CN110510148B - Rotor wing test bed of large-load unmanned helicopter - Google Patents
Rotor wing test bed of large-load unmanned helicopter Download PDFInfo
- Publication number
- CN110510148B CN110510148B CN201910805221.9A CN201910805221A CN110510148B CN 110510148 B CN110510148 B CN 110510148B CN 201910805221 A CN201910805221 A CN 201910805221A CN 110510148 B CN110510148 B CN 110510148B
- Authority
- CN
- China
- Prior art keywords
- rotor
- shaft
- bearing
- supporting plate
- deep groove
- 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
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention relates to a large-load unmanned helicopter rotor wing test bed, and belongs to the technical field of unmanned helicopter rotor wing measurement and control. The invention comprises a bench, a mechanical transmission system support frame, a rotor system support and a rotor measurement and control system; the mechanical transmission system is used for realizing power transmission from the engine to the rotor to be tested, the rotor system is used for installing the rotor to be tested, adjusting the pitch angle and the pitch angle, and the rotor measurement and control system is used for detecting and controlling parameters such as engine accelerator, rotating speed of the propeller, lifting force, torque and the like. Aiming at the problem of complex operation of the existing test bed, the invention can measure and control a rotor system with large load, high rotating speed, high sampling rate and multiple parameters, and has the advantages of high structural strength, good portability, safety and reliability.
Description
Technical Field
The invention relates to a large-load unmanned helicopter rotor wing test bed, and belongs to the technical field of unmanned helicopter rotor wing measurement and control.
Background
Both helicopters and airplanes belong to aviation aircrafts, and the airfoils and the air are required to generate relative motion so as to generate upward lift force to fly in the air. Rotor systems are the most distinctive systems of helicopters, and rotor testing involves the development of helicopters in its entire process of development becoming increasingly important for rotor pre-research and verification of rotor design. The rotor wing test bed is a helicopter rotor wing measurement and control device widely used at home and abroad at present. The method is mainly used for experimental study on aerodynamic performance, dynamics problems, flight mechanics and the like of the rotor wing.
The main dynamics and kinematics of the unmanned helicopter are derived from a test bed, the unmanned helicopter cannot fly without the test bed, and a later-stage flight control system and a control system are based on the platform. The unmanned helicopter needs to master the power performance of the engine and the propeller, lays a foundation for later development around a series of basic tests, and can be used for basic research of the unmanned helicopter in later flight.
Therefore, how to provide a test bed for a rotor system of a high-load unmanned aerial vehicle helicopter, and develop the rotor system are problems to be solved by researchers in the field.
Disclosure of Invention
The invention aims to solve the technical problems that: the invention provides a rotor wing test bed of a large-load unmanned helicopter, which is used for various tests of a power system and a rotor wing system of an oil-driven large-load unmanned helicopter, and can conveniently measure parameters such as rotating speed, lifting force, torque and the like.
The technical scheme of the invention is as follows: a rotor wing test bed of a large-load unmanned helicopter comprises a platform body frame 1, a mechanical transmission system 2, a mechanical transmission system support frame 3, a rotor wing system 4, a rotor wing system support 5 and a rotor wing measurement and control system 6;
the platform body frame comprises a foundation 11, foundation bolts 12, travelling wheels 13, a supporting frame 14 and a supporting plate 15; the foundation 11 is arranged at the bottom of the supporting frame 14 through the foundation bolts 12, the travelling wheels 13 are also arranged at the bottom of the supporting frame 14, and the supporting plate 15 is arranged at the top of the supporting frame 14;
the mechanical transmission system 2 is mounted on the bench 1 and comprises an engine bracket 201, a fixing bolt 202, an engine 203, a clutch 204, an output shaft 205, a first deep groove ball bearing 206, a first bearing seat 207, a first transmission shaft 208, a first coupling 209, a second transmission shaft 210, a second coupling 211, an input pulley shaft 212, a second deep groove ball bearing 213, a second bearing seat 214, an input pulley 215, a belt 216, an output pulley 217, an output pulley shaft 218, a third deep groove ball bearing 219, a third bearing seat 220, a fourth deep groove ball bearing 221, a fourth bearing seat 222, a third coupling 223, a first tapered roller bearing 224 and a bevel gear shaft 225;
