CN220535944U - Rotorcraft modular attitude control rotor head - Google Patents
Rotorcraft modular attitude control rotor head Download PDFInfo
- Publication number
- CN220535944U CN220535944U CN202321634238.0U CN202321634238U CN220535944U CN 220535944 U CN220535944 U CN 220535944U CN 202321634238 U CN202321634238 U CN 202321634238U CN 220535944 U CN220535944 U CN 220535944U
- Authority
- CN
- China
- Prior art keywords
- rotor
- rotor head
- wing
- flexible shaft
- gesture control
- 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
- 238000012423 maintenance Methods 0.000 claims abstract description 7
- 238000009434 installation Methods 0.000 claims description 9
- 238000005096 rolling process Methods 0.000 claims description 7
- 239000010935 stainless steel Substances 0.000 claims description 7
- 229910001220 stainless steel Inorganic materials 0.000 claims description 7
- 239000002131 composite material Substances 0.000 claims description 5
- 229910000838 Al alloy Inorganic materials 0.000 claims description 2
- 230000006978 adaptation Effects 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000007664 blowing Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000001141 propulsive effect Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 238000009987 spinning Methods 0.000 description 1
Abstract
Rotorcraft modularization gesture control rotor head, its characterized in that: the rotary wing comprises a machine body framework, a rotary wing head mounting base, a direction block, a gesture control mechanism, a brake, a pre-rotation mechanism, a rotary wing flapping limit mechanism, a rotary wing mounting assembly, a flexible shaft stay wire and other modularized components; the machine body framework is connected with the rotor head mounting base, and the gesture control mechanism is connected through a direction block; the brake, pre-rotation mechanism and the rotating mechanism are arranged above the gesture control mechanism; the rotor wing flapping limiting mechanism and the rotor wing mounting assembly are arranged above the rotating mechanism; the two groups of flexible shaft stay wires are respectively connected with two sides of the gesture control mechanism. The design is simple, practical and efficient, the maintenance cost of the rotor head of the autorotation rotorcraft is reduced, the rotor wings of different types and specifications are installed and used on the same rotor head, the rotor head does not need to be replaced integrally, and the weight of the rotor head can be effectively reduced by adopting the flexible shaft while the stability and the safety of the attitude control mechanism are ensured.
Description
Technical Field
The utility model relates to the technical field of autorotation rotor craft, in particular to a modularized attitude control rotor head of a rotor craft.
Background
A gyroplane is a rotorcraft that rotates by blowing a rotor with a relative airflow to generate lift, and its forward force is directly provided by an engine driving a propeller, which is an aircraft interposed between a helicopter and a fixed-wing aircraft. Owing to the unique flight principle and structural characteristics, compared with a fixed wing aircraft and a helicopter, the autorotor has the advantages of simple operation, lower cost, high safety, short take-off and landing distance, low-speed ultra-low-altitude flight capability and flexible operability, but cannot take off and land vertically and hover. The device has the characteristics of simplicity, light weight, convenience for concealment and the like, and can be used for aerial photography, weapon emission, battlefield reconnaissance and the like.
Autogyro lift is generated from rotation of the top rotor and forward power is generated from the propulsive propellers at the tail of the aircraft. The attitude control of the aircraft is mainly realized by controlling a rotor head attitude control rod and a vertical tail rudder, the rudder controls the heading of the aircraft, and the attitude control rod controls the inclination angle of a rotor system through a pull rod so as to control the pitching attitude and the rolling attitude of the aircraft.
The main attitude control part of the autorotation gyroplane is concentrated on a gyroplane head part, and the autorotation gyroplane on the market at present mainly uses the gyroplane head processed by integral aviation aluminum, and has the characteristics of high use and maintenance cost, incapability of adapting to different types of gyroplanes by a single gyroplane head, and the like. Therefore, the modularized rotor head can effectively improve maintenance cost and solve the problem of rotor adaptation of different types.
Disclosure of Invention
The utility model aims to solve the problems in the prior art, and provides a rotorcraft modularized attitude control rotor head, which is high in use and maintenance cost and cannot adapt to different types of rotors when providing safety and stability.
