CN110723277A - Unmanned digital telex control mechanism based on mosquito manned helicopter - Google Patents
Unmanned digital telex control mechanism based on mosquito manned helicopter Download PDFInfo
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- CN110723277A CN110723277A CN201911187240.6A CN201911187240A CN110723277A CN 110723277 A CN110723277 A CN 110723277A CN 201911187240 A CN201911187240 A CN 201911187240A CN 110723277 A CN110723277 A CN 110723277A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/24—Transmitting means
- B64C13/38—Transmitting means with power amplification
- B64C13/50—Transmitting means with power amplification using electrical energy
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/02—Mounting or supporting thereof
Abstract
The invention relates to the technical field of unmanned aerial vehicles, in particular to an unmanned digital telex control mechanism based on a mosquito manned helicopter, which comprises a pitching control mechanism, a rolling control mechanism, a tail rotor control mechanism, a total pitch control mechanism and an accelerator control mechanism, wherein the pitching control mechanism is arranged in a base cabin of the mosquito helicopter and used for controlling forward flight and backward flight, the rolling control mechanism is used for controlling left and right side flight, the tail rotor control mechanism is used for controlling the attack angle of a tail rotor, the total pitch control mechanism is used for controlling the attack angle of a main rotor, and the accelerator control mechanism is used for controlling the. The invention can quickly change the manned operation of the mosquito helicopter into unmanned telex digital operation, has little change to the original structure, has little damage to the body and reserves the capacity of changing the helicopter back to manned operation; the invention has the advantages of high safety, reasonable layout, simple and reliable structure and low cost of unmanned modification.
Description
Technical Field
The invention relates to the technical field of unmanned modification of manned helicopters, in particular to an unmanned digital telex control mechanism based on a mosquito manned helicopter.
Background
At present, a plurality of rotors occupy most of the river mountains in the unmanned aerial vehicle market, but the small unmanned aerial vehicles are short boards in the aspects of endurance time and load, and cannot meet the requirements of specific occasions (remote investigation, heavy load transportation, battlefield fire support and the like), and large unmanned helicopters cannot be replaced in the application scenes, and the main characteristics of the scenes are the three characteristics: large load, long endurance and wide coverage. The application of the large unmanned helicopter is mainly towed by military application in the early stage, replaces the manned helicopter to execute battlefield tasks, realizes zero casualties in the battlefield as a main target, and simultaneously achieves intellectualization as a main starting point.
The large unmanned helicopter is mainly embodied in three aspects: firstly, the load is heavy: at present, a common rotor wing unmanned aerial vehicle carries dozens of kilograms, and a large unmanned helicopter at least runs 100 kilograms; secondly, the flight time is long: the current general rotor unmanned aerial vehicle has a endurance of about half an hour, and the endurance of a large unmanned helicopter can reach 2-4 hours according to the proportion of load and oil; thirdly, the flight radius is large: the coverage is at least 20km or more.
Military applications in battlefield environments are mainly tactical reconnaissance, biochemical reconnaissance, accurate target positioning and striking, ship-to-ship anti-diving coordination and the like. The equipment required to be mounted in the applications, such as the weight of a photoelectric pod is generally more than 40 kilograms, the weight of the mounted lightest missile is also more than 20 kilograms, the common combat mission can not be used for carrying a single mission load, and the combat is matched with a plurality of mission loads in most cases, so that the requirement on the carrying capacity of the unmanned helicopter is higher along with the complexity of the mission. Except military application, the large unmanned helicopter with large carrying capacity and long endurance is required for logistics transportation in long-distance complex environment, large-scale forest fire prevention and other applications.
