CN101712379B - Folding small-sized unmanned aerial vehicle - Google Patents
Folding small-sized unmanned aerial vehicle Download PDFInfo
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- CN101712379B CN101712379B CN2009100882646A CN200910088264A CN101712379B CN 101712379 B CN101712379 B CN 101712379B CN 2009100882646 A CN2009100882646 A CN 2009100882646A CN 200910088264 A CN200910088264 A CN 200910088264A CN 101712379 B CN101712379 B CN 101712379B
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Abstract
The invention provides a folding small-sized unmanned aerial vehicle, which comprises a wing-fuselage blended body, a pair of airfoils, an empennage and a tail boom, wherein the airfoils are respectively arranged on both sides of the wing-fuselage blended body; a connection position of each airfoil and the wing-fuselage blended body is provided with a first folding mechanism; the first folding mechanisms are used for folding the airfoils downwards relative to the wing-fuselage blended body and locking the unfolded airfoils in an unfolded state; one end of the tail boom is connected with the empennage, while the other end is connected with the wing-fuselage blended body through a second folding mechanism; and the second folding mechanism is used for folding the tail boom downwards relative to the wing-fuselage blended body and locking the unfolded tail boom in an unfolded state. After being folded, an airframe structure of the small-sized unmanned aerial vehicle can be accommodated in a cuboid packing chest; and the folding small-sized unmanned aerial vehicle can unfold to the flight condition automatically by utilizing an air-powered actuating device to execute flight tasks of air delivery and the like, and simultaneously, the small-sized unmanned aerial vehicle is short in assembly and disassembly time and convenient in transportation.
Description
Technical field
The present invention relates to a kind of aviation aircraft, be specifically related to a kind of folding small-sized unmanned aerial vehicle.
Background technology
Robot airplane is called for short unmanned plane, is a kind of dynamic driving, driverless operation on the machine, reusable aerocraft.Greatly promoted the update of unmanned plane technology in recent years owing to material science, microelectronic technique, fast development of computer technology.The unmanned plane field also just becomes the field that various countries fall over each other to develop.Unmanned plane is generally classified with weight; What wherein 20kg was following is called miniature or SUAV; Like " pointer-type " unmanned plane of the U.S. and " silver fox " unmanned plane etc.; Generally be used to carry out the battlefield investigation, injure military missions such as assessment, target guide, and be used for non-military tasks such as flight test, aerial mapping, searching rescue as carrying machine platform.
Because unmanned plane self take-off weight is less, fuel oil carries (then is the capacity limit of electrokinetic cell for electronic unmanned plane) limited in one's ability, and index will receive influence in various degree when the voyage of unmanned plane is with boat so.In some cases; As carry out wartime to the investigation, target of attack of enemy's depth guide, the tasks such as searching rescue of great geologic hazard; Airdreadnought subjects to greatly to attack owing to target or does not have under the situation of enough attendance rate; Just need SUAV to carry out these and have the task of high-altitude or remote request, existing conventional SUAV generally can not satisfy the requirement of this generic task.
With earthquake searching rescue task is example; Suppose at geology disaster initial times such as generation earthquakes; The external staff can't get into the inner understanding in earthquake region damaed cordition fast; But for the foundation of science decision in time being provided for relevant departments, must be multi-faceted to reconnoitring in the earthquake region through solid such as aerial, ground, use SUAV at this moment and carry out operation a kind of cost-effective means of can yet be regarded as.But existing SUAV is because the restriction of self take-off weight; Index can't satisfy the requirement of taking off the earthquake region is reconnoitred from the outside, earthquake region when making voyage, boat; Near SUAV being transported to earthquake region or earthquake region from ground; Can receive the influence of irresistible factors such as ground communications obstruct again and waste time, also just lose the rapid-action effect.If can be transported to the sky, earthquake region through the disposable lift-launch of large aircraft this moment with many SUAVs; Throw in zones of different; Throw in the spontaneous entering normal flight of back miniature self-service function pattern; Accomplish corresponding searching rescue and earthquake region prospecting task, so strong help will be provided the work of earthquake relief work.