the engine support 201 is provided with a bolt hole, the engine support is fixed on the supporting plate 15 of the bench 1 through a fixing bolt 202, meanwhile, the engine 203 is provided with a lifting lug, the engine 203 is connected with a support on the engine support 201 through the fixing bolt 202, the engine 203 is connected with a clutch 204, the clutch 204 is connected with an output shaft 205, one end of the output shaft 205 is provided with a first deep groove ball bearing 206 and is fixed on a first bearing seat 207, the other end of the output shaft 205 is connected with a first transmission shaft 208 through a first coupling 209, a second coupling 211 is connected with a second transmission shaft 210 and the first transmission shaft 208, power is transmitted to the second transmission shaft 210 through the first transmission shaft 208, the second coupling 211 is connected with the second transmission shaft 210 and one end of an input pulley shaft 212, the other end of the input pulley shaft 212 is provided with a second deep groove ball bearing 213 and is fixed on a second bearing seat 214, and the input pulley shaft 212 and the input pulley 215 are fixedly connected through a key connection or other modes; the input pulley 215 is connected with the output pulley 217 through the belt 216, torque is transmitted to the output pulley 217, the output pulley 217 is arranged on the output pulley shaft 218, and the output pulley 217 and the output pulley shaft 218 can be fixedly connected through key connection or other modes; one end of the output pulley shaft 218 is provided with a third deep groove ball bearing 219, the third deep groove ball bearing 219 is fixed in a third bearing seat 220, the other part of the output pulley shaft 218 is provided with a fourth deep groove ball bearing 221, the fourth deep groove ball bearing 221 is fixed in a fourth bearing seat 222, the other end of the output pulley shaft 218 is connected with a bevel gear shaft 225 through a third coupler 223, the bevel gear shaft 225 is provided with a first tapered roller bearing 224, the first tapered roller bearing 224 is fixed on a first supporting plate 408 and is used for supporting and transmitting torque, the bevel gear shaft 225 is meshed with a gear on a rotor main shaft 405, and motion and power between two intersecting shafts are transmitted;
the rotor system comprises a rotor blade 401, a rotor hub 402, a rotor main shaft bearing 403, a variable pitch mechanism 404, a rotor main shaft 405, a second tapered roller bearing 406, a third tapered roller bearing 407, a first support plate 408, a second support plate 409, a third support plate 410 and a fourth support plate 411; the rotor wing plate 401 is connected with a rotor wing hub 402, the rotor wing hub 402 is connected with a pitch-variable mechanism 404, the pitch-variable mechanism 404 is used for adjusting the pitch, a rotor wing main shaft bearing 403 is fixed in the pitch-variable mechanism 404 and is connected with one end of a rotor wing main shaft 405, the other end of the rotor wing main shaft 405 is meshed with a bevel gear shaft 225, and the rotating direction is vertical to the rotor wing main shaft 405;
the rotor head 405 is mounted on a second support plate 409 through a second tapered roller bearing 406, the rotor head 405 is mounted on a fourth support plate 411 through a third tapered roller bearing 407, and a third support plate 410 and a first support plate 408 are arranged between the second support plate 409 and the fourth support plate 411;
the rotor measurement and control system is arranged on a rotor main shaft 405 and comprises a rotor telemetering rotating component, a bit synchronizer 62, an induction power supply 65, a controller and a data receiving computer 61; the data receiving computer 61 includes data acquisition/conversion software and the rotor telemetry rotating assembly includes a rotor 63, a stator 64.
Specifically, the rotor 63 has a 2-ring structure, and is fixed to the rotor shaft by bolts after being positioned by pins. The stator 64 is also of a 2-ring type structure and is locked on the extending sleeve of the speed reducer through a bolt set. The rotor 63 is not in contact with the stator 64. The rotor 63 is provided with a data acquisition module, the acquired signals are modulated after being encoded, a receiving unit on the stator 64 receives the modulated optical signals, the receiving unit transmits data to the bit synchronizer 62, and the bit synchronizer 62 transmits the received data to the data receiving computer 61 or to the main body collector.
Further, rotor blades 401 in rotor system 4 can be adjusted to a diameter in the range of 1-3 meters, with adjustable pitch angles, and are equipped with a power control unit.
Further, the engine power in the mechanical transmission system 2 is greater than 30 horsepower, so as to meet the horsepower requirement of the high-load unmanned helicopter rotor test.
Further, the mechanical transmission system support frame 3 and the rotor system support frame 5 are composed of square tubes and are connected with the support plate 15, so that the mechanical transmission system support frame is good in structural strength and high in stability. The comprehensive mechanical property is good, and the cold and hot processing property and the corrosion resistance are good.