Because the large-scale helicopter is too complex in structural design, long in research and development period and high in cost, the forward direct design for research and development of the large-scale unmanned helicopter is not an optimal way, the existing medium and large-scale manned helicopter is subjected to unmanned transformation, unmanned autonomous flight is realized, and the method is an optimal method for research and development of the large-scale unmanned helicopter. The basic idea of unmanned transformation of the manned helicopter is that main structures such as an engine, a rotor wing and transmission of the manned helicopter are continuously used, and unmanned autonomous flight can be realized by carrying out structural transformation and electrical transformation on the main structures and additionally arranging a flight control system. The development period and the development cost of the unmanned helicopter are greatly shortened.
Disclosure of Invention
The invention aims to provide an unmanned digital fly-by-wire control mechanism based on a mosquito manned helicopter, which aims to solve the problems in the prior art.
The above object of the present invention is achieved by the following technical solutions:
an unmanned digital telex control mechanism based on a mosquito manned helicopter comprises a pitching control mechanism, a rolling control mechanism, a tail rotor control mechanism, a total distance control mechanism and an accelerator control mechanism, wherein the pitching control mechanism, the rolling control mechanism, the tail rotor control mechanism, the total distance control mechanism and the accelerator control mechanism are arranged in a cabin of the mosquito helicopter;
the pitching operation mechanism comprises a pitching steering engine fixing seat and a pitching operation rocker arm support which are arranged in the front of the cabin and distributed in the front and back direction, a pitching linear steering engine is hinged on the pitching steering engine fixing seat, an eccentrically arranged pitching operation rocker arm is hinged on the pitching operation rocker arm support, one end of the pitching operation rocker arm is rotatably connected with an output shaft of the pitching linear steering engine, and the other end of the pitching operation rocker arm is rotatably connected with a pitching operation connecting rod for controlling forward flight and backward movement;
the transverse rolling control mechanism comprises a transverse rolling steering engine fixing seat and a transverse rolling control rocker arm support which are arranged in the middle of the cabin and distributed left and right, a transverse rolling linear steering engine is hinged to the transverse rolling steering engine fixing seat, a pitching control linkage component is hinged to the transverse rolling control rocker arm support, the transverse rolling control mechanism further comprises a transverse rolling control torsion bar for controlling left and right flying, and an output shaft of the transverse rolling linear steering engine drives the transverse rolling control torsion bar to realize torsion through the pitching control linkage component;
the tail rotor operating mechanism comprises a tail rotor steering engine fixing seat and a tail rotor operating rocker arm support, the tail rotor steering engine fixing seat and the tail rotor operating rocker arm support are arranged on the left side of the front portion of the cabin and distributed in the front-back direction, a tail rotor linear steering engine is hinged to the tail rotor steering engine fixing seat, a tail rotor operating linkage assembly is hinged to the tail rotor operating rocker arm support, the tail rotor operating mechanism further comprises a tail rotor operating connecting rod used for controlling the attack angle of a tail rotor, and an output shaft of the tail rotor linear steering engine drives the tail rotor operating connecting rod through the tail rotor operating linkage assembly to realize forward-backward shifting;
the total distance control mechanism comprises a total distance steering engine fixing seat arranged on the left side of the back wall of the cabin, a total distance linear steering engine is hinged to the total distance steering engine fixing seat, and an output shaft of the total distance linear steering engine drives a total distance control lever used for controlling the attack angle of the main rotor;
the accelerator control mechanism comprises an accelerator steering engine fixing seat arranged at the bottom of the left rear side of the cabin, an accelerator rotary steering engine is fixedly mounted on the accelerator steering engine fixing seat, an output shaft of the accelerator rotary steering engine is fixedly sleeved with an accelerator cable winch, and an accelerator cable for controlling the size of an accelerator is wound on the accelerator cable winch.
Preferably, the pitching steering engine fixing seat and the pitching control rocker arm support are respectively and fixedly arranged at the front part and the rear part of the keel boss positioned at the front axial part of the cabin; the pitching control rocker arm is a folding arm with an included angle of 150 degrees, the long arm end of the pitching control rocker arm is rotatably connected with the output shaft of the pitching linear steering engine, and the short arm end of the pitching control rocker arm is rotatably connected with the pitching control connecting rod.
