CN104859859B - Pneumatic optimization oil-electricity hybrid multi-rotor aircraft - Google Patents
Pneumatic optimization oil-electricity hybrid multi-rotor aircraft Download PDFInfo
- Publication number
- CN104859859B CN104859859B CN201510250011.XA CN201510250011A CN104859859B CN 104859859 B CN104859859 B CN 104859859B CN 201510250011 A CN201510250011 A CN 201510250011A CN 104859859 B CN104859859 B CN 104859859B
- Authority
- CN
- China
- Prior art keywords
- slipstream
- rotor
- fixed
- steering engine
- rotor aircraft
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000005457 optimization Methods 0.000 title claims abstract description 27
- 239000000446 fuel Substances 0.000 claims abstract description 33
- 230000007246 mechanism Effects 0.000 claims abstract description 32
- 238000009434 installation Methods 0.000 claims description 7
- 230000000149 penetrating effect Effects 0.000 claims description 3
- 238000000034 method Methods 0.000 description 5
- 230000008569 process Effects 0.000 description 5
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 4
- 230000008859 change Effects 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 1
- 239000002551 biofuel Substances 0.000 description 1
- 238000007664 blowing Methods 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 229910052744 lithium Inorganic materials 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229920000642 polymer Polymers 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
Landscapes
- Toys (AREA)
- Transmission Devices (AREA)
Abstract
The invention provides a pneumatic optimized hybrid oil-electricity multi-rotor aircraft, which comprises an aircraft body, a first cavity, a second cavity and a third cavity, wherein the aircraft body is provided with an upper surface, a lower surface and the first cavity; a landing gear fixed to a lower surface of the fuselage; a fuel-powered engine; the semi-closed mounting platform is fixed on the lower surface of the engine body and used for mounting a fuel engine, and a second cavity connected with the first cavity is formed in the mounting platform; the power rotor wing is driven by the fuel engine to rotate to realize the flight of the aircraft, is arranged on the output shaft of the fuel engine and is positioned in the first cavity or the second cavity; the electric rotor wing mechanism is used for receiving the far-end first control signal to adjust the flight attitude of the aircraft; and the pneumatic optimization mechanism is used for receiving the far-end second control signal to eliminate the aircraft back twist in flight and is arranged on the outer wall of the mounting platform. By adopting the fuel engine and the electric rotor wing, the invention has the characteristics of simple structure, stable flight, easy operation and the like, and greatly improves the load, the endurance time, the cruising speed, the size and the structure.
Description
Technical Field
The invention relates to the field of multi-rotor aircrafts, in particular to a pneumatic optimization oil-electricity hybrid multi-rotor aircraft.
Background
The multi-rotor aircraft (Multirotor) is an aircraft capable of taking off and landing vertically, and the fuselage of the aircraft is provided with at least three rotor shafts, each rotor shaft is provided with a motor and a rotor driven by the motor to rotate to form thrust, and various flight actions can be realized by changing the rotating speed among different rotors. Because many rotor crafts have simple structure, flight stability, easy operation, convenient to carry, safety hazard nature low grade characteristics, consequently the wide application is in each field at home and abroad.
In the prior art, multi-rotor aircraft include electric multi-rotor aircraft and hybrid multi-axis aircraft. Compared with the traditional helicopter, the developed electric multi-rotor aircraft is mature, has simple structure, has fixed total distance between symmetrical rotors, has short blades of each rotor and slow linear velocity at the tail end of each blade, has the advantages of small impact force, difficult damage, higher safety and the like when collision occurs, but is difficult to be made large, and the main reason is that most of the existing electric multi-rotor aircraft adopt a lithium polymer battery as power energy. Because the energy density of the power energy is far lower than that of the biofuel, the endurance time of the electric multi-rotor aircraft is short, particularly, after the electric multi-rotor aircraft reaches a certain scale, the ratio of the weight of a battery to the takeoff weight of the electric multi-rotor aircraft is remarkably increased, and a series of problems which are difficult to solve occur, such as the increase of effective load, the increase of the idle time and the like.
Although the existing hybrid multi-axis aircraft can solve the problems of the electric multi-rotor aircraft, when a fuel engine on the hybrid multi-axis aircraft drives a power rotor to rotate, a large torque is formed. Theoretically speaking, the hybrid multi-axis aircraft can overcome the anti-torque by changing the rotation speed difference of the brushless direct current motor on the hybrid multi-axis aircraft, and the stability is kept, but because the size difference between the power rotor and the attitude adjusting rotor on the hybrid multi-axis aircraft is large, the generated air reaction force is not in the same order of magnitude, and the aim of overcoming the anti-torque is difficult to achieve in practical application.
