CN203727646U - Unmanned helicopter - Google Patents
Unmanned helicopter Download PDFInfo
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- CN203727646U CN203727646U CN201420114803.5U CN201420114803U CN203727646U CN 203727646 U CN203727646 U CN 203727646U CN 201420114803 U CN201420114803 U CN 201420114803U CN 203727646 U CN203727646 U CN 203727646U
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- tail boom
- retarder
- output shaft
- bevel gear
- frame
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Abstract
The utility model relates to an unmanned helicopter, in particular to a high-power and high-load unmanned helicopter with two pairs of coaxial main rotors and a water cooling radiator system. The unmanned helicopter comprises an engine, a main bearing frame, an undercarriage, a speed reducer, an empennage mechanism, a control steering gear system, a swashplate mechanism, a main rotor mechanism, a radiator system and a synchronous belt transmission mechanism, wherein the engine and the radiator system are arranged at the front end of the main bearing frame; the radiator system is connected with a cooling system on the engine; cooling fins in the radiator system are arranged obliquely; the rotors on the main rotor mechanism are in the same shape; ridges of the rotors are positioned on the same plane, that is to say, the two pairs of rotors are the main rotors; the swashplate mechanism is mounted on a main rotor output shaft of the speed reducer; and the control steering gear system controls the two pairs of main rotors via the swashplate mechanism.The helicopter is 200kg in weight and 25kg in maximum load weight, and heat can be still effectively dissipated when the power of the engine is increased.
Description
Technical field
The utility model relates to a kind of depopulated helicopter, specifically a kind of high-power, high load carrying ability depopulated helicopter with two pairs of coaxial main rotors and water-filled radiator system.
Background technology
In prior art, civilian depopulated helicopter is owing to being subject to engine power, the restriction of the factors such as airframe structure and engine radiating, often weight is lighter, load carrying ability is less, in addition, civilian depopulated helicopter of the prior art adopts coaxial quadrature antarafacial main wing to add the main rotor pattern of winglet about rotor part conventionally, this has also had influence on weight and the load carrying ability of civilian depopulated helicopter, the weight of common civilian depopulated helicopter is less than 100 kilograms, load carrying ability is less than 10 kilograms, this has greatly limited the range of use of civilian depopulated helicopter, the promotion and application of depopulated helicopter have been affected.
Utility model content
The purpose of this utility model is to provide a kind of depopulated helicopter with two pairs of coaxial main rotors and water-filled radiator system, and its weight reaches 200 kilograms, and load weight can reach 25 kilograms, still can efficiently radiates heat when engine power increases.
The purpose of this utility model is achieved through the following technical solutions:
A kind of depopulated helicopter, comprise driving engine, main bearing frame, alighting gear, retarder, empennage mechanism, control steering gear system, tilting frame mechanism, main rotor body, radiator system and synchronous belt drive mechanism, wherein driving engine and radiator system are all arranged at the front end of main bearing frame, described radiator system is connected with the cooling system on driving engine, and the radiating gill in described radiator system is inclined relative to horizontal setting, driving engine is connected with retarder by synchronous belt drive mechanism, described retarder is arranged on main bearing frame, retarder is provided with main rotor output shaft and empennage output shaft, described main rotor output shaft is connected with the main rotor body of body upper, described empennage output shaft is connected with the empennage mechanism of afterbody, control steering gear system is installed on described retarder, on the main rotor output shaft between main rotor body and retarder, tilting frame mechanism is installed, described tilting frame mechanism comprises dish and lower wall, the upper dish of described tilting frame mechanism is connected with the oar folder on main rotor body by connecting rod, the lower wall of described tilting frame mechanism is connected with the steering wheel in described control steering gear system by connecting rod, rotor shape on described main rotor body all crestal line identical and rotor is in the same plane, alighting gear is arranged on the below of main bearing frame, in described main bearing frame both sides, is provided with for hanging the bearing bar of various load.