Preferably, the middle part of the cabin is provided with a support frame for bearing the fixed seat of the rolling steering engine and the support of the rolling control rocker arm; the pitching operation linkage assembly comprises a rolling operation rocker arm rotating shaft which is hinged on a rolling operation rocker arm support through a bearing, and a rolling operation short rocker arm and a rolling operation long rocker arm are respectively fixedly sleeved at two ends of the rolling operation rocker arm rotating shaft; the transverse rolling control torsion bar is fixedly sleeved with a transverse rolling control small rocker arm, one end of the transverse rolling control small rocker arm, far away from the transverse rolling control torsion bar, is hinged with a transverse rolling rocker arm connecting rod, one end of the transverse rolling rocker arm connecting rod, far away from the transverse rolling control small rocker arm, is hinged with the transverse rolling control long rocker arm for limitation, and the output end of the transverse rolling linear steering engine is hinged with the transverse rolling control short rocker arm for limitation.
Preferably, the tail rotor operation linkage assembly comprises a tail rotor operation rocker arm rotating shaft which is hinged to a tail rotor operation rocker arm support through a bearing, a tail rotor operation short rocker arm and a tail rotor operation long rocker arm are fixedly sleeved at two ends of the tail rotor operation rocker arm rotating shaft respectively, an output shaft of the tail rotor linear steering engine is hinged to the tail rotor operation long rocker arm to be limited, and one end of the tail rotor operation connecting rod is hinged to the tail rotor operation short rocker arm to be limited.
Preferably, the total distance control mechanism further comprises a total distance control square pipe, a total distance control rod joint is fixedly mounted at one end of the total distance control square pipe, an output shaft of the total distance linear steering engine is hinged and limited with the total distance control rod joint, and the other end of the total distance control square pipe is fixedly mounted on the total distance control rod through a bolt matched clamping piece.
Preferably, the throttle cable winch is provided with a mounting hole, and the throttle cable chuck is embedded and fixed in the mounting hole; the throttle cable penetrates through a pressing hole of the throttle cable chuck and then is wound on the throttle cable winch.
Preferably, a sleeve is injected outside the throttle cable, and one end of the sleeve is clamped and fixed with the side wall of the throttle steering engine fixing seat so as to prevent the throttle cable from moving when being pulled; the sleeve is fixed at the bottom of the cabin along the length direction of the sleeve by sleeving a plurality of wire clamps.
Compared with the prior art, the invention provides an unmanned digital fly-by-wire control mechanism based on a mosquito manned helicopter, which has the following beneficial effects:
1. the invention can quickly change the manned operation of the mosquito helicopter into unmanned telex digital operation, has little change to the original structure, has little damage to the body and reserves the capacity of changing the helicopter back to manned operation;
2. according to the scheme, the steering engine and the mechanism are arranged in the front of the cabin far away from the main rotor shaft, the center of gravity deviated to the back of the main rotor shaft can be adjusted, the effective load capacity of the airplane is increased, and the flying safety is improved;
3. the unmanned control mechanism has simple and reliable structure and reasonable layout, can greatly reduce the unmanned modification cost, has good accessibility and is beneficial to the later use and maintenance of the airplane.
Drawings
FIG. 1 is a block diagram of an unmanned digital fly-by-wire operation retrofit for a mosquito manned helicopter;
FIG. 2 is a schematic sectional view of the portion A-A in FIG. 1;
FIG. 3 is a schematic sectional view of the portion B-B in FIG. 2;
fig. 4 is a schematic sectional view of the portion C-C in fig. 2.