The mechanical transmission system is used for realizing power transmission from the engine to the rotor to be tested, the rotor system is used for installing the rotor to be tested, adjusting the pitch angle and the pitch angle, and the rotor measurement and control system is used for detecting and controlling parameters such as an engine accelerator, a rotating speed of a propeller, a lifting force, a torque and the like;
the beneficial effects of the invention are as follows:
1. the test bed meets the measurement and control requirements of a test measurement and control machine on a rotor system.
2. Aiming at the problem of complex operation of the existing test bed, the test bed has a compact structure, and can measure and control a rotor system with large load, high rotating speed, high sampling rate and multiple parameters.
3. The rotor measurement and control system meets the requirements of small volume, light weight, good dynamic balance, safety, reliability and the like,
4. the rotor measurement and control system has the measurement and control capability of signals such as multipath load, strain and the like.
5. The optical signal transmission is carried out between the sender and the receiver in the form of optical signals, and the transmission signals have the advantages of strong anti-interference capability, no electromagnetic radiation, high confidentiality and the like.
6. The arrangement of the engine and the mechanical transmission system takes into account the inertia between the large and small pulleys, the power loss caused by the rigidity of the shaft, the friction between the pulleys and the shaft and the bearings, and can more reasonably meet the power requirements of the rotor and the accessory devices.
Drawings
FIG. 1 is an overall schematic of the present invention;
FIG. 2 is a side view of the present invention;
FIG. 3 is a schematic illustration of a mechanical drive train of the present invention;
FIG. 4 is a schematic view of the rotor system of the present invention;
FIG. 5 is a schematic view of the rotor system of the present invention;
fig. 6 is a schematic diagram of a rotor measurement and control system according to the present invention.
The reference numerals in fig. 1-6: the system comprises a 1-bench, a 2-mechanical transmission system, a 3-mechanical transmission system support frame, a 4-rotor system, a 5-rotor system support frame and a 6-rotor measurement and control system; the device comprises the following components of an 11-foundation, a 12-foundation bolt, a 13-travelling wheel, a 14-supporting frame and a 15-supporting plate; 201-engine mount, 202-fixing bolt, 203-engine, 204-clutch, 205-output shaft, 206-first deep groove ball bearing, 207-first bearing block, 208-first drive shaft, 209-first coupling, 210-second drive shaft, 211-second coupling, 212-input pulley shaft, 213-second deep groove ball bearing, 214-second bearing block, 215-input pulley, 216-belt, 217-output pulley, 218-output pulley shaft, 219-third deep groove ball bearing, 220-third bearing block, 221-fourth deep groove ball bearing, 222-fourth bearing block, 223-third coupling, 224-first tapered roller bearing, 225-tapered gear shaft; 401-rotor blade, 402-rotor hub, 403-rotor shaft bearing, 404-pitch mechanism, 405-rotor shaft, 406-second tapered roller bearing, 407-third tapered roller bearing, 408-first support plate, 409-second support plate, 410-third support plate, 411-fourth support plate; 61-data receiving computer, 62-bit synchronizer, 63-rotor, 64-stator, 65-induction power source.
Detailed Description
The invention will be further described with reference to the drawings and the specific examples.
Example 1: as shown in fig. 1-6, a rotor test stand of a high-load unmanned helicopter comprises a stand body frame 1, a mechanical transmission system 2, a mechanical transmission system support frame 3, a rotor system 4, a rotor system support 5 and a rotor measurement and control system 6;
the platform body frame comprises a foundation 11, foundation bolts 12, travelling wheels 13, a supporting frame 14 and a supporting plate 15; the foundation 11 is arranged at the bottom of the supporting frame 14 through the foundation bolts 12, the travelling wheels 13 are also arranged at the bottom of the supporting frame 14, and the supporting plate 15 is arranged at the top of the supporting frame 14; in the working state, the platform frame 1 is fixed on the ground through the foundation bolts 12. When the test bed is in an unoperated state, the movable traveling wheels 13 can move and turn to, and the device is simple in structure and convenient to assemble and disassemble, so that the portability of the whole test bed is improved.