The two aforementioned existing multi-rotor aircraft generally adopt symmetrical structures in design, so that the existing multi-rotor aircraft has basically the same flight performance in all directions, and although the existing multi-rotor aircraft has higher quick maneuverability, the overall aerodynamic performance is not optimal, and the provided lift force is limited, so that the resistance during cruising is greatly increased, the endurance and cruising speed are not favorable to being improved, and the existing multi-rotor aircraft is particularly more prominent in the case of wind blowing and lacks of higher wind resistance.
Disclosure of Invention
The technical problem to be solved by the embodiment of the invention is to provide a pneumatic optimization oil-electricity hybrid multi-rotor aircraft, which adopts a fuel engine and an electric rotor, has the characteristics of simple structure, stable flight, easiness in operation and the like, and is greatly improved in load, endurance time, cruising speed, size and structure.
In order to solve the above technical problem, an embodiment of the present invention provides a pneumatic optimization hybrid oil-electric multi-rotor aircraft, including:
the device comprises a machine body and a control device, wherein the machine body comprises an upper surface, a lower surface and a first cavity penetrating through the upper surface and the lower surface;
at least one landing gear, wherein the landing gear is fixed with the lower surface of the fuselage;
a fuel engine;
the semi-closed type mounting platform is used for mounting the fuel engine, the mounting platform is fixed with the lower surface of the engine body, and a second cavity with an opening facing the first cavity and communicated with the first cavity is formed in the mounting platform;
the power rotor wing is driven by the fuel engine to rotate and generates thrust to realize the flying of the multi-rotor aircraft, and the power rotor wing is arranged on an output shaft of the fuel engine and is positioned in the second cavity or the first cavity;
at least one electric rotor mechanism for receiving a distal first control signal to adjust the attitude of the multi-rotor aircraft; and
at least one pneumatic optimization mechanism for receiving a distal second control signal to eliminate back-twist of the multi-rotor aircraft during flight, the pneumatic optimization mechanism being disposed on an outer wall of the mounting platform;
the pneumatic optimization mechanism comprises a hinge, a slip flow rudder, a connecting rod and a slip flow steering engine; wherein,
the number of the hinges is at least one, one end of each hinge is fixed on the outer wall of the mounting platform, and the other end of each hinge is fixed with the first surface of the slipstream rudder;
the slipstream rudder can be rotatably arranged on the outer wall of the mounting platform through the hinge, and the second surface of the slipstream rudder is fixed with one end of the connecting rod;
the slipstream steering engine is fixed on the outer wall of the mounting platform and comprises a rotating rocker arm connected with the other end of the connecting rod;
when the slipstream steering engine drives the rotating rocker arm to rotate, the connecting rod controls the slipstream steering engine to rotate around the hinge towards or away from the slipstream steering engine.
The pneumatic optimization mechanism further comprises a fixed rocker arm, one end of the fixed rocker arm is fixed to the second surface of the slipstream rudder, and the other end of the fixed rocker arm is fixed to one end of the connecting rod.
When the slipstream steering engine drives the rotating rocker arm to rotate clockwise, the connecting rod controls the slipstream steering engine to rotate around the hinge towards the slipstream steering engine; when the slipstream steering engine drives the rotating rocker arm to rotate anticlockwise, the connecting rod controls the slipstream steering engine to rotate around the hinge and depart from the slipstream steering engine; or
When the slipstream steering engine drives the rotating rocker arm to rotate clockwise, the connecting rod controls the slipstream steering engine to rotate around the hinge and depart from the slipstream steering engine; when the slipstream steering engine drives the rotating rocker arm to rotate anticlockwise, the connecting rod controls the slipstream steering engine to rotate around the hinge towards the slipstream steering engine.
The multi-rotor aircraft further comprises a plurality of platform supporting rods, one end of each platform supporting rod is fixed to the lower surface of the aircraft body, the other end of each platform supporting rod is fixed to the outer wall of the installation platform, one slipstream steering engine is arranged on the outer side wall of each platform supporting rod and connected with the corresponding slipstream steering engine through hinges.
The electric rotor wing mechanism comprises a brushless direct current motor and an attitude adjusting rotor wing arranged on an output shaft of the brushless direct current motor.
