CN105523172A - Attack angle control system and attack angle control method - Google Patents

Attack angle control system and attack angle control method Download PDF

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Publication number
CN105523172A
CN105523172A CN201610013369.5A CN201610013369A CN105523172A CN 105523172 A CN105523172 A CN 105523172A CN 201610013369 A CN201610013369 A CN 201610013369A CN 105523172 A CN105523172 A CN 105523172A
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China
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angle
wing
fixed
attack
lifting
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CN201610013369.5A
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Chinese (zh)
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CN105523172B (en
Inventor
李吉
刘良存
杜定钟
彭智川
曾双友
淡俊杰
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成都学尚科技有限公司
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    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C13/00Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers

Abstract

The invention provides an attack angle control system and an attack angle control method, and belongs to the field of aircrafts. The attack angle control system is used for controlling the attack angle of a fixed wing; the fixed wing is connected with a machine frame, and comprises a hinge and an attack angle control mechanism, wherein a cross rod of the machine frame is connected with a vertical rod of the machine frame; the vertical rod is connected with the fixed wing through the hinge; the attack angle control mechanism is used for adjusting an inclined angle between the fixed wing and the machine frame. According to the attack angle control method, the attack angle control system is adopted. According to the attack angle control system and the attack angle control method disclosed by the invention, the attack angle of the fixed wing can be controlled through the attack angle control mechanism and the hinge, so that the attack angle of an aircraft during ascending, descending and flying can be real-time controlled, normal operation of the aircraft during ascending and descending is guaranteed, and smooth flight is guaranteed.

Description

Angle of attack control system and angle of attack control method

Technical field

The present invention relates to aircraft field, in particular to a kind of angle of attack control system and angle of attack control method.

Background technology

At present, aeromodelling aerocraft of a great variety, such as four-axle aircraft and fixed-wing unmanned plane etc.

The rotor of four-axle aircraft is symmetrically distributed in all around four direction of body, four rotors are in sustained height plane, and the structure of four rotors and radius are all identical, the bracket end being arranged on aircraft of four motor symmetries, support intermediate space lays flight-control computer and external device.Four-axle aircraft changes gyroplane rotate speed by regulating four motor speeds, realizes the change of lift, thus controls attitude and the position of aircraft, and the electric energy consumed in the process regulated is larger, the problem that high energy consumption directly causes cruise duration short; Four-axle aircraft flying speed is slow, and the vertical uplift maximum speed of the middle-size and small-size four-axle aircraft of current higher-end is generally 9m/s, and horizontal velocity is maximum only has 25m/s; Because cruise duration is short, flying speed is slow, causes such as transporting, express delivery, line walking etc. be all difficult to effective realization.The application of current four-axle aircraft great majority is all carried out in extremely finite space, time range.

General fixed-wing model plane are the electrical motor carrying screws high-speed operations relying on head, and then provide thrust, when thrust is greater than the friction drag of pulley, aircraft will travel forward.Fixed wing aircraft aloft flying speed is very fast, needs steering hand to have good capability of reaction, and also have stronger operation skill, compared to multiaxis unmanned plane, operation is more complicated.In addition, because fixed-wing unmanned plane only has a screw propeller providing thrust, and direction is level, in the vertical direction of aircraft, additional power does not carry out the gravity of balance airplane body, there is no additional power to adjust the attitude of aircraft, so when fixed-wing can only aloft fly, the lift utilizing wing and empennage to produce and other power, balance could be kept, and can not hover over aerial.

In addition, why fixed-wing unmanned plane can fly up, and is that the effect of wing and air produces lift because the lift of wing overcomes gravity.Cause wing to produce the reason of application force to have two: A, asymmetric aerofoil profile; B, wing and relative wind have the angle of attack.Aerofoil profile is the shape of wing profile.Wing profile mostly is asymmetrical type, following arc is straight upper arc K/UP and upper arc all K/UPs.Symmetrical airfoil then must have certain angle of attack to produce lift.The size of lift depends primarily on four factor: A, lift and is directly proportional to wing area; Square being directly proportional of B, lift and air speed.Under similarity condition, the faster lift of flying speed is larger; C, lift are relevant with aerofoil profile, and the lift of usual asymmetric aerofoil profile wing is larger; D, lift are relevant with the angle of attack, and during low incidence, lift (coefficient) increases with angle of attack straight line, and after certain limit, angle of attack increase lift reduces on the contrary rapidly, and the critical angle of attack is in this boundary.Wing and horizontal displacement also produce resistance except generation lift, and miscellaneous part generally only produces resistance.

