CN103963972B - What a kind of wing tip docked can oblique wing all-wing aircraft Unmanned Aircraft Systems (UAS) in parallel - Google Patents
What a kind of wing tip docked can oblique wing all-wing aircraft Unmanned Aircraft Systems (UAS) in parallel Download PDFInfo
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Abstract
The present invention relates to a kind of topological design technical field of Unmanned Aircraft Systems (UAS), is specifically a kind of Unmanned Aircraft Systems (UAS) utilizing wing tip connection/traction technology to be combined with flying wing type oblique wing airplane.The mode that this Unmanned Aircraft Systems (UAS) is docked by wing tip by several identical all-wing aircraft unmanned planes is formed in parallel; Rotatable around adapter shaft in the horizontal direction between the wing of described all-wing aircraft unmanned plane and driving engine.The mode of described wing tip docking is: the port wingtip of each all-wing aircraft unmanned plane is provided with corresponding wing tip with right flank point and docks and chart-drive mechanism, can only carry out the relative motion around abutment shaft rolling between the all-wing aircraft unmanned plane of two docking.The present invention can improve 1ift-drag ratio effectively, when making each unmanned plane all obtain larger voyage with boat, and, the flight performance of middle low regime, subsonic area and supersonic domain can be taken into account.When being necessary, formation or the restructuring formation of docking can be dismissed aloft according to the actual conditions such as mission requirements or atmospheric conditions.
Description
Technical field
The present invention relates to a kind of topological design technical field of Unmanned Aircraft Systems (UAS), is specifically a kind of Unmanned Aircraft Systems (UAS) utilizing wing tip connection/traction technology to be combined with flying wing type oblique wing airplane.
Background technology
In the past, people develop wing tip docking/traction technology, and use C-47/Q-14 to make a flight test; Simultaneously people also developing as Fig. 1 the oblique wing airplane of flying wing type looked.
20 forties on opportunity, people developed wing tip docking/traction technology, and used C-47/Q-14 to make a flight test to the fifties.The Objective Concept Germany scientist Richard Vogt doctor of wing tip docking/traction technology proposes.Two pieces of " free floating " expanding sections depositing extra fuel oil are added to increase aircraft range to aircraft two wing tip.Its design philosophy core is, makes expanding section can do limited motion relative to point of connection, and the aerodynamic lift that the weight of expanding section self can be produced by it supports, and such whole system can from the adverse effect of structural weight aspect.Wing tip free floating expanding section improves the aspect ratio of basic wing layout, reduces induced drag, increases voyage.United States Air Force once carried out the research of this technology the forties to the fifties in 20th century, and used C-47/Q-14 to make a flight test, and successfully dock 231 times, rear employing B-29 pulls F-84 and tests.
The wing tip docking operation of general aircraft is as follows: because the wing tip of general aircraft exists wing tip circulation from wing lower surface around to upper surface, and therefore wing docks the mode progressively can not drawn close with afflight and carries out.Rule of thumb, generally should take an airplane wing tip relatively front and another is rear, one side or both sides stretch out certain length to extension bar, the wing tip circulation of two airplanes should be able to be made not interfere with each other the overall length of extension bar.Preceding aircraft slows down gradually, makes the docking mechanism that can pin posterior aircraft to extension bar, then regains extension bar, makes the wing of two frame all-wing aircraft unmanned planes fit together and lock.
The research history of wing tip docking/traction technology is Zhang Nan " and bridle three " people " OK---the U.S.'s early stage wing tip docking/traction technology ", and " ordnance knowledge " 2007 07 is interim visible, and the document is incorporated to herein by reference at this.
Above-mentioned wing tip docking/traction technology was only once applied to manned aircraft, after the 1950's, was abandoned due to the maturation of air refuelling technology and widespread use.Because this technology is for manned aircraft on the one hand, operation easier is greater than air refuelling, because its field of application has larger limitation on the other hand, the aircraft of the straight wing can only be used for, for transonic and supersonic planes such as the swept wing occurred afterwards, delta wings, there is no Practical significance, simultaneously, wing tip docking/traction technology at that time is also confined to the occasion of the large-scale bomber of a frame or transport plane both sides wing tip each traction one frame escort fighter, does not have too large practical value for the air fighting after the fifties, transport.
Chinese patent CN201210167457.2 discloses a kind of conventional airplane that can only carry out wing tip docking on ground, be characterized in the docking carrying out wing tip before taking off at ground multi rack conventional airplane, together take off, utilize the feature of its high aspect ratio, obtain high cruise performance, aloft can unlock when task needs, be divided into multiple independent aircraft to execute the task.After controlling unblock, aircraft can not dock again.
US National Aeronautics and Space Administration (NASA) has manufactured small-sized oblique wing proof machine AD-1 on the basic upper strata of research and experiment, is in recent years carried out the oblique wing proof machine of " spring pocket knife " (Switchblade) flying wing type of initial designs by Nuo Siluopu Grumman Co., Ltd.It is similar to variable sweep aircraft in principle for oblique wing airplane.Aircraft taking off, land and low-speed operations time, wing position as shown in broken lines, is equivalent to straight wing, and at this moment wing length is maximum, and induced drag is little, and lift coefficient is large, takeoff and anding and low-speed operations performance good.When aircraft is with high subsonic speed and supersonic flight, wing can pivot a certain angle (in figure solid line position).At this moment, side wing sweepforward, the sweepback of opposite side wing, can postpone the generation of shock wave, thus reduces resistance, improves 1ift-drag ratio when cruising, and reduces oil consumption.The difference of oblique wing airplane and variable sweep aircraft is when left half wing is in sweepback position, the then sweepforward of right half wing.Wing is when oblique wing position, and comparatively swept-back wing aircraft is even along the distribution of fuselage axis for whole Aircraft Lateral sectional area, is bordering on fairing, in reduction wave resistance than swept wing advantageously.Oblique wing airplane left and right half wing is connected, and simplifies the connection structure of wing and fuselage, but left and right half wing is asymmetric on tilting position, can cause pitching and yawing rotation by roll guidance.The research history of oblique wing aircraft is at M.Hirschberg, " ASummaryofaHalf-CenturyofObliqueWingResearch " 45thAIAAAerospaceSciencesMeetingandExhibit of D.Hart and T.Beutner, AIAAPaper2007-150, visible in Jan.2007, the document is incorporated to herein by reference at this.
Chinese patent CN101795939A discloses a kind of scheme optimizing flying wing type oblique wing airplane, the program carries out configuration design mainly for single flying wing type oblique wing airplane, makes oblique wing airplane obtain larger loading space, better airworthiness and relatively satisfied maneuverability pattern.
When both having possessed distance flight, overlength boat, can carry out supersonic flight when executing the task again, be the important development target of unmanned plane always.Performing investigation and the task of hitting one is the important developing direction of of unmanned plane, and wherein investigation tasks, when needing aircraft to have long boat, the characteristic of large voyage, for this reason, in low earthquake intensity Antagonistic Environment, the unmanned plane of investigation type generally adopts Flying-wing or the normal arrangement tool of the straight wing of high aspect ratio, that aircraft has lower induced drag when middle low speed, higher 1ift-drag ratio.And enter highlight lines Antagonistic Environment perform prominent anti-with the task of strike time, unmanned plane more wishes to have ultrasonic flight performance, high aspect ratio is straight, and wing Flying-wing is not then suitable for supersonic flight completely, therefore people consider to adopt flying wing type oblique wing airplane to investigate as when can take into account long boat a kind of layout type hit with hyprsonic, but because the layout of flying wing type oblique wing airplane is limited to, make this kind of aircraft have larger difficulty on gesture stability and flight tracking control.When therefore how more effectively can improve boat under existing condition and voyage, aircraft can be made again to obtain ultrasonic task ability, is a vital task of current unmanned aerial vehicle design.
Unmanned plane all adopts fly-by-wire flight control system, aircraft can be controlled steadily, safely and perform aerial mission, very high control ability is had to the attitude of general aircraft and flight path, air refuelling technology between unmanned plane is day by day perfect, also describes unmanned plane and has had the ability accurately controlling relative position and motion.
Summary of the invention
All-wing aircraft unmanned plane identical for multi rack profile is utilized the docking of wing point and pulling method by the present invention, be organized into the large-scale all-wing aircraft Unmanned Aircraft Systems (UAS) of a wing parallel connection, effectively improve 1ift-drag ratio, when making each unmanned plane all obtain larger voyage with boat, further, the flight performance of middle low regime, subsonic area and supersonic domain can be taken into account.When being necessary, formation or the restructuring formation of docking can be dismissed aloft according to the actual conditions such as mission requirements or atmospheric conditions.
Wing tip docking can an oblique wing all-wing aircraft Unmanned Aircraft Systems (UAS) in parallel, the mode that this Unmanned Aircraft Systems (UAS) is docked by wing tip by several identical all-wing aircraft unmanned planes is formed in parallel;
Rotatable around adapter shaft in the horizontal direction between the wing of described all-wing aircraft unmanned plane and driving engine;
The mode of described wing tip docking is: the port wingtip of each all-wing aircraft unmanned plane is provided with corresponding wing tip with right flank point and docks and chart-drive mechanism, can only carry out the relative motion around abutment shaft rolling between the all-wing aircraft unmanned plane of two docking.
The invention has the advantages that problem when can solve or alleviate the design of following High Performance Unmanned Aerial Vehicle:
1, design after multiple identical all-wing aircraft unmanned plane carries out wing tip docking and fly, all-wing aircraft Unmanned Aircraft Systems (UAS) in parallel is made to have larger aspect ratio, thus ability when obtaining large voyage, long boat, single all-wing aircraft unmanned plane after decomposing then has supersonic flight ability, and this system can be taken into account large voyage, grow when navigating and supersonic flight ability.
2, compare fixed high-aspect-ratio aircraft, all-wing aircraft Unmanned Aircraft Systems (UAS) in parallel, when being subject to strong air flow interference, can being dismissed as multiple independent all-wing aircraft unmanned plane, easily produces aeroelastic divergence and disintegrate when avoiding unmanned plane aspect ratio excessive;
3, after being combined into all-wing aircraft Unmanned Aircraft Systems (UAS) in parallel, overall course change can be realized by the power adjusting wherein each all-wing aircraft unmanned plane, solving single all-wing aircraft unmanned plane aircraft due to its layout characteristics changes course difficulty, when the all-wing aircraft oblique wing airplane simultaneously also solving monomer carries oblique wing pattern, primary control surface can cause multiple axial motion, cannot remove the problem of coupling;
Accompanying drawing explanation
Fig. 1 is can oblique wing all-wing aircraft Unmanned Aircraft Systems (UAS) in parallel schematic diagram in embodiment.
Fig. 2 is an all-wing aircraft unmanned plane schematic diagram in embodiment.
Fig. 3 is wing tip docking operation schematic diagram in embodiment.
Fig. 4 is that in embodiment, wing tip has docked schematic diagram.
Detailed description of the invention
Wing tip docking can an oblique wing all-wing aircraft Unmanned Aircraft Systems (UAS) in parallel, the mode that this Unmanned Aircraft Systems (UAS) is docked by wing tip by several identical all-wing aircraft unmanned planes is formed in parallel;
Rotatable around adapter shaft in the horizontal direction between the wing of described all-wing aircraft unmanned plane and driving engine;
The mode of described wing tip docking is: the port wingtip of each all-wing aircraft unmanned plane is provided with corresponding wing tip with right flank point and docks and chart-drive mechanism, can only carry out the relative motion around abutment shaft rolling between the all-wing aircraft unmanned plane of two docking.
Embodiment 1: see Fig. 1, be the docking of a kind of wing tip can the schematic diagram of oblique wing all-wing aircraft Unmanned Aircraft Systems (UAS) in parallel, this all-wing aircraft Unmanned Aircraft Systems (UAS) 1 in parallel, from right to left 2,3,4 represent the identical all-wing aircraft unmanned plane of 3 identical framves of profile respectively, Regional Representative's all-wing aircraft unmanned plane 2 specified by square frame 5 and the docking mechanism between all-wing aircraft unmanned plane 3, hereinafter will be introduced according to Fig. 3 and Fig. 4.Dotted line wing 6,7,8 is all-wing aircraft Unmanned Aircraft Systems (UAS) 1 in parallel signals when being in oblique wing state, and now independent all-wing aircraft unmanned plane 6,7,8 is all in the state having leaning angle between driving engine and wing.
