CN103803065A - Belt-transmission disc type multi-rotor-wing aircraft - Google Patents
Belt-transmission disc type multi-rotor-wing aircraft Download PDFInfo
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- CN103803065A CN103803065A CN201210462439.7A CN201210462439A CN103803065A CN 103803065 A CN103803065 A CN 103803065A CN 201210462439 A CN201210462439 A CN 201210462439A CN 103803065 A CN103803065 A CN 103803065A
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Abstract
The invention relates to a belt-transmission disc type multi-rotor-wing aircraft. The belt-transmission disc type multi-rotor-wing aircraft is provided with covering skins, an engine, a main rack, a power distribution and transmission system and a flight control system, wherein the covering skins are buckled with each other; a plurality of brackets are outwards extended from the power distribution and transmission system and are uniformly spaced, and rotor wing assemblies with changeable propeller pitches are arranged at the front ends of the brackets and comprise rotor wing rotation driving components and rotor wing propeller pitch changing components. According to the belt-transmission disc type multi-rotor-wing aircraft, a plurality of shafts and a plurality of rotor wings are driven by the engine, and the size of rising power of all the shafts is changed through changing the propeller pitches of all the rotor wings, so as to realize the change of the flight attitude of the aircraft; the fuel-driven engine is adopted, so that the effective payload is increased, and the flight time is prolonged, thus the belt-transmission disc type multi-rotor-wing aircraft is particularly applicable to long-time and long-distance operation.
Description
Technical field
The invention belongs to aeronautical product technical field, relate to a kind of multiaxis multi-rotor aerocraft.
Background technology
Multiaxis multi-rotor aerocraft operates on it control by wireless remote control system and independent flight control system, to realize the landing of aircraft, flight all around, acceleration and deceleration and direction control etc.Manipulative capability, stability, effective mission payload and cruise duration are the important indicators of investigating multiaxis multi-rotor aerocraft, and under identical manipulative capability and stability condition, user pursues larger effective mission payload and long-time duration flight ability.
Thereby traditional multiaxis multi-rotor aerocraft is installed respectively electrical motor to drive screw propeller to reach the object of flight on the S. A. of screw propeller place, thereby by changing lift size that the rotating speed of electrical motor changes each axle to control flight attitude.There is following shortcoming in this frame mode, it is the state of kinematic motion that each screw propeller of multiaxis multi-rotor aerocraft needs to expend much electricity and go to control aircraft, want long-time effectively continuation of the journey just to require storage battery can store abundant electric energy, this has increased own wt and the manufacturing cost of aircraft, simultaneously because service lifetime of accumulator is limited, the electric energy of storage is also limited, thereby is difficult to meet the requirement of long-time continuation of the journey.
Summary of the invention
The object of the invention is to overcome deficiency of the prior art, the disc type multi-rotor aerocraft of the Novel waistband transmission that high, the effective mission payload of a kind of manipulative capability and stability is large, flying power is strong is provided.
To achieve these goals, the present invention realizes by following technical scheme:
A kind of bel-drivenn disc type multi-rotor aerocraft, comprise flight control system, engine, mainframe, power distribution driving system, by the outward extending multiple supports of mainframe, be positioned at the rotor assembly 1 of each support front end, its special character is, described aircraft also comprises two disc type coverings that fasten mutually, described disc type covering is by flight control system, engine, mainframe, power distribution driving system, multiple supports, in rotor assembly is fastened on, described aircraft also comprises two disc type coverings that fasten mutually, described disc type covering is by flight control system, engine, mainframe, power distribution driving system, multiple supports, in rotor assembly is fastened on, on described covering, be provided with the circular hole relative with rotor position, described flight control system comprises 2N Servo-controller, described power distribution driving system comprises the input shaft gear 3 that driven by engine, N the output gear that is driven and be uniform staggered with around input shaft circumference by input shaft gear and N reverse output gear group, described reverse output gear group comprises track adjusting wheel 2 and output gear and track adjusting wheel and the input shaft gear engagement of coaxial setting, described each output gear drives the work of corresponding rotor assembly, belt 1 transmission that described output gear consists of belt pulley 10 and belt 12 drives the work of rotor assembly.
Above-mentioned rotor assembly comprise the rotor that is output gear drive rotate input shaft 9, be enclosed within rotor rotate sculler arm 8 on input shaft 9 and pushing disk 7, be fixed on that rotor mounting clamp pedestal 5, symmetry that rotor rotates input shaft 9 upper ends are arranged on rotor mounting clamp pedestal and along two rotor mounting clamps 4 of rotor mounting clamp pedestal place axis rotation, be fixed on the rotor on rotor mounting clamp 4; Described pushing disk 7 is arranged between sculler arm 8 and rotor mounting clamp 4 and overhanging two symmetrical hangers, on described each rotor mounting clamp 4, is provided with overhanging lug, between described lug and corresponding hanger, is hinged with connecting rod 6; Between described sculler arm 8 and Servo-controller, be hinged with L-type Control arm, the middle flex point of L-type Control arm is arranged on rotor assembly pedestal.
Beneficial effect of the present invention is:
1, the present invention has adopted two disc type coverings of mutual fastening, and in all parts of rotor craft are all wrapped in, the lines flow smoothly, and air resistance is little.
2, drive the multiple rotors of multiaxis with an engine, thereby change each axle lift size to realize the change of aircraft flight attitude by changing the pitch of each rotor, reduced aircraft own wt and energy loss; Adopt the moving engine of oil to drive the multiple rotors of multiaxis can increase effective mission payload, extend the flight time, be particularly useful for long-time and remote job.In addition, the present invention adopts belt 1 transmission that belt pulley 10 and belt 12 form to drive the work of rotor assembly, can prevent that external interference is passed to engine by rotor, guarantees the normal work of the moving engine of oil.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention.
Fig. 2 is a kind of bel-drivenn disc type of the present invention multi-rotor aerocraft drive system structure figure.
Fig. 3 is that bel-drivenn disc type multi-rotor aerocraft of the present invention is from transmission component and rotor assembly structure chart.
The specific embodiment
Be a kind of gear-driven disc type multi-rotor aerocraft drive system structure figure of the present invention as illustrated in fig. 1 and 2, mainly formed by the disc type covering 21 mutually fastening, 22, rotor assembly 1, track adjusting wheel 2, input shaft gear 3.In disc type covering is fastened on flight control system, engine, mainframe, power distribution driving system, multiple support, rotor assembly, on covering, be provided with the circular hole relative with rotor position 25, input shaft gear 3 belongs to parts in power distribution driving system, this gear directly driven by the moving engine of oil or by the gear that is arranged on the moving engine output shaft of oil by with input shaft gear 3 engaged transmission.
In this structure, power distribution driving system is criss-cross by the outward extending support of input shaft gear 3, wherein there are two symmetrical rotor assemblies by band transmission by driven gear directly and input shaft gear 3 engaged transmission, two other symmetrical rotor assembly is engaged with track adjusting wheel 2 by driven gear by band transmission, lead via track adjusting wheel 2, track adjusting wheel 2 engages with input shaft gear 3 object that reaches transmission again; The hand of rotation of the rotor assembly after guiding is contrary with the hand of rotation of the rotor assembly not leading, and its objective is that eliminating himself in order to interact rotates the reactive torque power producing, and avoids aircraft spin orientation to fly.
Further, be illustrated in figure 3 bel-drivenn disc type multi-rotor aerocraft of the present invention from transmission component and rotor assembly structure chart, belt 1 transmission that can be formed by belt pulley 10, cog belt 12 from transmission component.Rotor assembly rotates input shaft 9 and L-type Control arm 11 etc. by rotor mounting clamp 4, rotor mounting clamp pedestal 5, connecting rod 6, pushing disk 7, rotor assembly pedestal, sculler arm 8, rotor and forms.On each rotor mounting clamp pedestal 5, two rotor mounting clamps 4 are all installed, and these two rotor mounting clamps 4 are symmetrical installation along rotor mounting clamp pedestal 5 cross sections, place, center, rotor mounting clamp 4 can be along the 5 place axis rotations of rotor mounting clamp pedestal, a lug is stretched out in rotor mounting clamp 4 bottoms, lug is provided with a cylindrical boss, this cylindrical boss coordinates with the corresponding and circular hole of connecting rod 6 one end, and connecting rod 6 other end circular holes stretch out the respective cylindrical boss arranging on hanger on one side with pushing disk 7 and coordinate; The axis that pushing disk 7 can rotate input shaft 9 along rotor moves up and down, also can rotate input shaft 9 axis along rotor rotates, the pushing disk 7 each symmetries in both sides are stretched out hanger, on two hangers, are equipped with cylindrical boss, and cylindrical boss can coordinate with the corresponding circle hole on pushing disk 7 formation revolute pair; Sculler arm 8 is firmly rabbeted by its inner breathing ring structure with pushing disk 7, and be enclosed within on rotor rotation input shaft 9, thereby can along rotor rotate input shaft 9 move up and down drive pushing disk 7 move up and down, the protruding cylindrical boss of sculler arm 8, the hole mix proportion revolute of this cylindrical boss and L-type Control arm 11 ends, L-type Control arm 11 other ends are connected with sculler arm 8, the other end is connected with described Servo-controller, intermediate point is arranged on rotor assembly pedestal, can rotate around the anchor shaft at intermediate point place; Handle Servo-controller and pull Control arm 11, Control arm 11 rotates around the anchor shaft at intermediate point place, pull sculler arm 8 to move downward, thereby drive pushing disk 7 to move up and down, pushing disk 7 pulls two rotor mounting clamps 4 to rotate by connecting rod 6, drive screw propeller to rotate around rotor mounting clamp pedestal 5 center shafts, thereby change pitch, reach the object that changes screw propeller lift size.
Servo-controller is arranged on mainframe, is electrically connected with flight-control computer, and the given impulse singla of flight-control computer drives steering wheel motion, accomplishes that machinery combines with electric, reaches and controls aircraft object.
The moving engine speed speed of oil is changed by steering wheel control throttle.
The power distribution driving system multiple supports (three, four, six, eight etc.) that stretch out, the even interval of above-mentioned support composition Trident Type, cross, rice font etc., each support front end is equipped with the rotor assembly that can change rotor pitch simultaneously.
Claims (2)
1. a bel-drivenn disc type multi-rotor aerocraft, comprise flight control system, engine, mainframe, power distribution driving system, by the outward extending multiple supports of mainframe, be positioned at the rotor assembly 1 of each support front end, it is characterized in that: described aircraft also comprises two disc type coverings that fasten mutually, described disc type covering is by flight control system, engine, mainframe, power distribution driving system, multiple supports, in rotor assembly is fastened on, described aircraft also comprises two disc type coverings that fasten mutually, described disc type covering is by flight control system, engine, mainframe, power distribution driving system, multiple supports, in rotor assembly is fastened on, on described covering, be provided with the circular hole relative with rotor position, described flight control system comprises 2N Servo-controller, described power distribution driving system comprises the input shaft gear (3) that driven by engine, N the output gear that is driven and be uniform staggered with around input shaft circumference by input shaft gear and N reverse output gear group, described reverse output gear group comprises track adjusting wheel (2) and output gear and track adjusting wheel and the input shaft gear engagement of coaxial setting, described each output gear drives the work of corresponding rotor assembly, described output gear drives the work of rotor assembly by belt pulley (10) and the belt-driving of belt (12) composition.
2. bel-drivenn disc type multi-rotor aerocraft according to claim 1, is characterized in that: described rotor assembly comprise the rotor that is output gear drive rotate input shaft (9), be enclosed within rotor rotate sculler arm (8) on input shaft (9) and pushing disk (7), be fixed on that rotor mounting clamp pedestal (5), symmetry that rotor rotates input shaft (9) upper end are arranged on rotor mounting clamp pedestal and along two rotor mounting clamps (4) of rotor mounting clamp pedestal place axis rotation, be fixed on the rotor on rotor mounting clamp (4); Described pushing disk (7) is arranged between sculler arm (8) and rotor mounting clamp (4) and overhanging two symmetrical hangers, on described each rotor mounting clamp (4), is provided with overhanging lug, between described lug and corresponding hanger, is hinged with connecting rod (6); Between described sculler arm (8) and Servo-controller, be hinged with L-type Control arm, the middle flex point of L-type Control arm is arranged on rotor assembly pedestal.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210462439.7A CN103803065A (en) | 2012-11-15 | 2012-11-15 | Belt-transmission disc type multi-rotor-wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210462439.7A CN103803065A (en) | 2012-11-15 | 2012-11-15 | Belt-transmission disc type multi-rotor-wing aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103803065A true CN103803065A (en) | 2014-05-21 |
Family
ID=50700557
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210462439.7A Withdrawn CN103803065A (en) | 2012-11-15 | 2012-11-15 | Belt-transmission disc type multi-rotor-wing aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103803065A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104627359A (en) * | 2015-02-17 | 2015-05-20 | 何春旺 | Multirotor |
| CN108473198A (en) * | 2015-09-03 | 2018-08-31 | 乔伊·音·陈 | More rotor gyroplane aircraft |
-
2012
- 2012-11-15 CN CN201210462439.7A patent/CN103803065A/en not_active Withdrawn
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104627359A (en) * | 2015-02-17 | 2015-05-20 | 何春旺 | Multirotor |
| CN108473198A (en) * | 2015-09-03 | 2018-08-31 | 乔伊·音·陈 | More rotor gyroplane aircraft |
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| Date | Code | Title | Description |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C04 | Withdrawal of patent application after publication (patent law 2001) | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20140521 |