The mechanical transmission system 2 is mounted on the bench 1 and comprises an engine bracket 201, a fixing bolt 202, an engine 203, a clutch 204, an output shaft 205, a first deep groove ball bearing 206, a first bearing seat 207, a first transmission shaft 208, a first coupling 209, a second transmission shaft 210, a second coupling 211, an input pulley shaft 212, a second deep groove ball bearing 213, a second bearing seat 214, an input pulley 215, a belt 216, an output pulley 217, an output pulley shaft 218, a third deep groove ball bearing 219, a third bearing seat 220, a fourth deep groove ball bearing 221, a fourth bearing seat 222, a third coupling 223, a first tapered roller bearing 224 and a bevel gear shaft 225;
the engine support 201 is provided with a bolt hole, the engine support is fixed on the supporting plate 15 of the bench 1 through a fixing bolt 202, meanwhile, the engine 203 is provided with a lifting lug, the engine 203 is connected with a support on the engine support 201 through the fixing bolt 202, the engine 203 is connected with a clutch 204, the clutch 204 is connected with an output shaft 205, one end of the output shaft 205 is provided with a first deep groove ball bearing 206 and is fixed on a first bearing seat 207, the other end of the output shaft 205 is connected with a first transmission shaft 208 through a first coupling 209, a second coupling 211 is connected with a second transmission shaft 210 and the first transmission shaft 208, power is transmitted to the second transmission shaft 210 through the first transmission shaft 208, the second coupling 211 is connected with the second transmission shaft 210 and one end of an input pulley shaft 212, the other end of the input pulley shaft 212 is provided with a second deep groove ball bearing 213 and is fixed on a second bearing seat 214, and the input pulley shaft 212 and the input pulley 215 are fixedly connected through a key connection or other modes; the input pulley 215 is connected with the output pulley 217 through the belt 216, torque is transmitted to the output pulley 217, the output pulley 217 is arranged on the output pulley shaft 218, and the output pulley 217 and the output pulley shaft 218 can be fixedly connected through key connection or other modes; one end of the output pulley shaft 218 is provided with a third deep groove ball bearing 219, the third deep groove ball bearing 219 is fixed in a third bearing seat 220, the other part of the output pulley shaft 218 is provided with a fourth deep groove ball bearing 221, the fourth deep groove ball bearing 221 is fixed in a fourth bearing seat 222, the other end of the output pulley shaft 218 is connected with a bevel gear shaft 225 through a third coupler 223, the bevel gear shaft 225 is provided with a first tapered roller bearing 224, the first tapered roller bearing 224 is fixed on a first supporting plate 408 and is used for supporting and transmitting torque, the bevel gear shaft 225 is meshed with a gear on a rotor main shaft 405, and motion and power between two intersecting shafts are transmitted;
the rotor system comprises a rotor blade 401, a rotor hub 402, a rotor main shaft bearing 403, a variable pitch mechanism 404, a rotor main shaft 405, a second tapered roller bearing 406, a third tapered roller bearing 407, a first support plate 408, a second support plate 409, a third support plate 410 and a fourth support plate 411; the rotor wing plate 401 is connected with a rotor wing hub 402, the rotor wing hub 402 is connected with a pitch-variable mechanism 404, the pitch-variable mechanism 404 is used for adjusting the pitch, a rotor wing main shaft bearing 403 is fixed in the pitch-variable mechanism 404 and is connected with one end of a rotor wing main shaft 405, the other end of the rotor wing main shaft 405 is meshed with a bevel gear shaft 225, and the rotating direction is vertical to the rotor wing main shaft 405;
the rotor head 405 is mounted on a second support plate 409 through a second tapered roller bearing 406, the rotor head 405 is mounted on a fourth support plate 411 through a third tapered roller bearing 407, and a third support plate 410 and a first support plate 408 are arranged between the second support plate 409 and the fourth support plate 411;
the rotor measurement and control system is arranged on a rotor main shaft 405 and comprises a rotor telemetering rotating component, a bit synchronizer 62, an induction power supply 65, a controller and a data receiving computer 61; the data receiving computer 61 includes data acquisition/conversion software and the rotor telemetry rotating assembly includes a rotor 63, a stator 64.
Specifically, the rotor 63 has a 2-ring structure, and is fixed to the rotor shaft by bolts after being positioned by pins. The stator 64 is also of a 2-ring type structure and is locked on the extending sleeve of the speed reducer through a bolt set. The rotor 63 is not in contact with the stator 64. The rotor 63 is provided with a data acquisition module, the acquired signals are modulated after being encoded, a receiving unit on the stator 64 receives the modulated optical signals, the receiving unit transmits data to the bit synchronizer 62, and the bit synchronizer 62 transmits the received data to the data receiving computer 61 or to the main body collector. The acquired data is processed and analyzed through data acquisition/conversion software, parameters such as engine throttle, rotating speed, rotor wing rotating speed, lifting force, torque and the like can be monitored, so that regular flight data can be obtained, verification and optimization of a support design scheme can be realized, and support can be provided for later-stage tests.
