CN206187328U - Reaction torque grid rudder of duct aircraft - Google Patents
Reaction torque grid rudder of duct aircraft Download PDFInfo
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- CN206187328U CN206187328U CN201621287895.2U CN201621287895U CN206187328U CN 206187328 U CN206187328 U CN 206187328U CN 201621287895 U CN201621287895 U CN 201621287895U CN 206187328 U CN206187328 U CN 206187328U
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- rudder
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- slip
- reaction torque
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Abstract
The utility model relates to a reaction torque grid rudder of duct aircraft, it is including a plurality of grid slipstream rudders of arranging in proper order (1), a plurality of grid slipstream rudder (1) links arbitrary one through grid slipstream rudder connecting rod (4) even as an organic whole and realization in step grid slipstream rudder (1) still is connected with drive servo steering wheel (5). The utility model discloses leave out current balanced anti -twisting device, used the balance of the reaction torque grid rudder realization reaction torque of brand -new structure to simplified the aircraft structure, the balance is more swift accurate, and has reduced the energy consumption of balanced needs, guarantees that the aircraft satisfies the requirement of VTOL, smooth flight, and state change is swift in flight, and the air current is mobile smooth and easy, can not influence normal flight.
Description
Technical field
The present invention relates to aircraft, belong to vehicle technology field, it is more particularly related to a kind of duct flies
The reaction torque grid rudder of device.
Background technology
Unmanned vehicle can be divided into fixed-wing class, rotor class and duct class by function, and duct aircraft is at present compared with forward position
Aircraft.
It is generally monomer duct that duct class aircraft is common at present, is only applicable to low-altitude low-speed flight, and be limited to separate unit hair
The problems such as motivation power and rotary inertia, monomer duct lifting capacity cannot have larger lifting, and structure is complex.
What duct aircraft was used is all that screw propeller (abbreviation propeller) is installed in duct, is provided by engine
Power rotates propeller, produces thrust aircraft is departed from ground, according to single group propeller, then when propeller rotates at a high speed
A reactive torque can be produced, it is necessary to the anti-twisted device of balance is installed in duct and offsets reaction torque, this adds increased system complex
Degree and reduce pneumatic efficiency in duct.If using double groups of screw propellers to turning cancel out each other itself reaction torque, spiral shell
Rotation oar propulsive efficiency can decrease, and need to increase duct depth dimensions and meet twin screw installing space.
The content of the invention
Based on above technical problem, the invention provides a kind of reaction torque grid rudder of duct aircraft, so as to solve
Conventional duct aircraft installs complex structure, the technical problem of efficiency reduction after the anti-twisted device of balance.
To solve above technical problem, the technical solution adopted by the present invention is as follows：
The reaction torque grid rudder of duct aircraft, including the grid slip-stream rudder that multiple is arranged in order, multiple grids are slided
Stream rudder is connected as a single entity by grid slip-stream rudder connecting rod and realizes synchronous interaction, and any one of grid slip-stream rudder is also associated with driving
Dynamic Servo-controller.
Further, multiple grid slip-stream rudder two ends are provided with rudder face rotating shaft, the driving Servo-controller connection
In the rudder face rotating shaft of any one of grid slip-stream rudder one end.
Further, the rudder face rotating shaft is connected with grid slip-stream rudder by rotor plate.
Further, the grid slip-stream rudder is provided with odd number, the grid that the driving Servo-controller is connected between altogether
Slip-stream rudder one end.
Further, the grid slip-stream rudder upper end is fixed with connecting plate, and connecting plate can with the grid slip-stream rudder connecting rod
What is rotated is articulated as one.
Further, the grid slip-stream rudder connecting rod is provided with two altogether, respectively positioned at the upper of multiple grid slip-stream rudders
End both sides.
Further, the grid slip-stream rudder is the smooth plate body structure in surface, and its cross section is for one end is big, one end is small
Taper.
Compared with prior art, the invention has effective effect that：Present invention omits the existing anti-twisted device of balance, use
The reaction torque grid rudder of brand new realizes the balance of reaction torque, and so as to simplify Flight Vehicle Structure, it is faster accurate to balance, and
Reduce the energy consumption that balance needs, it is ensured that aircraft meets the requirement of VTOL, smooth flight, state of flight changes quick,
And air current flow is smooth, normal flight is not interfered with.
Brief description of the drawings
Fig. 1 is the structural representation of reaction torque grid rudder；
Fig. 2 is the airflow direction schematic diagram of reaction torque grid rudder, and arrow represents airflow direction；
Label in figure is expressed as：1st, grid slip-stream rudder；2nd, connecting plate；3rd, rudder face rotating shaft；4th, grid slip-stream rudder connects
Bar；5th, Servo-controller is driven；6th, rotor plate.
Specific embodiment
The present invention is further illustrated below in conjunction with the accompanying drawings.Embodiments of the present invention include but is not limited to following reality
Apply example.
Embodiment 1
As shown in Figure 1 and Figure 2, the grid slip-stream rudder 1 that the reaction torque grid rudder of duct aircraft, including multiple is arranged in order,
Multiple grid slip-stream rudders 1 are connected as a single entity by grid slip-stream rudder connecting rod 4 and realize synchronous interaction, any one of grid
Slip-stream rudder 1 is also associated with driving Servo-controller 5.
The grid slip-stream rudder 1 of the present embodiment is spindle rotationally arranged in the duct of duct aircraft, positioned at propeller lower end；
Multiple grid slip-stream rudders 1 are connected as a single entity and realize synchronous interaction by grid slip-stream rudder connecting rod 4, can be by driving servo
Steering wheel 5 drives any one grid slip-stream rudder 1 to rotate, and realizes the synchronous axial system of all grid slip-stream rudders 1, changes and is slided by grid
The downwash flow direction of rudder 1 is flowed, such that it is able to change of flight device state of flight, and is adjusted by the deflection angle of grid slip-stream rudder 1
Its reaction being subject to, and then balance the reaction torque that aircraft brings by propeller rotational.
The present embodiment eliminates the existing anti-twisted device of balance, has used the reaction torque grid rudder of brand new to realize reaction torque
Balance, so as to simplify Flight Vehicle Structure, it is faster accurate to balance, and the rotation of whole device is realized by a steering wheel,
Reduce the energy consumption that balance needs, it is ensured that aircraft meets the requirement of VTOL, smooth flight, state of flight changes quick,
And air current flow is smooth, normal flight is not interfered with.
Embodiment 2
The present embodiment has done following optimization on the basis of embodiment 1：Multiple two ends of grid slip-stream rudder 1 are provided with
Rudder face rotating shaft 3, the driving Servo-controller 5 is connected in the rudder face rotating shaft 3 of any one of one end of grid slip-stream rudder 1.
The present embodiment by setting rudder face rotating shaft 3, such that it is able to whole reaction torque grid rudder is rotatably plugged on into culvert
On road aircraft, also, Servo-controller 5 is driven to be connected in the rudder face rotating shaft 3 of any one of one end of grid slip-stream rudder 1,
Such that it is able to Servo-controller 5 will be driven to be arranged on aircraft interior, it is to avoid steering wheel exposes and influences balance, using rudder face rotating shaft 3
Realize that connection has been also convenient for handling, increased the stability after grid slip-stream rudder 1 is installed.
Used as preferred, the rudder face rotating shaft 3 is connected with grid slip-stream rudder 1 by rotor plate 6.In order to realize flexibly control
System so that grid slip-stream rudder 1 rotates more accurate, realizes that rudder face rotating shaft 3 is connected with grid slip-stream rudder 5 using rotor plate 6, so as to drive
When dynamic Servo-controller 5 drives, the rotary action power of rudder face rotating shaft 3 can be converted into by rotor plate, determine its Impact direction,
And rotational angle control is more precisely, adjusts faster.
Embodiment 3
The present embodiment has done following optimization on the basis of embodiment 1 or embodiment 2：The grid slip-stream rudder 1 is provided with altogether
Odd number, one end of grid slip-stream rudder 1 that the driving Servo-controller 5 is connected between.
In order to ensure reaction torque grid rudder in adjustment reaction torque, realization that can be faster and better is balanced the present embodiment,
Grid slip-stream rudder 1 is arranged to odd number, and one end of grid slip-stream rudder 1 that driving Servo-controller 5 is connected between, so that even
Connect and drive the remaining number of grid slip-stream rudder 1 in the two ends of grid slip-stream rudder 1 or so of Servo-controller 5 identical, so as to adjust anti-twisted
During square, its active force is uniform, can preferably realize that reaction torque is balanced, and reduces regulating time and angle, reducing energy consumption.
Embodiment 4
The present embodiment increased following structure on the basis of any embodiment in embodiment 1- embodiments 4：The grid
The upper end of slip-stream rudder 1 is fixed with connecting plate 2, and connecting plate 2 is rotatably articulated as one with the grid slip-stream rudder connecting rod 4.
The connecting plate 2 of the present embodiment is fixed on the upper end of grid slip-stream rudder 1, and is rotatably cut with scissors with grid slip-stream rudder connecting rod 4
One is connected in, drives grid slip-stream rudder connecting rod 4 to move so as to connecting plate 2 when grid slip-stream rudder 1 is rotated, can be immediately passed through, from
And other grid slip-stream rudders 1 can also be moved at once, run duration zero deflection, such that it is able to it is faster, accurately control grid
The rotation of slip-stream rudder 1, the operation response time is short.
Embodiment 5
The present embodiment has done following optimization on the basis of any of the above-described embodiment：The grid slip-stream rudder connecting rod 4 sets altogether
There are two, respectively positioned at the upper end both sides of multiple grid slip-stream rudders 1.