In addition, SUAV generally is designed to the detouchable form now, and complete machine can resolve into a plurality of parts such as wing, fuselage, empennage, alighting gear cases, with convenient transportation.But such is olation makes unmanned plane need carry out work such as the installation of being connected of control path and pipeline, parts is fastening later on arriving the destination, just can reach state to be flown, and this process is comparatively loaded down with trivial details, consuming time; , aerial mission need same time and step to go to accomplish the vanning work of disassembling after accomplishing again.In military operation, the fitness for purpose equipment can satisfy the rapid-action requirement, so that hold the opportunity of combat that promptly dies in wink slightly; In the searching rescue task, also require to seize every minute and second, drop to minimum in the hope of loss with disaster; At civilian and scientific research field, efficient is an important indicator of weighing product and achievement especially equally.This has just proposed requirement to the design of unmanned plane, should make it simultaneously to satisfy to load and unload fast and make things convenient for requirements on transport.
Summary of the invention
The objective of the invention is to solve existing SUAV and carry out the weak problem of task ability that has high-altitude and remote request; And overcome on " dismounting-installation " pattern deficiencies such as required time is long, process is loaded down with trivial details; A kind of folding small-sized unmanned aerial vehicle is provided, and its housing construction can fold in the packing chest that is accommodated in profile rule.SUAV after folding be through aerial input, step such as expansions can change the normal flight state over to and goes to execute the task automatically, and thinking that should folding body is applied to make its loadingunloading time shortening behind the SUAV, transports convenient.
According to an aspect of the present invention, a kind of folding small-sized unmanned aerial vehicle is provided, it comprises: a blended wing-body; A pair of wing; Be separately positioned on the left and right sides of said blended wing-body; Each said wing and said blended wing-body junction are provided with one first fold mechanism, and said first fold mechanism is set to make said wing can the said wing that launch be locked in deployed condition with respect to downward the folding also of said blended wing-body; An empennage; A shoe; The one of which end connects said empennage; The other end is connected with said blended wing-body through one second fold mechanism, and said second fold mechanism is set to make said shoe can the said shoe that launch be locked in deployed condition with respect to downward the folding also of said blended wing-body.
According to an embodiment of the invention; Said first fold mechanism is set to make said wing to fold 90 ° with respect to said blended wing-body is downward, and said second fold mechanism is set to make said shoe to fold 100 ° with respect to said blended wing-body is downward.
According to one embodiment of present invention; Said first fold mechanism is identical with the said second fold mechanism principle, and its structure comprises: one first hinge, and it is captiveed joint with said wing or said shoe; And one second hinge, it is captiveed joint with said blended wing-body; Said first hinge and said second hinge are hinged through a bearing pin in the bottom, and the top of said first hinge is provided with an auricle, has a barb on the said auricle; The said second hinge top is provided with a boss, and said boss top is provided with a breach, wherein is provided with a dead bolt and supports a spring holding up this dead bolt; The corresponding setting of said dead bolt with said barb; Thus, under said wing or said shoe deployed condition, the upper surface of said first hinge fits in the upper surface of said boss; Said dead bolt is ejected by action of the spring, catches on said barb.
According to a preferred implementation of the present invention, also be provided with first between said wing and the said blended wing-body and launch actuation mechanism, also be provided with second between said shoe and the said blended wing-body and launch actuation mechanism.
According to one embodiment of present invention; It is identical that the said first expansion actuation mechanism and said second is launched the actuation mechanism principle; Its structure comprises: a pneumatic cylinders, be fixed on the said blended wing-body, and the operating bar front end on the said pneumatic cylinders is provided with one second bearing pin; A support arm, one of which end are fixed on said wing or the said shoe, and the other end has a chute, and said chute can hold said second bearing pin and slide therein.
Preferably, said blended wing-body is a flat lifting body with certain aerofoil profile, and merge through rational curve and said wing its both sides.
According to one embodiment of present invention, both sides, said blended wing-body rear end are equipped with two electrical motors that have screw propeller.
