CN212605803U - Composite attitude stable type coaxial double-propeller rotor aircraft - Google Patents
Composite attitude stable type coaxial double-propeller rotor aircraft Download PDFInfo
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- CN212605803U CN212605803U CN202021532310.5U CN202021532310U CN212605803U CN 212605803 U CN212605803 U CN 212605803U CN 202021532310 U CN202021532310 U CN 202021532310U CN 212605803 U CN212605803 U CN 212605803U
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Abstract
The utility model discloses a composite attitude stable type coaxial double-rotor-wing aircraft, which comprises an aircraft fuselage, a coaxial double-rotor-wing blade group and a control system, wherein the coaxial double-rotor-wing blade group is arranged on the aircraft fuselage, the control system is arranged in the aircraft fuselage and also comprises a support arm and an attitude control rotor wing, one end of the support arm is connected with the aircraft fuselage, and the other end of the support arm is connected with the attitude control rotor wing; when the horizontal attitude of the aircraft is unstable or needs to turn, the control system controls the attitude control rotor to work, so that the horizontal attitude of the aircraft is stable or turns. An object of the utility model is to provide a coaxial double-oar rotor craft of stable formula of compound gesture through set up the gesture control oar around coaxial double-rotor paddle coplanar, has saved vector paddle control mechanism, and the cost reduces, maintains that the maintenance is easier, makes aircraft range of application greatly increased.
Description
Technical Field
The utility model relates to an aircraft technical field especially relates to a coaxial double-oar rotor craft of stable formula of compound gesture.
Background
The current vertical take-off and landing aircraft are commonly used in various fields, and the model design of the aircraft is developed towards the direction of small volume, high efficiency and simplification. The coaxial double-propeller technology has high efficiency (no tail propeller, the loss of the tail propeller is reduced by 12-15 percent), small volume (the power of blades overlapped up and down and the power of an engine are equivalent to 50 percent of the diameter of a rotor wing of a helicopter with the tail propeller, the length of a fuselage is reduced without the tail propeller), and good stability.
However, the attitude vector control system has the problems of complex structure, high requirement on manufacturing precision, complex maintenance and the like, and cannot be widely used. And the current oar (the contained angle of attitude control paddle plane and lift rotor blade is 90 degrees) attitude control mode paddle perpendicular to main lift rotor blade and need leave main lift rotor blade certain distance and produce attitude control moment, has increased aircraft owner axial dimension, and this kind of structure still needs to consume extra energy at the during operation, and its structural rationality and efficiency can not reach the best.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a coaxial double-oar rotor craft of stable formula of compound gesture through set up the gesture control oar around coaxial double-rotor paddle coplanar, has saved vector paddle control mechanism, and the cost reduces, maintains that the maintenance is easier, makes aircraft range of application greatly increased.
The utility model discloses a following technical scheme realizes:
the utility model provides a coaxial double-rotor wing aircraft of stable formula of compound gesture, includes aircraft fuselage, coaxial double-rotor wing paddle group and control system, coaxial double-rotor wing paddle group sets up in the middle part of aircraft fuselage, control system set up in the aircraft fuselage. The aircraft further comprises a supporting arm and a posture control rotor wing, wherein one end of the supporting arm is connected with the aircraft body, and the other end of the supporting arm is connected with the posture control rotor wing;
when the horizontal attitude of the aircraft is unstable or needs to turn, the control system controls the attitude control rotor to work, so that the horizontal attitude of the aircraft is stable or turns.
Further, the attitude control rotor includes gesture pivot, gesture rotor and gesture motor, the bottom of gesture pivot with the support arm is connected, the top of gesture pivot with the gesture rotor is connected, the power take off end of gesture motor with the gesture pivot is connected.
Further, the number of attitude control rotors includes at least 3.
Further, the blades of the attitude rotor are variable pitch blades.
Further, the blades of the attitude rotor are fixed-pitch blades.
Further, the blade of the attitude rotor includes at least 2 pieces.
Further, the coaxial dual-rotor blade set comprises a first rotating shaft, a second rotating shaft, a first rotor, a second rotor, a first motor and a second motor;
the first rotating shaft and the second rotating shaft are coaxial, the second rotating shaft is sleeved at the top of the first rotating shaft, and the first rotating shaft is connected with the aircraft body in a rotating manner;
the first rotor wing is arranged at the top of the first rotating shaft, the second rotor wing is arranged at the top of the second rotating shaft, and the rotating directions of the first rotor wing and the second rotor wing are opposite;
the power output end of the first motor is connected with the first rotating shaft, and the power output end of the second motor is connected with the second rotating shaft.
Further, the blades of the first rotor or the second rotor comprise at least 2 pieces.
Further, the blades of the first rotor or the second rotor are variable pitch blades.
Further, the blades of the first rotor or the second rotor are fixed pitch blades.
Compared with the prior art, the utility model, following advantage and beneficial effect have:
1. when the attitude control works, the direction of the lift force of the double-rotor blade coaxial with the main lift force is consistent, and the consumed power of the part is superposed on the total lift force of the aircraft, so the efficiency is high;
2. when the attitude control rotor and the main lift coaxial dual-rotor blade plane are parallel, the flight direction projection area is smaller, and the course flight resistance is small;
3. the vector paddle control mechanism is omitted, the manufacturing cost is reduced, the maintenance is easier, and the application range of the aircraft is greatly increased.
Drawings
The accompanying drawings, which are included to provide a further understanding of the embodiments of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the principles of the invention. In the drawings:
fig. 1 is a top view of the overall structure of the present invention;
FIG. 2 is a side view of the overall structure of the present invention;
fig. 3 is the utility model discloses the local enlarged schematic diagram of attitude control rotor.
Reference numbers and corresponding part names in the drawings:
1. an aircraft fuselage; 2. a coaxial dual rotor blade set; 3. a support arm; 4. an attitude control rotor; 5. an attitude rotating shaft; 6. a base; 7. an attitude blade.
Detailed Description
To make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail below with reference to the following examples and drawings, and the exemplary embodiments and descriptions thereof of the present invention are only used for explaining the present invention, and are not intended as limitations of the present invention.
Examples
A composite attitude stabilization type coaxial double-rotor aircraft is shown in figures 1 and 2 and comprises an aircraft body 1, a coaxial double-rotor blade group 2 and a control system, wherein the coaxial double-rotor blade group 2 is arranged in the middle of the aircraft body 1, the control system is arranged in the aircraft body 1, the composite attitude stabilization type coaxial double-rotor aircraft further comprises a supporting arm 3 and an attitude control rotor 4, one end of the supporting arm 3 is connected with the aircraft body 1, and the other end of the supporting arm 3 is connected with the attitude control rotor 4;
when the horizontal attitude of the aircraft is unstable or needs to turn, the control system controls the attitude control rotor 4 to work, so that the horizontal attitude of the aircraft is stable or turns.
Specifically, in the present embodiment, as shown in fig. 1, the number of the attitude control rotors 4 is four, the four attitude control rotors 4 are symmetrically disposed around the aircraft body 1, and the blade planes of the attitude control rotors 4 are parallel to the blade planes of the coaxial dual rotors, so that the lift force generated when the attitude control rotors 4 operate is in the same direction as the lift force generated by the coaxial dual rotor blade group 2. Further, as shown in fig. 3, the attitude control rotor 4 includes an attitude rotating shaft 5, an attitude motor and an attitude rotor, wherein the attitude rotor includes a circular base 6 and four attitude blades 7, a bearing is disposed in the middle of the base 6, and the four attitude blades 7 are symmetrically disposed on the side of the base 6. The bottom of the posture rotating shaft 5 is connected with the supporting arm 3, the top of the posture rotating shaft 5 is rotatably connected with the bearing, and the power output end of the posture motor is connected with the top of the posture rotating shaft 5. During operation, the rotating speeds of different motors are controlled to adjust the rotating speeds or the screw pitches of the attitude blades 7 of the different attitude control rotors 4, so that the attitude of the airplane is adjusted.
It is worth mentioning that the attitude blade 7 can be provided in different forms depending on the driving mode of the aircraft, and when the driving is performed by using an internal combustion engine, the attitude blade 7 is in a variable pitch blade form, and when the driving is performed by using electric power, the attitude blade 7 is in a fixed pitch form.
Further, in the present embodiment, the coaxial dual-rotor blade set 2 includes a first rotating shaft, a second rotating shaft, a first rotor, a second rotor, a first motor, and a second motor;
the first rotating shaft is coaxial with the second rotating shaft, the second rotating shaft is sleeved at the top of the first rotating shaft, the first rotating shaft is located in the middle of the interior of the aircraft body 1, and the first rotating shaft is rotatably connected with the aircraft body 1. First rotor and second rotor respectively set up 4 paddles, and first rotor sets up in the top of first axis of rotation, and the second rotor sets up in the top of second axis of rotation, and the rotation direction of first rotor and second rotor is opposite. The power output end of the first motor is connected with the first rotating shaft, and the power output end of the second motor is connected with the second rotating shaft.
The blades of the first rotor and the second rotor can be variable-pitch blades or fixed-pitch blades, and are selected according to the driving mode of the aircraft. Namely: when driven by an internal combustion engine, the blades are in the form of variable pitch blades and when driven by electricity, the blades are in the form of fixed pitch blades.
When the aircraft is in operation, after the power of the aircraft is input into the coaxial double-rotor-wing blades, the first rotor wing and the second rotor wing are driven to rotate to generate lift force, so that the aircraft vertically takes off, lifts or hovers. The course control torque is generated by adjusting the rotating speed or the pitch of the first rotor blade and the second rotor blade, so that the horizontal plane steering of the aircraft is realized, or the course deviation of the aircraft is corrected.
Specifically, when the horizontal attitude of the aircraft is unstable, the control system controls the attitude to control the rotor 4 to work, so that the horizontal attitude of the aircraft is stable;
when the aircraft needs to fly leftwards, the control system controls the posture arranged at the right part of the aircraft to adjust the speed increase of the blades of the rotor wing or increase the pitch, so that the lift force is increased, the aircraft inclines leftwards, and at the moment, the lift force component of the aircraft generates a lift force axis to incline leftwards, so that a leftward component force is generated to push the aircraft to fly leftwards; flying to the right and vice versa.
When the aircraft needs to fly forwards, the control system controls the posture arranged at the rear part of the aircraft to adjust the speed increase of the blades of the rotor wing or increase the pitch, so that the lift force is increased, the aircraft tilts forwards, the lift force component of the aircraft generates a lift force axis to tilt forwards, the forward component force is generated to push the aircraft to fly forwards, and the backward flight is not the reverse.
The above-mentioned embodiments, further detailed description of the objects, technical solutions and advantages of the present invention, it should be understood that the above description is only the embodiments of the present invention, and is not intended to limit the scope of the present invention, and any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (10)
1. A composite attitude stabilization type coaxial double-rotor aircraft comprises an aircraft fuselage (1), a coaxial double-rotor blade group (2) and a control system, wherein the coaxial double-rotor blade group (2) is arranged on the aircraft fuselage (1), the control system is arranged in the aircraft fuselage (1), and the composite attitude stabilization type coaxial double-rotor aircraft is characterized by further comprising a supporting arm (3) and an attitude control rotor (4), one end of the supporting arm (3) is connected with the aircraft fuselage (1), and the other end of the supporting arm (3) is connected with the attitude control rotor (4);
when the horizontal attitude of the aircraft is unstable or the aircraft needs to turn, the control system controls the attitude control rotor wing (4) to work, so that the horizontal attitude of the aircraft is stable or the aircraft needs to turn.
2. A composite attitude stabilised coaxial twin-screw rotorcraft according to claim 1, characterised in that the attitude control rotor (4) comprises an attitude pivot (5), an attitude rotor and an attitude motor, the bottom of the attitude pivot (5) being connected to the support arm (3), the top of the attitude pivot (5) being connected to the attitude rotor, the power take-off of the attitude motor being connected to the attitude pivot (5).
3. A compound-attitude-stabilized coaxial twin-screw rotorcraft according to claim 2, characterized in that the number of attitude control rotors (4) is at least 3.
4. A compound-attitude stabilized coaxial twin-screw rotorcraft according to claim 3, wherein the blades of the attitude rotors are variable pitch blades.
5. A compound-attitude stabilized coaxial twin-screw rotorcraft according to claim 3, wherein the attitude rotor blades are fixed-pitch blades.
6. A compound-attitude stabilized coaxial twin-screw rotorcraft according to claim 3, wherein the blades of the attitude rotors comprise at least 2 blades.
7. A compound attitude stabilised coaxial twin-screw rotorcraft according to any one of claims 1 to 6, characterised in that the set of coaxial twin-rotor blades (2) comprises a first rotary shaft, a second rotary shaft, a first rotor, a second rotor, a first motor and a second motor;
the first rotating shaft and the second rotating shaft are coaxial, the second rotating shaft is sleeved at the top of the first rotating shaft, and the first rotating shaft is rotatably connected with the aircraft body (1);
the first rotor wing is arranged at the top of the first rotating shaft, the second rotor wing is arranged at the top of the second rotating shaft, and the rotating directions of the first rotor wing and the second rotor wing are opposite;
the power output end of the first motor is connected with the first rotating shaft, and the power output end of the second motor is connected with the second rotating shaft.
8. A compound-attitude-stabilized coaxial twin-screw rotorcraft according to claim 7, wherein the blades of the first or second rotors include at least 2 blades.
9. A compound-attitude-stabilized coaxial twin-screw rotorcraft according to claim 8, wherein the blades of the first or second rotors are variable-pitch blades.
10. A compound-attitude-stabilized coaxial twin-screw rotorcraft according to claim 7, wherein the blades of the first or second rotors are fixed-pitch blades.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021532310.5U CN212605803U (en) | 2020-07-29 | 2020-07-29 | Composite attitude stable type coaxial double-propeller rotor aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021532310.5U CN212605803U (en) | 2020-07-29 | 2020-07-29 | Composite attitude stable type coaxial double-propeller rotor aircraft |
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| CN212605803U true CN212605803U (en) | 2021-02-26 |
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| CN202021532310.5U Active CN212605803U (en) | 2020-07-29 | 2020-07-29 | Composite attitude stable type coaxial double-propeller rotor aircraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113022860A (en) * | 2021-05-24 | 2021-06-25 | 四川迅联达智能科技有限公司 | Electric control multifunctional differential course control system |
-
2020
- 2020-07-29 CN CN202021532310.5U patent/CN212605803U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113022860A (en) * | 2021-05-24 | 2021-06-25 | 四川迅联达智能科技有限公司 | Electric control multifunctional differential course control system |
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