In the figure: 10. a pitch steering mechanism; 11. a pitching steering engine fixing seat; 12. a pitching operation rocker arm support; 13. a pitching linear steering engine; 14. a pitch control rocker arm; 15. a pitch steering link; 20. a roll operating mechanism; 21. a fixed base of a rolling steering engine; 22. a roll control rocker arm support; 23. a roll linear steering engine; 24. a roll steering linkage assembly; 241. a roll control rocker arm rotating shaft; 242. the short rocker arm is operated by rolling; 2. a long rocker arm is operated by rolling; 243. a small rocker arm is operated by rolling; 25. a roll steering torsion bar; 26. a support frame; 27. a roll rocker arm linkage; 30. a tail rotor operating mechanism; 31. a tail rotor steering engine fixing seat; 32. the tail rotor operates the rocker arm support; 33. a tail rotor linear steering engine; 34. a tail rotor operating linkage assembly; 35. a tail rotor operating connecting rod; 40. a collective pitch control mechanism; 41. a total distance steering engine fixing seat; 42. a total distance linear steering engine; 43. operating the square tube at the total distance; 431. a collective lever joint; 50. an accelerator operating mechanism; 51. an accelerator steering engine fixing seat; 52. a throttle rotating steering engine; 53. a throttle cable winch; 54. a throttle cable; 55. a throttle wire chuck; 56. a sleeve.
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.
Example (b): referring to fig. 1-3, the present invention provides a technical solution: an unmanned digital fly-by-wire control mechanism based on a mosquito manned helicopter comprises a pitch control mechanism 10, a roll control mechanism 20, a tail rotor control mechanism 30, a total distance control mechanism 40 and a throttle control mechanism 50 which are arranged in a cabin of the mosquito helicopter.
Every single move operating device 10 includes through bolt fixed mounting on the anterior fossil fragments boss of passenger cabin, be the every single move steering wheel fixing base 11 and the every single move control rocking arm support 12 of front and back distribution, is equipped with the ears on the every single move steering wheel fixing base 11 and connects, is equipped with the round hole on connecting for articulated installation every single move straight line steering wheel 13, the ears both sides are equipped with the strengthening rib, are used for improving 11 side direction rigidity of every single move steering wheel fixing base. The pitching control rocker arm 14 is also provided with a double-lug joint, the joint is provided with a round hole and used for being hinged with the pitching control rocker arm 14, the pitching control rocker arm 14 can swing back and forth around the round hole between the double lugs, and reinforcing ribs are arranged on two sides of the double lugs and used for improving the lateral rigidity of the pitching control rocker arm support 12. The pitching control rocker arm 14 is a folding arm with an included angle of 150 degrees, a center hole is formed in the top angle of the folding arm, a deep groove ball bearing is arranged in the folding arm and used for being installed on the pitching control rocker arm support 12, the long arm end of the pitching control rocker arm 14 is rotatably connected with the output shaft of the pitching linear steering engine 13, and the short arm end of the pitching control rocker arm 14 is rotatably connected with a pitching control connecting rod 15 used for controlling forward flying and backward moving.
When the pitching linear steering engine 13 extends or shortens, the output shaft of the pitching linear steering engine 13 drives the pitching control rocker arm 14 to rotate, the pitching control rocker arm 14 pushes and pulls the pitching control connecting rod 15, the front and back inclination of the airplane paddle disk is controlled, and the pitching control of the helicopter is realized.
Compared with the original manual pitching operation, the pitching linear steering engine 13, the pitching steering engine fixing seat 11, the pitching operation rocker arm 14, the pitching rocker arm support and other parts are added, the pitching operation connecting rod 15 is shortened, and the manual operating lever is reduced
The roll control mechanism 20 comprises a support frame 26 which is fixedly arranged in the middle of the cabin through bolts and distributed left and right, and the support frame 26 is made of glass fiber composite materials. A transverse-rolling steering engine fixing seat 21 and a transverse-rolling control rocker arm support 22 are fixedly installed on the supporting frame 26 through bolts, a transverse-rolling linear steering engine 23 is hinged to the transverse-rolling steering engine fixing seat 21, a transverse-rolling control linkage component 24 is hinged to the transverse-rolling control rocker arm support 22, the transverse-rolling control mechanism 20 further comprises a transverse-rolling control torsion bar 25 for controlling left and right flying, and an output shaft of the transverse-rolling linear steering engine 23 drives the transverse-rolling control torsion bar 25 to twist through the transverse-rolling control linkage component 24; the roll control linkage assembly 24 comprises a roll control rocker arm rotating shaft 241 which is hinged on the roll control rocker arm support 22 through a bearing, and a roll control short rocker arm 242 and a roll control long rocker arm 2 are respectively fixedly sleeved at two ends of the roll control rocker arm rotating shaft 241; a small roll control rocker arm 243 is fixedly sleeved on the roll control torsion bar 25, one end of the small roll control rocker arm 243, far away from the roll control torsion bar 25, is hinged with a roll rocker arm connecting rod 27, one end of the roll rocker arm connecting rod 27, far away from the small roll control rocker arm 243, is hinged with the long roll control rocker arm 2 for limitation, and the output end of the roll linear steering engine 23 is hinged with the short roll control rocker arm 242 for limitation.
When the roll linear steering engine 23 extends or shortens, the roll linear steering engine 23 drives the roll control short rocker arm 242 to rotate, the roll control short rocker arm 242 sequentially drives the roll control long rocker arm 2, the roll rocker arm connecting rod 27 and the roll control small rocker arm 243 to be linked through the roll control rocker arm rotating shaft 241, so that the roll control torsion bar 25 rotates around the axis of the roll control torsion bar, the main rotor blade disc inclines left and right, the main rotor blade disc swings the hand lever left and right just like a person drives, and roll control of the helicopter is realized.
Compared with the original manual roll operation, the roll linear steering engine 23, the roll operation linkage assembly 24 and other parts are added, and the manual operating rods are reduced.
The tail rotor operating mechanism 30 comprises a tail rotor steering engine fixing seat 31 and a tail rotor operating rocker arm support 32 which are fixedly arranged on the left side of the front part of the cabin through bolts and distributed front and back, a tail rotor linear steering engine 33 is hinged on the tail rotor steering engine fixing seat 31, a tail rotor operating linkage assembly 34 is hinged on the tail rotor operating rocker arm support 32, the tail rotor operating mechanism 30 further comprises a tail rotor operating connecting rod 35 used for controlling the attack angle of the tail rotor, and an output shaft of the tail rotor linear steering engine 33 drives the tail rotor operating connecting rod 35 through the tail rotor operating linkage assembly 34 to realize forward and backward shifting; the tail rotor control linkage assembly 34 comprises a tail rotor control rocker arm rotating shaft which is hinged to the tail rotor control rocker arm support 32 through a bearing, a tail rotor control short rocker arm and a tail rotor control long rocker arm are fixedly sleeved at two ends of the tail rotor control rocker arm rotating shaft respectively, an output shaft of the tail rotor linear steering engine 33 is hinged to the tail rotor control long rocker arm to be limited, and one end of a tail rotor control connecting rod 35 is hinged to the tail rotor control short rocker arm to be limited.
When the tail rotor linear steering engine 33 extends or shortens, the tail rotor control rocker arm is driven to rotate, so that the tail rotor control lever extends or shortens, the attack angle of the tail rotor is increased or decreased, and the tail rotor is controlled. The tail rotor linear steering engine 33 drives the tail rotor control long rocker arm to rotate, the tail rotor control long rocker arm sequentially drives the tail rotor control short rocker arm and the tail rotor control connecting rod 35 to be linked through a tail rotor control rocker arm rotating shaft, and therefore the tail rotor control connecting rod 35 extends or shortens, the increase or reduction of the attack angle of the tail rotor is achieved, and therefore the control of the tail rotor is achieved.
Compared with the original manual tail rotor operation, the tail rotor linear steering engine 33, the tail rotor steering engine fixing seat 31, the tail rotor operation linkage assembly 34 and other parts are added, and the left pedal, the right pedal and the transmission mechanism thereof can be dismounted.
The total distance control mechanism 40 comprises a total distance steering engine fixing seat 41 fixedly installed on the left side of the back wall of the cabin through bolts, a total distance linear steering engine 42 is installed on the total distance steering engine fixing seat 41 in a hinged mode, the total distance control mechanism 40 further comprises a total distance control square tube 43, a total distance control rod joint is installed at one end of the total distance control square tube 43 through bolts in a fixed mode, an output shaft of the total distance linear steering engine 42 is limited to be hinged with the total distance control rod joint, and the other end of the total distance control square tube 43 is fixedly installed on the total distance control rod through a bolt matching clamping piece.
When the collective pitch linear steering engine 42 extends or shortens, the collective pitch control lever is driven to move, the incidence angle of the main rotor wing is increased or decreased accordingly, and the incidence angle of the helicopter rotor wing is controlled.
Compared with the original manual collective pitch operation, the parts such as the collective pitch linear steering engine 42, the collective pitch steering engine fixing seat 41, the collective pitch control rod joint and the like are added, the original longer collective pitch control rod is replaced by a section of square aluminum pipe with proper length, the arm length of the collective pitch control rod is shortened, and the throttle control device on the manual control rod is reduced.
The accelerator operating mechanism 50 comprises an accelerator steering engine fixing seat 51 fixedly mounted at the bottom of the left rear side of the cabin through bolts, an accelerator rotary steering engine 52 is fixedly mounted on the accelerator steering engine fixing seat 51, an output shaft of the accelerator rotary steering engine 52 is fixedly sleeved with an accelerator cable winch 53, the accelerator cable winch 53 rotates along with the output shaft of the accelerator rotary steering engine 52, a mounting hole is formed in the accelerator cable winch 53, and an accelerator cable clamping head 55 is fixedly embedded in the mounting hole; the throttle cable 54 is wound on the throttle cable winch 53 after passing through a compression hole of the throttle cable chuck 55, and a bolt for compressing the throttle cable 54 is connected to one side of the compression hole of the throttle cable chuck 55 in a threaded manner. A sleeve 56 is injected outside the throttle cable 54, one end of the sleeve 56 is clamped and fixed with the side wall of the throttle steering engine fixing seat 51, and particularly, a limiting head fixedly sleeved at one end of the sleeve 56 is in threaded connection with a matching nut to realize the clamping effect on the side wall of the throttle steering engine fixing seat 51 so as to prevent the sleeve 56 from being driven to move when the throttle cable 54 is pulled; the sleeve 56 is fixed at the bottom of the cabin along the length direction by sleeving a plurality of wire clamps, so that collision with a movable mechanism during shaking is prevented.
When the accelerator rotary steering engine 52 rotates clockwise, the accelerator cable winch 53 pulls the accelerator cable 54 to wind the steel wire, the accelerator opening is increased, when the accelerator rotary steering engine 52 rotates anticlockwise, the accelerator cable 54 resets under the action of the reset spring, the accelerator opening is decreased, and therefore the control of the size of the engine accelerator is achieved.
Compared with the original manual throttle control, the throttle rotary steering gear 52, the throttle steering gear fixing seat 51, the throttle cable winch 53, the throttle cable chuck 55 and other parts are added, and the original throttle control handle and the rotary pulling device thereof can be disassembled.
The steering engine that this scheme adopted all selects according to the stroke, the load that operating mechanism needs, what chose for use is the goods shelves product of the maturity on the market.