According to one embodiment of present invention; Said wing planform is trapezoidal, its leading-edge sweep, trailing edge sweepforward, and the outside trailing edge of every side wing stabilator is provided with aileron; Said wing is conventional single-beam formula structure; 30% chord length place at said wing is provided with a girder, wall after 75% chord length place is provided with, wherein said girder and said blended wing-body axis normal; Said wing is connected with said blended wing-body with wall place, back two place's joints through girder, and the laced belt at its middle girder place has said first fold mechanism; The joint at back wall place is a hinge.
According to one embodiment of present invention, said empennage is a vee tail, and its left and right sides empennage is mutually 110 °, and empennage stabilator trailing edge is provided with control surface.
Beneficial effect of the present invention is mainly reflected in:
1) SUAV of the present invention can be thrown under folded state in the air; Effect through folding-expansion start and lockout mechanism in the decline process launches body automatically; Return to normal aerodynamic configuration, change the orthodox flight state over to, can be used for accomplishing the special air mission long-range like the high-altitude;
2) SUAV of the present invention adopts the distribution form of blended wing-body, single shoe, vee tail; The well requirement of adaline folded body; The designs of the air dynamic behaviour that has excellence simultaneously, particularly blended wing-body have increased the lifting area of full machine, help to improve the lift of aircraft; Simultaneously can effectively reduce the interference drag between wing and the fuselage, thereby increase the 1ift-drag ratio of aircraft;
3) the present invention's design of being used for the fold mechanism of folded wing and shoe has been shortened this type unmanned plane from depositing the vanning state to the setup time of waiting that the state of flying is required; When needs fly, the unmanned plane of folded state is taken out, get final product both sides wing and the shoe cocked position that automatically locks to fold mechanism that makes progress; After accomplishing flight, only need press the locking insurance (for example making the dead bolt of fold mechanism break away from barb) at fold mechanism place, can wing and shoe is folding downwards, make unmanned plane return to storage configuration;
4) SUAV of the present invention can be accommodated under folded state in the rectangular casing, has saved the space greatly, conveniently transports and deposits.
Description of drawings
Fig. 1 is SUAV monnolithic case figure under the state of flight;
Fig. 2 is SUAV monnolithic case figure under the folded state;
Fig. 3 folds-launches the required start and the structural representation of lockout mechanism for SUAV.
The specific embodiment
Specify total arrangement, folding mode, the folding-required start of expansion and the lockout mechanism of collapsible SUAV of the present invention below in conjunction with accompanying drawing.
1) total arrangement of SUAV
This SUAV is conventional formula aerodynamic arrangement, and is as shown in Figure 1, adopts wing body to merge design, single shoe band vee tail.The organization of this SUAV comprises blended wing-body 8, wing 6,7, empennage 4,5, shoe 3, power system 1,2, folding-as to launch required start and lockout mechanism, and tricycle landing gear can be installed where necessary.
Wherein blended wing-body 8 is a flat lifting body with certain aerofoil profile, and upper surface is provided with a cabin lid, and inside is a high-capacity cabin, is used for the installation of airborne equipment.Merge through rational curve and wing 6,7 blended wing-body 8 both sides, to guarantee to have aerodynamic characteristic preferably.Both sides, blended wing-body 8 rear end are equipped with for example two electrical motors 1 that have screw propeller 2, for this SUAV provides flight required power.
The left and right sides empennage of vee tail 4,5 is mutually 110 °; Empennage stabilator 4 trailing edges are provided with control surface 5; Can realize the function of elevating rudder and yaw rudder through V tail mixing pattern; The rudder face deflection up or down simultaneously that is to say left and right sides empennage is the effect of lifting rudder, and one of the rudder face of left and right sides empennage is gone up another inclined to one side down yaw rudder that promptly plays a part partially.
2) folded form
When this SUAV is folding; Wing 6,7 edges are rolled over about 90 ° downwards with the rotating shaft of blended wing-body 8 bonded assembly wingfold mechanisms 10; Shoe 3 is rolled over about 100 ° downwards along the rotating shaft at afterbody fold mechanism 9 places; This moment, shoe 3 was middle, as shown in Figure 2 with the left and right sides wing 6,7 that vee tail 4,5 is positioned at folded state.This unmanned plane under the folded state can be accommodated in the rectangular casing.In practical application; To fold aircraft through corresponding supporting construction when folding aircraft will be packed packing chest into fixes; Prevent the vibrations of aircraft and collide with and cause the damage of structure that therefore folding angle is relatively freer, mainly receives the restriction of packing chest and inner supporting structure thereof.
3) folding-required start and lockout mechanism of expansion
Preferably; Collapsible SUAV of the present invention; In the set connection structure 10 of the connecting portion of wing 6,7 and blended wing-body 8 is a fold mechanism and the fabricate block that launches driver train; Hereinafter is referred to as to fold-launch start and lockout mechanism 10, be provided with another fold mechanism and the fabricate block that launches driver train at the connecting portion of shoe 3 and blended wing-body 8, and hereinafter is referred to as to fold-launch start and lockout mechanism 9.Described folding-expansion start and lockout mechanism 9,10 comprise fold mechanism and expansion actuation mechanism, and its concrete structure can adopt various ways, and Fig. 3 has only shown wherein a kind of example of structure.
Because that two places are provided with is folding-and to launch start identical with lockout mechanism 9,10 principles, therefore only describe as example with the required start of folding of using between wing 6,7 and the blended wing-body 8-expansion and lockout mechanism 10 here.
As shown in Figure 3, the main body of fold mechanism is two hinges, and promptly first hinge 104 and second hinge, 102, the first hinges 104 are connected with the girder 106 of wing, and second hinge 102 is connected with the girder 101 of blended wing-body 8.First hinge 104 and second hinge 102 are hinged through bearing pin 103 in the bottom.One auricle 107 is arranged at the top of first hinge 104, has the barb 105 that locks usefulness on the auricle 107.Second hinge, 102 tops are a boss 113, and under the situation of mechanism's closed (being the wing deployed condition), the upper surface of first hinge 104 just in time fits in the upper surface of said boss 113, to guarantee the dihedral angle of wing.One breach is arranged at boss 113 tops, wherein is furnished with a spring and a dead bolt 110, and dead bolt 110 receives the elastic force effect of spring.Fold mechanism is by opening during to closure state; First hinge 104 is around bearing pin 103 rotations, and auricle 107 is pressed into dead bolt 110, and is closed fully until first hinge 104 and second hinge 102; Dead bolt 110 is ejected by action of the spring; Catch on the barb 105 on the auricle, so far fold mechanism is locked, and unmanned plane has stable aerodynamic configuration during having guaranteed to fly.
Launch the pneumatic cylinders 112 that actuation mechanism mainly includes girder 101 sides that are installed on blended wing-body 8, the support arm 108 that is installed on wing girder 106 sides, be used for automatically the unmanned plane of folded state is expanded to state of flight.Have a chute 109 on the support arm 108, the bearing pin 114 of pressurized strut joint can slide in chute 109.When the pneumatic cylinders compressed gas is done the time spent, operating bar 111 is regained, and the operating bar joint drives support arms 108 through bearing pin 114, and wing girder 106 is upwards rotated around fold mechanism bearing pin 103, reaches the state of complete closure until fold mechanism.
In practical application, folding small-sized unmanned aerial vehicle of the present invention, fold mechanism wherein can carry out corresponding configuration as the case may be with the expansion actuation mechanism, for example:
Instance one is carried out the aerial mission that aerial input launches
SUAV under this state is installed fold mechanism simultaneously and is launched actuation mechanism.When carrying out the aerial mission of aerial input expansion; This SUAV that is equipped with corresponding capacity weight at first is in folded state as shown in Figure 2; And be incorporated in the rectangular packing chest, can carry by modes such as fire balloon, dirigible, helicopter or large transport airplanes and be transported to predetermined height and the spatial domain is thrown in the air.The brick pack case that is used for taking in SUAV is equipped with the operatorless device of parachute and opened door, is thrown in aloft that the back automatic deployment is stable to descend, and the self-opening hatch door discharges the unmanned plane of folded inside state then.
After the unmanned plane of folded state skids off the packing casing; Its left and right sides wing 6,7 and shoe 3 launch automatically under the effect of pneumatically spreading actuation mechanism and are locked in normal flight form as shown in Figure 1, under the control of this unmanned aerial vehicle onboard equipment, carry out operation flight then.
