CN211519891U - Rotor wing test tower - Google Patents
Rotor wing test tower Download PDFInfo
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- CN211519891U CN211519891U CN201921148957.5U CN201921148957U CN211519891U CN 211519891 U CN211519891 U CN 211519891U CN 201921148957 U CN201921148957 U CN 201921148957U CN 211519891 U CN211519891 U CN 211519891U
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Abstract
The embodiment of the utility model provides a rotor test tower, through the support frame of predetermineeing the height, arrange the fixed bolster in on predetermineeing the height, can reduce the influence of ground effect helicopter rotor to, be connected with the helicopter rotor through actuating mechanism, be in under the motion state at actuating mechanism drive helicopter rotor, the dynamic force that the helicopter rotor is in under the motion state just can be measured to the multidimension force sensor who is fixed in on the fixed bolster, just so can realize testing the performance of helicopter rotor.
Description
Technical Field
The utility model relates to an unmanned helicopter technical field especially relates to a rotor test tower.
Background
With the rapid development of helicopters, people put higher demands on the flight performance of helicopters. Since the performance of the helicopter rotor directly determines the flight performance and flight quality of the helicopter, the performance research of the helicopter rotor is very important.
At present, in the related art, the performance of a helicopter rotor is tested through a rotor test tower, and in order to test the performance of the helicopter rotor, the influence of a ground effect is generally required to be eliminated firstly. Due to the complexity of the ground effect mechanism, it is very important to perform relevant experimental research on the ground effect. In China, due to the limitation of test conditions, how to test the performance of the helicopter rotor under the condition of reducing the influence of the ground effect on the helicopter rotor is a problem to be solved urgently.
SUMMERY OF THE UTILITY MODEL
An object of the embodiment of the utility model is to provide a rotor test tower for under the condition of the influence of reducing ground effect to helicopter rotor, realize testing the performance of helicopter rotor. The specific technical scheme is as follows:
an embodiment of the utility model provides a rotor test tower, include:
a support frame 1 with a preset height;
a fixed bracket 2 fixed on the support frame 1;
a force measuring structure 3 provided on the fixed bracket 2, the force measuring structure 3 including: a multi-dimensional force sensor 31 for measuring dynamic force of the helicopter rotor 4 in motion, a main frame 32, and a driving mechanism 33 for driving the helicopter rotor 4 in motion, wherein,
the multi-dimensional force sensor 31 is fixed on the fixed bracket 2, the main frame 32 is arranged between the multi-dimensional force sensor 31 and the driving mechanism 33, and the driving mechanism 33 is connected with the helicopter rotor 4.
Further, the driving mechanism 33 includes: an electric control cabinet 331, a driving motor 332, a synchronous belt 333 and a main reducer 334;
the electric control cabinet 331 is connected to the driving motor 332, the driving motor 332 is mounted on the main frame 32, the main reducer 334 is mounted on the main frame 32, and the timing belt 333 is connected between the driving motor 332 and the main reducer 334, wherein the driving motor 332 is connected to an input pulley of the main reducer 334 through the timing belt 333 and transmits power to the main reducer 334; the output shaft 3341 of the final drive 334 is connected to the helicopter rotor 4 for driving the helicopter rotor 4 in rotation.
Further, the driving mechanism includes: the helicopter rotor steering engine and the flight control 335, the flight control 335 is mounted on the main frame 32, and the main speed reducer 334 is spaced from the driving motor 332, the flight control 335 is located on one side of the main speed reducer 334, and the driving motor 332 is located on the other side of the main speed reducer 334;
the rotor steering engine is installed on the output shaft 3341 of the main speed reducer 334 and used for driving the helicopter rotor 4 to change the pitch.
Further, the rotor testing tower further comprises: a cooling structure, the cooling structure comprising: and the water pump and the water tank 51 are connected with the water tank 51, and the water tank 51 is connected with the driving motor 332 through a water pipe.
Further, the multidimensional force sensor 31 and the main frame 32 are fixedly connected through screws;
the multidimensional force sensor 31 is fixedly connected with the fixed support 2 through a pin.
Furthermore, a ladder stand 11 is arranged on the support frame 1; the rotor test tower further comprises: and the supporting platform 12 is connected to the supporting frame 1, a guardrail 121 is arranged on the supporting platform 12, and the guardrail 121 is positioned on the periphery of the helicopter rotor 4.
The embodiment of the utility model provides a pair of rotor test tower, through the support frame of predetermineeing the height, arrange the fixed bolster in on predetermineeing the height, can reduce the influence of ground effect helicopter rotor to, be connected with the helicopter rotor through actuating mechanism, be in under actuating mechanism drive helicopter rotor, the multi-dimensional force sensor who is fixed in on the fixed bolster just can measure the dynamic force that the helicopter rotor is in under the motion state, just so can realize testing the performance of helicopter rotor.
Of course, it is not necessary for any product or method of the invention to achieve all of the above-described advantages at the same time.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
Fig. 1 is a schematic view of a first structure of a rotor testing tower according to an embodiment of the present invention;
fig. 2 is a second schematic structural diagram of a rotor testing tower according to an embodiment of the present invention;
description of reference numerals:
1-a support frame; 2-fixing the bracket; 3-a force measuring structure; 31-a multi-dimensional force sensor; 32-a main frame; 33-a drive mechanism; 331-an electric control cabinet; 332-a drive motor; 333-synchronous belt; 334-main reducer; 3341-output shaft of main reducer; 335-flight control; 4-helicopter rotors; 51-a water tank; 12-a support platform; 121-guard bar; 6-concrete foundation.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
To how among the prior art under the condition of the influence of reduction ground effect helicopter rotor, realize the problem that the performance of helicopter rotor tests, the embodiment of the utility model provides a rotor test tower, the embodiment of the utility model provides an in, through the support frame of predetermineeing the height, place the fixed bolster on predetermineeing the height, can reduce the influence of ground effect helicopter rotor to, be connected with the helicopter rotor through actuating mechanism, under actuating mechanism drive helicopter rotor is in the motion state, be fixed in the multi-dimensional force transducer on the fixed bolster and just can measure the dynamic force that the helicopter rotor is under the motion state, just so can realize testing the performance of helicopter rotor.
First, the influence of the ground effect on the helicopter is described.
The ground effect means that when the helicopter is hovering close to the ground or flying at a low speed, under a certain power, the pulling force of a rotor wing of the helicopter is increased when the rotor wing is far away from the ground; or, at a certain tension, the power demand of the helicopter rotor is reduced when it is far from the ground. The ground effect is of great significance for take-off and landing of helicopters. Due to the complexity of the ground effect mechanism, it is very important to perform relevant experimental research on the ground effect mechanism.
The ground effect is generated because the ground significantly influences the flow field of the helicopter rotor, including the magnitude and distribution of the induced velocity and the pedestrian flow velocity.
In order to be able to test the performance of helicopter rotor under the condition of reducing the influence of ground effect to helicopter rotor, it is right to continue below the utility model provides a rotor test tower introduces.
The embodiment of the utility model provides a rotor test tower to server provides can be applied to the helicopter field, and further be applied to unmanned helicopter field.
As shown in fig. 1, an embodiment of the present invention provides a rotor testing tower, which may include:
a support frame 1 with a preset height; a fixed bracket 2 fixed on the support frame 1; set up in force measurement structure 3 on fixed bolster 2, force measurement structure 3 includes: the dynamic force measuring device comprises a multi-dimensional force sensor 31 for measuring the dynamic force of the helicopter rotor 4 in a moving state, a main frame 32 and a driving mechanism 33 for driving the helicopter rotor 4 to move, wherein the multi-dimensional force sensor 31 is fixed on the fixed bracket 2, the main frame 32 is arranged between the multi-dimensional force sensor 31 and the driving mechanism 33, and the driving mechanism 33 is connected with the helicopter rotor 4.
The preset height can be a distance higher than a supporting surface for supporting the supporting frame, and the preset height can be set according to user requirements. Illustratively, the preset height may be, but is not limited to, greater than 20 meters and less than 30 meters. For example, the preset height may be, but is not limited to, 21.5 meters.
The supporting surface can be the ground or a measuring table. For reinforcing the support surface, the support surface may be a surface on a concrete foundation. The concrete foundation can be reinforced on supporting legs which are in contact with the supporting surface and are used for supporting the concrete foundation with force. For example, the support frame may be a support frame that is disposed on the ground and is higher than the ground by a predetermined height, or the support frame may be a support frame that is disposed under the ground and is spaced from the concave ground by a predetermined height, and the support frame is used to keep the helicopter rotor away from an obstacle that affects a flow field of the helicopter rotor, such as the ground or the concave ground, where the obstacle may cause the helicopter rotor to generate a ground effect.
The above-mentioned support frame may include, but is not limited to: the supporting platform is used for supporting the fixing support, supporting legs for fixing the supporting frame, a supporting frame main body connected between the supporting platform and the supporting legs, and the supporting platform and the supporting legs are arranged at two ends of the supporting main body. Wherein, the support frame main part can be by a plurality of poles connection shaping, mutual interval between a plurality of poles, the support frame main part also can be by a plurality of pipe connection shaping, mutual interval between a plurality of pipes, the support frame main part that has the interval like this or have the hole, the support frame main part does not have the complete surface, reduces and bears the rotatory pressure to the air production of helicopter rotor.
Under the state that can normally use the support frame, supporting platform is located the top of support frame, and the supporting legs is located the lowermost end of support frame, in order to improve the stability of support frame, the supporting legs can set up according to user's demand. The number of support feet can generally be greater than 3, such as 3 or 4, the greater the number of support feet, the greater the stability of the support, but the greater the cost. The support frame can be a steel bar frame or an iron frame.
The above-mentioned support frame may include, but is not limited to: set up in the cat ladder of support frame, furtherly, set up a side cat ladder on the support frame, perhaps set up in the multi-side cat ladder of support frame. Therefore, the ladder stand can be convenient for people to climb. Further, as shown in fig. 1, a ladder stand 11 is arranged on the support frame 1; be provided with the guard circle on the cat ladder, can guarantee climbing personnel's security like this. The rotor test tower still includes: and a support platform 12 connected to the support frame 1, wherein a guardrail 121 is arranged on the support platform 12, and the guardrail 121 is positioned on the periphery of the helicopter rotor 4. Therefore, when the helicopter rotor wing is in accident, people and property around the helicopter rotor wing can be protected and prevented.
For the driving mechanism 33, the driving mechanism 33 may be a driving mechanism 33 of a helicopter, or may be a driving mechanism 33 that is separately provided, as long as the driving mechanism 33 that can be realized by the embodiment of the present invention all belongs to the protection scope of the embodiment of the present invention, and no example is given here. Further, the driving mechanism 33 is explained as follows:
in one of the driving mechanisms 33, the driving mechanism 33 may include: an electric control cabinet 331, a driving motor 332, a synchronous belt 333 and a main reducer 334;
the electric control cabinet 331 is connected with the driving motor 332, the driving motor 332 is mounted on the main frame 32, the main reducer 334 is mounted on the main frame 32, the synchronous belt 333 is connected between the driving motor 332 and the main reducer 334, wherein the driving motor 332 is connected with an input pulley of the main reducer 334 through the synchronous belt 333 and transmits power to the main reducer 334; an output shaft 3341 of final drive 334 is connected to helicopter rotor 4 for driving helicopter rotor 4 in rotation.
The electric control cabinet and the driving motor can be arranged at the same position, for example, the electric control cabinet is arranged on a supporting platform; above-mentioned automatically controlled cabinet also can set up the least significant end at rotor test tower, for example, above-mentioned automatically controlled cabinet can use same holding surface with the fixed bolster, also exactly above-mentioned automatically controlled cabinet can set up with be used for supporting the holding surface of support frame on, the automatically controlled cabinet of the former passes through cable or cable like this, with driving motor connects for supporting platform's pressure grow may influence the measurement, consequently can adopt the latter, the automatically controlled cabinet of the latter sets up on the holding surface.
The main reducer includes: an input belt wheel of the main speed reducer and an output shaft of the main speed reducer.
As shown in fig. 2, in another above-mentioned drive mechanism 33, the drive mechanism includes: the helicopter rotor steering engine and the flight control 335, wherein the flight control 335 is arranged on the main frame 32, a main speed reducer 334 is arranged between the flight control 335 and the driving motor 332, the flight control 335 is positioned at one side of the main speed reducer 334, and the driving motor 332 is positioned at the other side of the main speed reducer 334; the flight control 335 is arranged opposite to the driving motor 332;
the rotor steering engine is installed on the output shaft 3341 of the main speed reducer 334 and used for driving the helicopter rotor 4 to change the pitch.
The rotor steering engine is arranged on an output shaft 3341 of the main speed reducer 334 and provides the operating force for the pitch change of the helicopter rotor. Therefore, the rotor steering engine is controlled through the flight control instruction, so that the pitch of the helicopter rotor is changed. The multi-dimensional force sensor measures the dynamic force of the operated helicopter rotor in a motion state, so that the mechanical property of the helicopter rotor can be obtained.
The embodiment of the utility model can also comprise the above driving mechanism and another above driving mechanism at the same time, thus the helicopter rotor can be driven to pitch and rotate; if the driving mechanism works, the helicopter rotor is driven to rotate; if the other driving mechanism works, the helicopter rotor wing is driven to pitch. In practical application, the setting is performed according to the user requirement, and the detailed description is omitted here.
In order to obtain the mechanical characteristics of the helicopter rotor, the multi-dimensional force sensor can be, but is not limited to, a six-dimensional force sensor, and the ground effect is eliminated and the dynamic force is accurately measured through the six-dimensional force sensor. The dynamic force may be, but is not limited to, the force experienced by the main frame, or may be, but is not limited to, the drag of the helicopter rotor, or may be, but is not limited to, the force generated by the rotation of the helicopter rotor on the air. The dynamic force that six-dimensional force sensor can measure can be referred to six degree of freedom direction's force and moment in six-dimensional force sensor.
The multi-dimensional force sensor may be, but is not limited to, an eight-dimensional force sensor. The multi-dimensional force sensor can be connected with the main frame and the fixing bracket respectively in various ways, for example, the multi-dimensional force sensor 31 and the main frame 32 are fixed by screws for positioning; the multidimensional force sensor 31 is fixedly connected with the fixed support 2 through a pin for positioning.
Based on the above-mentioned multidimensional sensor, actuating mechanism, support frame, in order to reduce the pressure that bears the weight of the helicopter rotor rotation and produces the air, continue to describe the fixed bolster below.
The fixed bracket may not form an obstacle affecting the flow field of the helicopter rotor. Each of fixed bolster personally submits the fretwork form or is the wire side, the fixed bolster can be by a plurality of poles connection shaping, separate each other between a plurality of poles, the fixed bolster also can be by a plurality of union coupling shaping, separate each other between a plurality of pipes, the fixed bolster that has the interval like this or has the hole, the fixed bolster does not have the complete face, reduces and bears the rotatory pressure that produces the air of helicopter rotor.
The embodiment of the utility model provides an in, through the support frame of predetermineeing the height, arrange the fixed bolster in on predetermineeing the height, can reduce the influence of ground effect to helicopter rotor to, be connected through actuating mechanism and helicopter rotor, under actuating mechanism drive helicopter rotor is in the motion state, the dynamic force that the helicopter rotor is in the motion state just can be measured to the multidimensional force sensor who is fixed in on the fixed bolster, just so can realize testing the performance of helicopter rotor.
The performance of the helicopter rotor refers to different lift/roll/yaw/pitch magnitudes reflected by the helicopter rotor in a plurality of flight control states.
The embodiment of the utility model provides a rotor test tower that still provides, rotor test tower still includes: a cooling structure, the cooling structure comprising: a water pump and a water tank 51, the water pump is connected to the water tank 51, and the water tank 51 is connected to the driving motor 332 through a water pipe.
The water tank may be, but not limited to, a water tank for containing cooling water, and may also be referred to as a cold water tank; the water pipe may be, but not limited to, a pipe for containing cold water, and may also be referred to as a cold water pipe. Cooling water in the cold water tank is connected to a driving motor through a water pump and a cold water pipe, and the driving motor is connected with the electric control cabinet through a cable or a cable.
Above-mentioned water tank can set up in same position with automatically controlled cabinet, also set up the least significant end at rotor test tower promptly, for example, above-mentioned water tank can use same holding surface with the fixed bolster, also promptly also above-mentioned water tank can set up with be used for supporting the holding surface of support frame on, the water tank passes through the cold water pipe like this, is connected with driving motor, uses contents such as water tank like this, can guarantee driving motor's normal work for driving motor cooling.
It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention shall fall within the protection scope of the present invention.
Claims (6)
1. A rotor testing tower, comprising:
a support frame (1) with a preset height;
a fixed bracket (2) fixed on the support frame (1);
set up in force measurement structure (3) on fixed bolster (2), force measurement structure (3) includes: a multi-dimensional force sensor (31) for measuring the dynamic force of the helicopter rotor (4) in a moving state, a main frame (32) and a driving mechanism (33) for driving the helicopter rotor (4) to move, wherein,
multidimensional force sensor (31) is fixed in on fixed bolster (2), main frame (32) set up in multidimensional force sensor (31) with between actuating mechanism (33), actuating mechanism (33) with helicopter rotor (4) are connected.
2. A rotor testing tower according to claim 1, wherein said drive mechanism (33) comprises: the electric control cabinet (331), the driving motor (332), the synchronous belt (333) and the main reducer (334);
the electric control cabinet (331) is connected with the driving motor (332), the driving motor (332) is mounted on the main frame (32), the main speed reducer (334) is mounted on the main frame (32), and the synchronous belt (333) is connected between the driving motor (332) and the main speed reducer (334), wherein the driving motor (332) is connected with an input pulley of the main speed reducer (334) through the synchronous belt (333) and transmits power to the main speed reducer (334); an output shaft (3341) of the main reducer (334) is connected to the helicopter rotor (4) for driving the helicopter rotor (4) to rotate.
3. The rotor test tower of claim 2, wherein the drive mechanism comprises: the helicopter rotor steering engine and the flight control (335), wherein the flight control (335) is installed on the main frame (32), the main speed reducer (334) is arranged between the flight control (335) and the driving motor (332), the flight control (335) is positioned on one side of the main speed reducer (334), and the driving motor (332) is positioned on the other side of the main speed reducer (334);
the rotor wing steering engine is installed on an output shaft (3341) of the main speed reducer (334) and used for driving the helicopter rotor wing (4) to change the pitch.
4. The rotor test tower of claim 2, further comprising: a cooling structure, the cooling structure comprising: the water pump is connected with the water tank (51), and the water tank (51) is connected with the driving motor (332) through a water pipe.
5. A rotor testing tower according to claim 1, wherein the multi-dimensional force sensor (31) is secured to the main frame (32) by a screw connection;
the multi-dimensional force sensor (31) is fixedly connected with the fixed support (2) through a pin.
6. A rotor testing tower according to any of claims 1 to 4, wherein a ladder (11) is provided on the mast (1); the rotor test tower further comprises: connect in support platform (12) on support frame (1), be provided with guardrail (121) on support platform (12), guardrail (121) are located the periphery of helicopter rotor (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921148957.5U CN211519891U (en) | 2019-07-22 | 2019-07-22 | Rotor wing test tower |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921148957.5U CN211519891U (en) | 2019-07-22 | 2019-07-22 | Rotor wing test tower |
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| Publication Number | Publication Date |
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| CN211519891U true CN211519891U (en) | 2020-09-18 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201921148957.5U Active CN211519891U (en) | 2019-07-22 | 2019-07-22 | Rotor wing test tower |
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| CN (1) | CN211519891U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110435923A (en) * | 2019-07-22 | 2019-11-12 | 北京中航智科技有限公司 | A kind of rotor test tower |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110435923A (en) * | 2019-07-22 | 2019-11-12 | 北京中航智科技有限公司 | A kind of rotor test tower |
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Effective date of registration: 20230421 Address after: Room 40, 9th Floor, Building 5, Beihang Wuhu Navigation Innovation Park, Anhui Xinwu Economic Development Zone, Wanzhou District, Wuhu City, Anhui Province, 241119 Patentee after: Wuhu United Aircraft Technology Co.,Ltd. Address before: 100176 1st floor, building 1, No.20, Tongji South Road, Beijing Economic and Technological Development Zone, Daxing District, Beijing Patentee before: BEIJING ZHZ TECHNOLOGY Co.,Ltd. |