In order to achieve the above purpose, the utility model adopts the following technical scheme:
the gyroplane modular attitude control rotor head includes: the device comprises a frame body, a rotor head mounting base, a direction block, a gesture control mechanism, a brake, a pre-rotation mechanism, a rotor flapping limit mechanism, a rotor mounting assembly and a flexible shaft stay wire; the machine body framework is connected with the rotor head mounting base, and the gesture control mechanism is connected through a direction block; the brake, pre-rotation mechanism and the rotating mechanism are arranged above the gesture control mechanism; the rotor wing flapping limiting mechanism and the rotor wing mounting assembly are arranged above the rotating mechanism; the two groups of flexible shaft stay wires are respectively connected with two sides of the gesture control mechanism.
In the utility model, the direction block has left-right rolling and pitching control angle limiting.
In the utility model, the gesture control mechanism adopts a flexible shaft stay wire.
In the utility model, the brake adopts a bicycle brake component, and the replacement and maintenance cost is low.
In the utility model, the pre-rotation mechanism is driven by a flexible shaft, and the driving head is driven by a pneumatic shifting fork ejection mode.
In the utility model, the rotating mechanism adopts a double tapered roller bearing.
According to the rotary wing flapping limiting mechanism, the stainless steel teeterboard is connected with the rotating mechanism, and the main rotary wing flapping angle is limited by the limiting block.
In the utility model, the rotor wing installation component consists of a stainless steel rotor wing installation clamping plate and a main rotor wing height clamping block and is used for installing an aluminum alloy main rotor wing; the composite main rotor wing is used, the rotor wing mounting assembly can be dismounted, and the rotor wing mounting assembly is directly mounted on the rotor wing flapping limiting mechanism.
Compared with the prior art, the technical scheme of the utility model has the beneficial effects that:
the design is simple, practical and efficient, the maintenance cost of the rotor head of the autorotation rotorcraft is reduced, the rotor wings of different types and specifications are installed and used on the same rotor head, the rotor head does not need to be replaced integrally, and the weight of the rotor head can be effectively reduced by adopting the flexible shaft while the stability and the safety of the attitude control mechanism are ensured.
Drawings
FIG. 1 is a schematic elevational view of the present utility model;
FIG. 2 is an enlarged partial structural view of section A of FIG. 1 (including pitch angle, rotor flapping angle);
FIG. 3 is a schematic view of the roll angle of the present utility model;
FIG. 4 is a schematic diagram of the structure of the present utility model;
FIG. 5 is a schematic front view of a replacement composite blade according to the present utility model;
FIG. 6 is a perspective view of a replacement composite blade according to the present utility model;
reference numerals: the device comprises a 0-rotor, a 1-frame, a 2-rotor head mounting base, a 3-direction block, a 4-gesture control mechanism, a 5-brake, a 6-pre-rotation driven tooth, a 7-pre-rotation driving tooth, an 8-shifting fork, a 9-cylinder, a 10-rotation mechanism, a 11-rotor flapping limiting mechanism, a 12-rotor mounting assembly, a 13-flexible shaft and a 14-flexible shaft stay wire.
Detailed Description
In order to make the objects, technical solutions and advantages of the present utility model more clear, the technical problems, technical solutions and advantageous effects to be solved are more clear, and the present utility model will be further described in detail with reference to the accompanying drawings in the embodiments.
As shown in fig. 1-4, the modularized attitude control rotor head of the rotorcraft of the embodiment comprises a 0-rotor, a 1-frame, a 2-rotor head mounting base, a 3-direction block, a 4-attitude control mechanism, a 5-brake, a 6-pre-rotation driven tooth, a 7-pre-rotation driving tooth, an 8-shifting fork, a 9-cylinder, a 10-rotating mechanism, an 11-rotor flapping limiting mechanism, a 12-rotor mounting assembly, a 13-flexible shaft and a 14-flexible shaft stay wire.
The top of the 1-rack is connected and fixed with a 2-rotor head mounting base (comprising a left-right rolling limit rod); the 3-direction block (comprising a pitching angle limiting rod) is connected with the 2-rotor head mounting base, and the maximum rolling angle is limited to be 0+/-10 degrees; the 4-attitude control mechanism is connected with the 3-direction block, and the maximum pitching angle is limited to be 0+/-10 degrees.