It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (7)
1. An unmanned digital fly-by-wire control mechanism based on a mosquito manned helicopter is characterized by comprising a pitching control mechanism (10), a rolling control mechanism (20), a tail rotor control mechanism (30), a total distance control mechanism (40) and an accelerator control mechanism (50) which are arranged in a cabin of the mosquito helicopter;
the pitching operation mechanism (10) comprises a pitching steering engine fixing seat (11) and a pitching operation rocker arm support (12) which are arranged in the front of the cabin and distributed front and back, a pitching linear steering engine (13) is hinged on the pitching steering engine fixing seat (11), an eccentrically arranged pitching operation rocker arm (14) is hinged on the pitching operation rocker arm support (12), one end of the pitching operation rocker arm (14) is rotatably connected with an output shaft of the pitching linear steering engine (13), and the other end of the pitching operation rocker arm (14) is rotatably connected with a pitching operation connecting rod (15) used for controlling forward flight and backward movement;
the transverse rolling control mechanism (20) comprises a transverse rolling steering engine fixing seat (21) and a transverse rolling control rocker arm support (22) which are arranged in the middle of the cabin and distributed left and right, a transverse rolling linear steering engine (23) is hinged to the transverse rolling steering engine fixing seat (21), a transverse rolling control linkage assembly (24) is hinged to the transverse rolling control rocker arm support (22), the transverse rolling control mechanism (20) further comprises a transverse rolling control torsion bar (25) used for controlling left and right flying, and an output shaft of the transverse rolling linear steering engine (23) drives the transverse rolling control torsion bar (25) to realize torsion through the transverse rolling control linkage assembly (24);
the tail rotor control mechanism (30) comprises a tail rotor steering engine fixing seat (31) and a tail rotor control rocker arm support (32), the tail rotor steering engine fixing seat (31) is arranged on the left side of the front portion of the cabin and distributed in the front-back direction, a tail rotor linear steering engine (33) is hinged to the tail rotor steering engine fixing seat (31), a tail rotor control linkage assembly (34) is hinged to the tail rotor control rocker arm support (32), the tail rotor control mechanism (30) further comprises a tail rotor control connecting rod (35) used for controlling a tail rotor attack angle, and an output shaft of the tail rotor linear steering engine (33) drives the tail rotor control connecting rod (35) through the tail rotor control linkage assembly (34) to realize forward-backward shifting;
the total distance control mechanism (40) comprises a total distance steering engine fixing seat (41) arranged on the left side of the back wall of the cabin, a total distance linear steering engine (42) is hinged to the total distance steering engine fixing seat (41), and an output shaft of the total distance linear steering engine (42) drives a total distance control lever used for controlling the incidence angle of the main rotor;
the accelerator control mechanism (50) comprises an accelerator steering engine fixing seat (51) arranged at the bottom of the left back side of the cabin, an accelerator rotary steering engine (52) is fixedly mounted on the accelerator steering engine fixing seat (51), an accelerator wire winch (53) is fixedly sleeved on an output shaft of the accelerator rotary steering engine (52), and an accelerator wire (54) used for controlling the size of an accelerator is wound on the accelerator wire winch (53).
2. The unmanned digital fly-by-wire control mechanism based on the mosquito manned helicopter according to claim 1, characterized in that the pitching steering engine fixing seat (11) and the pitching control rocker arm support (12) are respectively and fixedly arranged at the front part and the rear part of a keel boss positioned at the front axial part of the cabin; the pitching control rocker arm (14) is a folding arm with an included angle of 150 degrees, the long arm end of the pitching control rocker arm (14) is rotatably connected with the output shaft of the pitching linear steering engine (13), and the short arm end of the pitching control rocker arm (14) is rotatably connected with the pitching control connecting rod (15).
3. The unmanned digital fly-by-wire operating mechanism based on the mosquito manned helicopter according to claim 1, characterized in that a support frame (26) for bearing the roll steering engine fixing seat (21) and the roll operating rocker arm support (22) is arranged in the middle of the cabin; the roll control linkage assembly (24) comprises a roll control rocker arm rotating shaft (241) which is hinged to the roll control rocker arm support (22) through a bearing, and two ends of the roll control rocker arm rotating shaft (241) are respectively fixedly sleeved with a roll control short rocker arm (242) and a roll control long rocker arm (2); the transverse-rolling control torsion bar (25) is fixedly sleeved with a transverse-rolling control small rocker arm (243), one end, far away from the transverse-rolling control torsion bar (25), of the transverse-rolling control small rocker arm (243) is hinged to a transverse-rolling rocker arm connecting rod (27), one end, far away from the transverse-rolling control small rocker arm (243), of the transverse-rolling rocker arm connecting rod (27) is hinged to the transverse-rolling control long rocker arm (2) for limitation, and the output end of the transverse-rolling linear steering engine (23) is hinged to the transverse-rolling control short rocker arm (242) for limitation.
4. The unmanned digital telex control mechanism based on the manned helicopter with mosquitoes according to claim 1, wherein the tail rotor control linkage assembly (34) comprises a tail rotor control rocker rotating shaft which is hinged and installed on a tail rotor control rocker support (32) through a bearing, a tail rotor control short rocker and a tail rotor control long rocker are fixedly sleeved at two ends of the tail rotor control rocker rotating shaft respectively, an output shaft of the tail rotor linear steering engine (33) is hinged and limited with the tail rotor control long rocker, and one end of the tail rotor control connecting rod (35) is hinged and limited with the tail rotor control short rocker.
5. The unmanned digital fly-by-wire operating mechanism based on the mosquito manned helicopter according to claim 1, characterized in that the collective pitch operating mechanism (40) further comprises a collective pitch operating square pipe (43), one end of the collective pitch operating square pipe (43) is fixedly provided with a collective pitch operating rod joint (431), an output shaft of the collective pitch linear steering engine (42) is hinged and limited with the collective pitch operating rod joint (431), and the other end of the collective pitch operating square pipe (43) is fixedly arranged on the collective pitch operating rod through a bolt-fit clamping piece.
6. The unmanned digital fly-by-wire operating mechanism based on the mosquito manned helicopter of claim 1, wherein the throttle wire winch (53) is provided with a mounting hole, and the throttle wire clamp (55) is embedded in the mounting hole; the throttle cable (54) penetrates through a pressing hole of the throttle cable chuck (55) and then is wound on the throttle cable winch (53).
7. The unmanned digital telex control mechanism based on the mosquito manned helicopter is characterized in that a sleeve (56) is injected outside the throttle cable (54), one end of the sleeve (56) is clamped and fixed with the side wall of the throttle steering engine fixing seat (51) so as to prevent the sleeve (56) from moving when the throttle cable (54) is pulled; the sleeve (56) is fixed at the bottom of the cabin along the length direction of the sleeve by sleeving a plurality of wire clamps.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911187240.6A CN110723277B (en) | 2019-11-28 | 2019-11-28 | Unmanned digital telex control mechanism based on mosquito manned helicopter |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201911187240.6A CN110723277B (en) | 2019-11-28 | 2019-11-28 | Unmanned digital telex control mechanism based on mosquito manned helicopter |
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| CN110723277A true CN110723277A (en) | 2020-01-24 |
| CN110723277B CN110723277B (en) | 2021-05-07 |
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| CN201911187240.6A Active CN110723277B (en) | 2019-11-28 | 2019-11-28 | Unmanned digital telex control mechanism based on mosquito manned helicopter |
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| CN (1) | CN110723277B (en) |
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| CN116735144A (en) * | 2023-08-16 | 2023-09-12 | 中国空气动力研究与发展中心低速空气动力研究所 | Ground simulation method for helicopter side flight aerodynamic characteristic test |
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| US5209429A (en) * | 1991-05-16 | 1993-05-11 | United Technologies Corporation | Helicopter with retractable rotor for transport |
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| CN116735144A (en) * | 2023-08-16 | 2023-09-12 | 中国空气动力研究与发展中心低速空气动力研究所 | Ground simulation method for helicopter side flight aerodynamic characteristic test |
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| CN110723277B (en) | 2021-05-07 |
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