CN108284939A - A kind of folding ejection unmanned plane - Google Patents
A kind of folding ejection unmanned plane Download PDFInfo
- Publication number
- CN108284939A CN108284939A CN201810222919.3A CN201810222919A CN108284939A CN 108284939 A CN108284939 A CN 108284939A CN 201810222919 A CN201810222919 A CN 201810222919A CN 108284939 A CN108284939 A CN 108284939A
- Authority
- CN
- China
- Prior art keywords
- unmanned plane
- wing
- fold mechanism
- hook
- pedestal
- 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
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/04—Launching or towing gear
- B64F1/06—Launching or towing gear using catapults
Abstract
Needle of the present invention on wing and fuselage by devising new fold mechanism, expansion locking device, and foldable, saving loading space can not only be realized by providing one kind, additionally it is possible to the foldable ejection type unmanned plane suitable for the Automatic-expanding that ejection type takes off.The present invention can be applied not only to cross, I-shaped unmanned plane, is equally applicable to the other kinds of unmanned planes such as more rotor types, has a wide range of application；Unmanned plane can fold loading in non-working condition, save storage and loading space；Unmanned plane can be with Automatic-expanding wing when ejection type takes off, and is automatically locked when reaching fully expanded position, and wing is made to be fixed on required position, realizes application of the folding unmanned plane when ejection type takes off.Foldable ejection type unmanned aerial vehicle design provided by the present invention is exquisite, rationally, is easy to load and transport, can in catapult-assisted take-off Automatic-expanding, filled up the blank in this field.
Description
Technical field
The present invention relates to unmanned plane field more particularly to a kind of folding ejection unmanned planes of wing.
Background technology
Unmanned plane is the abbreviation of " UAV ", no matter studies in recent years or industrial applications are obtained for rapidly
Development, be widely used in the numerous areas such as military, agricultural, communication, photography.However, in the prior art it is most nobody
Machine structure design is unreasonable, since wing can not fold, causes structure size big, it has not been convenient to which storage and carrying such as tear component open
It is stored and is carried after unloading, and there are problems that needing repeatedly dismounting assembling, especially applied band in military field
Carry out big inconvenience.To overcome this disadvantage, also there are development and production folding unmanned plane in recent years, most of is that wing can
It folds, however this folding unmanned plane in the prior art has the following problems again：Although wing is foldable, only exist
It carries out folding when storing the unmanned plane and place to save space, also need to take out and be unfolded before use, with fixed wing aircraft phase
Than advantage is only that in storage time save space.It especially applies and receives many restrictions in military field, because in army
Using upper, unmanned plane is often used together with car launcher thing, uses ejection type to take off to complete the purpose of impact target, existing at present
Some folding unmanned planes cannot be satisfied this requirement, therefore it provides one kind can not only realize that foldable, saving loads sky
Between, additionally it is possible to suitable for the foldable ejection type unmanned plane for the Automatic-expanding that ejection type takes off, for unmanned plane including military affairs
The application in equal fields is of great significance.
Invention content
The present invention in view of the deficiencies in the prior art, by the structure design of aircraft, devises new on wing
Fold mechanism, expansion locking device, foldable, saving loading space can not only be realized by providing one kind, additionally it is possible to be suitable for
The foldable ejection type unmanned plane for the Automatic-expanding that ejection type takes off.
The present invention is achieved by the following technical solutions：
A kind of folding ejection unmanned plane, including fuselage, wing further include the fold mechanism being mounted on wing and embedding
Enter the pedestal in fuselage, wing is mounted on by fold mechanism on the pedestal of fuselage；
Location hole, elastomeric element fixed block are provided on fold mechanism；
It is provided with locating shaft on pedestal, is matched with the location hole on the fold mechanism installed on wing, fold mechanism is logical
Location hole is crossed to be hinged on the locating shaft of pedestal；It is additionally provided with positioning card column on pedestal, is used for one end of secure resilient member, bullet
The other end of property component is fixed on the elastomeric element fixed block of fold mechanism.
Further, it is additionally provided with wing retaining mechanism on the unmanned plane, includes the extension being arranged on fold mechanism
The hook card slot of corresponding position setting is linked up with when being fully deployed with wing on hook and pedestal.
Further, the pocket for the punch head of fold mechanism is provided through on the fold mechanism, hook setting exists
In pocket for the punch head, hook is hinged on pocket for the punch head by transfer rod and is rotated round transfer rod, in pocket for the punch head, links up with both sides and is additionally provided with the
One protrusion and the second protrusion, band one end of stumbling are arranged in the first protrusion, and the other end is arranged in the second protrusion, applies pressure to hook
Power.
Further, the band of stumbling is preferably elastomeric element.
Further, the hook structure is preferably：Tail portion is anchor-shaped, is risen to the bait respectively and lower hook 7, is rising to the bait and is hanging
It is additionally provided with center protrusion between the head of hook, forms a recess portion between center protrusion and head, recess portion bottom end to centre is prominent
A slope is formed between rising.
Further, the wing is symmetrical two, and the fold mechanism installed on two wings passes through it
On location hole be symmetrically hinged on the locating shaft of pedestal.
Further, the wing further includes two empennages.
The present invention has the following technical effects：
(1) cross, I-shaped unmanned plane is can be applied not only to, it is other kinds of to be equally applicable to more rotor types etc.
Unmanned plane has a wide range of application；
(2) unmanned plane can fold loading in non-working condition, storage and loading space be saved, especially in military affairs
Field is in application, can enhance fight capability；
(3) unmanned plane can be with Automatic-expanding wing when ejection type takes off, and is locked automatically when reaching fully expanded position
Extremely, so that wing is fixed on required position, application of the folding unmanned plane when ejection type takes off is realized, especially in military affairs
Field is in application, can enhance fight capability.
Description of the drawings
Fig. 1 is the structural schematic diagram of fold mechanism；
Fig. 2 is the structural schematic diagram of pedestal；
Fig. 3 is the structural schematic diagram of hook；
The vertical view of Fig. 4 is collapsible unmanned plane when being fully unfolded position fold mechanism part.
Wherein：1- fuselages, 2- wings, 3- fold mechanisms, 31- location holes, 32- elastomeric element fixed blocks, 33- pocket for the punch heads,
34- is linked up with, 35- transfer rods, the first protrusions of 36-, the second protrusions of 37-, and 38- stumbles band, 4- pedestals, 41- locating shafts, and 42- positions card column,
43- links up with card slot, 5- elastomeric elements, and 6- rises to the bait, hook under 7-, 8- center protrusions.
Specific embodiment
This part will make further explanation specific implementation mode in conjunction with attached drawing, it should be pointed out that our department
Specific implementation mode described in point is only used for the explanation and illustration present invention, is not construed as limiting the invention.
As shown in attached drawing 1,2,4, a kind of folding ejection unmanned plane, including fuselage 1, wing 2, it is characterised in that：Also
Include the pedestal 4 in the fold mechanism 3 and embedded fuselage 1 on wing 2, wing 2 is mounted on fuselage by fold mechanism 3
On 1 pedestal 4；The unmanned plane is " scholar " font unmanned plane, and wing is two main wings.Since main wing is symmetrical two,
The fold mechanism 3 installed on wing is symmetrically hinged on by location hole 31 thereon on the locating shaft 41 of pedestal 4.
Location hole 31 is provided on fold mechanism 3, the structure of elastomeric element fixed block 32, elastomeric element fixed block 32 is preferred
For：A slot is opened on fold mechanism 3, and a card is set in slot, elastomeric element 5 is caught on, to be fixed on elastic force apparatus
On fixed block 32.
It is provided with locating shaft 41 on pedestal 4, is matched with the location hole 31 on the fold mechanism 3 installed on wing 2, folds
Mechanism 3 is hinged on by location hole 31 on the locating shaft 41 of pedestal 4；Positioning card column 42 is additionally provided on pedestal 4, for fixing bullet
One end of property component 5, the other end of elastomeric element 5 are fixed on the elastomeric element fixed block 32 of fold mechanism 3, the positioning card column
42 be two, is symmetricly set on pedestal 4, the elastomeric element 5 being respectively used on fixed two, both sides wing.
It is additionally provided with wing retaining mechanism on unmanned plane, includes on the hook 34 being arranged on fold mechanism 3 and pedestal 4
The hook card slot 43 of 34 corresponding position settings is linked up with when being fully deployed with wing 2.Folding locking mechanism concrete structure is：It is rolling over
Pocket for the punch head 33 is provided in folded mechanism 3, the hook 34 is arranged in pocket for the punch head 33, and hook 34 is hinged on extension by transfer rod 35
It being rotated in hook groove 33 and round transfer rod 35, pocket for the punch head 33 is interior, 34 both sides of hook are additionally provided with the first protrusion 36 and the second protrusion 37,
The setting of 38 one end of band stumble in the first protrusion 36, the other end is arranged in the second protrusion 37, and band 38 of stumbling uses elastomeric element, to hanging
Hook 34 applies pressure.Its course of work is：When unmanned plane is in folded state income ejection case, elastomeric element 5 is by ejection case
Constraint it is in tension, unmanned plane wing by catapult-launching gear keep folded state.When unmanned plane is launched away, bullet
Property component 5 lose ejection case constraint, to elastomeric element fixed block 32 exert a force, to drive wing 2 be unfolded, when wing 2 rotate
When to fully expanded position, in the present embodiment, wing as wing exhibition in fully expanded position of " scholar " font unmanned plane
Open to it is vertical with fuselage when, since band 38 of stumbling selects elastomeric element, one end to be arranged in the first protrusion 36, other end setting is the
It is in tension in two protrusions 37, a downward pressure is applied to hook 34, hook 34 is by complete with wing 2 on pedestal 4
When full expansion when the hook card slot 43 of 34 corresponding position setting of hook, band 38 of stumbling will link up with 34 and press downward to hook card slot 43
In, the position corresponding with hook card slot 43 of hook 34 is provided with the hamulus into hook card slot 43, therefore tightly catches on extension
Hook card slot 43, to lock wing 2 in the position being fully deployed.