Further, rotor blades 401 in rotor system 4 can be adjusted to a diameter in the range of 1-3 meters, with adjustable pitch angles, and are equipped with a power control unit.
Further, the engine power in the mechanical transmission system 2 is greater than 30 horsepower, so as to meet the horsepower requirement of the high-load unmanned helicopter rotor test.
Further, the mechanical transmission system support frame 3 and the rotor system support frame 5 are composed of square tubes and are connected with the support plate 15, so that the mechanical transmission system support frame is good in structural strength and high in stability. The comprehensive mechanical property is good, and the cold and hot processing property and the corrosion resistance are good.
The rotor measurement and control system 6 can monitor parameters such as engine throttle, rotating speed, rotor rotating speed, lifting force, torque and the like.
The working principle of the invention is as follows: starting a power supply, running an engine 203, transmitting motion and power to an output shaft 205 through a clutch 204, and mounting a first deep groove ball bearing 206 at one end of the output shaft 205 and fixing the first deep groove ball bearing on a first bearing seat 207 to play a supporting role; the other end of the output shaft 205 is connected with a first transmission shaft 208 through a first coupling 209, the output shaft 205 outputs power from the engine 203, and the power is transmitted to the first transmission shaft 208 after friction loss through a first deep groove ball bearing 206 and a first bearing seat 207; the second coupling 211 connects the second transmission shaft 210 and the first transmission shaft 208, transmits power from the first transmission shaft 208 to the second transmission shaft 210, and the second transmission shaft 210 is connected through the second coupling 211 and transmits power to the input pulley shaft 212; the input pulley shaft 212 rotates to drive the input pulley 215 to synchronously rotate, the input pulley 215 is connected with the output pulley 217 through a belt 216, torque is transmitted to the output pulley 217, the output pulley 217 is arranged on the output pulley shaft 218 to drive the output pulley shaft 218 to move, the types of the input pulley 215 and the output pulley 217 can be different, and the specific type can be selected according to test requirements; one end of the output pulley shaft 218 is provided with a third deep groove ball bearing 219, the third deep groove ball bearing 219 is fixed in a third bearing seat 220, the other part of the output pulley shaft 218 is provided with a fourth deep groove ball bearing 221, the fourth deep groove ball bearing 221 is fixed in a fourth bearing seat 222, the output pulley 217 drives the output pulley shaft 218 to operate, the other end of the output pulley shaft 218 is connected with a bevel gear shaft 225 through a third coupling 223 and transmits power to the bevel gear shaft 225, a first tapered roller bearing 224 is arranged on the bevel gear shaft 225, and the first tapered roller bearing 224 is fixed on a first supporting plate 408 and plays a role in supporting and transmitting torque. The bevel gear shaft 225 is meshed with gears on the rotor shaft 405, and the rotation of the bevel gear shaft 225 drives the rotor shaft 405 to rotate, so that the motion and power between two intersecting shafts are transmitted, namely, the rotor to be tested is driven to rotate. Meanwhile, a data acquisition module on a rotor 63 of the rotor measurement and control system 6 mounted on the rotor main shaft 405 modulates the acquired signals after encoding, a receiving unit on a stator 64 receives the modulated optical signals, the receiving unit transmits data to a bit synchronizer 62, and the bit synchronizer 62 transmits the received data to a data receiving computer 61 or to a main body collector. The engine accelerator, the rotating speed of the rotor wing, the lifting force, the torque and other parameters can be monitored to obtain regular flight data, so that basic research is carried out for the later-stage unmanned helicopter flight.
The specific embodiments of the present invention have been described in detail with reference to the accompanying drawings, but the present invention is not limited to the above embodiments, and various changes can be made within the knowledge of those skilled in the art without departing from the spirit of the present invention.