Described main bearing frame comprises the bracing frame of both sides, front end at support frame as described above is provided with back-up block, Nut pole and fixed mount are installed on described back-up block, driving engine is arranged at radiator system below, described driving engine is arranged on described Nut pole, and described radiator system is arranged on described fixed mount.
Described main bearing frame is provided with support, tail boom rear support, tail boom bracket and battery carrier in tail boom front support, tail boom, tail boom bracket is arranged at the rear end of support frame as described above, described tail boom bracket is arranged on support frame as described above by pedestal, on described pedestal, be provided with tail boom front support, at tail boom bracket, away from one end of support frame as described above, be provided with tail boom rear support, at the middle part of tail boom bracket, be provided with for placing the battery carrier of circuit power, and supporting in being provided with tail boom on the battery carrier of support frame as described above.
On described main bearing frame, tail boom is installed, described tail boom is arranged on described main bearing frame by support and tail boom rear support in described tail boom front support, tail boom, and the empennage output shaft of described retarder passes and is connected with empennage mechanism in described tail boom.
Described radiator system also comprises water pipe and buffer container except radiating gill, radiating gill is connected with the cooling system water inlet end on driving engine by water pipe, cooling system water side on driving engine is connected with buffer container, cooling system on described radiating gill, driving engine and described buffer container have formed a complete cooling water circulation pipeline together, and the cylinder head freeing pipe of driving engine is connected with described buffer container.
In described retarder, be provided with input finishing bevel gear cuter, drive bevel gear and output bevel gear, described input finishing bevel gear cuter, drive bevel gear and output bevel gear mesh successively, the input shaft of retarder and described input finishing bevel gear cuter are connected, main rotor output shaft and the described drive bevel gear of retarder are connected, and the empennage output shaft of retarder and described output bevel gear are connected.
Described synchronous belt drive mechanism comprises active synchronization belt wheel, driven synchronous pulley and Timing Belt, described active synchronization belt wheel is arranged on the output shaft of driving engine, driven synchronous pulley is arranged on the input shaft of retarder, and described active synchronization belt wheel is connected by described Timing Belt with driven synchronous pulley.
Described main rotor body comprises oar folder pedestal and oar folder, wherein oar folder pedestal is fixedly mounted on the main rotor output shaft of retarder, oar folder is installed in rotation on respectively on described oar folder pedestal, oar folder is provided with oar folder attaching parts, and the oar folder attaching parts on described oar folder is connected with the upper dish of described tilting frame mechanism by connecting rod.
Described empennage mechanism comprises gear case, steering wheel Jia He anti-torque rotor mechanism, the empennage output shaft of retarder is connected with the input shaft of described gear case, the output shaft of described gear case is connected with anti-torque rotor mechanism, steering wheel frame is arranged on described gear case, and the steering wheel of controlling anti-torque rotor mechanism inclination angle is installed on described steering wheel frame.
In described gear case, be provided with intermeshing input finishing bevel gear cuter and output bevel gear, the input shaft of gear case and described input finishing bevel gear cuter are connected, and the output shaft of gear case and described output bevel gear are connected.
Advantage of the present utility model and good effect are:
1, engine power of the present utility model is large, and fuselage weight reaches 200 kilograms, and load weight reaches 25 kilograms, still can efficiently radiates heat when engine power increases.
2, the utility model is two pairs of coaxial main rotor patterns, and two pairs of rotors in main rotor body are all main wings, and this is different from the main rotor pattern that common coaxial quadrature antarafacial main wing adds winglet, has guaranteed the aerial flight of aircraft.
Accompanying drawing explanation
Fig. 1 is structure side view of the present utility model,
Fig. 2 is structural perspective of the present utility model in Fig. 1,
Fig. 3 is the structural representation of the main bearing frame of the utility model and alighting gear in Fig. 1,
Fig. 4 is that in Fig. 1, the utility model removes the structural representation after main rotor body, empennage mechanism and tail boom,
Fig. 5 is driving engine and cooling system connection diagram in Fig. 4,
Fig. 6 is the structural representation of retarder and synchronous belt drive mechanism in Fig. 4,
Fig. 7 is the cutaway view of retarder in Fig. 6,
Fig. 8 is main rotor in Fig. 1, tilting frame and control steering gear system structural representation,
Fig. 9 is the structural representation of main rotor in Fig. 8,
Figure 10 is Fig. 8 medium dip dish and control steering gear system structural perspective,
Figure 11 is tail structure schematic diagram in Fig. 1,
Figure 12 is Figure 11 middle gear case cutaway view.
Wherein, 1 is driving engine, 101 is output shaft, 102 is cooling water inlet port, 103 is cooling water outlet port, 104 is cylinder head freeing pipe, 2 is main bearing frame, 201 is bracing frame, 202 is back-up block, 203 is Nut pole, 204 is pedestal, 205 is tail boom front support, 206 support in tail boom, 207 is tail boom rear support, 208 is tail boom bracket, 209 is battery carrier, 210 is bearing bar, 3 is alighting gear, 301 is connecting panel, 4 is retarder, 401 is output bevel gear, 402 is empennage output shaft, 403 is main rotor output shaft, 404 is input shaft, 405 is input finishing bevel gear cuter, 406 is drive bevel gear, 5 is empennage mechanism, 501 is gear case, 502 is steering wheel frame, 503 is anti-torque rotor, 504 is input shaft, 505 is output shaft, 506 is input finishing bevel gear cuter, 507 is output bevel gear, 6 for controlling steering gear system, 601 is steering wheel, 602 is steering wheel attaching parts, 603 is steering wheel adapter plate, 7 is tilting frame mechanism, 701 is upper dish, 702 is lower wall, 703 is hinged block, 8 is main rotor body, 801 is oar folder pedestal, 802 is oar folder, 803 is oar folder attaching parts, 804 is rotor, 9 is radiator system, 901 is radiating gill, 902 is water pipe, 903 is buffer container, 904 is reflux valve, 905 is overflow pipe, 906 is overflow bottle, 10 is synchronous belt drive mechanism, 11 is driven synchronous pulley, 12 is Timing Belt, 13 is active synchronization belt wheel, 14 is connecting rod, 15 is connecting rod, 16 is fixed mount, 17 is tail boom.
The specific embodiment
Below in conjunction with accompanying drawing, the utility model is described in further detail.
As shown in Fig. 1～2, the utility model comprises driving engine 1, main bearing frame 2, alighting gear 3, retarder 4, empennage mechanism 5, control steering gear system 6, tilting frame mechanism 7, main rotor body 8, radiator system 9 and synchronous belt drive mechanism 10, wherein driving engine 1 and radiator system 9 are all arranged at the front end of depopulated helicopter fuselage, front end at main bearing frame 2 is provided with fixed mount 16, described radiator system 9 is arranged on described fixed mount 16, driving engine 1 is arranged on main bearing frame 2 and is arranged at the below of radiator system 9, described radiator system 9 is connected and takes away the unnecessary heat of driving engine 1 by cooling water circulation with the cooling system on driving engine 1, driving engine 1 is obtained cooling, described driving engine 1 is connected with retarder 4 by synchronous belt drive mechanism 10, described retarder 4 is arranged on main bearing frame 2, described retarder 4 is provided with main rotor output shaft 403 and 402 two output shafts of empennage output shaft, described main rotor output shaft 403 is perpendicular to the length direction setting of depopulated helicopter fuselage and be connected with main rotor body 8, described empennage output shaft 402 is parallel to the length direction setting of depopulated helicopter fuselage and is connected with empennage mechanism 5, on the main rotor output shaft 403 between main rotor body 8 and retarder 4, tilting frame mechanism 7 is installed, described tilting frame mechanism 7 comprises dish 701 and lower wall 702, in the upper end of described retarder 4, be provided with and control steering gear system 6, the upper dish 701 of described tilting frame mechanism 7 is connected with main rotor body 8 by connecting rod, the lower wall 702 of described tilting frame mechanism 7 is connected with described control steering gear system 6 by connecting rod, alighting gear 3 is installed below described main bearing frame 2, in the rear end of described main bearing frame 2, tail boom 17 is installed, the empennage output shaft 402 of retarder 4 passes and is connected with empennage mechanism 5 in described tail boom 17.
As shown in Figure 3, described main bearing frame 2 comprises the bracing frame 201 of both sides, Nut pole 203, tail boom front support 205, in tail boom, support 206, tail boom rear support 207, tail boom bracket 208, battery carrier 209 and bearing bar 210, front end at bracing frame 201 is provided with back-up block 202, Nut pole 203 is arranged on described back-up block 202, driving engine 1 is arranged on described Nut pole 203, in the rear end of bracing frame 201, be provided with tail boom bracket 208, described tail boom bracket 208 is arranged on bracing frame 201 by pedestal 204, the electronic devices and components of various necessity can be installed on described tail boom bracket 208, on described pedestal 204, be provided with tail boom front support 205, at tail boom bracket 208, away from one end of bracing frame 201, tail boom rear support 207 is installed, the battery carrier 209 of supporting whole depopulated helicopter circuit power for placing is installed at the middle part of tail boom bracket 208, in being provided with tail boom on the battery carrier 209 of bracing frame 201, supporting 206, tail boom 17 is by described tail boom front support 205, in tail boom, support 206 and tail boom rear support 207 be arranged on main bearing frame 2, in the both sides of main bearing frame 2, be respectively equipped with for hanging the bearing bar 210 of various load, described alighting gear 3 is arranged on the below of bracing frame 201 by connecting panel 301.
As shown in Figures 4 and 5, fixed mount 16 is arranged on the back-up block 202 of support frame as described above 201 front ends, radiator system 9 is arranged on described fixed mount 16, described radiator system 9 comprises radiating gill 901, water pipe 902, buffer container 903 and overvoltage recycling device, radiating gill 901 is connected with the cooling system water inlet end 102 on driving engine 1 by water pipe 902, cooling system water side 103 on driving engine 1 is connected with buffer container 903, described radiating gill 901, cooling system on driving engine 1 and described buffer container 903 have formed a complete cooling water circulation pipeline together, the cylinder head freeing pipe 104 of driving engine 1 is connected with described buffer container 903, the gas that driving engine 1 is discharged by described cylinder head freeing pipe 104 is the propulsion source that drives cooling water circulation, described overvoltage recycling device is connected with described buffer container 903, described overvoltage recycling device comprises reflux valve 904, overflow pipe 905 and overflow bottle 906, described buffer container 903 is connected with overflow bottle 906 by overflow pipe 905, in described overflow pipe 905 and the junction of buffer container 903, be provided with a reflux valve 904, described overvoltage recycling device is that system is from belting, effect is overvoltage protection.As shown in Figure 4, radiating gill 901 integral body in described radiator system 9 are rectangle structure, and arrange horizontal by certain inclination angle, in the present embodiment, described inclination angle is 16 degree, this makes the front surface of described radiating gill 901 can not only receive the wind being caused by flight, but also can receive the down gust from main rotor body 8, strengthened water in radiating gill 901 cooling performance in the flight course of depopulated helicopter, in addition, on radiating gill 901, carry double fan, when unmanned plane low speed move ahead or floating state under, now radiating gill 901 receives that aircraft flies forward and the wind that brings of rotor is less, rely on the cooling effect of natural wind poor, now on radiating gill 901, double fan is had an effect, guarantee the water effective cooling in radiating gill 901.In this example, the model of described driving engine 1 is 582ul type, and manufacturer is rotax company, and the model of described radiating gill 901 is wing god MN156092 type, and manufacturer is Mitsubishi.
As shown in Figure 4 and Figure 6, driving engine 1 is connected with retarder 4 by synchronous belt drive mechanism 10, described retarder 4 is arranged on the bracing frame 201 of main bearing frame 2, synchronous belt drive mechanism 10 comprises active synchronization belt wheel 13, driven synchronous pulley 11 and Timing Belt 12, described active synchronization belt wheel 13 is arranged on the output shaft 101 of driving engine 1, driven synchronous pulley 11 is arranged on the input shaft 404 of retarder 4, and described active synchronization belt wheel 13 is connected by Timing Belt 12 with driven synchronous pulley 11.As shown in Figure 7, in described retarder 4, be provided with input finishing bevel gear cuter 405, drive bevel gear 406 and output bevel gear 401, described input finishing bevel gear cuter 405, drive bevel gear 406 and output bevel gear 401 mesh successively, input shaft 404 and the described input finishing bevel gear cuter 405 of retarder 4 are connected, main rotor output shaft 403 and the described drive bevel gear 406 of retarder 4 are connected, and empennage output shaft 402 and the described output bevel gear 401 of retarder 4 are connected.
As shown in Fig. 8～10, control steering gear system 6 and be arranged on described retarder 4, on the main rotor output shaft 403 of described retarder 4, tilting frame mechanism 7 is installed.Described control steering gear system 6 comprises that 601, three steering wheels 601 of three steering wheels are arranged on described retarder 4 by steering wheel adapter plate 603, and in this enforcement, the model of described steering wheel is ps105, and manufacturer is NSK precision optical machinery Co., Ltd.Main rotor body 8 is arranged on the end of the main rotor output shaft 403 of retarder 4, described main rotor body 8 comprises oar folder pedestal 801 and four oar folders 802, wherein oar folder pedestal 801 is fixedly mounted on the main rotor output shaft 403 of retarder 4, four oar folders 802 are installed in rotation on respectively on described oar folder pedestal 801, on each oar folder 802, be equipped with an oar folder attaching parts 803, described tilting frame mechanism 7 comprises dish 701 and lower wall 702, coil on described 701 and the outer rim of lower wall 702 on the uniform hinged block 703 that is provided with, oar folder attaching parts 803 on described oar folder 802 is connected by corresponding hinged block 703 on the upper dish 701 of connecting rod 14Yu tilting frame mechanism 7, on each steering wheel 601, be equipped with steering wheel attaching parts 602, described steering wheel attaching parts 602 is connected by corresponding hinged block 703 on the lower wall 702 of connecting rod 15Yu tilting frame mechanism 7, the upper dish 701 of tilting frame mechanism 7 and lower wall 702 synchronously rotate around the main rotor output shaft 403 of retarder 4, the oar that steering wheel 601 controls main rotor body 8 by the transmission of described tilting frame mechanism 7 presss from both sides 802 inclination angles.Rotor 804 on described main rotor body 8 is arranged on described oar folder 802, rotor 804 shapes on described main rotor body 8, material are all identical, and the crestal line of described rotor 804 is in the same plane, be that two pairs of coaxial rotors 804 of the utility model are all main wing, this is different from the main rotor pattern that common main wing adds winglet, and described tilting frame mechanism 7 has guaranteed that steering wheel 601 can effectively control two pairs of main wings.
As shown in Figure 11～12, empennage mechanism 5 comprises gear case 501, steering wheel frame 502 and anti-torque rotor 503, the empennage output shaft 402 of described retarder 4 is connected with the input shaft 504 of described gear case 501, output shaft 505 and the anti-torque rotor 503 of described gear case 501 are connected, as shown in figure 12, in described gear case 501, be provided with intermeshing input finishing bevel gear cuter 506 and output bevel gear 507, input shaft 504 and the described input finishing bevel gear cuter 506 of gear case 501 are connected, output shaft 505 and the described output bevel gear 507 of gear case 501 are connected, described gear case 501 is arranged on tail boom 17, steering wheel frame 502 is arranged on described gear case 501, the steering wheel of controlling anti-torque rotor 503 inclination angles is installed on described steering wheel frame 502, in the present embodiment, the steering wheel model at described control anti-torque rotor 503 inclination angles is BLS157HV, manufacturer is Futaba group.
Principle of work of the present utility model is:
Driving engine 1 power of the present utility model is larger, in this enforcement, the power of driving engine 1 is 48kw, the weight of whole fuselage is 200 kilograms, Maximum Loading Capacity is 25 kilograms, because the power of driving engine 1 is larger, rotating speed is higher, need cooling in time, the utility model is preposition by driving engine 1, and at front fuselage, above described driving engine 1, be provided with radiator system 9, described radiator system 9 is circulated and has been solved the heat dissipation problem of driving engine 1 by water cooling, radiating gill 901 in radiator system 9 arranges horizontal by certain inclination angle, make the front surface of described radiating gill 901 can not only receive the wind being caused by flight, but also can receive the down gust from main rotor body 8, in addition, on radiating gill 901, carry double fan, when unmanned plane low speed move ahead or floating state under still can efficiently radiates heat.Because driving engine 1 power is larger, if main rotor body 8 adopts traditional coaxial quadrature antarafacial main wing to add the main rotor pattern of winglet, effective operation of autogyro will be difficult to guarantee, in main rotor body 8 of the present utility model, rotor 804 shapes, the material that are arranged on oar folder 802 are all identical, two pairs of rotors 804 are all main wing, this is different from the main rotor pattern that common main wing adds winglet, on the main rotor output shaft 403 of retarder 4, be provided with tilting frame mechanism 7, described tilting frame mechanism 7 has guaranteed that steering wheel 601 effectively controls two pairs of main wings.
Claims (10)
1. a depopulated helicopter, it is characterized in that: comprise driving engine (1), main bearing frame (2), alighting gear (3), retarder (4), empennage mechanism (5), control steering gear system (6), tilting frame mechanism (7), main rotor body (8), radiator system (9) and synchronous belt drive mechanism (10), wherein driving engine (1) and radiator system (9) are all arranged at the front end of main bearing frame (2), described radiator system (9) is connected with the cooling system on driving engine (1), and the radiating gill (901) in described radiator system (9) is inclined relative to horizontal setting, driving engine (1) is connected with retarder (4) by synchronous belt drive mechanism (10), described retarder (4) is arranged on main bearing frame (2), retarder (4) is provided with main rotor output shaft (403) and empennage output shaft (402), described main rotor output shaft (403) is connected with the main rotor body (8) of body upper, described empennage output shaft (402) is connected with the empennage mechanism (5) of afterbody, on described retarder (4), be provided with and control steering gear system (6), on the main rotor output shaft (403) between main rotor body (8) and retarder (4), tilting frame mechanism (7) is installed, described tilting frame mechanism (7) comprises dish (701) and lower wall (702), the upper dish (701) of described tilting frame mechanism (7) is connected with the oar folder (802) on main rotor body (8) by connecting rod (14), the lower wall (702) of described tilting frame mechanism (7) is connected with the steering wheel (601) in described control steering gear system (6) by connecting rod (15), rotor (804) shape on described main rotor body (8) all crestal line identical and rotor (804) is in the same plane, alighting gear (3) is arranged on the below of main bearing frame (2), in described main bearing frame (2) both sides, is provided with the bearing bar (210) for hanging various load.
2. depopulated helicopter according to claim 1, it is characterized in that: described main bearing frame (2) comprises the bracing frame (201) of both sides, front end at support frame as described above (201) is provided with back-up block (202), Nut pole (203) and fixed mount (16) are installed on described back-up block (202), driving engine (1) is arranged at radiator system (9) below, it is upper that described driving engine (1) is arranged on described Nut pole (203), and described radiator system (9) is arranged on described fixed mount (16).
3. depopulated helicopter according to claim 2, it is characterized in that: described main bearing frame (2) is provided with tail boom front support (205), in tail boom, support (206), tail boom rear support (207), tail boom bracket (208) and battery carrier (209), tail boom bracket (208) is arranged at the rear end of support frame as described above (201), described tail boom bracket (208) is arranged on support frame as described above (201) by pedestal (204), on described pedestal (204), be provided with tail boom front support (205), at tail boom bracket (208), away from one end of support frame as described above (201), be provided with tail boom rear support (207), battery carrier (209) for placing circuit power is installed at the middle part of tail boom bracket (208), and supporting (206) near in being provided with tail boom on the battery carrier (209) of support frame as described above (201).
4. depopulated helicopter according to claim 3, it is characterized in that: tail boom (17) is installed on described main bearing frame (2), described tail boom (17) is arranged on described main bearing frame (2) above by supporting (206) and tail boom rear support (207) in described tail boom front support (205), tail boom, and the empennage output shaft (402) of described retarder (4) passes and is connected with empennage mechanism (5) in described tail boom (17).
5. depopulated helicopter according to claim 1, it is characterized in that: described radiator system (9) also comprises water pipe (902) and buffer container (903) except radiating gill (901), radiating gill (901) is connected with the cooling system water inlet end (102) on driving engine (1) by water pipe (902), cooling system water side (103) on driving engine (1) is connected with buffer container (903), described radiating gill (901), cooling system on driving engine (1) and described buffer container (903) have formed a complete cooling water circulation pipeline together, the cylinder head freeing pipe (104) of driving engine (1) is connected with described buffer container (903).
6. depopulated helicopter according to claim 1, it is characterized in that: in described retarder (4), be provided with input finishing bevel gear cuter (405), drive bevel gear (406) and output bevel gear (401), described input finishing bevel gear cuter (405), drive bevel gear (406) and output bevel gear (401) mesh successively, the input shaft (404) of retarder (4) is connected with described input finishing bevel gear cuter (405), the main rotor output shaft (403) of retarder (4) is connected with described drive bevel gear (406), the empennage output shaft (402) of retarder (4) is connected with described output bevel gear (401).
7. depopulated helicopter according to claim 1, it is characterized in that: described synchronous belt drive mechanism (10) comprises active synchronization belt wheel (13), driven synchronous pulley (11) and Timing Belt (12), described active synchronization belt wheel (13) is arranged on the output shaft (101) of driving engine (1), driven synchronous pulley (11) is arranged on the input shaft (404) of retarder (4), and described active synchronization belt wheel (13) is connected by described Timing Belt (12) with driven synchronous pulley (11).
8. depopulated helicopter according to claim 1, it is characterized in that: described main rotor body (8) comprises oar folder pedestal (801) and oar folder (802), wherein oar folder pedestal (801) is fixedly mounted on the main rotor output shaft (403) of retarder (4), oar folder (802) is installed in rotation on respectively on described oar folder pedestal (801), oar folder (802) is provided with oar folder attaching parts (803), and the oar folder attaching parts (803) on described oar folder (802) is connected with the upper dish (701) of described tilting frame mechanism (7) by connecting rod (14).
9. depopulated helicopter according to claim 1, it is characterized in that: described empennage mechanism (5) comprises gear case (501), steering wheel frame (502) and anti-torque rotor mechanism (503), the empennage output shaft (402) of retarder (4) is connected with the input shaft (504) of described gear case (501), the output shaft (505) of described gear case (501) is connected with anti-torque rotor mechanism (503), it is upper that steering wheel frame (502) is arranged on described gear case (501), and the steering wheel of controlling anti-torque rotor mechanism (503) inclination angle is installed on described steering wheel frame (502).
10. depopulated helicopter according to claim 9, it is characterized in that: in described gear case (501), be provided with intermeshing input finishing bevel gear cuter (506) and output bevel gear (507), the input shaft (504) of gear case (501) is connected with described input finishing bevel gear cuter (506), and the output shaft (505) of gear case (501) is connected with described output bevel gear (507).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420114803.5U CN203727646U (en) | 2014-03-13 | 2014-03-13 | Unmanned helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420114803.5U CN203727646U (en) | 2014-03-13 | 2014-03-13 | Unmanned helicopter |
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| CN203727646U true CN203727646U (en) | 2014-07-23 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201420114803.5U Withdrawn - After Issue CN203727646U (en) | 2014-03-13 | 2014-03-13 | Unmanned helicopter |
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| CN105752349A (en) * | 2016-04-07 | 2016-07-13 | 湖北易瓦特科技股份有限公司 | Unmanned helicopter |
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