In addition, one is had to take into account vertical takeoff and landing, hovering, fast, the high-time aircraft of flying speed, fixed-wing unmanned aerial vehicle body is adopted to match with multiaxis screw propeller, multiaxis pattern, fixed-wing pattern and fixed-wing and multiaxis mixed mode can be realized, realized the switching of each pattern by the S. A. rotating this aircraft multiaxis screw propeller.In addition, how the angle of attack of this aircraft controls, and becomes the gordian technique of taking off with smooth flight.

Summary of the invention

The invention provides a kind of angle of attack control system and angle of attack control method, be intended to improve the problems referred to above.

The present invention is achieved in that

A kind of angle of attack control system, for controlling the angle of attack of fixed-wing, described fixed-wing is connected with frame, comprise hinge and angle of attack control mechanism, the cross bar of described frame is connected with montant, described montant and described fixed-wing are by described chain connection, and described angle of attack control mechanism is for regulating the angle between described fixed-wing and described frame.

Further, described angle of attack control mechanism comprises control module, lifting drive and jacking system, described control module and described lifting drive are installed in described frame, described control module is connected with described lifting drive, described lifting drive is connected with described jacking system, and described jacking system is connected with described fixed-wing.

Control module controls lifting drive work, lifting drive drives jacking system action, jacking system drives one end lifting of fixed-wing, and fixed-wing and montant are connected through the hinge, so the point of connection of fixed-wing when being elevated around itself and montant rotates, the invariant position of frame, then the angle between fixed-wing and frame changes, thus achieves the control of the angle of attack of fixed-wing.

Further, described jacking system comprises lifting bar and transmission device, and described transmission device is connected with described lifting drive, and described transmission device is connected with described lifting bar, and described lifting bar is connected with described fixed-wing.

Lifting drive drive transmission device, transmission device drive lifting bar, lifting bar can be elevated thus drives fixed-wing one end be elevated and around hinge through.

Further, described lifting bar is tooth bar, and described transmission device is lifting driven wheel, and described tooth bar engages with described lifting driven wheel, and described tooth bar is connected with described fixed-wing away from one end of described lifting driven wheel.

Under the driving of lifting drive, lifting driven wheel rotates, band carry-over bar up-and-down movement, one end lifting of rack drives fixed-wing around hinge through.The structure adopting lifting driven wheel and tooth bar to coordinate, can make lifting more quick, stable drive, be easy to control.

Further, described lifting bar is slide block, and described transmission device is screw rod, and described slide block coordinates with described screw rod, and described slide block is connected with described fixed-wing away from one end of described screw rod.

Under the driving of lifting drive, bolt rotary, simultaneously slide block can along screw rod moving linearly, thus drive fixed-wing one end lifting and around hinge through.The structure adopting screw rod and slide block to match, can make lifting steady, is convenient to control.

Further, the point of connection of described lifting bar and described fixed-wing is higher than the hinge-point of described hinge, and described angle of attack control mechanism is arranged between the head of described hinge and described fixed-wing.

When taking off, adjusted the hinge-point of point of connection higher than hinge of lifting bar and fixed-wing by angle of attack control mechanism, the head of such fixed-wing upwards lifts, and forms positive lift force stagger angle between fixed-wing and frame, can produce positive lift force.

Further, also comprise lifting attaching parts, described lifting attaching parts comprises the first clamping plate and the second clamping plate, described frame is provided with pipe link, described pipe link is fixed between described first clamping plate and described second clamping plate, and described control module and described lifting drive are installed on described first clamping plate.

By arranging the first clamping plate and the second clamping plate, pipe link firmly can be clamped between the first clamping plate and the second clamping plate, and the installation of control module and lifting drive can be made more firm.

Further, described hinge comprises hinge connector and rotating shaft, and described rotating shaft is connected with described fixed-wing, and described hinge connector is provided with bearing, and described rotating shaft is through described bearing, and described montant and described rotating shaft are rotationally connected by described hinge connector.

Fixed-wing is when rotating, and rotating shaft is rotated by bearing, thus can carry out the control of the angle of attack better.

Further, described hinge connector comprises T-connecting piece and adapter plate, and described bearing is arranged on one end of described T-connecting piece, and described montant is fixed between described T-connecting piece and described adapter plate.

By arranging T-connecting piece and adapter plate, can firmly montant be fixed between T-connecting piece and adapter plate.

Present invention also offers a kind of angle of attack control method, solve the problem with auxiliary, the process employs above-mentioned arbitrary angle of attack control system, the method comprises, utilize described angle of attack control mechanism that described fixed-wing is rotated around described montant by described hinge, to regulate the angle between described fixed-wing and described frame.

The beneficial effect of angle of attack control system provided by the invention and angle of attack control method is: this angle of attack control system regulates the angle between fixed-wing and frame by angle of attack control mechanism, when regulating, fixed-wing is rotated by the point of connection of hinge around itself and montant, thus realizes the control to the angle of attack of fixed-wing.Angle of attack control system provided by the invention and angle of attack control method can control the angle of attack of fixed-wing by angle of attack control mechanism and hinge, aircraft can be regulated by the angle of attack in landing and flight course in real time, ensure normally carrying out of landing, ensure smooth flight.

Accompanying drawing explanation

In order to be illustrated more clearly in the technical scheme of the embodiment of the present invention, be briefly described to the accompanying drawing used required in embodiment below, be to be understood that, the following drawings illustrate only some embodiment of the present invention, therefore the restriction to scope should be counted as, for those of ordinary skill in the art, under the prerequisite not paying creative work, other relevant accompanying drawings can also be obtained according to these accompanying drawings.

The structural representation of the angle of attack control system that Fig. 1 provides for first embodiment of the invention;

The structural representation of the angle of attack control mechanism of the angle of attack control system that Fig. 2 provides for first embodiment of the invention;

The structural representation of the hinge of the angle of attack control system that Fig. 3 provides for first embodiment of the invention;

The integral structure schematic diagram of the fixed-wing Multi-axis aircraft that Fig. 4 applies for the angle of attack control system that first embodiment of the invention provides;

Wherein a kind of state of flight figure of aircraft when the angle of attack control system that Fig. 5 provides for first embodiment of the invention is on fixed-wing Multi-axis aircraft;

The another kind of state of flight figure of aircraft when the angle of attack control system that Fig. 6 provides for first embodiment of the invention is on fixed-wing Multi-axis aircraft.

Figure acceptance of the bid note is respectively:

Fixed-wing 101; Frame 102; Hinge 103; Angle of attack control mechanism 104; Cross bar 105; Montant 106; Lifting drive 107; Tooth bar 108; Lifting driven wheel 109; Lifting attaching parts 110; First clamping plate 111; Second clamping plate 112; Pipe link 113; Hinge connector 114; T-connecting piece 115; Adapter plate 116; Rotating shaft 117; Screw propeller 118; Rotation control mechanism 119; S. A. 120.

Detailed description of the invention

For making the object of the embodiment of the present invention, technical scheme and advantage clearly, below in conjunction with the accompanying drawing in the embodiment of the present invention, technical scheme in the embodiment of the present invention is clearly and completely described, obviously, described embodiment is the present invention's part embodiment, instead of whole embodiments.The assembly of the embodiment of the present invention describing and illustrate in usual accompanying drawing herein can be arranged with various different configuration and design.Therefore, below to the detailed description of the embodiments of the invention provided in the accompanying drawings and the claimed scope of the present invention of not intended to be limiting, but selected embodiment of the present invention is only represented.Based on the embodiment in the present invention, those of ordinary skill in the art, not making the every other embodiment obtained under creative work prerequisite, belong to the scope of protection of the invention.

First embodiment

Present embodiments provide a kind of angle of attack control system, on aircraft, control the angle of attack of fixed-wing 101.The present embodiment is applied as example with this angle of attack control system on fixed-wing Multi-axis aircraft, illustrates structure and the principle of this angle of attack control system.

Refer to Fig. 1, the fuselage of fixed-wing Multi-axis aircraft is fixed-wing 101, fixed-wing 101 is connected with frame 102, frame 102 is provided with S. A. 120, S. A. 120 with for driving the actuating device of screw propeller 118 to be fixedly connected with, actuating device is connected with screw propeller 118, and screw propeller 118 is multiple, each screw propeller 118 connects an actuating device, and actuating device is motor.In addition, can be that a screw propeller 118 is equipped with a S. A. 120, also can be that a S. A. 120 installs multiple screw propeller 118, with four screw propellers 118, every two totally one S. A. 120 be example.In addition, frame 102 is provided with rotation control mechanism 119, for controlling the rotation of S. A. 120.This rotation control mechanism 119 comprises control setup and transmission gear, and transmission gear fixed cover is located on S. A. 120, and control setup is connected by drive mechanism with transmission gear.

The principle of work of this fixed-wing Multi-axis aircraft is: when landing, adopt multijoint control pattern, the rotational plane level of screw propeller 118 rotation, by actuating device carrying screws 118 rotation, for aircraft provides lift, vertical takeoff and landing makes aircraft takeoff no longer retrain by topographic condition, can complete to take off, land in any landform; After having taken off, adopt fixed-wing 101 pattern, rotation control mechanism 119 has controlled S. A. 120 half-twist, makes the rotational plane of screw propeller 118 rotation vertical, by actuating device carrying screws 118 rotation, for aircraft provides thrust; In flight course, can adopt fixed-wing 101 and multiaxis mixed mode, rotation control mechanism 119 through hole controls the rotational angle of S. A. 120 and coordinates the rotation of screw propeller 118, controls the state of flight of aircraft, has stable, operating feature flexibly.Thus, multiaxis pattern, fixed-wing 101 pattern and fixed-wing 101 and multiaxis mixed mode can be realized, vertical takeoff and landing, hovering, fast, the high-time feature of flying speed can be taken into account.

Refer to Fig. 1 and Fig. 2, this angle of attack control system comprises hinge 103 and angle of attack control mechanism 104, the cross bar 105 of frame 102 is connected with montant 106, and montant 106 is connected by hinge 103 with fixed-wing 101, and angle of attack control mechanism 104 is for regulating the angle between fixed-wing 101 and frame 102.

This angle of attack control system regulates the angle between fixed-wing 101 and frame 102 by angle of attack control mechanism 104, and when regulating, fixed-wing 101 is rotated around its point of connection with montant 106 by hinge 103, thus the control of realization to the angle of attack of fixed-wing 101.Angle of attack control system provided by the invention can control the angle of attack of fixed-wing 101 by angle of attack control mechanism 104 and hinge 103, aircraft can be regulated by the angle of attack in landing and flight course in real time, ensure normally carrying out of landing, ensure smooth flight.

Refer to Fig. 1, Fig. 4 ~ Fig. 6, the angle of attack Control System Design of fixed-wing Multi-axis aircraft, make aircraft held stationary flight in offline mode switching process.From the switching process vertically rising to horizontal flight, first use multijoint control pattern, four screw propeller 118 entirety turned forward, start flight forward, in the process rotated forward, four motors are in same plane.Multiaxis oar causes the angle of attack to reduce towards aircraft entirety can be caused during top rake to lean forward, and regulates the change in angle of attack because causing in switching process by the control of angle of attack control system.When needing in flight course to change the angle of attack, regulate the angle of attack by angle of attack control system.Fixed-wing 101 offline mode can be switched to when the speed of flying reaches when fixed-wing 101 can produce enough lift.

Refer to Fig. 1 and Fig. 2, angle of attack control mechanism 104 comprises control module, lifting drive 107 and jacking system, control module and lifting drive 107 are installed in frame 102, control module is connected with lifting drive 107, lifting drive 107 is connected with jacking system, and jacking system is connected with fixed-wing 101.

Control module controls lifting drive 107 and works, lifting drive 107 drives jacking system action, jacking system drives one end lifting of fixed-wing 101, and fixed-wing 101 and montant 106 are connected by hinge 103, so the point of connection of fixed-wing 101 when being elevated around itself and montant 106 rotates, the invariant position of frame 102, then the angle between fixed-wing 101 and frame 102 changes, thus achieves the control of the angle of attack of fixed-wing 101.

Refer to Fig. 1 and Fig. 2, jacking system comprises lifting bar and transmission device, and transmission device is connected with lifting drive 107, and transmission device is connected with lifting bar, and lifting bar is connected with fixed-wing 101.

Lifting drive 107 drive transmission device, transmission device drives lifting bar, and lifting bar can be elevated thus drive one end of fixed-wing 101 be elevated and rotate around hinge 103.

Refer to Fig. 2, lifting bar is tooth bar 108, and transmission device is for being elevated driven wheel 109, and tooth bar 108 engages with lifting driven wheel 109, and tooth bar 108 is connected with fixed-wing 101 away from one end of lifting driven wheel 109.

Under the driving of lifting drive 107, lifting driven wheel 109 rotates, and band carry-over bar 108 up-and-down movement, tooth bar 108 drives one end of fixed-wing 101 be elevated and rotate around hinge 103.The structure adopting lifting driven wheel 109 and tooth bar 108 to coordinate, can make lifting more quick, stable drive, be easy to control.

In addition, lifting bar also can be slide block, and transmission device can be also screw rod (illustrating not shown), and slide block coordinates with screw rod, and slide block is connected with fixed-wing 101 away from one end of screw rod.Under the driving of lifting drive 107, bolt rotary, slide block along screw rod moving linearly, thus can drive one end of fixed-wing 101 lifting and rotates around hinge 103 simultaneously.The structure adopting screw rod and slide block to match, can make lifting steady, is convenient to control.

Refer to Fig. 1, the point of connection of lifting bar and fixed-wing 101 is higher than the hinge-point of hinge 103, and angle of attack control mechanism 104 is arranged between the head of hinge 103 and fixed-wing 101.

When taking off, the hinge-point of point of connection higher than hinge 103 of lifting bar and fixed-wing 101 is adjusted by angle of attack control mechanism 104, the head of such fixed-wing 101 upwards lifts, and is formed " positive lift force stagger angle ", can produce positive lift force between fixed-wing 101 and frame 102.

" positive lift force stagger angle " design of fixed-wing Multi-axis aircraft, makes aircraft held stationary flight in offline mode switching process.From the switching process vertically rising to horizontal flight, use multijoint control pattern, multiaxis oar, towards top rake, flies forward.Multiaxis oar certainly will cause aircraft entirety to lean forward towards top rake producing the negative angle of attack, hinder wing to produce positive lift force.Initial settling angle and the design of the adjustable angle of attack, take into account multiaxis forward leaning angle, make wing have larger stagger angle with multi-axle planar when mounted, ensureing that wing still can produce positive lift force when leaning forward flight, overcoming the contradiction that multiaxis and fixed-wing 101 merge.Obtain enough horizontal velocities with multiaxis offline mode, reach flying speed when requiring, then switch to fixed-wing 101 pattern, thus ensure that by multiaxis pattern switch to fixed-wing 101 pattern steadily and safety.Be multiaxis pattern from fixed-wing 101 patten transformation and carry out the process of landing, then under fixed-wing 101 pattern, open multiaxis pattern, reduce flying speed gradually, reduce the lift of wing generation and substituted by rotor lift gradually, multiaxis pattern is taken over after fixed-wing 101 completes, and realizes vertical landing with multiaxis pattern.Positive lift force stagger angle can manual regulation, to the position needed.

Refer to Fig. 2, this angle of attack control system also comprises lifting attaching parts 110, lifting attaching parts 110 comprises the first clamping plate 111 and the second clamping plate 112, frame 102 is provided with pipe link 113, pipe link 113 is fixed between the first clamping plate 111 and the second clamping plate 112, and control module and lifting drive 107 are installed on the first clamping plate 111.

By arranging the first clamping plate 111 and the second clamping plate 112, pipe link 113 firmly can be clamped between the first clamping plate 111 and the second clamping plate 112, and the installation of control module and lifting drive 107 can be made more firm.

Refer to Fig. 3, hinge 103 comprises hinge connector 114 and rotating shaft 117, and rotating shaft 117 is connected with fixed-wing 101, and hinge connector 114 is provided with bearing, and rotating shaft 117 is through bearing, and montant 106 and rotating shaft 117 part 114 that is connected through the hinge is rotationally connected.

Fixed-wing 101 is when rotating, and rotating shaft 117 is rotated by bearing, thus can carry out the control of the angle of attack better.

Refer to Fig. 3, hinge connector 114 comprises T-connecting piece 115 and adapter plate 116, and bearing is arranged on one end of T-connecting piece 115, and montant 106 is fixed between T-connecting piece 115 and adapter plate 116.

By arranging T-connecting piece 115 and adapter plate 116, can firmly montant 106 be fixed between T-connecting piece 115 and adapter plate 116.

Hinge connector 114 is two, and the two ends of rotating shaft 117 are connected with fixed-wing 101 respectively, and the cross bar 105 of frame 102 is two, and every root cross bar 105 is all connected with a montant 106, and two hinge connectors 114 are respectively connected with a montant 106.

Adopt two hinge connectors 114, the two ends of countershaft 117 can play a supporting role, make fixed-wing 101 stability of rotation, make the control of the angle of attack and regulate more accurate.

Second embodiment

Present embodiments provide a kind of angle of attack control method, the process employs the angle of attack control system that the first embodiment provides, the method comprises, and utilizes angle of attack control mechanism 104 that fixed-wing 101 is rotated around montant 106 by hinge, to regulate the angle between fixed-wing 101 and frame 102.

Specifically, control module controls lifting drive 107 and works, lifting drive 107 drives jacking system action, jacking system drives one end lifting of fixed-wing 101, and fixed-wing 101 and montant 106 are connected by hinge 103, so the point of connection of fixed-wing 101 when being elevated around itself and montant 106 rotates, the invariant position of frame 102, angle then between fixed-wing 101 and frame 102 changes, thus achieves the control of the angle of attack of fixed-wing 101.

Under the driving of lifting drive 107, lifting driven wheel 109 rotates, and band carry-over bar 108 up-and-down movement, tooth bar 108 drives one end of fixed-wing 101 be elevated and rotate around hinge 103.Thus realize the control of the angle of attack.

In describing the invention, it will be appreciated that, term " " center ", " longitudinal direction ", " transverse direction ", " length ", " width ", " thickness ", " on ", D score, " front ", " afterwards ", " left side ", " right side ", " vertically ", " level ", " top ", " end " " interior ", " outward ", " cw ", orientation or the position relationship of the instruction such as " conter clockwise " are based on orientation shown in the drawings or position relationship, only the present invention for convenience of description and simplified characterization, instead of indicate or imply that the equipment of indication or element must have specific orientation, with specific azimuth configuration and operation, therefore limitation of the present invention can not be interpreted as.

In addition, term " first ", " second " only for describing object, and can not be interpreted as instruction or hint relative importance or imply the quantity indicating indicated technical characteristic.Thus, be limited with " first ", the feature of " second " can express or impliedly comprise one or more these features.In describing the invention, the implication of " multiple " is two or more, unless otherwise expressly limited specifically.

In the present invention, unless otherwise clearly defined and limited, the term such as term " installation ", " being connected ", " connection ", " fixing " should be interpreted broadly, and such as, can be fixedly connected with, also can be removably connect, or integral; Can be mechanical connection, also can be electrical connection; Can be directly be connected, also indirectly can be connected by intermediary, can be the connection of two element internals or the interaction relationship of two elements.For the ordinary skill in the art, above-mentioned term concrete meaning in the present invention can be understood as the case may be.

In the present invention, unless otherwise clearly defined and limited, fisrt feature second feature it " on " or D score can comprise the first and second features and directly contact, also can comprise the first and second features and not be directly contact but by the other characterisation contact between them.And, fisrt feature second feature " on ", " top " and " above " comprise fisrt feature directly over second feature and oblique upper, or only represent that fisrt feature level height is higher than second feature.Fisrt feature second feature " under ", " below " and " below " comprise fisrt feature immediately below second feature and tiltedly below, or only represent that fisrt feature level height is less than second feature.

The foregoing is only the preferred embodiments of the present invention, be not limited to the present invention, for a person skilled in the art, the present invention can have various modifications and variations.Within the spirit and principles in the present invention all, any amendment done, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.

Claims (10)

1. an angle of attack control system, for controlling the angle of attack of fixed-wing, described fixed-wing is connected with frame, it is characterized in that, comprise hinge and angle of attack control mechanism, the cross bar of described frame is connected with montant, and described montant and described fixed-wing are by described chain connection, and described angle of attack control mechanism is for regulating the angle between described fixed-wing and described frame.
2. angle of attack control system according to claim 1, it is characterized in that, described angle of attack control mechanism comprises control module, lifting drive and jacking system, described control module and described lifting drive are installed in described frame, described control module is connected with described lifting drive, described lifting drive is connected with described jacking system, and described jacking system is connected with described fixed-wing.
3. angle of attack control system according to claim 2, it is characterized in that, described jacking system comprises lifting bar and transmission device, and described transmission device is connected with described lifting drive, described transmission device is connected with described lifting bar, and described lifting bar is connected with described fixed-wing.
4. angle of attack control system according to claim 3, it is characterized in that, described lifting bar is tooth bar, and described transmission device is lifting driven wheel, described tooth bar engages with described lifting driven wheel, and described tooth bar is connected with described fixed-wing away from one end of described lifting driven wheel.
5. angle of attack control system according to claim 3, is characterized in that, described lifting bar is slide block, and described transmission device is screw rod, and described slide block coordinates with described screw rod, and described slide block is connected with described fixed-wing away from one end of described screw rod.
6. angle of attack control system according to claim 3, is characterized in that, the point of connection of described lifting bar and described fixed-wing is higher than the hinge-point of described hinge, and described angle of attack control mechanism is arranged between the head of described hinge and described fixed-wing.
7. angle of attack control system according to claim 2, it is characterized in that, also comprise lifting attaching parts, described lifting attaching parts comprises the first clamping plate and the second clamping plate, described frame is provided with pipe link, described pipe link is fixed between described first clamping plate and described second clamping plate, and described control module and described lifting drive are installed on described first clamping plate.
8. angle of attack control system according to claim 1, it is characterized in that, described hinge comprises hinge connector and rotating shaft, described rotating shaft is connected with described fixed-wing, described hinge connector is provided with bearing, described rotating shaft is through described bearing, and described montant and described rotating shaft are rotationally connected by described hinge connector.
9. angle of attack control system according to claim 8, it is characterized in that, described hinge connector comprises T-connecting piece and adapter plate, and described bearing is arranged on one end of described T-connecting piece, and described montant is fixed between described T-connecting piece and described adapter plate.
10. an angle of attack control method, it is characterized in that, have employed the angle of attack control system as described in any one of claim 1-9, the method comprises: utilize described angle of attack control mechanism that described fixed-wing is rotated around described montant by described hinge, to regulate the angle between described fixed-wing and described frame.
CN201610013369.5A 2016-01-11 2016-01-11 Angle of attack control system and angle of attack control method CN105523172B (en)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106965933A (en) * 2017-03-10 2017-07-21 佛山市神风航空科技有限公司 The launching apparatus and mode of a kind of aircraft

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5509623A (en) * 1994-06-15 1996-04-23 Freewing Aerial Robotics Corporation Free wing aircraft having a free wing used as an air brake to shorten roll-out following touchdown
CN1660668A (en) * 2004-02-24 2005-08-31 陈启星 Attack angle changeable aircraft wing
CN201951711U (en) * 2010-10-18 2011-08-31 南京航空航天大学 Tilting mechanism
CN203944127U (en) * 2014-07-01 2014-11-19 王领军 Wing model aircraft wing whirligig verts
CN204895839U (en) * 2015-07-06 2015-12-23 杨钧杰 Light aerocraft all -moving wing
CN205469781U (en) * 2016-01-11 2016-08-17 成都学尚科技有限公司 Angle of attack control system

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5509623A (en) * 1994-06-15 1996-04-23 Freewing Aerial Robotics Corporation Free wing aircraft having a free wing used as an air brake to shorten roll-out following touchdown
CN1660668A (en) * 2004-02-24 2005-08-31 陈启星 Attack angle changeable aircraft wing
CN201951711U (en) * 2010-10-18 2011-08-31 南京航空航天大学 Tilting mechanism
CN203944127U (en) * 2014-07-01 2014-11-19 王领军 Wing model aircraft wing whirligig verts
CN204895839U (en) * 2015-07-06 2015-12-23 杨钧杰 Light aerocraft all -moving wing
CN205469781U (en) * 2016-01-11 2016-08-17 成都学尚科技有限公司 Angle of attack control system

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106965933A (en) * 2017-03-10 2017-07-21 佛山市神风航空科技有限公司 The launching apparatus and mode of a kind of aircraft

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