The multi-rotor aircraft further comprises two support frames, and the aircraft body further comprises a first side surface and a second side surface; wherein,
the two support frames are respectively fixed on the first side surface and the second side surface and then are parallel to each other, and each support frame extends to two sides respectively along the axial direction of the first side surface of the machine body to form two installation positions for installing the brushless direct current motor outside the machine body.
Each support frame is fixed with the machine body through screws.
Wherein the fuselage further comprises a third side; the thickness of the machine body is gradually reduced from the third side face along the direction of the first side face axis deviating from the third side face, the upper surface and the lower surface of the machine body are both formed into curved surfaces with certain radian, and the radian of the curved surface of the upper surface is larger than that of the curved surface of the lower surface.
And the output shaft of the fuel engine is vertical to the central axis of the machine body.
The embodiment of the invention has the following beneficial effects:
1. in the embodiment of the invention, the multi-rotor aircraft uses the fuel engine to provide main flight power, so that the mounting capacity and the endurance time of the multi-rotor aircraft are greatly increased;
2. in the embodiment of the invention, the multi-rotor aircraft adopts the slipstream rudder design on the basis of the fuel engine, so that the problem of back-twisting generated when the fuel engine works is solved, and the multi-rotor aircraft has the characteristics of simple control and small influence on the flight performance of the multi-rotor aircraft;
3. in the embodiment of the invention, the multi-rotor aircraft adopts the design that the aircraft body and the rotor plane have the installation angle difference, namely the aircraft body is designed to have the thickness difference change and the upper surface and the lower surface are curved surfaces with different radians, so that the aircraft body is in a horizontal posture in the front flying process of the multi-rotor aircraft, has smaller aerodynamic resistance in cruising, and simultaneously generates certain aerodynamic lift force, thereby effectively improving the overall cruising time and cruising speed of the aircraft;
4. in the embodiment of the invention, as the multi-rotor aircraft adopts the oil-electricity hybrid design, when the fuel engine fails, the multi-rotor aircraft can still be controlled to safely force to land through the electric rotor mechanism.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is within the scope of the present invention for those skilled in the art to obtain other drawings based on the drawings without inventive exercise.
Fig. 1 is a schematic perspective view of a pneumatic optimized hybrid oil-electric multi-rotor aircraft according to an embodiment of the present invention;
FIG. 2 is a schematic top perspective view of FIG. 1;
FIG. 3 is an enlarged view of a portion of the point A in FIG. 1;
FIG. 4 is a partial enlarged view of point B in FIG. 3;
FIG. 5 is a schematic view of the partial plan structure of FIG. 2;
fig. 6 is a schematic diagram of an application scenario of a pneumatic optimization hybrid multi-rotor aircraft according to an embodiment of the present invention;
fig. 7 is a schematic diagram of another application scenario of the pneumatic optimization hybrid multi-rotor aircraft according to the embodiment of the present invention;
in the figure: 1-fuselage, 11-upper surface, 12-lower surface, 13-first cavity, 14-first side surface, 15-second side surface, 16-third side surface, 2-landing gear, 3-fuel engine, 4-mounting platform, 41-second cavity, 5-power rotor, 6-electric rotor mechanism, 61-brushless direct current motor, 62-attitude adjustment rotor, 7-pneumatic optimization mechanism, 71-hinge, 72-slip flow rudder, 721-first surface, 722-second surface, 73-connecting rod, 74-slip flow steering engine, 741-rotating rocker arm, 75-fixed rocker arm, 8-platform supporting rod, 9-supporting frame, 91-mounting position of brushless direct current motor.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in further detail with reference to the accompanying drawings.
As shown in fig. 1 to 5, in an embodiment of the present invention, a pneumatic optimized hybrid oil-electric multi-rotor aircraft is provided, where the multi-rotor aircraft includes:
the device comprises a machine body 1, wherein the machine body 1 comprises an upper surface 11, a lower surface 12 and a first cavity 13 penetrating through the upper surface 11 and the lower surface 12; wherein, the machine body 1 is made of carbon fiber material;
at least one landing gear 2, wherein the landing gear 2 is fixed with the lower surface 12 of the fuselage 1;
a fuel engine 3;
the semi-closed type mounting platform 4 is used for mounting the fuel engine 3, the mounting platform 4 is fixed with the lower surface 12 of the machine body 1, and a second cavity 41 with an opening facing the first cavity 13 and communicated with the first cavity 13 is formed in the mounting platform 4;
the power rotor wing 5 is driven by the fuel engine 3 to rotate and generates thrust to realize the flight of the multi-rotor aircraft, and the power rotor wing 5 is arranged on an output shaft of the fuel engine 3 and is positioned in the second cavity 41 or the first cavity 13;
at least one electric rotor mechanism 6 for receiving the distal first control signal to adjust the flight attitude of the multi-rotor aircraft; and
and at least one pneumatic optimization mechanism 7 for receiving the far-end second control signal to eliminate the back torsion of the multi-rotor aircraft during flight, wherein the pneumatic optimization mechanism 7 is arranged on the outer wall of the mounting platform 4.