In the present invention, identical all-wing aircraft unmanned plane quantity can equal and be not limited to 3 framves.Every frame all-wing aircraft unmanned plane adopts modular design, that is: every frame unmanned plane has identical aircraft platform, the modes of aircraft configuration, cabin size and shape, hanging etc. are all identical, should possess flight control administrating system, data link and mission payload ability etc. that general unmanned plane should have simultaneously.Every airplane by installing the different task cabin of function additional or carrying additionally different mission payloads, can realize different functions.
A. a kind of design plan of all-wing aircraft unmanned plane:
See Fig. 2, be the profile of all-wing aircraft unmanned plane 2 in present embodiment, this figure is upward view, namely upwards observes from the below of aircraft.Below wing 11, driving engine 12 is installed, between wing 11 and driving engine 12, can have rotated around S. A. 13, as dotted line wing 14.Outside wing 11 the right and left, trailing edge respectively has three elevons 15, handles for the attitude completing flying wing type oblique wing airplane.
When multiple UAVs carries out wing tip docking traction flight, see Fig. 4, the right side docking mechanism 9 of every frame unmanned plane docks with the left side docking mechanism 10 of the frame unmanned plane on the right side of it, and whole formation is turned left from the right side a frame one frame docking successively, final forms all-wing aircraft Unmanned Aircraft Systems (UAS) 1 in parallel.
After forming all-wing aircraft Unmanned Aircraft Systems (UAS) 1 in parallel, can only carry out the relative motion by a small margin (see Fig. 3 and Fig. 4) in rolling direction between adjacent all-wing aircraft unmanned plane around abutment shaft, luffing mutual between all-wing aircraft unmanned plane and yawing rotation will be consistent.
B. wing tip docking and pulling method
Fig. 3 is the concrete schematic diagram of position shown in square frame 5 in Fig. 1, illustrates the adoptable one of the present invention and carries out wing tip docking structure in the air.Fig. 3 docks for the right side docking mechanism 9 of the left side docking mechanism 10 of in Fig. 1 No. 2 all-wing aircraft unmanned plane and No. 3 all-wing aircraft unmanned planes the docking mode illustrated between all-wing aircraft unmanned plane.Represented by Fig. 3 design, be a kind of wing tip docking method, the present invention can adopt this kind of docking calculation, is also not limited to this kind of method.
In the docking calculation shown in Fig. 3, fly relatively forward in the flight position of the all-wing aircraft unmanned plane 3 in left side, and the position of the all-wing aircraft unmanned plane 2 in right side that flies relatively rearward, two machines are in sustained height.
In the docking mechanism 9 of the right flank point of all-wing aircraft unmanned plane 3, the actuator 23 of roller screw has been installed in rib 41 side of wing tip, actuator 23 can drive leading screw 22 to be stretched out along spanwise by the nut 25 of the rib 43 of the nut 24 and wing tip that are arranged on the rib 42 of wing tip or regain, play the effect of the sense of motion of stable leading screw 22, the right-hand member of leading screw 22 is equipped with extension bar 21.
Locking ring drive motor 26, active oblique gear 27, passive helical wheel 28 are installed in the rib 43 rear outside face of wing tip and make locking ring 29, drive motor 26 and active oblique gear 27 are connected, turning cylinder is parallel with airfoil chord length direction, passive helical wheel 28 changes 29 with locking and is connected, and turning cylinder is perpendicular to wingpiston.Active oblique gear 27 is engaged with passive helical wheel 28, realizes the rotation rotation that drive motor 26 is changed in locking being converted into locking ring 29.
When inserting docking passage 30 to extension bar 21 and recovery puts in place, locking ring drive motor 26 drives active oblique gear 27 to rotate, passive helical wheel 28 is driven to rotate counterclockwise, make locking ring 29 from trailing edge counterclockwise movement, until locking ring 29 fastens extension bar 21, locking ring drive motor 26 carries out brake locking, makes locking ring 29 locked.
The docking mechanism 10 of the port wingtip of all-wing aircraft unmanned plane 2 is that passage 30 is docked in the taper coordinated with to extension bar 21, has reinforcement structure between docking passage 30 and wing.
When carrying out mating operation, leading screw 22 reaches maximum position, rule of thumb, general extension elongation should between 1.5 metric system 2 meters, docking 21 bar be now connected with leading screw end should aim at the docking passage 30 of the left side docking mechanism 10 of all-wing aircraft unmanned plane 3, and then all-wing aircraft unmanned plane 3 slows down, and makes to stretch in the docking passage 30 of all-wing aircraft unmanned plane 2 to extension bar 21, until to the through whole docking passage 30 of extension bar 21, and stretch out in docking passage 30 rear end.Now actuator 23 counter-rotation, makes leading screw 22 regain, and draws close by making all-wing aircraft unmanned plane 2 and all-wing aircraft unmanned plane 3 to extension bar 21.When two all-wing aircraft unmanned planes close to immediate distance are, as shown in Figure 4, the locking ring drive motor 26 being arranged on rib 43 rear outside face drives active oblique gear 27 to rotate, passive helical wheel 28 is driven to rotate counterclockwise, thus make locking ring 29 from trailing edge counterclockwise movement, until locking ring 29 fastens extension bar 21, locking ring drive motor 26 carries out brake locking, make locking ring 29 locked, thus front-back staggered disengagement can not be there is in two all-wing aircraft unmanned planes.Now docked, the small size rolling movement around the axis 31 to extension bar 21 between all-wing aircraft unmanned plane 2 and all-wing aircraft unmanned plane 3, can have been carried out, and pitch axis and course axle locked mutually, there is not relative motion.
Mode of motion wherein between leading screw 22 and actuator 23 adopts common roller screw, and the design that locking ring drive motor 26 makes locking ring 29 move by active oblique gear 27 and passive helical wheel 28, be common type of drive, its principle be not described at this.
When will free between all-wing aircraft unmanned plane, as long as make locking ring drive motor 26 remove brake, locking ring 29 is made to be in free release position, actuator 23 rotates and leading screw 22 is stretched out simultaneously, the all-wing aircraft unmanned plane in left side accelerates, the all-wing aircraft unmanned plane on right side slows down, then can throw off wing tip docking, can fly respectively.
C. the three axes control of all-wing aircraft unmanned plane is with stable
As previously mentioned, after forming all-wing aircraft Unmanned Aircraft Systems (UAS) 1 in parallel, relative pitching and yawing rotation can not be carried out between each all-wing aircraft unmanned plane, rolling movement more by a small margin can only be carried out, therefore the every frame all-wing aircraft unmanned plane before combining should utilize low coverage Data-Link to carry out networking, realize atmospheric parameter, the mutual transmission of attitude parameter and instruction, after formation all-wing aircraft Unmanned Aircraft Systems (UAS) 1 in parallel, confirm with the exercise data of a frame all-wing aircraft unmanned plane of central authorities of forming into columns for core, in conjunction with the flight parameter of the machine, calculate the controlsurface motion of the machine, to keep the smooth flight of every frame all-wing aircraft unmanned plane in formation.
Because docking mechanism 9,10 can bear the torsion of certain pitch orientation, pitching moment difference between two frame all-wing aircraft unmanned planes is in suitable scope, can be cancelled each other by docking mechanism, consistent with the pitch attitude of each all-wing aircraft unmanned plane ensureing all-wing aircraft Unmanned Aircraft Systems (UAS) 1 in parallel.After docking, all-wing aircraft unmanned plane utilizes the differential of elevon 15, carry out handling to wobble shaft and adjust, and when the luffing of all all-wing aircraft unmanned planes, all with the luffing of all-wing aircraft Unmanned Aircraft Systems (UAS) 1 in parallel always, its motion handles in the same way by the elevon 15 of each all-wing aircraft unmanned plane, make whole all-wing aircraft Unmanned Aircraft Systems (UAS) 1 in parallel have more consistent pitching moment, realize overall luffing.
And yaw direction, after all-wing aircraft unmanned plane docked, the port wingtip of right side all-wing aircraft unmanned plane and the right flank point of left side all-wing aircraft unmanned plane can be fitted completely and be locked, therefore, when the course moment of adjacent two frame all-wing aircraft unmanned planes is inconsistent, also offset by the mutual power transmission of wing tip structure of locking bonded to each other.
D. the coordinated movement of various economic factors method of unmanned plane is combined
Unmanned plane has been formed into columns docking, after forming all-wing aircraft Unmanned Aircraft Systems (UAS) 1 in parallel, mainly contains and climbs/decline and turn two kinds of mode of motion in left and right.For all-wing aircraft Unmanned Aircraft Systems (UAS) 1 in parallel, no matter carry out that motion, can only do motor-driven slowly, and fierce manipulation can not be carried out.
When carrying out the motion of climbing/declining, manipulation schemes is, utilize low coverage Data Link Communication, make every frame all-wing aircraft unmanned plane elevon 15 carry out hormany operating, when there is pitching moment difference, can docking mechanism carry-over moment be passed through, make the pitching moment between each all-wing aircraft unmanned plane basically identical, rising or falling speed is basically identical, thus realizes stable climb or declining.
When carrying out turning motion, the turn control independent with all-wing aircraft unmanned plane is completely different, the turning of all-wing aircraft Unmanned Aircraft Systems (UAS) 1 in parallel should be flat bank, namely all-wing aircraft Unmanned Aircraft Systems (UAS) 1 entirety in parallel does not carry out the turning of rolling movement, do not utilize traditional aileron control mode, but utilizing the all-wing aircraft unmanned plane outside turn direction to accelerate flight, inner side all-wing aircraft unmanned plane keeps the constant mode of flying speed to carry out turning motion.Concrete turn control might as well be described for turnon left.
When all-wing aircraft Unmanned Aircraft Systems (UAS) 1 in parallel needs turnon left, No. 2 all-wing aircraft unmanned planes of the rightmost side strengthen power and accelerate, and power reduces successively from right to left, and No. 4 all-wing aircraft unmanned planes of the leftmost side keep original power constant.Now, the all-wing aircraft unmanned plane in outside improves due to flying speed, lift on wing 11 will increase, the trend that nature climbs can be there is, therefore the reply elevon group 15 of every frame all-wing aircraft unmanned plane carries out compound manipulation, the speed of every frame all-wing aircraft unmanned plane is changed and highly constant, concrete operation method is similar with the foregoing mode changed highly.After completing turning, the Power output of every frame all-wing aircraft unmanned plane is modified to approximate value again, makes combination unmanned plane 1 reenter the state of rectilinear flight.
When needs all-wing aircraft Unmanned Aircraft Systems (UAS) 1 in parallel carries out subsonic flight, all all-wing aircraft unmanned planes should carry out driving engine simultaneously turn to, and make all-wing aircraft Unmanned Aircraft Systems (UAS) 1 in parallel form the form of a lengthening swept wing.Now the climbing of aircraft, decline and turn all with the state class of straight all-wing aircraft seemingly.
E. combination and dismission
The connection of all-wing aircraft Unmanned Aircraft Systems (UAS) 1 in parallel can be carried out on ground or in the air.If airport conditions being possessed, can dock complete in advance by some frame all-wing aircraft unmanned planes on ground, take off after forming all-wing aircraft Unmanned Aircraft Systems (UAS) 1 in parallel; Can also when surface condition to be poor, multi rack all-wing aircraft unmanned plane takes off respectively, forms into columns in Ben Chang overhead, and starts to execute the task after completing docking formation all-wing aircraft Unmanned Aircraft Systems (UAS) 1 in parallel again.
Generally speaking, whole unmanned plane form into columns should ensure to cruise as far as possible/loitering phase is in the state of all-wing aircraft Unmanned Aircraft Systems (UAS) 1 in parallel, and when needing when executing the task, needs collecting and distributing combination, start to execute the task.During dismission, should from of a leftmost side docking unlocked mechanism successively, stretch out extension bar, the all-wing aircraft unmanned plane in left side accelerates to automatically disengage formation, successively break away from the formation gradually, executes the task.When needing to reconfigure, then right-to-left docks one by one, forms all-wing aircraft Unmanned Aircraft Systems (UAS) 1 in parallel, carries out cruising or making a return voyage.
When the aircraft after having docked be subject to comparatively large disturbances time, wing tip joint exist larger stress time, wing docking leading screw 22 shoot out, locking ring 29 is untied, and the aircraft in outside accelerates break away from the formation automatically.When the most serious, the docking structure of wing tip is damaged, and each aircraft still can lean on the power of self to make a return voyage.
In actual applications, the size of aircraft is always subject to the restriction of landing site, therefore, in order to higher cruise 1ift-drag ratio and adopt high-aspect-ratio aircraft layout time, the size of aircraft can be subject to the restriction of airfield runway width, for the design or other similar designs, also take off in the face of aircraft is connected on ground simultaneously, and it is unrealistic, and the limited ground of freedom of motion of aircraft and the restriction of runway heading on the ground, carry out connecting together taking off in ground, its risk will higher than aloft docking.
The present invention also has other potential advantages.As carry out tactics dash forward anti-time, first combine the mode of unmanned plane close to the other side defence area, after being locked into target, dismissing and form into columns, implement multichannel prominent anti-, the raising completion rate of tactical mission and the serviceability rate of aircraft.In addition, adopt the present invention, the modular design of unmanned plane can be advanced, improve the commonality of unmanned aerial vehicle platform and the interchangeability of parts, reduce manufacture and usage cost.
According to foregoing disclosure, within the scope of the appended claims, other variants multiple of aircraft of the present invention, will be able to expect for those skilled in the art.Owing to can carry out various change when not deviating from scope of the present invention in aforementioned structure, all the elements that are that be thus contained in the above description or that show in the accompanying drawings, should be understood to be exemplary, instead of restrictive.
Claims (1)
1. wing tip docking can an oblique wing all-wing aircraft Unmanned Aircraft Systems (UAS) in parallel, it is characterized in that, the mode that this Unmanned Aircraft Systems (UAS) is docked by wing tip by several identical all-wing aircraft unmanned planes is formed in parallel;
Rotatable around adapter shaft in the horizontal direction between the wing of described all-wing aircraft unmanned plane and driving engine;
The mode of described wing tip docking is: the port wingtip of each all-wing aircraft unmanned plane is provided with corresponding wing tip with right flank point and docks and chart-drive mechanism, can only carry out the relative motion around abutment shaft rolling between the all-wing aircraft unmanned plane of two docking; In the docking mechanism of the right flank point of described each all-wing aircraft unmanned plane, wing tip has been installed the actuator of roller screw, actuator can drive leading screw to be stretched out along spanwise by the nut on wing tip or regain, and the right-hand member of leading screw (22) is equipped with extension bar; The docking mechanism of the port wingtip of all-wing aircraft unmanned plane is that passage is docked in the taper coordinated with to extension bar;
Wing tip is also provided with locking ring drive motor, active oblique gear, passive helical wheel and makes locking ring, drive motor and active oblique gear are connected, turning cylinder is parallel with airfoil chord length direction, passive helical wheel changes with locking the company of being fixedly connected with, turning cylinder is perpendicular to wingpiston, and active oblique gear is engaged with passive helical wheel;
When inserting docking passage to extension bar and recovery puts in place, locking ring drive motor drives active oblique gear to rotate, passive helical wheel is driven to rotate counterclockwise, make locking ring from trailing edge counterclockwise movement, until locking ring fastens extension bar, locking ring drive motor carries out brake locking, makes locking ring locked.
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| CN202686762U (en) * | 2012-05-25 | 2013-01-23 | 辽宁通用航空研究院 | Axisymmetric conjoined airplane of unit airplanes with flying wings |
| CN102658866A (en) * | 2012-05-25 | 2012-09-12 | 辽宁通用航空研究院 | Conjoined aircraft with straight layout |
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2013
- 2013-01-29 CN CN201310034166.0A patent/CN103963972B/en active Active
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