Instance two, storage configuration in the normal work to do-the wait quick conversion of the state of flying
SUAV under this form can only be installed fold mechanism and omit the expansion actuation mechanism.Left and right sides wing 6,7, shoe 3 are connected with blended wing-body 8 through the folding mechanism of a cover respectively.Take in travelling position lower wing and shoe and all be folded, after arriving the destination, the unmanned plane of folded state is taken out from packing chest, and left and right sides wing and shoe upwards pulled until fold mechanism automatically lock, unmanned plane can arrive state to be flown.After accomplishing aerial mission, only need the dead bolt 110 of fold mechanism is pushed back, make it break away from barb 105, and, can make unmanned plane return to storage configuration downwards wing and the folding packing chest of packing into then of shoe, whole implementation process is simple and convenient.
Below only be concrete exemplary applications of the present invention, protection scope of the present invention is not constituted any limitation.All employing equivalents or equivalence are replaced and the technical scheme of formation, all drop within the rights protection scope of the present invention.
Claims (8)
1. folding small-sized unmanned aerial vehicle is characterized in that it comprises:
A blended wing-body (8);
A pair of wing (6,7); Be separately positioned on the left and right sides of said blended wing-body (8); Each said wing (6,7) is provided with one first fold mechanism (10) with said blended wing-body (8) junction, and said first fold mechanism (10) is set to make said wing (6,7) can the said wing (6,7) that launch be locked in deployed condition with respect to downward the folding also of said blended wing-body (8);
An empennage (4,5);
A shoe (3); The one of which end connects said empennage (4,5); The other end is connected with said blended wing-body (8) through one second fold mechanism (9), and said second fold mechanism (9) is set to make said shoe (3) can the said shoe (3) that launch be locked in deployed condition with respect to downward the folding also of said blended wing-body (8);
Be arranged on first between said wing (6,7) and the said blended wing-body (8) and launch actuation mechanism (10);
Be arranged on second between said shoe (3) and the said blended wing-body (8) and launch actuation mechanism (9);
Wherein, the said first expansion actuation mechanism (10) comprising:
A pneumatic cylinders (112) is fixed on the said blended wing-body (8), and operating bar (111) front end on the said pneumatic cylinders (112) is provided with one second bearing pin (114);
A support arm (108), one of which end are fixed on the said wing (6,7), and the other end has a chute (109), and said chute (109) can hold said second bearing pin (114) and slide therein.
2. folding small-sized unmanned aerial vehicle according to claim 1; It is characterized in that; Said first fold mechanism (10) is set to make said wing (6,7) with respect to folding 90 ° of said blended wing-bodies (8) downwards, and said second fold mechanism (9) is set to make said shoe (3) with respect to folding 100 ° of said blended wing-bodies (8) downwards.
3. folding small-sized unmanned aerial vehicle according to claim 1 is characterized in that, said first fold mechanism (10) comprising:
One first hinge (104), it is captiveed joint with said wing (6,7), and
One second hinge (102), it is captiveed joint with said blended wing-body (8);
Said first hinge (104) is hinged through a bearing pin (103) in the bottom with said second hinge (102),
The top of said first hinge (104) is provided with an auricle (107), has a barb (105) on the said auricle (107), and said second hinge (102) top is provided with a boss; Said boss top is provided with a breach; Wherein be provided with a dead bolt (110) and support a spring holding up this dead bolt (110), said dead bolt (110) and the corresponding setting of said barb (105), thus; Under said wing (6,7) deployed condition; The upper surface of said first hinge (104) fits in the upper surface of said boss (113), and said dead bolt (110) is ejected by action of the spring, catches on said barb (105).
4. folding small-sized unmanned aerial vehicle according to claim 1 is characterized in that, said second fold mechanism (9) comprising:
One first hinge (104), it is captiveed joint with said shoe (3), and
One second hinge (102), it is captiveed joint with said blended wing-body (8);
Said first hinge (104) is hinged through a bearing pin (103) in the bottom with said second hinge (102),
The top of said first hinge (104) is provided with an auricle (107), has a barb (105) on the said auricle (107), and said second hinge (102) top is provided with a boss; Said boss top is provided with a breach; Wherein be provided with a dead bolt (110) and support a spring holding up this dead bolt (110), said dead bolt (110) and the corresponding setting of said barb (105), thus; Under said shoe (3) deployed condition; The upper surface of said first hinge (104) fits in the upper surface of said boss (113), and said dead bolt (110) is ejected by action of the spring, catches on said barb (105).
5. folding small-sized unmanned aerial vehicle according to claim 1 is characterized in that, said second launches actuation mechanism (9) comprising:
A pneumatic cylinders (112) is fixed on the said blended wing-body (8), and operating bar (111) front end on the said pneumatic cylinders (112) is provided with one second bearing pin (114);
A support arm (108), one of which end are fixed on the said shoe (3), and the other end has a chute (109), and said chute (109) can hold said second bearing pin (114) and slide therein.
6. folding small-sized unmanned aerial vehicle according to claim 1 is characterized in that, said blended wing-body (8) is a flat lifting body with certain aerofoil profile, and merge through rational curve and said wing (6,7) its both sides.
7. folding small-sized unmanned aerial vehicle according to claim 1 is characterized in that, said blended wing-body (8) both sides, rear end are equipped with two electrical motors (1) that have screw propeller (2).
8. folding small-sized unmanned aerial vehicle according to claim 1 is characterized in that,
Said wing (6,7) aspect is trapezoidal; Its leading-edge sweep, trailing edge sweepforward; The outside trailing edge of every side wing stabilator (7) is provided with aileron (6), and said wing (6,7) is conventional single-beam formula structure, is provided with a girder (106) at 30% chord length place of said wing; Wall (11) after 75% chord length place is provided with one; Wherein said girder (106) and said blended wing-body (8) axis normal, said wing (6,7) are located two place's joints through girder (106) with back wall (11) and are connected with said blended wing-body (8), and the laced belt at its middle girder place has said first fold mechanism (10); The joint (12) at back wall place is a hinge;
Said empennage (4,5) is a vee tail (4,5), and its left and right sides empennage is mutually 110 °, and empennage stabilator (4) trailing edge is provided with control surface (5).
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| CN2009100882646A CN101712379B (en) | 2009-07-14 | 2009-07-14 | Folding small-sized unmanned aerial vehicle |
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| CN2009100882646A CN101712379B (en) | 2009-07-14 | 2009-07-14 | Folding small-sized unmanned aerial vehicle |
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| CN101712379B true CN101712379B (en) | 2012-02-01 |
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| DE2935044A1 (en) * | 1979-08-30 | 1981-03-19 | Vereinigte Flugtechnische Werke Gmbh, 2800 Bremen | UNMANNED MISSILE TO BE LAUNCHED FROM A CONTAINER |
| US5423706A (en) * | 1994-01-28 | 1995-06-13 | Chase; George W. | Toy aircraft glider with rotating and folding wings |
| US5671899A (en) * | 1996-02-26 | 1997-09-30 | Lockheed Martin Corporation | Airborne vehicle with wing extension and roll control |
| CN2589730Y (en) * | 2002-12-20 | 2003-12-03 | 黄可胜 | Safety locking mechanism of folding joint |
-
2009
- 2009-07-14 CN CN2009100882646A patent/CN101712379B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2935044A1 (en) * | 1979-08-30 | 1981-03-19 | Vereinigte Flugtechnische Werke Gmbh, 2800 Bremen | UNMANNED MISSILE TO BE LAUNCHED FROM A CONTAINER |
| US5423706A (en) * | 1994-01-28 | 1995-06-13 | Chase; George W. | Toy aircraft glider with rotating and folding wings |
| US5671899A (en) * | 1996-02-26 | 1997-09-30 | Lockheed Martin Corporation | Airborne vehicle with wing extension and roll control |
| CN2589730Y (en) * | 2002-12-20 | 2003-12-03 | 黄可胜 | Safety locking mechanism of folding joint |
Also Published As
| Publication number | Publication date |
|---|---|
| CN101712379A (en) | 2010-05-26 |
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