The structure of hook can match the various shapes realized and positioned for that can realize in the prior art and link up with card slot 43
Shape.As shown in Fig. 3, it is preferably in the present embodiment：It is it that hook 34 is mounted on one end in pocket for the punch head 33 by transfer rod 35
Head, the other end are its tail portion, and tail portion is anchor-shaped, rise to the bait respectively 6 and lower hook 7, are being risen to the bait between 6 and the head of hook 34 also
It is provided with center protrusion 8, forms a recess portion between center protrusion 8 and head, recess portion bottom end forms one between center protrusion 8
A slope.Its course of work is：When wing 2 is in folded state, band 38 of stumbling is pressed in be formed between center protrusion 8 and head
In recess portion, avoids band 38 of stumbling and arbitrarily slip；During wing 2 is unfolded, hook 34 slips over the hook card slot on pedestal 4
43, it is made of elastomeric element, in tension band 38 of stumbling applies downward pressure to hook 34, help is linked up with to be arranged on 34
Lower hook 7 slide into hook card slot 43 in, due to recess portion bottom end between center protrusion 8 be a slope so that stumbling band 38 can
Lower hook 7 is more successfully helped to enter to the hook pushing of card slot 43, thus using hook card slot 43 is caught on, and caught in lower hook 7
After linking up with card slot 43, if band 38 of stumbling skids off the recess portion, additionally it is possible to slide into fixed in the groove risen to the bait between 6 and center protrusion 8
Firmly, avoid stumbling the random slippage of band 38.Thus, which lower hook 7 catches on hook card slot 43 and hook tail portion can withstand on hook card
On slot 43, realize that the Automatic-expanding of foldable unmanned plane, be automatically locked work(in fully expanded position to lock wing 2
Can, it is applicable to the unmanned plane of catapult-assisted take-off.
Further include two empennages since the unmanned plane is " scholar " font unmanned plane, empennage passes through embedded afterbody
Pedestal 4 be mounted on fuselage on, mounting means, fold mechanism structure, base construction are identical as main wing.
Embodiment listed above is the case where present invention is suitable for " scholar " font unmanned plane, in fact, the present invention is equally suitable
For more rotor types etc., other can not constitute the limitation to its scope of application with the unmanned plane of folded wing, the present embodiment.
In conclusion the present invention can be applied not only to cross, I-shaped unmanned plane, it is equally applicable to more rotor types
Etc. other kinds of unmanned plane, have a wide range of application；Unmanned plane can fold loading in non-working condition, save storage and dress
Carry space；Unmanned plane can be with Automatic-expanding wing when ejection type takes off, and is automatically locked when reaching fully expanded position, makes
Wing is fixed on required position, realizes application of the folding unmanned plane when ejection type takes off.It is provided by the present invention can
It is exquisite, rationally to fold ejection type unmanned aerial vehicle design, is easy to load and transport, can in catapult-assisted take-off Automatic-expanding, be automatically locked,
The blank in this field is filled up.
Claims (9)
1. a kind of folding ejection unmanned plane, including fuselage (1), wing (2), it is characterised in that：Further include being mounted on wing
(2) pedestal (4) in fold mechanism (3) and embedded fuselage (1) on, wing (2) are mounted on fuselage by fold mechanism (3)
(1) on pedestal (4)；
Location hole (31), elastomeric element fixed block (32) are provided on the fold mechanism (3)；
It is provided on the pedestal (4) and location hole (31) matched locating shaft on the fold mechanism (3) on wing (2)
(41), fold mechanism (3) is hinged on by location hole (31) on the locating shaft (41) of pedestal (4)；Positioning is additionally provided on pedestal
Card column (42), is used for one end of secure resilient member (5), and the other end of elastomeric element (5) is fixed on the elasticity of fold mechanism (3)
On component fixed block (32).
2. a kind of folding ejection unmanned plane as described in claim 1, it is characterised in that：It is also set up on the unmanned plane
There is wing retaining mechanism, is included on the hook (34) being arranged on the fold mechanism (3) and pedestal (4) and wing (2)
The hook card slot (43) of (34) corresponding position setting is linked up with when being fully deployed.
3. a kind of folding ejection unmanned plane as claimed in claim 2, it is characterised in that：On the fold mechanism (3)
It is provided through the pocket for the punch head (33) of fold mechanism (3), the hook (34) is hinged on pocket for the punch head (33) by transfer rod (35)
It is interior and rotated round transfer rod (35), in pocket for the punch head (33), hook (34) both sides is additionally provided with the first protrusion (36) and the second protrusion
(37), band (38) one end is stumbled in the first protrusion (36), and the other end is mounted in the second protrusion (37), is applied to hook (34)
Plus-pressure.
4. a kind of folding ejection unmanned plane as claimed in claim 3, it is characterised in that：The band (38) of stumbling is elasticity
Component.
5. a kind of folding ejection unmanned plane as described in claim 3 or 4, it is characterised in that：The hook (34)
Tail portion is anchor-shaped, is risen to the bait respectively (6) and lower hook (7), is additionally provided between the head for rising to the bait (6) and linking up with (34) intermediate prominent
It rises (8), center protrusion (8) forms a recess portion between head, and one is formed between recess portion bottom end to center protrusion (8) tiltedly
Slope.
6. a kind of folding ejection unmanned plane as described in claim 1,2,3,4 is any, it is characterised in that：The wing
(2) it is symmetrical two, the fold mechanism (3) installed on two wings (2) is symmetrical by location hole (31) thereon
It is hinged on the locating shaft (41) of pedestal (4).
7. such as a kind of folding ejection unmanned plane as claimed in claim 5, it is characterised in that：The wing (2) is pair
Two claimed, the fold mechanism (3) installed on two wings (2) are symmetrically hinged on base by location hole (31) thereon
On the locating shaft (41) of seat (4).
8. a kind of folding ejection unmanned plane as claimed in claim 6, it is characterised in that：The wing (2) further includes
Two empennages.
9. a kind of folding ejection unmanned plane as claimed in claim 7, it is characterised in that：The wing (2) further includes
Two empennages.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810222919.3A CN108284939A (en) | 2018-03-19 | 2018-03-19 | A kind of folding ejection unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810222919.3A CN108284939A (en) | 2018-03-19 | 2018-03-19 | A kind of folding ejection unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108284939A true CN108284939A (en) | 2018-07-17 |
Family
ID=62833881
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810222919.3A Pending CN108284939A (en) | 2018-03-19 | 2018-03-19 | A kind of folding ejection unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108284939A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB274151A (en) * | 1926-03-11 | 1927-07-11 | Charles Richard Fairey | Improvements in or relating to aeroplanes and like aircraft having folding wings |
| CN2253240Y (en) * | 1996-01-10 | 1997-04-30 | 柴超 | Model gliding aircraft capable of self-spreading the wings |
| CN204822082U (en) * | 2015-07-08 | 2015-12-02 | 中国电子科技集团公司第二十七研究所 | Small -size cylinder transmission unmanned aerial vehicle and emitter |
| CN105799915A (en) * | 2016-03-18 | 2016-07-27 | 北京理工大学 | Synchronous folding and unfolding mechanism of wings of unmanned aerial vehicle |
| CN208393617U (en) * | 2018-03-19 | 2019-01-18 | 王洪涛 | A kind of folding ejection unmanned plane |
-
2018
- 2018-03-19 CN CN201810222919.3A patent/CN108284939A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB274151A (en) * | 1926-03-11 | 1927-07-11 | Charles Richard Fairey | Improvements in or relating to aeroplanes and like aircraft having folding wings |
| CN2253240Y (en) * | 1996-01-10 | 1997-04-30 | 柴超 | Model gliding aircraft capable of self-spreading the wings |
| CN204822082U (en) * | 2015-07-08 | 2015-12-02 | 中国电子科技集团公司第二十七研究所 | Small -size cylinder transmission unmanned aerial vehicle and emitter |
| CN105799915A (en) * | 2016-03-18 | 2016-07-27 | 北京理工大学 | Synchronous folding and unfolding mechanism of wings of unmanned aerial vehicle |
| CN208393617U (en) * | 2018-03-19 | 2019-01-18 | 王洪涛 | A kind of folding ejection unmanned plane |
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