * 2018-05-31 2023-12-05 深圳市华讯方舟系统技术有限公司 Unmanned aerial vehicle transmitting cylinder
CN110001935A (en) * 2019-05-07 2019-07-12 广州中国科学院沈阳自动化研究所分所 A kind of unmanned plane is from active platform landing auxiliary device
CN110001935B (en) * 2019-05-07 2024-05-17 广州中国科学院沈阳自动化研究所分所 Unmanned aerial vehicle takes off and land auxiliary device from initiative platform
CN110844051A (en) * 2019-11-29 2020-02-28 夏国富 Unmanned aerial vehicle system of rising and falling
CN110844051B (en) * 2019-11-29 2021-04-23 夏国富 Unmanned aerial vehicle system of rising and falling
CN112606971A (en) * 2020-12-11 2021-04-06 上海海事大学 Unmanned on-board sensor carrying device capable of being automatically retracted and released

Similar Documents

Publication Publication Date Title
CN207466961U (en) The collapsible undercarriage and its foldable structure of balloon borne near space solar energy unmanned plane
US11273922B2 (en) Aerodynamically efficient lightweight vertical take-off and landing aircraft with pivoting rotors and box wing design
CN107600393A (en) The collapsible undercarriage and its foldable structure of balloon borne near space solar energy unmanned plane
US10414483B2 (en) Tiltrotor articulated wing extension
JP6630286B2 (en) Aerodynamically efficient lightweight vertical takeoff and landing aircraft with swirling rotor blades and contained rotor blades
US10005554B2 (en) Unmanned aerial vehicle
CN108674636B (en) Twin-engine quadrotor unmanned aerial vehicle and foot rest device thereof
CN207450249U (en) A kind of unmanned plane rotor pulp distance varying mechanism
CN103332293A (en) Tilting double-duct subminiature unmanned plane
CN110466750A (en) A kind of Portable vertical landing scouting monitoring unmanned plane
CN110712742A (en) Unmanned aerial vehicle with foldable fixed wings converted from controllable umbrella wings and conversion method
CN106347625A (en) Unmanned aerial vehicle linkage folding mechanism
CN110422339B (en) Method for assembling coaxial double-rotor unmanned aerial vehicle
CN110963029A (en) Method for forming large-wing bird-lift aircraft dragged by power of tilting rotor wing
CN210310861U (en) Automatic expansion undercarriage
US11155345B2 (en) Side folding and reforming linkage for landing gear
CN106628193A (en) High-reliability lightweight drag parachute connecting device
CN111086625A (en) Double-duct variable cabin tailstock type manned vertical take-off and landing fixed wing aircraft
US20160214711A1 (en) Non-loaded manual blade fold assembly
CN203638082U (en) Airfoil for unmanned annunciator and unmanned annunciator adopting same
CN213292702U (en) Vertical take-off and landing unmanned aerial vehicle
CN115195998B (en) Undercarriage winding and unwinding devices and aircraft
CN202879790U (en) Parafoil type unmanned aircraft
CN107128486A (en) A kind of change wheelbase unmanned plane mechanism for taking fire extinguishing emitter
RU2302976C1 (en) Light aircraft

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
RJ01 Rejection of invention patent application after publication
RJ01 Rejection of invention patent application after publication

Application publication date: 20180119