Claims (4)
1. The utility model provides a big unmanned helicopter rotor test stand of load which characterized in that: the device comprises a bench (1), a mechanical transmission system (2), a mechanical transmission system support frame (3), a rotor system (4), a rotor system support frame (5) and a rotor measurement and control system (6);
the platform body frame comprises a foundation (11), foundation bolts (12), travelling wheels (13), a supporting frame (14) and a supporting plate (15); the ground feet (11) are arranged at the bottom of the supporting frame (14) through the ground bolts (12), the travelling wheels (13) are also arranged at the bottom of the supporting frame (14), and the supporting plate (15) is arranged at the top of the supporting frame (14);
the mechanical transmission system (2) is arranged on the platform frame (1) and comprises an engine bracket (201), a fixing bolt (202), an engine (203), a clutch (204), an output shaft (205), a first deep groove ball bearing (206), a first bearing seat (207), a first transmission shaft (208), a first coupling (209), a second transmission shaft (210), a second coupling (211), an input pulley shaft (212), a second deep groove ball bearing (213), a second bearing seat (214), an input pulley (215), a belt (216), an output pulley (217), an output pulley shaft (218), a third deep groove ball bearing (219), a third bearing seat (220), a fourth deep groove ball bearing (221), a fourth bearing seat (222), a third coupling (223), a first conical roller bearing (224) and a bevel gear shaft (225);
the engine support (201) is provided with a bolt hole, the engine support is fixed on a supporting plate (15) of the platform body frame (1) through a fixing bolt (202), meanwhile, the engine (203) is provided with a lifting lug, the engine (203) is connected with a support on the engine support (201) through the fixing bolt (202), the engine (203) is connected with a clutch (204), the clutch (204) is connected with an output shaft (205), one end of the output shaft (205) is provided with a first deep groove ball bearing (206) and is fixed on a first bearing seat (207), the other end of the output shaft (205) is connected with a first transmission shaft (208) through a first coupling (209), a second coupling (211) is connected with a second transmission shaft (210) and the first transmission shaft (208), power is transmitted to the second transmission shaft (210) through the first transmission shaft (208), the second coupling (211) is connected with one end of a second transmission shaft (210) and one end of an input belt wheel shaft (212), the other end of the input belt wheel shaft (212) is provided with a second deep groove ball bearing (213) and is fixed on a second bearing seat (214), and the other end of the input belt wheel (212) is connected with the input belt wheel (215) through a key or other fixed connection modes; the input belt pulley (215) is connected with the output belt pulley (217) through a belt (216), torque is transmitted to the output belt pulley (217), the output belt pulley (217) is arranged on an output belt pulley shaft (218), and the output belt pulley (217) and the output belt pulley shaft (218) can be fixedly connected through key connection or other modes; one end of an output belt wheel shaft (218) is provided with a third deep groove ball bearing (219), the third deep groove ball bearing (219) is fixed in a third bearing seat (220), the other part of the output belt wheel shaft (218) is provided with a fourth deep groove ball bearing (221), the fourth deep groove ball bearing (221) is fixed in a fourth bearing seat (222), the other end of the output belt wheel shaft (218) is connected with a bevel gear shaft (225) through a third coupler (223), a first tapered roller bearing (224) is arranged on the bevel gear shaft (225), the first tapered roller bearing (224) is fixed on a first supporting plate (408) and is used for supporting and transmitting torque, the bevel gear shaft (225) is meshed with a gear on a rotor main shaft (405), and motion and power between two intersecting shafts are transmitted;
the rotor system comprises a rotor wing (401), a rotor hub (402), a rotor main shaft bearing (403), a pitch mechanism (404), a rotor main shaft (405), a second tapered roller bearing (406), a third tapered roller bearing (407), a first supporting plate (408), a second supporting plate (409), a third supporting plate (410) and a fourth supporting plate (411); the rotor wing (401) is connected with a rotor hub (402), the rotor hub (402) is connected with a pitch-variable mechanism (404), the pitch-variable mechanism (404) is used for adjusting the pitch, a rotor shaft bearing (403) is fixed in the pitch-variable mechanism (404) and is connected with one end of a rotor shaft (405), the other end of the rotor shaft (405) is meshed with a bevel gear shaft (225), and the rotating direction is perpendicular to the rotor shaft (405);
the rotor head (405) is arranged on a second supporting plate (409) through a second tapered roller bearing (406), the rotor head (405) is arranged on a fourth supporting plate (411) through a third tapered roller bearing (407), and a third supporting plate (410) and a first supporting plate (408) are arranged between the second supporting plate (409) and the fourth supporting plate (411);
the rotor measurement and control system is arranged on a rotor main shaft (405) and comprises a rotor telemetering rotating assembly, a bit synchronizer (62), an induction power supply (65), a controller and a data receiving computer (61); the data receiving computer (61) comprises data acquisition/conversion software, and the rotor telemetry rotating assembly comprises a rotor (63) and a stator (64).
2. The high load unmanned helicopter rotor stand according to claim 1, wherein: the rotor blade (401) in the rotor system (4) can be adjusted, the diameter range is 1-3 meters, the pitch angle is adjustable, and the rotor system is provided with a power control unit.
3. The high load unmanned helicopter rotor stand according to claim 1, wherein: the engine power in the mechanical transmission system (2) is larger than 30 horsepower and is used for meeting the horsepower requirement of a large-load unmanned helicopter rotor wing test.
4. The high load unmanned helicopter rotor stand according to claim 1, wherein: the mechanical transmission system support frame (3) and the rotor system support frame (5) are formed by square tubes and are connected with the support plate (15).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910805221.9A CN110510148B (en) | 2019-08-29 | 2019-08-29 | Rotor wing test bed of large-load unmanned helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910805221.9A CN110510148B (en) | 2019-08-29 | 2019-08-29 | Rotor wing test bed of large-load unmanned helicopter |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110510148A CN110510148A (en) | 2019-11-29 |
| CN110510148B true CN110510148B (en) | 2023-06-16 |
Family
ID=68627845
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910805221.9A Active CN110510148B (en) | 2019-08-29 | 2019-08-29 | Rotor wing test bed of large-load unmanned helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110510148B (en) |
Families Citing this family (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111207923B (en) * | 2020-04-22 | 2020-08-21 | 北京清航紫荆装备科技有限公司 | Test bed for transmission device of cross dual-rotor unmanned helicopter |
| CN111516900B (en) * | 2020-04-30 | 2023-03-14 | 庆安集团有限公司 | Helicopter course tail locking test device and method thereof |
| CN111855201B (en) * | 2020-09-01 | 2022-03-22 | 常州华创航空科技有限公司 | Helicopter main reducer test bench |
| CN112278319A (en) * | 2020-10-21 | 2021-01-29 | 中国航空工业集团公司上海航空测控技术研究所 | Multi-model helicopter rotor dynamic balance simulation platform mechanism |
| CN112478193B (en) * | 2020-10-30 | 2022-09-16 | 中国直升机设计研究所 | Real-time online measuring device and method for helicopter rotor cone |
| CN112407321B (en) * | 2020-10-30 | 2022-05-31 | 中国直升机设计研究所 | Method for generating azimuth angle signal based on helicopter rotor rotation speed |
| CN112498738B (en) * | 2020-12-11 | 2022-10-18 | 中国直升机设计研究所 | Helicopter flight control system transfer characteristic test method |
| CN112945548A (en) * | 2021-02-01 | 2021-06-11 | 中国兵器工业计算机应用技术研究所 | Running-in test and torque test device and method for coaxial double-propeller unmanned helicopter |
| CN113532859B (en) * | 2021-08-27 | 2024-06-07 | 中浙高铁轴承有限公司 | Engine input end shafting bearing testing machine and testing method |
| CN114715427A (en) * | 2022-06-09 | 2022-07-08 | 北京航景创新科技有限公司 | Main rotor lift force test bench of unmanned helicopter |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2034257C1 (en) * | 1991-06-24 | 1995-04-30 | Вертолетный научно-технический комплекс им.Н.И.Камова | Method of testing the helicopter rotor members and test stand for its realization |
| US6467726B1 (en) * | 1999-06-29 | 2002-10-22 | Rokuro Hosoda | Aircraft and torque transmission |
| RU59251U1 (en) * | 2006-08-01 | 2006-12-10 | Открытое акционерное общество "Камов" | STAND FOR TESTING THE SYSTEM OF THE DRIVE SYSTEM OF THE COXIAL CARRYING SCREWS OF THE HELICOPTER |
| KR20120068187A (en) * | 2010-12-17 | 2012-06-27 | 한국항공우주연구원 | Apparatus and method for testng rotation of helicopter rotor system |
| CN104743103A (en) * | 2015-03-31 | 2015-07-01 | 东莞市汇天玩具模型有限公司 | Super-miniature fuel oil unmanned helicopter |
| CN104908976A (en) * | 2015-05-19 | 2015-09-16 | 北京航空航天大学 | Simple rotor mechanism of coaxial dual-rotor helicopter test stand |
| CN206787744U (en) * | 2017-04-14 | 2017-12-22 | 西安天问智能科技有限公司 | A kind of multi-rotor unmanned aerial vehicle rotor test system |
| CN208802158U (en) * | 2018-09-17 | 2019-04-30 | 北京清航紫荆装备科技有限公司 | Rotor model.test system |
-
2019
- 2019-08-29 CN CN201910805221.9A patent/CN110510148B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2034257C1 (en) * | 1991-06-24 | 1995-04-30 | Вертолетный научно-технический комплекс им.Н.И.Камова | Method of testing the helicopter rotor members and test stand for its realization |
| US6467726B1 (en) * | 1999-06-29 | 2002-10-22 | Rokuro Hosoda | Aircraft and torque transmission |
| RU59251U1 (en) * | 2006-08-01 | 2006-12-10 | Открытое акционерное общество "Камов" | STAND FOR TESTING THE SYSTEM OF THE DRIVE SYSTEM OF THE COXIAL CARRYING SCREWS OF THE HELICOPTER |
| KR20120068187A (en) * | 2010-12-17 | 2012-06-27 | 한국항공우주연구원 | Apparatus and method for testng rotation of helicopter rotor system |
| CN104743103A (en) * | 2015-03-31 | 2015-07-01 | 东莞市汇天玩具模型有限公司 | Super-miniature fuel oil unmanned helicopter |
| CN104908976A (en) * | 2015-05-19 | 2015-09-16 | 北京航空航天大学 | Simple rotor mechanism of coaxial dual-rotor helicopter test stand |
| CN206787744U (en) * | 2017-04-14 | 2017-12-22 | 西安天问智能科技有限公司 | A kind of multi-rotor unmanned aerial vehicle rotor test system |
| CN208802158U (en) * | 2018-09-17 | 2019-04-30 | 北京清航紫荆装备科技有限公司 | Rotor model.test system |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110510148A (en) | 2019-11-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110510148B (en) | Rotor wing test bed of large-load unmanned helicopter | |
| CN109018430B (en) | Rotorcraft blade performance test bench | |
| CN112161795A (en) | Double-shaft cooperative loading measuring device for fatigue test of wind driven generator blade | |
| CN109632249B (en) | Wing type high-speed wind tunnel dynamic test device | |
| CN107117332A (en) | A kind of test platform of small-sized multi-rotor unmanned aerial vehicle rotor power system | |
| CN112478193B (en) | Real-time online measuring device and method for helicopter rotor cone | |
| CN108593319B (en) | A kind of disk-type friction loading system and method | |
| CN110562485B (en) | Coaxial rotor hovering characteristic measuring device of mars aircraft with adjustable propeller pitch | |
| CN111994301B (en) | Helicopter transmission system test device and system | |
| CN209214916U (en) | A kind of electric propeller system aeroperformance and efficiency synchronous measuring apparatus | |
| CN110779678A (en) | Test bed capable of synchronously measuring aerodynamic characteristics and acoustic characteristics of large-size propeller | |
| CN109708883A (en) | A kind of electrically driven (operated) duty testing device of empennage of helicopter and control method | |
| CN201327429Y (en) | Impulsive torque test device | |
| CN109556878B (en) | Synchronous measurement device and method for pneumatic performance and efficiency of electric propeller system | |
| CN105021337A (en) | Propeller driving rotation force measuring apparatus and force measuring method | |
| CN109774971B (en) | Unmanned aerial vehicle screw aerodynamic performance test platform | |
| CN113942655A (en) | Light-duty helicopter piston sender transmission system | |
| CN115144185A (en) | Simulation test bed for analyzing vibration characteristics of coaxial contra-rotating structure of paddle fan | |
| CN114426102A (en) | Transmission system of tilt rotorcraft | |
| CN212172579U (en) | Comprehensive test bed for oil-electricity hybrid power transmission system of rotary wing aircraft | |
| CN107121288B (en) | Complete machine test run method of turboprop engine and engine test run device | |
| CN110606222A (en) | Pneumatic characteristic testing device for single rotor system of suspended Mars aircraft | |
| CN203965148U (en) | A kind of panzer Fault Diagnosis of Gearbox system | |
| CN113357100B (en) | Offshore wind power cluster gear box accelerated life and environmental corrosion simulation test bed and working method thereof | |
| CN109941457A (en) | A kind of electrically driven (operated) duty testing device of empennage of helicopter and control method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |