CN114030645A - Rotor system for extraterrestrial exploration helicopter and operating mechanism thereof - Google Patents
Rotor system for extraterrestrial exploration helicopter and operating mechanism thereof Download PDFInfo
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- CN114030645A CN114030645A CN202111179808.7A CN202111179808A CN114030645A CN 114030645 A CN114030645 A CN 114030645A CN 202111179808 A CN202111179808 A CN 202111179808A CN 114030645 A CN114030645 A CN 114030645A
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- 230000007246 mechanism Effects 0.000 title claims abstract description 12
- 230000008859 change Effects 0.000 claims description 11
- 238000000034 method Methods 0.000 claims description 3
- 238000001514 detection method Methods 0.000 abstract description 9
- 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
- 230000000737 periodic effect Effects 0.000 description 3
- 238000006243 chemical reaction Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000000354 decomposition reaction Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000005406 washing Methods 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/14—Space shuttles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/467—Aerodynamic features
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/473—Constructional features
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses a rotor system for a planet detection helicopter, which relates to the technical field of planet detection helicopters and can comprise: the middle part of the hub is arranged on a rotor shaft, and the hub is also connected with a driving device which can drive the hub to rotate; a rotor comprising a plurality of rotor blades mounted to the hub; the inner side of the support wing is connected with a central connecting piece, and the central connecting piece is rotatably arranged on the rotor wing shaft; the duct is connected to the outer side of the supporting wings, and the supporting wings can support the duct. The invention also discloses an operating mechanism of the rotor system of the extraterrestrial globe detection helicopter. The invention can meet the functional requirements and the limitations of load capacity and volume under unknown environment.
Description
Technical Field
The invention relates to the technical field of exoplanet detection helicopters, in particular to a rotor system for an exoplanet detection helicopter and a control mechanism thereof.
Background
The helicopter has the capability of vertical flight, can fly in an environment of an extraterrestrial globe with unknown environment, and performs a detection task.
In the current conventional helicopter configuration, a rotor serves as a lifting surface, a propelling surface and a control surface, and the generated reaction torque is balanced by a tail rotor. In a coaxial helicopter, such as the Mars helicopter-Intelligent number in America, two pairs of rotors are coaxial and are used as a lifting surface, a propelling surface and a control surface together, and the two pairs of rotors rotate reversely to balance reaction torque. In addition, some aircrafts with multiple rotor wing configurations change the generated force and the moment relative to the gravity center through the rotation speed adjustment of different rotor wings, so that the effect of flight control is achieved.
Except for the multi-rotor configuration, the rotors of the rotor type aircraft are similar to the rotors of a helicopter with a conventional configuration, a coaxial rotor helicopter and the like, and are used as a lifting surface, a propelling surface and a control surface. When a flight task is executed, flight is realized by applying total pitch control and periodic pitch control to the rotor, under the control mode, the pitch of each blade can change for one period in the process of rotating for one circle, and under the condition of high rotating speed of the rotor, the pitch change of the blade is obvious, high-order aerodynamic load change can occur, and high-order blade structure load is brought, so that higher design requirements are required to be provided for the internal structure of the blade.
Therefore, it is desirable to provide a new rotor system for a planetary exploration helicopter and a control mechanism thereof to solve the above problems in the prior art.
Disclosure of Invention
The invention aims to provide a rotor system for an extraterrestrial planet detection helicopter and an operating mechanism thereof, which are used for solving the problems in the prior art and can meet the functional requirements and the limitations of load capacity and volume under unknown environments.
In order to achieve the purpose, the invention provides the following scheme:
the invention provides a rotor system for an extraterrestrial exploration helicopter, comprising:
the middle part of the hub is arranged on a rotor shaft, and the hub is also connected with a driving device which can drive the hub to rotate;
a rotor comprising a plurality of rotor blades mounted to the hub;
the inner side of the support wing is connected with a central connecting piece, and the central connecting piece is rotatably arranged on the rotor wing shaft;
the duct is connected to the outer side of the supporting wings, and the supporting wings can support the duct.
Preferably, the driving device adopts a direct drive motor, the direct drive motor can drive the hub to rotate so as to drive the rotor wing to rotate, and the output of the direct drive motor is controlled so as to change the rotating speed of the rotor wing, thereby changing the aerodynamic force of the rotor wing.
Preferably, rotor blade adopts inflatable paddle, rotor blade is provided with 8, 8 rotor blade follows the propeller hub is the circumference equipartition.
Preferably, the support wings are inflatable support wings, each support wing comprises an outer support wing and an inner support wing, the inner sides of the inner support wings are connected with the central connecting piece, the outer sides of the inner support wings are connected with the inner sides of the outer support wings through sleeves, and the outer sides of the outer support wings are connected with the duct.
Preferably, a variable pitch rocker arm is connected to the position of an inner side 1/4 chord line of the inner side support wing, the variable pitch rocker arm is connected with a pull rod, and a steering engine is connected below the pull rod.
Preferably, the number of the support wings is 4, and the 4 support wings are uniformly distributed along the circumference of the rotor shaft.
Preferably, the central link is rotatably connected to the rotor shaft by a bearing.
Preferably, the duct is an inflatable duct, the duct is an inflatable airbag before being unfolded, and the duct is the duct on the outer side after being unfolded.
The invention also discloses an operating mechanism of the rotor system for the extraterrestrial globe detection helicopter, which comprises the hub, wherein the hub is arranged on the rotor shaft and is connected with a driving device, the driving device can drive the hub and the rotor to rotate, and the lift force of the rotor is changed by adopting a rotating speed control mode;
the support wing is installed on the rotor shaft through a central connecting piece, and is used as a control surface and located below the rotor.
Compared with the prior art, the invention has the following beneficial technical effects:
1. the invention decomposes the functions of the original rotor system, controls the aircraft by applying manipulation to different parts, simplifies the complex hub system and reduces the structural load in the moving parts.
2. The invention changes the operation mode of the traditional rotor wing, the rotor wing changes the lift force through the control of the rotating speed, the mechanical structure of the existing propeller hub is simplified, the purpose of weight reduction is achieved, and the rotor wing does not have periodic change of the attack angle any more.
3. When the aircraft flies in any direction, the rotor wing still has the function of a part of propelling surface, and on the premise of ensuring stability, the flying speed is not high, the amplitude change of the aerodynamic load on the blade is not obvious, and the influence on the structure is small.
4. The function of the control surface of the invention is borne by the support wings, the lift force provided by the support wings is used for control, the balance and flight control of the aircraft are realized, the control of the support wings has no periodicity, and the generated aerodynamic force has no periodic load, so that the support wings have no obvious alternating load, and the requirement on the structural design is reduced.
In conclusion, the reasonable functional decomposition of the invention can unload the rotor, simplify the design structure and prolong the service life of the rotor, and the rotor shaft passes through the center of the whole aircraft, so that the generated aerodynamic force does not influence the attitude of the whole aircraft.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
FIG. 1 is a schematic view of a rotor system for an extraterrestrial exploration helicopter according to the present invention in a deployed state;
FIG. 2 is a schematic view of the assembly of the support wing tip of the present invention;
wherein, 1 is the duct, 2 is the propeller hub, 3 is the rotor blade, 4 is outside supporting wing, 5 is the sleeve, 6 is inside supporting wing, 7 is the displacement rocking arm, 8 is the pull rod, 9 is central connecting piece.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The invention aims to provide a rotor system for an extraterrestrial planet detection helicopter and an operating mechanism thereof, which are used for solving the problems in the prior art and can meet the functional requirements and the limitations of load capacity and volume under unknown environments.
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in further detail below.
Example one
As shown in fig. 1-2, the present embodiment provides a rotor system for an extraterrestrial exploration helicopter, mainly comprising:
a hub 2, the middle part of the hub 2 is arranged on a rotor shaft, and a driving device is connected to the hub 2 and can drive the hub 2 to rotate;
a rotor comprising a plurality of rotor blades 3, said plurality of rotor blades 3 being mounted on said hub 2;
the inner side of the support wing is connected with a central connecting piece 9, and the central connecting piece 9 is rotatably arranged on the rotor wing shaft;
the culvert 1, the culvert 1 connect in the outside of prop the wing, the prop the wing can be to the culvert 1 supports.
In this embodiment, the rotor and the fuselage can be put into operation after being inflated and deployed, and the supporting wings are deployed by inflating the air bags of the duct 1 and combining the auxiliary mechanism, as shown in fig. 1.
In the embodiment, the duct 1 is an inflatable airbag before being unfolded, and is an outer duct after being unfolded, and the shape of the duct is designed according to the pneumatic requirement; because the rotor wing in the embodiment only comprises the rotation speed control, the hub 2 has a simple structure, does not have a variable pitch structure similar to the rotor wing, is arranged on the rotor wing shaft in the middle, is connected with a direct drive motor (not shown in the figure) below, and changes the rotation speed of the rotor wing by controlling the output of the direct drive motor so as to change the aerodynamic force of the rotor wing; in the embodiment, 8 rotor blades 3 are adopted to form the rotor, and the installation angle is fixed; in this embodiment the duct 1 is supported by the outer support wings 4, the outer support wings 4 being in a folded state before deployment and after deployment being provided with a sleeve 5 at the location of attachment to the inner support wings 6.
In this embodiment, the connection relationship between the support wing and the rotor shaft is as follows:
as shown in fig. 2, in the present embodiment, the outer position of the inner support wing 6 is connected to the outer support wing 4 by the sleeve 5 after being deployed, and the pitch horn 7 is connected to the inner side 1/4 chord position of the inner support wing 6, and the aerodynamic moment changes little with respect to the pitch axis at the time of pitch change. The variable-pitch rocker arm 7 is connected with a pull rod 8, the lower part of the pull rod 8 is connected to a steering engine (not shown in the figure), the variable-pitch rocker arm is essentially a crank rocker mechanism, the angles of the support wings are changed through the control of the steering engine, the four groups of support wings can generate different forces under the condition that the installation angles are changed, the four groups of forces are synthesized, on one hand, the counter torque of the rotor wing is balanced, and on the other hand, the flight control is realized.
In this embodiment, the inner side of the prop wing is connected to the rotor shaft through a central connection member 9, the central connection member 9 and the rotor shaft are coaxial and rotate with each other, so that the central connection member 9 and the rotor shaft need to be connected by a bearing; the steering engine is arranged below a connecting plate (used for being connected with the supporting wings) extending out of the central connecting piece 9.
In the embodiment, the inner support wing 6 is fixed with the center of the rotor wing, does not participate in unfolding the variant, and the pull rod 8 is arranged at a more inner position, so that structural interference with the mechanism is avoided during variable pitch; the inner support wing 6 serves to connect the outer support wings 4 and is designed as an aerodynamic surface to improve the steering efficiency during flight control. In addition, the specific parameters of each connecting component in the embodiment can also be designed and adjusted according to specific performance requirements.
In the embodiment, the lifting force component is an inflatable rotor wing and a supporting wing for maintaining the appearance of the duct 1, and the whole aircraft is operated by the force and the moment generated by the aerodynamic surfaces. The rotor blade 3 of the embodiment is an inflatable blade, the rigidity of the rotor blade depends on the internal pressure of the air bag, and the rigidity of the rotor blade 3 is influenced by the rotating speed of the rotor under constant inflation pressure; therefore, in the embodiment, partial functions of the rotor are independent, the existing rotor is still used as a lifting surface and a propelling surface, and the lifting force is changed by adopting a rotating speed control mode to replace the existing collective pitch control, so that the aerodynamic load on the rotor blade 3 is not changed greatly when the rotating speed is constant; the supporting wings are used as control surfaces and are positioned in the downward washing flow of the rotor wing, the flow speed is low, and the control efficiency requirement under the environment of an extraterrestrial globe is met by selecting proper wing sections and shape design for the supporting wings.
In the embodiment, the configuration of the inflatable rotor wing and the inflatable duct 1 is adopted, so that the functional requirements, the carrying capacity and the volume limitation in an unknown environment are met.
It will be evident to those skilled in the art that the invention is not limited to the details of the foregoing illustrative embodiments, and that the present invention may be embodied in other specific forms without departing from the spirit or essential attributes thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein, and any reference signs in the claims are not intended to be construed as limiting the claim concerned.
The principle and the implementation mode of the invention are explained by applying a specific example, and the description of the embodiment is only used for helping to understand the method and the core idea of the invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, the specific embodiments and the application range may be changed. In view of the above, the present disclosure should not be construed as limiting the invention.
Claims (9)
1. A rotor system for a celestial exploration helicopter, comprising: the method comprises the following steps:
the middle part of the hub is arranged on a rotor shaft, and the hub is also connected with a driving device which can drive the hub to rotate;
a rotor comprising a plurality of rotor blades mounted to the hub;
the inner side of the support wing is connected with a central connecting piece, and the central connecting piece is rotatably arranged on the rotor wing shaft;
the duct is connected to the outer side of the supporting wings, and the supporting wings can support the duct.
2. A rotor system for a celestial exploration helicopter according to claim 1, wherein: the driving device adopts a direct-drive motor, the direct-drive motor can drive the hub to rotate so as to drive the rotor to rotate, and the output of the direct-drive motor is controlled to change the rotating speed of the rotor so as to change the aerodynamic force of the rotor.
3. A rotor system for a celestial exploration helicopter according to claim 1, wherein: rotor blade adopts inflatable paddle, rotor blade is provided with 8, 8 rotor blade follows the propeller hub is the circumference equipartition.
4. A rotor system for a celestial exploration helicopter according to claim 1, wherein: the support wings are inflatable support wings, each support wing comprises an outer side support wing and an inner side support wing, the inner sides of the inner side support wings are connected with the central connecting piece, the outer sides of the inner side support wings are connected with the inner sides of the outer side support wings through sleeves, and the outer sides of the outer side support wings are connected with the duct.
5. A rotor system for a celestial exploration helicopter according to claim 4, wherein: the inner side 1/4 chord line position of the inner side support wing is connected with a variable pitch rocker arm, the variable pitch rocker arm is connected with a pull rod, and a steering engine is connected below the pull rod.
6. A rotor system for a celestial exploration helicopter according to claim 5, wherein: the support wings are provided with 4, and 4 support wings are circumferentially and uniformly distributed along the rotor wing shaft.
7. A rotor system for a celestial exploration helicopter according to claim 1, wherein: the central connecting piece is rotatably connected with the rotor shaft through a bearing.
8. A rotor system for a celestial exploration helicopter according to claim 1, wherein: the duct is an inflatable duct, an inflatable air bag is arranged before the duct is unfolded, and the duct is arranged outside the duct after the duct is unfolded.
9. A steering mechanism for a rotor system of a extraterrestrial exploration helicopter according to any one of claims 1 to 8 wherein: the lifting force of the rotor wing is changed by adopting a rotating speed control mode;
the support wing is installed on the rotor shaft through a central connecting piece, and is used as a control surface and located below the rotor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111179808.7A CN114030645A (en) | 2021-10-11 | 2021-10-11 | Rotor system for extraterrestrial exploration helicopter and operating mechanism thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111179808.7A CN114030645A (en) | 2021-10-11 | 2021-10-11 | Rotor system for extraterrestrial exploration helicopter and operating mechanism thereof |
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| Publication Number | Publication Date |
|---|---|
| CN114030645A true CN114030645A (en) | 2022-02-11 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111179808.7A Pending CN114030645A (en) | 2021-10-11 | 2021-10-11 | Rotor system for extraterrestrial exploration helicopter and operating mechanism thereof |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103625640A (en) * | 2013-10-25 | 2014-03-12 | 南京航空航天大学 | Multi-rotor unmanned aerial vehicle |
| CN104816823A (en) * | 2015-04-21 | 2015-08-05 | 南京航空航天大学 | Duct rotary wing aircraft |
| CN106945829A (en) * | 2017-04-13 | 2017-07-14 | 南京航空航天大学 | A kind of universal hinge duct double-rotor aerobat |
| US9975633B1 (en) * | 2016-05-10 | 2018-05-22 | Northrop Grumman Systems Corporation | Collapsible ducted fan unmanned aerial system |
| CN109515704A (en) * | 2018-12-18 | 2019-03-26 | 南京航空航天大学 | Duct plume rotor craft based on cycloid propeller technology |
| CN113415438A (en) * | 2021-07-27 | 2021-09-21 | 南京航空航天大学 | Collapsible fuselage suitable for foreign body surveys helicopter |
-
2021
- 2021-10-11 CN CN202111179808.7A patent/CN114030645A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103625640A (en) * | 2013-10-25 | 2014-03-12 | 南京航空航天大学 | Multi-rotor unmanned aerial vehicle |
| CN104816823A (en) * | 2015-04-21 | 2015-08-05 | 南京航空航天大学 | Duct rotary wing aircraft |
| US9975633B1 (en) * | 2016-05-10 | 2018-05-22 | Northrop Grumman Systems Corporation | Collapsible ducted fan unmanned aerial system |
| CN106945829A (en) * | 2017-04-13 | 2017-07-14 | 南京航空航天大学 | A kind of universal hinge duct double-rotor aerobat |
| CN109515704A (en) * | 2018-12-18 | 2019-03-26 | 南京航空航天大学 | Duct plume rotor craft based on cycloid propeller technology |
| CN113415438A (en) * | 2021-07-27 | 2021-09-21 | 南京航空航天大学 | Collapsible fuselage suitable for foreign body surveys helicopter |
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