The 5-brake (comprising a brake disc and a brake pump); the 10-rotating mechanism is formed by fixing an upper part and a lower part through bolts; the 5-brake disc and the 6-pre-rotation driven teeth are fixedly arranged on the lower part of the 10-rotating mechanism; the 5-brake pump is fixedly arranged on the 4-gesture control mechanism so as to realize the synchronization of braking and pre-rotation with the rotating mechanism; two groups of single-row tapered roller bearings at the lower part of the 10-rotating mechanism are fixedly arranged on the 4-gesture control mechanism through bolts so as to bear axial and radial loads and control axial displacement.
The 11-rotor wing flapping limiting mechanism is formed by fixing a stainless steel teeterboard and a rotor wing flapping limiting block through bolts; the two deep groove ball bearings are connected through bolts and are fixedly arranged above the 10-rotating mechanism, so that the rotor wing flapping limit is realized, meanwhile, good sliding performance is realized, and the maximum limiting angle of the main rotor wing flapping is limited to be 0+/-8 degrees.
The 12-rotor wing installation assembly is formed by fixing a stainless steel rotor wing installation clamping plate and a main rotor wing height clamping block through bolts, and the main rotor wing height clamping block is fixedly installed on the 11-rotor wing flapping limiting mechanism; the 0-rotor and the stainless steel rotor mounting clamp plate are fixed through bolts.
The 7-pre-rotation starting teeth are arranged on the 13-flexible shaft; the upper end and the lower end of the 13-flexible shaft are fixedly arranged in the 4-gesture control mechanism by deep groove ball bearings; the 8 shifting fork is connected with the 9-cylinder and is arranged in the 4-gesture control mechanism to form a four-bar mechanism so as to realize that the cylinder pushes the shifting fork, jack up the 7-pre-rotation starting tooth to realize the engagement and separation with the 6-pre-rotation driven tooth, and realize the pre-rotation of the rotor head when the other end of the flexible shaft is combined with the power of the engine.
The joint bearings at the end parts of the 14-flexible shaft stay wires are fixedly arranged at two sides of the 4-gesture control mechanism; the 14-flexible shaft stay wire sleeve is fixedly arranged on the 1-frame by a fixed base so as to control the pitching angle and the rolling angle of the rotor head.
The 0-rotor mount is secured to a 12-rotor mount assembly.
As shown in fig. 2-3, the working principle of the utility model is as follows:
the utility model is specifically executed by using 14-flexible shaft stay wires on two sides of a 4-gesture control mechanism respectively, and the pitch angle and the roll gesture of the spinning wing machine are changed to change the inclination angle of a rotor wing system to control the gesture. The pitch shaft and the roll shaft are arranged in the 3-direction block, and the 10-rotation mechanism changes angles through the two shafts. The pitching angle of the aircraft can be controlled by the same-direction operation of the two 14-flexible shaft stay wires, and the rolling angle of the aircraft can be controlled by the reverse operation. Specifically, when two 14-flexible axle guys act in the same direction (same upwards/same downwards), the 14-flexible axle guys can bring the 4-gesture control mechanism and the 10-rotary mechanism, the 11-rotor flapping limiting mechanism, the 12-rotor installation assembly and the 0-rotor fixed on the 4-gesture control mechanism to act around a pitching axis (upwards/downwards), so that a pitching angle limiting rod is realized, and the mechanical limiting control of the limiting position of the pitching angle of 0+/-10 degrees of the aircraft is realized.
When two 14-flexible shaft stay wires act reversely (up and down), the 14-flexible shaft stay wires can carry the 4-gesture control mechanism, the 10-rotating mechanism, the 11-rotor flapping limit mechanism, the 12-rotor installation assembly and the 0-rotor to act around a roll shaft (leftwards/rightwards) around a pitch axis, so that a left-right roll limit rod is realized, and the mechanical limit control of the limit position of the pitch angle of 0+/-10 degrees of the aircraft is realized.
As shown in fig. 5-6, in this example, in order to realize that the rotor blades with different types and specifications are installed and used on the same rotor head, the rotor head does not need to be replaced integrally, and the composite rotor can be directly installed by only removing the 12-rotor installation component.
Claims (8)
1. Rotorcraft modularization gesture control rotor head, its characterized in that: the rotary wing comprises a frame body, a rotary wing head mounting base, a direction block, a gesture control mechanism, a brake, a pre-rotation mechanism, a rotary wing flapping limit mechanism, a rotary wing mounting assembly, a flexible shaft and a flexible shaft stay wire; the machine body framework is connected with the rotor head mounting base, and the gesture control mechanism is connected through a direction block; the brake, pre-rotation mechanism and the rotating mechanism are arranged above the gesture control mechanism; the rotor wing flapping limiting mechanism and the rotor wing mounting assembly are arranged above the rotating mechanism; the two groups of flexible shaft stay wires are respectively connected with two sides of the gesture control mechanism.
2. The gyroplane modular attitude control rotor head according to claim 1, wherein: the direction block is provided with left-right rolling and pitching control angle limiting.
3. The gyroplane modular attitude control rotor head according to claim 1, wherein: the gesture control mechanism adopts a flexible shaft stay wire.
4. The gyroplane modular attitude control rotor head according to claim 1, wherein: the bicycle brake component is adopted for braking, and the replacement and maintenance cost is low.
5. The gyroplane modular attitude control rotor head according to claim 1, wherein: the pre-rotation mechanism is driven by a flexible shaft, and the driving teeth are ejected by a pneumatic shifting fork.
6. The gyroplane modular attitude control rotor head according to claim 1, wherein: the rotating mechanism adopts two groups of single-row tapered roller bearings.
7. The gyroplane modular attitude control rotor head according to claim 1, wherein: the rotor wing flapping limiting mechanism is connected with the rotating mechanism through a stainless steel teeterboard, and the limiting block limits the flapping angle of the main rotor wing.
8. The gyroplane modular attitude control rotor head according to claim 1, wherein: the rotor wing installation assembly consists of a stainless steel rotor wing installation clamping plate and a main rotor wing height clamping block and is used for installing an aluminum alloy main rotor wing; the composite main rotor wing is used, the rotor wing mounting assembly can be dismounted, and the rotor wing mounting assembly is directly mounted on the rotor wing flapping limiting mechanism.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321634238.0U CN220535944U (en) | 2023-06-26 | 2023-06-26 | Rotorcraft modular attitude control rotor head |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321634238.0U CN220535944U (en) | 2023-06-26 | 2023-06-26 | Rotorcraft modular attitude control rotor head |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220535944U true CN220535944U (en) | 2024-02-27 |
Family
ID=89965714
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202321634238.0U Active CN220535944U (en) | 2023-06-26 | 2023-06-26 | Rotorcraft modular attitude control rotor head |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220535944U (en) |
-
2023
- 2023-06-26 CN CN202321634238.0U patent/CN220535944U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106927030B (en) | Oil-electricity hybrid power multi-rotor aircraft and flight control method thereof | |
| US20220055744A1 (en) | Compound rotorcraft with propeller | |
| CN205707301U (en) | A kind of pulp distance varying mechanism | |
| CN201419624Y (en) | Double-bypass propeller aerocar capable of vertical taking off and landing | |
| RU129485U1 (en) | COXY SPEED HELICOPTER | |
| RU2673933C1 (en) | Gyroplane | |
| US3720387A (en) | Rotary wing system | |
| CN109515704B (en) | Ducted plume rotorcraft based on cycloidal propeller technology | |
| US3921939A (en) | Directional control system for helicopters | |
| CN213800172U (en) | Cross type tilt rotorcraft | |
| WO2014177591A1 (en) | Aircraft for vertical take-off and landing with an engine and a propeller unit | |
| CN209581870U (en) | Duct plume rotor craft based on cycloid propeller technology | |
| CN1754777A (en) | Vertical take-off and landing aircraft | |
| CN220535944U (en) | Rotorcraft modular attitude control rotor head | |
| CN116101478B (en) | Single-layer variable-pitch structure for miniature coaxial double-oar unmanned aerial vehicle and control method | |
| CN218537100U (en) | Single power driven unmanned aerial vehicle that verts | |
| CN214729655U (en) | Vertical take-off and landing fixed wing unmanned aerial vehicle | |
| CN112478151B (en) | Electric direct-drive tilting rotor craft | |
| CN211442754U (en) | Five-engine tilt rotor unmanned aerial vehicle | |
| CN110562444B (en) | Low-altitude composite aircraft | |
| GB2535231A (en) | Propeller for an aircraft for vertical take-off and landing | |
| CN217706254U (en) | Variable-pitch unmanned aerial vehicle power module | |
| CN214451817U (en) | Many rotor crafts with tail thrust | |
| CN218786084U (en) | Unmanned autorotation gyroplane control system | |
| CN216301464U (en) | Auxiliary emergency control device for helicopter |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |