CN111516900B - Helicopter course tail locking test device and method thereof - Google Patents
Helicopter course tail locking test device and method thereof Download PDFInfo
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- CN111516900B CN111516900B CN202010364223.1A CN202010364223A CN111516900B CN 111516900 B CN111516900 B CN 111516900B CN 202010364223 A CN202010364223 A CN 202010364223A CN 111516900 B CN111516900 B CN 111516900B
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- 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
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Abstract
The invention belongs to the technical field of aviation, and discloses a helicopter course tail locking test device and a method thereof, wherein the helicopter course tail locking test device comprises the following steps: the device comprises a base, a positioning shaft, a first deep groove ball bearing, a rotating disc and a limiting sheet; the helicopter is fixed on the rotating disc; the base is fixed on the ground, a drill hole is formed in the center of the base, the first deep groove ball bearing is embedded into the drill hole, and the positioning shaft is installed in the deep groove ball bearing; at least one circle of round holes are arranged on the upper surface of the base around the circle center, and a universal ball bearing is embedded into each round hole; the rotating disc is coaxially arranged above the base, and the lower surface of the rotating disc is in contact with the upper surfaces of the universal ball bearings on the base; the limiting piece is fixed on the upper surface of the base, the extending part above the limiting piece is positioned above the rotating disk, and a gap is reserved between the extending part and the rotating disk.
Description
Technical Field
The invention belongs to the technical field of aviation, and particularly relates to a helicopter course tail locking test device and a method thereof.
Background
The matching of the main pitch and the tail pitch (dual rotor pitch differential motion of the dual rotor helicopter/unmanned helicopter) in the development of the existing helicopter/unmanned helicopter is generally realized by the modes of design, calculation, analysis, simulation, a simulator, special test equipment, a three-axis turntable and the like.
For helicopters/unmanned helicopters developed in folk in recent years, on one hand, the design, calculation and analysis capabilities are not enough, on the other hand, the cost of simulation, a simulator, special equipment, a three-axis turntable and the like is high, no better solution is provided for the matching problem of the main pitch and the tail pitch of the helicopters/unmanned helicopters before takeoff, the matching relation of the main pitch and the tail pitch is adjusted through trial flight in many cases, and the method has great potential safety hazards.
Disclosure of Invention
In view of the above problems, an object of the present invention is to provide a helicopter course locking tail test device and a method thereof, the device has a simple structure, can be applied to all helicopters/unmanned helicopters, can be adapted in size according to the sizes of the helicopters/unmanned helicopters, and has a great potential application prospect and a great market.
In order to achieve the purpose, the invention adopts the following technical scheme to realize.
The first technical scheme is as follows:
a helicopter course tail locking test device, the device includes: the device comprises a base 4, a positioning shaft 5, a first deep groove ball bearing 6, a rotating disc 3 and a limiting piece 2;
the helicopter is fixed on the rotating disc 3;
the base 4 is fixed on the ground, a drill hole is formed in the center of the base 4, the first deep groove ball bearing 6 is embedded into the drill hole, and the positioning shaft 5 is installed in the deep groove ball bearing 6;
at least one circle of round holes are formed in the upper surface of the base around the circle center, and a universal ball bearing 7 is embedded into each round hole;
the rotating disc 3 is coaxially arranged above the base 4, and the lower surface of the rotating disc 3 is in contact with the upper surfaces of a plurality of universal ball bearings on the base 4;
the limiting piece is fixed on the upper surface of the base 4, and the extending part above the limiting piece is positioned above the rotating disk, and a gap is reserved between the limiting piece and the rotating disk.
The first technical scheme of the invention has the characteristics and further improvements that:
(1) The device further comprises: a second deep groove ball bearing;
the center of the rotating disc is provided with a drill hole, the second deep groove ball bearing is embedded into the drill hole, and the positioning shaft is installed in the second deep groove ball bearing.
(2) The base is a metal disc, and the rotary disc is a metal disc.
(3) The heights of the universal ball bearings are the same.
(4) The number of the limiting pieces is four, and the limiting pieces are fixed on the upper surface of the base respectively by eight countersunk head screws at intervals of 90 degrees.
(5) The base upper surface is provided with two circles of round holes around the centre of a circle, eight round holes per circle, and evenly distributed.
The second technical scheme is as follows:
a helicopter course tail locking test method is applied to a test device in the technical scheme I and comprises the following steps:
fixing the helicopter on the upper surface of the rotating disc;
when the helicopter is started and the rotor rotates, if the counter torque of the rotor is not equal to the counter force of the tail rotor, the helicopter rotates in the yaw direction to drive the rotating disc to rotate together;
the helicopter stops rotating by adjusting the main pitch and the tail pitch of the rotor wing, so that a group of angle matching data of the main pitch and the tail pitch is obtained.
The third technical scheme is as follows:
a helicopter course tail locking test method is applied to a test device in the technical scheme I and comprises the following steps:
fixing the helicopter on the upper surface of the rotating disc;
when the helicopter is started and the rotors rotate, if the reactive torques of the two main rotors of the double rotors are not equal, the helicopter generates the rotation in the yaw direction to drive the rotating disk to rotate together;
the helicopter stops rotating by adjusting the two main pitches of the double rotors, so that differential matching data of the two main pitches are obtained.
The helicopter/unmanned helicopter is characterized in that the vertical motion of the helicopter/unmanned helicopter has a coupling effect with the course motion around a main rotor shaft in the process of controlling and controlling the main pitch to increase or decrease, and the course motion can be generated when the helicopter/unmanned helicopter vertically rises or falls, so that the helicopter/unmanned helicopter does not need to firstly complete the matching relation between the main pitch and the tail pitch (the difference between two different main pitches for a double-rotor helicopter/unmanned helicopter) in design and ground tests, and the matching relation is theoretically calculated and simulated on one hand and also verified by tests on the other hand. Compared with the prior art, the invention has simple structure and no special material or equipment requirement, can be applied to all helicopters/unmanned helicopters, can be adapted according to the sizes of the helicopters/unmanned helicopters, is easy to popularize, has larger potential market and has larger economic benefit.
Drawings
FIG. 1 is a general diagram of a helicopter course tail locking test device;
FIG. 2 is a diagram illustrating an exemplary application of a helicopter heading tail-locking test device;
wherein, 1-countersunk head screw; 2-a limiting piece; 3-rotating the disc; 4-a base; 5-positioning the shaft; 6-deep groove ball bearing; 7-universal ball bearing.
Detailed Description
The invention provides a helicopter/unmanned helicopter course tail locking test device, which can be used for carrying out ground course tail locking test before flight on a newly researched or improved helicopter/unmanned helicopter. The device can be placed on the ground, and a helicopter/unmanned helicopter which needs to carry out a ground course debugging test is fixed on the upper surface of a rotating disk of the device, so that the device is used for carrying out a test on the matching relation between the total pitch of main propellers and the pitch of tail propellers of the helicopter/unmanned helicopter (for the double-rotor helicopter/unmanned helicopter, the two main propellers are differential).
The device can fix the helicopter/unmanned helicopter on the test device, and the rotating disk on the test device is observed to adjust the tail propeller pitch by increasing and decreasing the total pitch, so that the corresponding relation between any main propeller pitch and the tail propeller pitch is obtained (or two main propeller pitches of the dual-rotor helicopter/unmanned helicopter are respectively adjusted, so that the differential matching relation of the two main propeller pitches is obtained).
The invention relates to a helicopter/unmanned helicopter course tail locking test device, which comprises a base 4, a positioning shaft 5, a deep groove ball bearing 6, a universal ball bearing 7, a rotating disk 3, a limiting plate 2 and a countersunk head screw 1, wherein the positioning shaft 5 is arranged on the base;
the base 4 is a metal disc and is placed on the ground, two deep groove ball bearings 6 are drilled in the circle center of the base 4, a positioning shaft 5 is installed in each deep groove ball bearing 6, two circles of round holes are respectively drilled in the upper surface of the base 4 around the circle center, eight round holes are drilled in each circle, sixteen universal ball bearings 7 are embedded in sixteen round holes of the base 4, the sixteen universal ball bearings 7 are guaranteed to roll flexibly, and the heights of the universal ball bearings 7 are consistent;
the rotary disk 3 is a metal disc, two deep groove ball bearings 6 are embedded into a hole drilled in the center of the rotary disk 3, the rotary disk 3 and the two deep groove ball bearings 6 embedded in the rotary disk are installed above the base 4 together, the base 4 and the rotary disk 3 are kept coaxial, the upper surfaces of sixteen universal ball bearings 7 are kept to be in contact with the lower surface of the rotary disk 3 and are used for supporting the rotary disk 3 and a helicopter/unmanned helicopter on the rotary disk 3, the four limiting pieces 2 are fixed to the upper surface of the base 4 at intervals of 90 degrees by eight countersunk head screws 1 respectively, the protruding portion above the limiting piece 4 is guaranteed to be located above the rotary disk 3, and a certain gap is reserved so that the rotary disk 3 can rotate freely around the positioning shaft 5.
As shown in fig. 2, the helicopter/unmanned helicopter may be fixed on the upper surface of the rotating disc 3, when the helicopter/unmanned helicopter is started and the rotor rotates, if the counter torque of the rotor is not equal to the counter torque of the tail rotor (or the counter torques of the two main rotors of the dual rotor), the helicopter may generate a rotation in the yaw direction, and drive the rotating disc to rotate together, and the helicopter/unmanned helicopter may stop rotating by adjusting the main pitch and the tail pitch of the rotor (or the two main pitches of the dual rotor), so as to obtain a set of matching data of the main pitch and the tail pitch (or the differential matching data of the two main pitches), and in turn, collect enough data points, and gradually determine the matching curves of the different main pitches and the tail pitch (or the differential matching curves of the two main pitches), thereby being used for controlling the system.
The helicopter/unmanned helicopter is characterized in that the vertical motion of the helicopter/unmanned helicopter has a coupling effect with the course motion around a main rotor shaft in the process of controlling and controlling the main pitch to increase or decrease, and the course motion can be generated when the helicopter/unmanned helicopter vertically rises or falls, so that the helicopter/unmanned helicopter does not need to firstly complete the matching relation between the main pitch and the tail pitch (the difference between two different main pitches for a double-rotor helicopter/unmanned helicopter) in design and ground tests, and the matching relation is theoretically calculated and simulated on one hand and also verified by tests on the other hand.
Compared with the prior art, the invention has simple structure and no special material or equipment requirement, can be applied to all helicopters/unmanned helicopters, can be adapted according to the sizes of the helicopters/unmanned helicopters, is easy to popularize, has larger potential market and has larger economic benefit.
Claims (8)
1. The utility model provides a helicopter course lock tail test device which characterized in that, the device includes: the device comprises a base (4), a positioning shaft (5), a first deep groove ball bearing (6), a rotating disc (3) and a limiting piece (2);
the helicopter is fixed on the rotating disc (3);
the positioning device comprises a base (4), a drill hole, a first deep groove ball bearing (6), a positioning shaft (5) and a second deep groove ball bearing (6), wherein the base (4) is fixed on the ground, the center of the base (4) is provided with the drill hole, the first deep groove ball bearing (6) is embedded into the drill hole, and the positioning shaft (5) is installed in the deep groove ball bearing (6);
at least one circle of round holes are arranged on the upper surface of the base around the circle center, and a universal ball bearing (7) is embedded into each round hole;
the rotating disc (3) is coaxially arranged above the base (4), and the lower surface of the rotating disc (3) is in contact with the upper surfaces of the universal ball bearings on the base (4);
the limiting piece is fixed on the upper surface of the base (4), and the extending part above the limiting piece is positioned above the rotating disk, and a gap is reserved between the limiting piece and the rotating disk.
2. A helicopter heading tail-lock testing device according to claim 1, said device further comprising: a second deep groove ball bearing;
the center of the rotating disc is provided with a drill hole, the second deep groove ball bearing is embedded into the drill hole, and the positioning shaft is installed in the second deep groove ball bearing.
3. The helicopter course lock tail test device of claim 1, wherein the base is a metal disc and the rotating disc is a metal disc.
4. The helicopter course tail-locking test device of claim 1, characterized in that the heights of the plurality of universal ball bearings are the same.
5. The helicopter course lock tail test device of claim 1, wherein the number of the limiting pieces is four, and eight countersunk head screws are respectively fixed on the upper surface of the base at intervals of 90 degrees.
6. The helicopter course lock tail test device of claim 1, wherein the base upper surface is provided with two circles of round holes around the center of a circle, eight round holes per circle, and the round holes are evenly distributed.
7. A helicopter heading tail-lock test method applied to the test device as claimed in any one of claims 1-5, the method comprising:
fixing the helicopter on the upper surface of the rotating disc;
when the helicopter is started and the rotor rotates, if the counter torque of the rotor is not equal to the counter force of the tail rotor, the helicopter rotates in the yaw direction to drive the rotating disc to rotate together;
and the helicopter stops rotating by adjusting the main pitch and the tail pitch of the rotor wing, so that a group of angle matching data of the main pitch and the tail pitch is obtained.
8. A helicopter heading tail-lock test method applied to the test device as claimed in any one of claims 1-5, the method comprising:
fixing the helicopter on the upper surface of the rotating disc;
when the helicopter is started and the rotors rotate, if the reactive torques of the two main rotors of the double rotors are not equal, the helicopter generates the rotation in the yaw direction to drive the rotating disk to rotate together;
and (3) stopping the helicopter by adjusting the two main pitches of the double rotors, so as to obtain differential matching data of the two main pitches.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010364223.1A CN111516900B (en) | 2020-04-30 | 2020-04-30 | Helicopter course tail locking test device and method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010364223.1A CN111516900B (en) | 2020-04-30 | 2020-04-30 | Helicopter course tail locking test device and method thereof |
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| Publication Number | Publication Date |
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| CN111516900A CN111516900A (en) | 2020-08-11 |
| CN111516900B true CN111516900B (en) | 2023-03-14 |
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| CN105270617A (en) * | 2014-06-19 | 2016-01-27 | 庆安集团有限公司 | Coaxial double propeller helicopter middle propeller pitch control device |
| CN105620788A (en) * | 2016-01-26 | 2016-06-01 | 上海圣尧智能科技有限公司 | Universal platform and unmanned aerial vehicle test system |
| CN106927064A (en) * | 2017-04-21 | 2017-07-07 | 北京建中数字科技有限公司 | One kind intersects DCB Specimen depopulated helicopter ground test platform |
| CN209351624U (en) * | 2018-12-04 | 2019-09-06 | 湖南山河科技股份有限公司 | A kind of unmanned helicopter test platform |
| CN209410358U (en) * | 2018-10-12 | 2019-09-20 | 北方通用电子集团有限公司 | Target drone flight attitude ground simulator |
| CN110510148A (en) * | 2019-08-29 | 2019-11-29 | 昆明理工大学 | A kind of big load unmanned helicopter rotor model.test system |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10836479B2 (en) * | 2018-06-19 | 2020-11-17 | Bell Textron Inc. | Rotating swashplate ring to rotor mast connection |
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2020
- 2020-04-30 CN CN202010364223.1A patent/CN111516900B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105270617A (en) * | 2014-06-19 | 2016-01-27 | 庆安集团有限公司 | Coaxial double propeller helicopter middle propeller pitch control device |
| CN105620788A (en) * | 2016-01-26 | 2016-06-01 | 上海圣尧智能科技有限公司 | Universal platform and unmanned aerial vehicle test system |
| CN106927064A (en) * | 2017-04-21 | 2017-07-07 | 北京建中数字科技有限公司 | One kind intersects DCB Specimen depopulated helicopter ground test platform |
| CN209410358U (en) * | 2018-10-12 | 2019-09-20 | 北方通用电子集团有限公司 | Target drone flight attitude ground simulator |
| CN209351624U (en) * | 2018-12-04 | 2019-09-06 | 湖南山河科技股份有限公司 | A kind of unmanned helicopter test platform |
| CN110510148A (en) * | 2019-08-29 | 2019-11-29 | 昆明理工大学 | A kind of big load unmanned helicopter rotor model.test system |
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| CN111516900A (en) | 2020-08-11 |
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