The present embodiment being provided with grid slip-stream rudder connecting rod 4 positioned at the upper end both sides of multiple grid slip-stream rudders 1, from
And can ensure that, in the case where grid slip-stream rudder connecting rod 4 is acted on, the two ends of grid slip-stream rudder 1 can rotate, it is to avoid when rotating, grid is slided
The stream two ends rotatory force of rudder 1 is inconsistent and influence is rotated, or even increases the problem of rotating torque and energy consumption so that grid slip-stream rudder 1
Rotate more flexibly laborsaving.
Embodiment 6
The present embodiment optimizes grid slip-stream rudder on the basis of any of the above-described embodiment, specially：The grid slip-stream
Rudder 1 is the smooth plate body structure in surface, and its cross section is the taper that one end is big, one end is small.
The grid slip-stream rudder 1 of the present embodiment is mainly used in changing the direction of downwash flow, produces opposition to realize anti-
Balance, in order to ensure the constant magnitude of reaction force in desirable value, grid slip-stream rudder 1 is the smooth plate body structure in surface,
Be more uniformly distributed so as to gas flowing, it is smooth, be not in sinuous flow, flow direction is consistent, while its cross section is that one end is big, one end
Small taper so that gas can accelerate to pass through in outflow with the surface transition face of grid slip-stream rudder 1, improve reaction torque active force
And gas flow rate, reaction torque efficiency is improved, reduce the operating time.
Embodiments of the invention are as described above.Design parameter in above-described embodiment and embodiment is merely to clear
The invention verification process of inventor is stated by Chu, and is not used to limit scope of patent protection of the invention, patent protection of the invention
Scope is still defined by its claims, and every equivalent structure made with specification of the invention and accompanying drawing content becomes
Change, similarly should be included within the scope of the present invention.
Claims (7)
1. the reaction torque grid rudder of duct aircraft, it is characterised in that：It is many including grid slip-stream rudder (1) that multiple is arranged in order
The individual grid slip-stream rudder (1) is connected as a single entity by grid slip-stream rudder connecting rod (4) and realizes synchronous interaction, any one of grid
Lattice slip-stream rudder (1) is also associated with driving Servo-controller (5).
2. the reaction torque grid rudder of duct aircraft according to claim 1, it is characterised in that：Multiple grid slip-streams
Rudder (1) two ends are provided with rudder face rotating shaft (3), and driving Servo-controller (5) is connected to any one of grid slip-stream rudder
(1) in the rudder face rotating shaft (3) of one end.
3. the reaction torque grid rudder of duct aircraft according to claim 2, it is characterised in that：The rudder face rotating shaft (3)
It is connected by rotor plate (6) with grid slip-stream rudder (1).
4. the reaction torque grid rudder of the duct aircraft according to claim any one of 1-3, it is characterised in that：The grid
Slip-stream rudder (1) is provided with odd number altogether, grid slip-stream rudder (1) one end that the driving Servo-controller (5) is connected between.
5. the reaction torque grid rudder of duct aircraft according to claim 1, it is characterised in that：The grid slip-stream rudder
(1) upper end is fixed with connecting plate (2), and connecting plate (2) is rotatably articulated as one with the grid slip-stream rudder connecting rod (4).
6. the reaction torque grid rudder of duct aircraft according to claim 1, it is characterised in that：The grid slip-stream rudder connects
Bar (4) is provided with two altogether, respectively positioned at the upper end both sides of multiple grid slip-stream rudders (1).
7. the reaction torque grid rudder of duct aircraft according to claim 1, it is characterised in that：The grid slip-stream rudder
(1) it is the plate body structure that surface is smooth, its cross section is the taper that one end is big, one end is small.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621287895.2U CN206187328U (en) | 2016-11-29 | 2016-11-29 | Reaction torque grid rudder of duct aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621287895.2U CN206187328U (en) | 2016-11-29 | 2016-11-29 | Reaction torque grid rudder of duct aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206187328U true CN206187328U (en) | 2017-05-24 |
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ID=58725344
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621287895.2U Active CN206187328U (en) | 2016-11-29 | 2016-11-29 | Reaction torque grid rudder of duct aircraft |
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| CN (1) | CN206187328U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110979741A (en) * | 2019-11-25 | 2020-04-10 | 北京宇航系统工程研究所 | Sawtooth step type variable profile grid rudder structure based on falling area control |
-
2016
- 2016-11-29 CN CN201621287895.2U patent/CN206187328U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110979741A (en) * | 2019-11-25 | 2020-04-10 | 北京宇航系统工程研究所 | Sawtooth step type variable profile grid rudder structure based on falling area control |
| CN110979741B (en) * | 2019-11-25 | 2021-02-09 | 北京宇航系统工程研究所 | Sawtooth step type variable profile grid rudder structure based on falling area control |
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