CN203889054U - Wing body rotatable and aspect ratio variable unmanned aerial vehicle - Google Patents
Wing body rotatable and aspect ratio variable unmanned aerial vehicle Download PDFInfo
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- CN203889054U CN203889054U CN201420174590.5U CN201420174590U CN203889054U CN 203889054 U CN203889054 U CN 203889054U CN 201420174590 U CN201420174590 U CN 201420174590U CN 203889054 U CN203889054 U CN 203889054U
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- 230000007246 mechanism Effects 0.000 claims abstract description 31
- 238000005096 rolling process Methods 0.000 claims description 21
- 230000003014 reinforcing effect Effects 0.000 claims description 19
- 229910003460 diamond Inorganic materials 0.000 claims description 16
- 239000010432 diamond Substances 0.000 claims description 16
- 230000001681 protective effect Effects 0.000 claims description 11
- 240000007182 Ochroma pyramidale Species 0.000 claims description 6
- 230000003068 static effect Effects 0.000 claims description 6
- 238000012856 packing Methods 0.000 claims description 5
- 230000008901 benefit Effects 0.000 abstract description 8
- 230000008859 change Effects 0.000 description 9
- 238000010586 diagram Methods 0.000 description 5
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 4
- 229910052799 carbon Inorganic materials 0.000 description 4
- 238000009434 installation Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 230000001360 synchronised effect Effects 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000001808 coupling effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
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Abstract
The utility model relates to a wing body rotatable and aspect ratio variable unmanned aerial vehicle, and belongs to the field of unmanned aerial vehicles. The unmanned aerial vehicle comprises a body, a diamond-shaped wing, a thruster and a rotation mechanism, wherein the body is connected with the diamond-shaped wing by the rotation mechanism; the thruster is arranged on the head of the body; a tail wing is arranged at the tail of the body; the diamond-shaped wing is horizontally rotated by the rotation mechanism, and a control surface is arranged on the diamond-shaped wing. The unmanned aerial vehicle disclosed by the utility model sufficiently brings inherent advantages of an aspect ratio variable airplane into play. The aerial vehicle takes off with a great aspect ratio, flies to a determined height by controlling the posture of the aerial vehicle via the control surface, then is shifted to be in a cruising flight state with a small aspect ratio, and finally lands with a great aspect ratio, so that the unmanned aerial vehicle suffers from small resistance within whole flight envelope, and can meet high-speed performance requirements and low-speed performance requirements to the greatest extent.
Description
Technical field
The utility model relates to a kind of wing body rotation and becomes aspect ratio unmanned vehicle, belongs to unmanned vehicle field.
Background technology
Becoming aspect ratio aircraft is between subsonic and hyprsonic, to change in order to solve flying speed the contradiction of bringing, and makes aircraft in the time of low speed and high-speed flight, all have good aerodynamic characteristic.Existing change aspect ratio aircraft is all in wing tip or root is installed some mechanical mechanisms, makes both sides wing rotate to change sweepback angle around certain axis simultaneously.When wing rotation, aspect ratio changes thereupon.When low sweep angle, wing aspect ratio is larger, and relative thickness is larger.In the time that sweepback angle increases, aspect ratio reduces, and relative thickness reduces, thereby makes aircraft take into account high, low speed performance requriements.But existing this aircraft aspect ratio variation range is less, match appliance system complex simultaneously.It should be noted that its sweepback angle of existing change aspect ratio aircraft changes less, make the Airfoil under large low aspect ratio state have coupling effect, can not bring into play to greatest extent the advantage that becomes aspect ratio.
Utility model content
The wing body rotation that the utility model provides becomes aspect ratio unmanned vehicle, change less for solving existing change aspect ratio aircraft aspect ratio, can not give full play to and become aspect ratio aircraft it takes into account the advantage of high, low speed flight simultaneously, the utility model has designed that a kind of aspect ratio can change between 6 and 1 and sweepback angle change reaches the change aspect ratio aircraft of 90 degree.Because the downstream direction of two state lower wings is mutually vertical, therefore two direction aerofoil profile can independent design, give full play to the advantage that becomes aspect ratio wing.
the utility model adopts following technical scheme:
Wing body rotation described in the utility model becomes aspect ratio unmanned vehicle, comprises fuselage, diamond wing, propelling unit and rotating mechanism; Described fuselage is connected with diamond wing by rotating mechanism, and the head place of fuselage is provided with propelling unit, and the tail place of fuselage is provided with empennage; Diamond wing horizontally rotates by rotating mechanism, and diamond wing is provided with rudder face.
Wing body rotation described in the utility model becomes aspect ratio unmanned vehicle, and the rudder face on described diamond wing is separately positioned on the edge of diamond wing, symmetrical before and after Airfoil.
Wing body rotation described in the utility model becomes aspect ratio unmanned vehicle, and described rotating mechanism comprises brace panel, reinforcing frame, turning cylinder, bearing arrangement, fuselage bracing means, servomechanism; Described reinforcing frame is three, the placement that is parallel to each other of three reinforcing frames, and brace panel is arranged respectively in the both sides of three reinforcing frames, the brace panel of three reinforcing frames and both sides encloses a closed frame, in three reinforcing frames, wherein between two reinforcing frames, turning cylinder is set;
The arranged beneath bearing arrangement of described closed frame, bearing arrangement is fixed on fuselage bracing means, and fuselage bracing means has servomechanism, and servomechanism is connected with turning cylinder.
Wing body described in the utility model rotation becomes aspect ratio unmanned vehicle, and described bearing arrangement comprises and increases packing ring, bearing protective case, rolling bearing, turning cylinder; In described bearing protective case, arrange rolling bearing, the top of bearing protective case is provided with increases packing ring;
Described rotating mechanism comprises upper cover plate with fuselage bracing means, padded cork wood, lower cover; The both ends of the surface up and down of padded cork wood are respectively equipped with upper cover plate and lower cover;
The turning cylinder of described servomechanism is nested with in rolling bearing; Servomechanism is arranged in the below of lower cover, and turning cylinder is through upper cover plate and lower cover; Bearing protective case is arranged in upper cover plate top.
Wing body rotation described in the utility model becomes aspect ratio unmanned vehicle, between described bearing protective case and upper cover plate, is provided with chip shield.
Wing body rotation described in the utility model becomes aspect ratio unmanned vehicle, is respectively equipped with first total rudder face and second total rudder face on described diamond wing;
Taking off, in landing state first total rudder face up and down with amplitude in the same way deflection provide pitching moment to aircraft, controlling aircraft comes back and bows, first total rudder face provides rolling moment with the reverse deflection of amplitude to aircraft, controls the left and right rolling of aircraft, and second total rudder face maintains static;
In cruising condition second total rudder face up and down with amplitude in the same way deflection provide pitching moment to aircraft, control aircraft come back and bow; Second total rudder face provides rolling moment with the reverse deflection of amplitude to aircraft, controls the left and right rolling of aircraft, and first total rudder face maintains static.
beneficial effect
The beneficial effects of the utility model are to give full play to the intrinsic advantage that becomes aspect ratio aircraft.Aircraft takes off with the state of high aspect ratio, specified altitude assignment is arrived in attitude flight by rudder face control aircraft, after aircraft reaches certain speed and settles out, under the driving of servomechanism, utilizing rotating mechanism to make diamond wing and fuselage that 90 degree occur rotates, be transformed into the state flight of low aspect ratio, and enable another set of rudder face control aspect, in the time that aircraft is about to landing, the state that converts back high aspect ratio by identical action lands, by such flying method, make aircraft in whole flight envelope, all there is less resistance, make aircraft can take into account to greatest extent height, low-speed performance requirement.
Brief description of the drawings
Schematic diagram when Fig. 1 is the utility model high aspect ratio;
Flight schematic diagram when Fig. 2 is the utility model high aspect ratio;
Schematic diagram when Fig. 3 is the utility model low aspect ratio;
Flight schematic diagram when Fig. 4 is the utility model low aspect ratio;
Fig. 5 is that wing shapes of the present utility model and rudder face are arranged;
Fig. 6 is airframe structure arrangement plan of the present utility model;
Fig. 7 is engine installation structural representation of the present utility model;
Fig. 8 a is afterbody exterior view of the present utility model;
Fig. 8 b is tail structure schematic diagram of the present utility model;
Fig. 9 is the structural representation of the utility model rotating mechanism;
Figure 10 is the inner structure exploded view of the utility model rotating mechanism;
Figure 11 is the constructional drawing of the utility model wing.
Detailed description of the invention
Below in conjunction with accompanying drawing, the utility model is further described
In Fig. 1, shown the view of aircraft high aspect ratio, this kind of state of flight be aircraft be in take off, the landing stage, there is length, aspect ratio is larger, low-speed operations low resistance and other advantages.
In Fig. 2, flight attitude while having shown aircraft high aspect ratio, now the total rudder face 4 of wing first, vertical fin rudder face 6 is in running order by control system, the total rudder face 5 of wing second is zero degree in off working state and angle of inclination, be equivalent to not play the effect that increases lift, two driving engines 3 are by the adjusting of control system, in flight course, carry out equidirectional, with the deflection up and down of amplitude, in the time taking off and land, the pitching characteristic of controlling aircraft with the total rudder face 4 of wing first together with vertical fin rudder face 6, can make aircraft reach the advantage of short take-off and landing (STOL).
The advantages such as this kind of state of flight is that aircraft is in cruising phase in Fig. 3, has length, aspect ratio is less, and at a high speed lower flight resistance is low.
In Fig. 4, flight attitude while having shown aircraft low aspect ratio, now the total rudder face 5 of wing second is in running order by control system, the total rudder face 4 of wing first is zero degree in off working state and angle of inclination, be equivalent to not play the effect that increases lift, two driving engines 3 are by the adjusting of control system, in flight course, carry out reversing sense, with the deflection up and down of amplitude, effectively improve the wing rudder face arm of force shorter, control the poor shortcoming of aircraft ability, in cruising phase, work rolling and the yawing characteristic of controlling aircraft with wing rudder face, can make the aircraft can smooth flight in the situation that of flow perturbation.
In Fig. 5, show the layout of two cover flight rudder faces, being different from conventional rudder face is arranged symmetrically with, the rudder face of this aircraft is arranged the feature that presents three rudder faces of one side, a rudder face of one side, by designing the control system of a set of uniqueness, utilize the mechanism of control system, cireular frequency and the overload signal of introducing aircraft form closed loop control, the second total rudder face 5 using when the first total rudder face 4 using while making high aspect ratio flight and low aspect ratio flight can independently carry out work, and respectively the aircraft under two states is carried out to attitude control.Because aircraft needs to carry out the conversion of large low aspect ratio aloft, all class diamond wing aspects of symmetry of all around are therefore designed.
Taking off, in landing process, Wing-Body Configurations relative position is as Fig. 1, first total rudder face 4 up and down with amplitude in the same way deflection provide pitching moment to aircraft, controlling aircraft comes back and bows, first total rudder face 4 provides rolling moment with the reverse deflection of amplitude to aircraft, control the left and right rolling of aircraft, now second total rudder face 5 maintains static; In the process of cruising, Wing-Body Configurations relative position is as Fig. 3, second total rudder face 5 up and down with amplitude in the same way deflection provide pitching moment to aircraft, control aircraft and come back and bow; Second total rudder face 5 provides rolling moment with the reverse deflection of amplitude to aircraft, controls the left and right rolling of aircraft; Now first total rudder face 4 maintains static.The motion of all rudder faces is all separately by a small-sized servo control, and small-sized servo principle is consistent with servomechanism 44.Due to the setting of two cover rudder faces, aircraft is seen down from top, present three rudder faces of one side, the layout of a rudder face of one side.
In Fig. 6, show aircraft fuselage structure arrangement plan, forebody reinforcing frame 17 is connected with forebody base plate 21 below, left and right is connected with forebody side plate 22, front portion is connected with forebody cover plate 18, forebody cover plate 18 is connected with driving engine installation side plate 19 simultaneously, form semiclosed frame, the concentrated force at driving engine place is delivered in frame, can effectively bear moment of torsion and moment of flexure stress, several opening frames that forebody reinforcing frame 17 forms, sufficient space placing battery is provided, receiver, the space of the electronic original parts such as control system circuit card, at fuselage 20 places, space foremost, lay the small-sized servomechanism of control engine, for the motion of control engine, also play the effect of access opening simultaneously.At rear body, rear body reinforcing frame 23 is connected with rear body side plate 24, rear body cover plate 25, and at rear body reinforcing frame 23 sealed bottoms, forms rear body frame, and forward and backward fuselage connects at bolt hole place 26.
In Fig. 7, show the engine installation of aircraft, two clamping plates 28 wraps driving engine 27, form sealing circle by reinforced plate 29, and be connected with reinforcement end plate 30, be connected to forebody front end, by the design of clamping plate 28, reinforced plate 29, driving engine can be disassembled from aircraft, facilitate examination and maintenance.
In Fig. 8 a and Fig. 8 b, show the vertical fin peace caudal knot composition of aircraft, aircraft horizontal tail 31 is connected by bolt 33 with vertical fin 32, in vertical fin 32 inside, form inner skeleton figure by dull and stereotyped rib 34 and brace panel 35, brace panel 35 is connected with carbon pipe 36 in vertical fin 32 bottoms, carbon pipe 36 is inserted in rear body frame, overall load.
In Fig. 9, show the design drawing of rotating mechanism, mainly containing upper and lower two parts forms, three reinforcing frames 38 of upper part form a sealing frame with both sides brace panel 37, by being connected with rear body with forebody at bolt hole place 40, make like this part on rotating mechanism be linked to be together and be synchronized with the movement with fuselage.The lower part of rotating mechanism is made up of with fuselage bracing means 42 and servomechanism 44 bearing arrangement 41, rotating mechanism, wherein wing carbon pipe is connected with fuselage bracing means 42 with rotating mechanism at 43 places, position, make under rotating mechanism part and wing be synchronized with the movement, rotating mechanism top and the bottom are connected by turning cylinder 39.Servomechanism 44 can be under the control of remote control, and the rotation of 90 degree occurs servomechanism output shaft, thereby drive turning cylinder 39 to rotate.Fuselage is connected with wing by rotating mechanism main shaft, and in the time that rotating mechanism main shaft rotates, engine installation occurs to rotate relative to 90 degree with wing, thereby the aspect ratio of wing is switched between 6 and 1.(under the state of high aspect ratio, aspect ratio is 6, and under the state of low aspect ratio, aspect ratio is 1).
In Figure 10, show the broken away view of rotating mechanism; rotating mechanism internal main will form by increasing packing ring 45, bearing protective case 46, rolling bearing 47, chip shield 48, turning cylinder 39, upper cover plate 50, padded cork wood 51, lower cover 52, servomechanism 44; wherein; rolling bearing 47 is placed in bearing protecting jacket 46 inside; upper cover plate 50, padded cork wood 51, lower cover 52 link into an integrated entity by bolt 54; servomechanism 44 is fixed on lower cover 52 places, and servomechanism output shaft is connected with turning cylinder 39.
In Figure 11, shown the constructional drawing of wing, wing load-carrying construction is mainly made up of carbon pipe 55, rib 57, stringer 58, and covers with light composite material thereon, forms whole wing.In whole wing, have two to overlap independently rudder face, the second total rudder face 5 using when the first total rudder face 4 using while being low speed respectively and high speed.In the time of low speed, near first total rudder face 4, a Servo-controller 59 is set respectively, in Figure 11, respectively there is up and down one, for controlling the motion of rudder face when the low speed, now Servo-controller 61 is controlled second total rudder face 5 transfixions.In the time of high speed, near second total rudder face 5, a Servo-controller 61 is set respectively, in Figure 11, left and right respectively has one, and for controlling the motion of rudder face when the high speed, now Servo-controller 59 is controlled first total rudder face 4 transfixions.
Claims (6)
1. the rotation of wing body becomes aspect ratio unmanned vehicle, it is characterized in that: comprise fuselage (1), diamond wing (2), propelling unit (3) and rotating mechanism; Described fuselage is connected with diamond wing by rotating mechanism, and the head place of fuselage is provided with propelling unit, and the tail place of fuselage is provided with empennage; Diamond wing horizontally rotates by rotating mechanism, and diamond wing is provided with rudder face.
2. wing body rotation according to claim 1 becomes aspect ratio unmanned vehicle, it is characterized in that: the rudder face on described diamond wing (2) is separately positioned on the edge of diamond wing, symmetrical before and after Airfoil.
3. wing body rotation according to claim 1 becomes aspect ratio unmanned vehicle, it is characterized in that: described rotating mechanism comprises brace panel (37) reinforcing frame (38), turning cylinder (39), bearing arrangement (41), rotating mechanism is with fuselage bracing means (42), servomechanism (44); Described reinforcing frame (38) is three, three reinforcing frames (38) placement that is parallel to each other, brace panel (37) is arranged respectively in the both sides of three reinforcing frames (38), three reinforcing frames (38) enclose a closed frame with the brace panel (37) of both sides, between wherein two reinforcing frames (38) in three reinforcing frames (38), turning cylinder (39) are set;
The arranged beneath bearing arrangement (41) of described closed frame, it is upper that bearing arrangement (41) is fixed on fuselage bracing means (42), and rotating mechanism has servomechanism (44) with fuselage bracing means (42), and servomechanism (44) is connected with turning cylinder (39).
4. wing body according to claim 3 rotation becomes aspect ratio unmanned vehicle, it is characterized in that: described bearing arrangement (41) comprises and increases packing ring (45), bearing protective case (46), rolling bearing (47), turning cylinder (39); In described bearing protective case (46), arrange rolling bearing (47), the top of bearing protective case (46) is provided with increases packing ring (45), and turning cylinder (39) is nested with in rolling bearing (47);
Described rotating mechanism comprises upper cover plate (50) with fuselage bracing means (42), padded cork wood (51), lower cover (52); The both ends of the surface up and down of described padded cork wood (51) are respectively equipped with upper cover plate (50) and lower cover (52);
Described servomechanism (44) is arranged in the below of lower cover (52), and turning cylinder (39) is through upper cover plate (50) and lower cover (52); Bearing protective case (46) is arranged in upper cover plate (50) top.
5. wing body rotation according to claim 4 becomes aspect ratio unmanned vehicle, it is characterized in that: between described bearing protective case (46) and upper cover plate (50), be provided with chip shield (48).
6. wing body rotation according to claim 4 becomes aspect ratio unmanned vehicle, it is characterized in that: on described diamond wing, be respectively equipped with first total rudder face (4) and second total rudder face (5);
Taking off, in landing state first total rudder face (4) up and down with amplitude in the same way deflection provide pitching moment to aircraft, controlling aircraft comes back and bows, first total rudder face (4) provides rolling moment with the reverse deflection of amplitude to aircraft, control the left and right rolling of aircraft, second total rudder face (5) maintains static;
In cruising condition second total rudder face (5) up and down with amplitude in the same way deflection provide pitching moment to aircraft, control aircraft come back and bow; Second total rudder face (5) provides rolling moment with the reverse deflection of amplitude to aircraft, controls the left and right rolling of aircraft, and first total rudder face (4) maintains static.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420174590.5U CN203889054U (en) | 2014-04-11 | 2014-04-11 | Wing body rotatable and aspect ratio variable unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420174590.5U CN203889054U (en) | 2014-04-11 | 2014-04-11 | Wing body rotatable and aspect ratio variable unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203889054U true CN203889054U (en) | 2014-10-22 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420174590.5U Expired - Lifetime CN203889054U (en) | 2014-04-11 | 2014-04-11 | Wing body rotatable and aspect ratio variable unmanned aerial vehicle |
Country Status (1)
| Country | Link |
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| CN (1) | CN203889054U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104015922A (en) * | 2014-04-11 | 2014-09-03 | 南京航空航天大学 | Unmanned aerial vehicle with rotary wing body and variable aspect ratio |
| CN105711808A (en) * | 2016-01-19 | 2016-06-29 | 林建民 | Unmanned aerial vehicle for landscaping |
-
2014
- 2014-04-11 CN CN201420174590.5U patent/CN203889054U/en not_active Expired - Lifetime
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104015922A (en) * | 2014-04-11 | 2014-09-03 | 南京航空航天大学 | Unmanned aerial vehicle with rotary wing body and variable aspect ratio |
| CN104015922B (en) * | 2014-04-11 | 2016-08-24 | 南京航空航天大学 | Wing body rotates and becomes aspect ratio unmanned vehicle |
| CN105711808A (en) * | 2016-01-19 | 2016-06-29 | 林建民 | Unmanned aerial vehicle for landscaping |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20141022 Effective date of abandoning: 20160824 |
|
| C25 | Abandonment of patent right or utility model to avoid double patenting |