It should be noted that, a flight control system, a fuel oil tank, an accelerator steering engine, a power supply unit, a data transceiver unit for receiving a remote control signal, and various sensors should be further provided in the fuselage 1 for the multi-rotor aircraft to fly. The first control signal and the second control signal are sent to the flight control system through the data receiving and sending unit, so that the flight control system outputs different control instructions according to different control signals, wherein the control instructions comprise starting or closing instructions of the fuel engine 3, speed adjusting instructions of the electric rotor wing mechanism 6, starting, closing and torque direction change instructions of the pneumatic optimization mechanism 7 and the like.
It should be noted that the pneumatic optimization mechanism 7 is controlled according to the rotation direction of the power rotor 5, so that the pneumatic optimization mechanism 7 forms a torsion force opposite to the power rotor 5, thereby achieving the purpose of eliminating the torsion, for example, when the power rotor 5 rotates counterclockwise, the pneumatic optimization mechanism 7 is controlled to form the torsion force in the counterclockwise direction.
It will be appreciated that the output shaft of the fuel engine 3 should be perpendicular to the central axis of the fuselage 1 so that the power rotor 5 is parallel to the central axis of the fuselage 1 to generate aerodynamic lift. In order to reduce air resistance, the semi-closed installation platform 4 is adopted, so that the whole endurance time and cruising speed of the aircraft can be effectively improved.
In the embodiment of the invention, the pneumatic optimization mechanism 7 comprises a hinge 71, a slipstream rudder 72, a connecting rod 73 and a slipstream steering engine 74; wherein,
at least one hinge 71 is provided, one end of each hinge 71 is fixed on the outer wall of the mounting platform 4, and the other end of each hinge 71 is fixed with the first surface 721 of the slipstream rudder 72;
the slipstream rudder 72 can be rotatably arranged on the outer wall of the mounting platform 4 through a hinge 71, and a second face 722 of the slipstream rudder is fixed with one end of the connecting rod 73;
the slipstream steering engine 74 is fixed on the outer wall of the mounting platform 4 and comprises a rotary rocker 741 connected with the other end of the connecting rod 73;
when the slip flow steering gear 74 drives the rotating rocker arm 741 to rotate, the connecting rod 73 controls the slip flow rudder 72 to rotate around the hinge 71 towards or away from the slip flow steering gear 74.
Because the rotational rocker arm 741 driven by the slipstream steering engine 74 can rotate in both clockwise and counterclockwise directions, the rotational directions of the slipstream steering engine 72 are also two corresponding directions, specifically as follows:
(1) when the slip flow steering engine 74 drives the rotating rocker arm 741 to rotate clockwise, the connecting rod 73 controls the slip flow rudder 72 to rotate around the hinge 71 towards the slip flow steering engine 74; when the slip flow steering engine 74 drives the rotating rocker arm 741 to rotate anticlockwise, the connecting rod 73 controls the slip flow rudder 72 to rotate around the hinge 71 and depart from the slip flow steering engine 74;
(2) when the slip flow steering engine 74 drives the rotating rocker arm 741 to rotate clockwise, the connecting rod 73 controls the slip flow rudder 72 to rotate around the hinge 71 away from the slip flow steering engine 74; when the slip flow steering gear 74 drives the rotating rocker arm 741 to rotate anticlockwise, the connecting rod 73 controls the slip flow rudder 72 to rotate around the hinge 71 towards the slip flow steering gear 74.
In order to enhance the firmness of the connection between the second face 722 of the slipstream rudder 72 and the connecting rod 73, the pneumatic optimization mechanism 7 further comprises a fixed rocker arm 75, one end of the fixed rocker arm 75 is fixed to the second face 722 of the slipstream rudder 72, and the other end is fixed to one end of the connecting rod 73.
In one embodiment, hinge 71, slipstream rudder 72, link 73, slipstream steering gear 74 and fixed rocker arm 75 are all fixed by glue.
For the torsion that power rotor 5 produced is eliminated in further improvement, consequently many rotor crafts still includes a plurality of platform bracing pieces 8, the one end of each platform bracing piece 8 all is fixed mutually with the lower surface 12 of fuselage 1, the other end all is fixed mutually with the outer wall of mounting platform 4, and all be equipped with a slipstream steering wheel 74 on each platform bracing piece 8 lateral wall, and all link to each other with a corresponding slipstream rudder 72 through hinge 71, make slipstream rudder 72 distribute on different platform bracing pieces 8 like this, the air resistance of slipstream rudder 72 has been increased.
The embodiment of the invention adopts a fuel-electric hybrid design, and when the fuel engine 3 breaks down, the multi-rotor aircraft can still be controlled to safely approach the ground through the electric rotor mechanism 6, so that the electric rotor mechanism 6 comprises the brushless direct current motor 61 and the attitude adjusting rotor 62 arranged on the output shaft of the brushless direct current motor 61, and the brushless direct current motor 61 is controlled to adjust the rotating speed of the attitude adjusting rotor 62 through the first control signal, thereby achieving the purpose of safely approaching the ground of the multi-rotor aircraft.
Generally, the multi-rotor aircraft adopts two support frames 9 to install the electric rotor mechanism 6, the two support frames 9 are respectively fixed on two opposite side surfaces or end surfaces of the fuselage 2, and are designed in a symmetrical structure, so that the multi-rotor aircraft further comprises two support frames 9, and the fuselage 1 further comprises a first side surface 14 and a second side surface 15; wherein, two support frames 9 are fixed on the first side 14 and the second side 15 of the fuselage 1 respectively and are parallel to each other, and each support frame 9 extends to both sides respectively along the first side 14 of the fuselage 1 axially to form two installation positions 91 for installing the brushless dc motor 61 outside the fuselage 1. Wherein, each support frame 9 is fixed with the machine body 1 through screws.
In the embodiment of the invention, by introducing the aerodynamic design concept of the traditional aircraft, the outline of the fuselage 1 can be designed to be approximately in a semi-ellipse shape, and the wing shape design of the fixed wing aircraft is adopted, at this time, the fuselage 1 also comprises a third side surface 16; the thickness of the machine body 1 is gradually reduced from the third side surface 16 along the direction of the first side surface 14 deviating from the third side surface 16 along the axis, so that the machine body has a thickness difference, the upper surface 11 and the lower surface 12 of the machine body 1 are both formed into curved surfaces with certain radians, and the radian of the curved surface of the upper surface 11 is greater than that of the curved surface of the lower surface 12. When the airframe 1 and the air move relatively, the air flowing through the upper surface 11 has a longer path than the air flowing through the lower surface 12 at the same time, so the relative speed of the air on the upper surface 11 is faster than that of the air on the lower surface 12, and it can be known from panuli's theorem that "the pressure generated by the fluid on the surrounding substances is inversely proportional to the relative speed of the fluid", so the pressure generated by the upper surface 11 of the airframe 1 is less than that generated by the lower surface 12 of the airframe 1, so that the airframe 1 can generate a certain lift force, and the multi-rotor aircraft can be ensured to have a certain maneuvering capability in different directions, and the precision of fixed-point hovering can be improved.
The working principle of the pneumatic optimization oil-electricity hybrid multi-rotor aircraft provided by the embodiment of the invention is as follows: when the power rotor 5 of the multi-rotor aircraft rotates counterclockwise (as the arrow a moving direction in fig. 5), the multi-rotor aircraft body generates a clockwise torque (as the arrow b moving direction in fig. 5), and in order to overcome the torque, the flight control system sends a command to the pneumatic optimization mechanism 7, so that the slip flow steering engine 74 controls the slip flow rudder 72 to uniformly deflect in the same direction (as the arrow b moving direction in fig. 5), and thus the airflow flowing direction deflects (as the arrow b moving direction in fig. 5), and a corresponding reverse direction (as the arrow a moving direction in fig. 5) thrust is generated; at the moment, the aim of counteracting the torsion generated by the power rotor 5 of the multi-rotor aircraft is achieved through the thrust in the opposite direction generated by the airflow;
in the taking-off and landing process of the multi-rotor aircraft, as shown in fig. 6, the rotating speeds of the attitude adjusting rotors 61 are adjusted to be consistent, so that the rotating planes of the attitude adjusting rotors 61 are parallel to the horizontal plane, at the moment, the multi-rotor aircraft body 1 keeps a certain attack angle, and the multi-rotor aircraft is controlled to take off and land by the rotation of the power rotors 5 driven by the fuel engine 3;
during the forward flight of the multi-rotor aircraft, as shown in fig. 7, the rotation speed of the attitude control rotors 61 facing away from the third side surface 16 of the fuselage 1 is adjusted to increase, and at this time, the lift force generated by the attitude control rotors 61 facing away from the third side surface 16 is greater than the lift force generated by the attitude control rotors 61 facing toward the third side surface 16, so that the multi-rotor aircraft has a tendency of lowering its head, and the multi-rotor aircraft is advanced to fly by the horizontal component of the lift force generated by the respective attitude control rotors 61. Because the attack angle of the fuselage 1 of the multi-rotor aircraft is reduced, the horizontal aerodynamic resistance of the multi-rotor aircraft in the advancing direction is reduced, the multi-rotor aircraft has the optimal aerodynamic performance in the advancing direction, and the fuselage 1 can generate a certain lift force to achieve the increase of the cruising speed of the multi-rotor aircraft;
similarly, the principle of the retreating or lateral flying process of the multi-rotor aircraft is similar to that of the forward flying process of the multi-rotor aircraft, and is not repeated herein.
The embodiment of the invention has the following beneficial effects:
1. in the embodiment of the invention, the multi-rotor aircraft uses the fuel engine to provide main flight power, so that the mounting capacity and the endurance time of the multi-rotor aircraft are greatly increased;
2. in the embodiment of the invention, the multi-rotor aircraft adopts the slipstream rudder design on the basis of the fuel engine, so that the problem of back-twisting generated when the fuel engine works is solved, and the multi-rotor aircraft has the characteristics of simple control and small influence on the flight performance of the multi-rotor aircraft;
3. in the embodiment of the invention, the multi-rotor aircraft adopts the design that the aircraft body and the rotor plane have the installation angle difference, namely the aircraft body is designed to have the thickness difference change and the upper surface and the lower surface are curved surfaces with different radians, so that the aircraft body is in a horizontal posture in the front flying process of the multi-rotor aircraft, has smaller aerodynamic resistance in cruising, and simultaneously generates certain aerodynamic lift force, thereby effectively improving the overall cruising time and cruising speed of the aircraft;
4. in the embodiment of the invention, as the multi-rotor aircraft adopts the oil-electricity hybrid design, when the fuel engine fails, the multi-rotor aircraft can still be controlled to safely force to land through the electric rotor mechanism.
While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not to be limited to the disclosed embodiment, but on the contrary, is intended to cover various modifications and equivalent arrangements included within the spirit and scope of the appended claims.
Claims (9)
1. A pneumatic optimized hybrid multi-rotor aircraft, comprising:
the device comprises a machine body (1), wherein the machine body (1) comprises an upper surface (11), a lower surface (12) and a first cavity (13) penetrating through the upper surface (11) and the lower surface (12);
at least one landing gear (2), wherein the landing gear (2) is fixed with the lower surface (12) of the fuselage (1);
a fuel engine (3);
the semi-closed type mounting platform (4) is used for mounting the fuel engine (3), the mounting platform (4) is fixed with the lower surface (12) of the machine body (1), and a second cavity (41) with an opening facing the first cavity (13) and communicated with the first cavity (13) is formed in the mounting platform;
the power rotor wing (5) is driven by the fuel engine (3) to rotate and generates thrust to realize the flight of the multi-rotor aircraft, and the power rotor wing (5) is arranged on an output shaft of the fuel engine (3) and is positioned in the second cavity (41) or the first cavity (13);
at least one electric rotor mechanism (6) for receiving a distal first control signal to adjust the attitude of said multi-rotor craft; and
at least one pneumatic optimization mechanism (7) for receiving a distal second control signal to eliminate the back-twist of the multi-rotor aircraft during flight, wherein the pneumatic optimization mechanism (7) is arranged on the outer wall of the mounting platform (4);
the pneumatic optimization mechanism (7) comprises a hinge (71), a slip flow rudder (72), a connecting rod (73) and a slip flow steering engine (74); wherein,
at least one hinge (71) is arranged, one end of each hinge (71) is fixed on the outer wall of the mounting platform (4), and the other end of each hinge (71) is fixed with the first surface (721) of the slipstream rudder (72);
the slipstream rudder (72) can be rotatably arranged on the outer wall of the mounting platform (4) through the hinge (71), and a second surface (722) of the slipstream rudder is fixed with one end of the connecting rod (73);
the slipstream steering engine (74) is fixed on the outer wall of the mounting platform (4) and comprises a rotary rocker arm (741) connected with the other end of the connecting rod (73);
when the slipstream steering engine (74) drives the rotating rocker arm (741) to rotate, the connecting rod (73) is used for controlling the slipstream rudder (72) to rotate around the hinge (71) towards or away from the slipstream steering engine (74).
2. The multi-rotor aircraft according to claim 1, wherein the aerodynamic optimization mechanism (7) further comprises a fixed rocker arm (75), one end of the fixed rocker arm (75) being fixed to the second face (722) of the slipstream rudder (72) and the other end being fixed to one end of the link (73).
3. The multi-rotor aircraft according to claim 2, wherein when the slip steering engine (74) drives the rotary rocker arm (741) to rotate clockwise, the slip steering engine (72) is controlled to rotate around the hinge (71) towards the slip steering engine (74) through the connecting rod (73); when the slipstream steering engine (74) drives the rotating rocker arm (741) to rotate anticlockwise, the connecting rod (73) is used for controlling the slipstream rudder (72) to rotate around the hinge (71) and depart from the slipstream steering engine (74); or
When the slipstream steering engine (74) drives the rotating rocker arm (741) to rotate clockwise, the connecting rod (73) is used for controlling the slipstream rudder (72) to rotate around the hinge (71) and depart from the slipstream steering engine (74); when the slip flow steering engine (74) drives the rotating rocker arm (741) to rotate anticlockwise, the connecting rod (73) is used for controlling the slip flow rudder (72) to rotate around the hinge (71) towards the slip flow steering engine (74).
4. The multi-rotor aircraft according to claim 3, further comprising a plurality of platform support rods (8), wherein one end of each platform support rod (8) is fixed to the lower surface (12) of the fuselage (1), the other end of each platform support rod is fixed to the outer wall of the mounting platform (4), and the outer side wall of each platform support rod (8) is provided with one slip flow steering engine (74) and connected to a corresponding slip flow rudder (72) through the hinge (71).
5. The multi-rotor aircraft according to claim 4, wherein the electric rotor mechanism (6) comprises a brushless DC motor (61) and an attitude adjustment rotor (62) mounted on an output shaft of the brushless DC motor (61).
6. The multi-rotor aircraft according to claim 5, wherein the multi-rotor aircraft further comprises two support frames (9), the fuselage (1) further comprising a first side (14) and a second side (15); wherein,
two support frames (9) are fixed in respectively first side (14) and back are parallel to each other on second side (15), and each support frame (9) all follows fuselage (1) first side (14) axial respectively to both sides extend form two outside the fuselage (1) and are used for installing installation position (91) of brushless DC motor (61).
7. The rotorcraft according to claim 6, wherein each support frame (9) is fixed to the fuselage (1) by screws.
8. The multi-rotor aircraft according to claim 7, wherein the fuselage (1) further comprises a third side (16); the thickness of the machine body (1) is from the third side face (16) to follow the axis of the first side face (14) deviates from the direction movement of the third side face (16) is gradually reduced, the upper surface (11) and the lower surface (12) of the machine body (1) are both formed into curved surfaces with certain radians, and the curved surface radian of the upper surface (11) is greater than that of the lower surface (12).
9. The multi-rotor aircraft according to claim 8, wherein the output shaft of the fuel engine (3) is perpendicular to the central axis of the fuselage (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510250011.XA CN104859859B (en) | 2015-05-18 | 2015-05-18 | Pneumatic optimization oil-electricity hybrid multi-rotor aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510250011.XA CN104859859B (en) | 2015-05-18 | 2015-05-18 | Pneumatic optimization oil-electricity hybrid multi-rotor aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104859859A CN104859859A (en) | 2015-08-26 |
| CN104859859B true CN104859859B (en) | 2017-04-19 |
Family
ID=53906137
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510250011.XA Active CN104859859B (en) | 2015-05-18 | 2015-05-18 | Pneumatic optimization oil-electricity hybrid multi-rotor aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104859859B (en) |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105129079B (en) * | 2015-09-29 | 2017-08-25 | 郝建新 | A kind of long endurance Multi-axis aircraft of hybrid power |
| CN105539828B (en) * | 2015-12-08 | 2024-05-31 | 湖南众盛机械设备有限公司 | Self-generating oil-electricity hybrid power multi-rotor aircraft |
| CN206900666U (en) * | 2017-06-19 | 2018-01-19 | 张万民 | A kind of oil electric mixed dynamic multiaxis rotary wind type unmanned plane |
| CN110654534A (en) | 2018-06-29 | 2020-01-07 | 中光电智能机器人股份有限公司 | Rotorcraft |
| CN108773481B (en) * | 2018-07-02 | 2024-05-21 | 深圳市翔农创新科技有限公司 | Electric manned flight system |
| CN109466756B (en) * | 2018-12-06 | 2024-07-23 | 酷黑科技（北京）有限公司 | Multi-rotor aircraft |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2500577C1 (en) * | 2012-08-29 | 2013-12-10 | Яков Кузьмич Борзенко | Multirotor helicopter |
| CN103359284A (en) * | 2013-06-29 | 2013-10-23 | 天津大学 | Petrol-electric hybrid four-rotor unmanned aerial vehicle |
| CN203714176U (en) * | 2014-02-10 | 2014-07-16 | 安徽省华云高科技有限责任公司 | Hybrid power multi-rotor type aircraft |
| CN104260875B (en) * | 2014-09-19 | 2016-05-04 | 苏州天益航空科技有限公司 | The resistance to crash feature of agricultural plant protection unmanned plane |
| CN204750573U (en) * | 2015-05-18 | 2015-11-11 | 深圳供电局有限公司 | Pneumatic optimization oil-electricity hybrid multi-rotor aircraft |
-
2015
- 2015-05-18 CN CN201510250011.XA patent/CN104859859B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN104859859A (en) | 2015-08-26 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106927030B (en) | Oil-electricity hybrid power multi-rotor aircraft and flight control method thereof | |
| CN104859859B (en) | Pneumatic optimization oil-electricity hybrid multi-rotor aircraft | |
| KR101125870B1 (en) | The tiltrotor aircraft | |
| CN108298064B (en) | Unconventional yaw control system | |
| CN101875399A (en) | Tilt rotor aircraft adopting parallel coaxial dual rotors | |
| CN101559832A (en) | Fast hybrid helicopter with large range | |
| US20180244380A1 (en) | Apparatus And Method For Roll Moment Equalization At High Advance Ratios For Rotary Wing Aircraft | |
| CN109515704B (en) | Ducted plume rotorcraft based on cycloidal propeller technology | |
| CN106927035B (en) | Large maneuverability autorotation rotorcraft and control method thereof | |
| CN213800172U (en) | Cross type tilt rotorcraft | |
| CN112027073A (en) | Combined type tilting wing longitudinal rotation double-rotor aircraft | |
| CN117068370A (en) | Sweepback wing distributed unequal-diameter propeller disc tilting gyroplane and control method thereof | |
| CN217893226U (en) | Six-rotor electric vertical take-off and landing aircraft | |
| CN111532426A (en) | Aircraft with V-shaped empennage and multiple rotors in vertical take-off and landing layout | |
| CN107215458B (en) | Electric double coaxial tilting rotor craft | |
| CN206704538U (en) | The long continuation of the journey aerofoil multi-rotor unmanned aerial vehicle of one kind | |
| CN204750573U (en) | Pneumatic optimization oil-electricity hybrid multi-rotor aircraft | |
| CN216332756U (en) | Distributed electric tail rotor helicopter | |
| CN212354390U (en) | Vertical take-off and landing aircraft | |
| CN213649894U (en) | Thrust vector tail sitting type vertical take-off and landing unmanned aerial vehicle | |
| CN211618080U (en) | Vertical take-off and landing fixed wing aircraft with double-duct variable-pitch rotor wings | |
| CN213566470U (en) | Combined forward-pulling-in longitudinal-row autorotation double-rotor aircraft | |
| RU2412869C1 (en) | Universal "push-pull" aircraft | |
| CN111137450A (en) | Aircraft with split type lifting aileron and four-duct variable-pitch rotor wing | |
| CN111572764A (en) | Side-tipping longitudinal-row double-propeller electric helicopter |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| EXSB | Decision made by sipo to initiate substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |