CN107719696B - Dynamic characteristic synchronous testing device of axial compact type aircraft propeller - Google Patents
Dynamic characteristic synchronous testing device of axial compact type aircraft propeller Download PDFInfo
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- CN107719696B CN107719696B CN201710816501.0A CN201710816501A CN107719696B CN 107719696 B CN107719696 B CN 107719696B CN 201710816501 A CN201710816501 A CN 201710816501A CN 107719696 B CN107719696 B CN 107719696B
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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 discloses a device and a method for synchronously testing dynamic characteristics of an axial compact aircraft propeller. The device comprises a fixed base, a side bracket, a cylindrical guide shaft, a guide shaft support frame, a guide shaft sliding block, a sliding block adapter, a support plate, a rotary flange plate, a stop block, a propeller motor, a force measuring sensor support block, a tension pressure measuring and thrust measuring sensor, a rod end joint bearing, a tension pressure measuring and torsion measuring sensor and a torsion measuring sensor support block; the two dynamic characteristic synchronous testing devices are axially and symmetrically installed, and the propeller torque is obtained according to the numerical value of the tension-pressure torque measuring sensor and the geometric dimension of the rotary flange; obtaining the thrust of the propeller by the numerical value of a tension and pressure force measuring sensor at the bottom of the supporting plate and the geometrical parameters of a force arm; synchronous testing of the dynamic characteristics of the propellers of the aircraft is realized; the axial length of the testing device is shortened, and the efficiency of testing the dynamic characteristics is improved; the interference among different degrees of freedom is reduced, and the test precision is improved; the test cost is reduced.
Description
Technical Field
The invention belongs to the technical field of aerospace, and can be used for testing the dynamic characteristics of propellers of aircrafts such as unmanned planes, aerostats and the like, in particular to the dynamic characteristics of the propellers of coaxial double-propeller aircrafts.
Background
In recent years, propeller electric propulsion technology of aircrafts such as unmanned planes, aerostats and the like and application thereof are rapidly developed. The electric motor driven by electric energy drives the propeller to generate aircraft propulsion power, which becomes an important scheme for replacing the traditional internal combustion type aero-engine.
The propeller dynamic characteristics mainly comprise thrust characteristics and torque characteristics, and the comprehensive dynamic characteristics are the basis of the overall dynamic design and control of the relevant aircraft and are used for determining whether the selected power system performance parameters meet the requirements of the overall design. Meanwhile, the power characteristic of the propeller is an important basis for determining the design index of the propulsion motor, and the torque and rotating speed characteristics of the propulsion motor need to be matched with the power characteristic and the rotating speed characteristic so as to realize the integral optimization of the power density, the thermal performance and the efficiency of the electric propulsion system.
The existing propeller comprehensive dynamic characteristic test scheme mainly adopts thrust and torque to measure independently, needs two sets of test tools, and has low test efficiency and low test data accuracy and consistency. The synchronous measurement of the thrust and the torque can improve the efficiency and the accuracy of the test.
At present, propeller dynamic characteristic test bench design of thrust and torque synchronous measurement adopts propeller, torque sensor, motor, the coaxial series connection overall arrangement of force sensor more, specifically as follows:
patent document CN 103604608B discloses a propeller tension test bench for light sport aircraft, in which a motor, a torque sensor and a propeller are coaxially and serially arranged through a coupling, and are integrally placed on a platform supported by a hanger plate-four-bar mechanism, tension generated by rotation of the propeller is transmitted to the tension sensor through the supporting platform, and is tested, and the torque of the propeller is measured by the torque sensor between the motor and the propeller.
In a propulsion system dynamic characteristic experiment table disclosed in patent document CN 102937509 a, a motor, a torque sensor and a propeller which are coaxially and serially arranged are integrally placed on a linear slide rail, one end of a tension sensor is connected with an experiment table fixing base, and the other end of the tension sensor is connected with a platform supported by the linear slide rail. The propulsion of the propeller is tested by means of a tension sensor and the torque is measured by means of a torque sensor between the motor and the propeller.
Patent document CN 106143949 a discloses a vertical lift characteristic test bench for unmanned aerial vehicle rotor, rotor motor, torque sensor and tension sensor are vertically connected in series, wherein the torque direction is constrained by linear bearing and vertical guide shaft, the vertical direction is constrained by the tension sensor at the bottom, and the propeller lift and the input torque are measured by the tension sensor and the torque sensor respectively.
In the propeller dynamic characteristic experiment table in the series arrangement, the torque sensor is not only used for sensing the torque of the transmission shaft, but also needs to bear the thrust of the propeller in the axial direction, which puts high requirements on the axial structure and the fatigue strength of the torque sensor, and the cost of the torque sensor is high.
Aiming at a coaxial double-paddle electric propulsion system, the pneumatic coupling effect of an upper paddle and a lower paddle when the double paddles work simultaneously needs to be considered. When the rotating surfaces of the two propellers are close to each other, the propeller dynamic characteristic experiment table in the series layout mode can be constrained by a large axial space, and the series layout mode cannot realize the dynamic characteristic measurement of the coaxial double propellers.
Disclosure of Invention
In order to solve the problems, the invention provides an axial compact type aircraft propeller dynamic characteristic testing device with a brand new structure, which can simultaneously measure the propeller thrust and torque characteristics, has small axial length, is particularly suitable for the coaxial double-propeller dynamic characteristic test, and has compact structure, low cost and strong universality.
The technical scheme of the invention is as follows: an axial compact type synchronous testing device for dynamic characteristics of an aircraft propeller comprises a fixed base, a side support, a cylindrical guide shaft, a guide shaft support frame, a guide shaft sliding block, a sliding block adapter, a support plate, a rotary flange plate, a stop baffle block, a propeller motor, a force measuring sensor support block, a tension pressure and thrust measuring sensor, a rod end joint bearing, a tension pressure and torsion measuring sensor and a torsion measuring sensor support block; the connection and matching relationship of the components is as follows: the side bracket is mechanically connected to the fixed base, two ends of the cylindrical guide shaft are fixed through a guide shaft support frame arranged on the side bracket, the force measuring sensor support block is mechanically connected with the fixed base, and two ends of the tension and pressure measuring and thrust sensor are respectively connected with the force measuring sensor support block and the support plate; the device comprises a cylindrical guide shaft, a guide shaft sliding block, a screw motor and a stop baffle block, wherein the cylindrical guide shaft is provided with the guide shaft sliding block, the guide shaft sliding block is provided with axial displacement and rotational freedom along the cylindrical guide shaft, the guide shaft sliding block is mechanically connected with a support plate through a sliding block adapter, an inner hole in the support plate is matched with the excircle of a rotating flange plate in a sliding or bearing mode, the screw motor is mechanically arranged on the rotating flange plate, the rotating flange plate and the support plate are locked on the axial displacement through the stop baffle block, the axial direction of the rotating flange plate is limited by the stop baffle block, the screw torque is transmitted to the rotating flange plate through a screw motor, and the screw torque is acted on a tension pressure torque measuring sensor through a rod end joint bearing fixed on the rotating flange plate so; the propeller thrust is transmitted to the rotary flange plate through the propeller motor, and the supporting plate applies force to the tension and pressure measuring thrust sensor to realize measurement of the propeller thrust.
A method for synchronously testing the dynamic characteristics of the propellers of an aircraft by utilizing the synchronous testing device for the dynamic characteristics of the propellers of the axially compact aircraft is characterized in that two synchronous testing devices for the dynamic characteristics of the propellers are axially and symmetrically installed, and the torque of the propellers is obtained according to the numerical value of a tension-pressure torque measuring sensor and the geometric dimension of a rotary flange plate; meanwhile, the thrust of the propeller can be calculated by measuring the numerical value of a thrust sensor and the geometrical parameter of the force arm according to the tension and pressure at the bottom of the supporting plate; the synchronous test of the propeller dynamic characteristics of the coaxial double-propeller aircraft is realized.
The principle of propeller torque measurement is as follows: the propeller motor 10 provides torque required by propeller rotation, and simultaneously, an equal reverse torque acts on the rotary flange 8, and as the rotary flange 8 has very small rotation displacement in the axial direction, the product of the torque force acting on the tension pressure torque measuring sensor 14 through the rod end joint bearing 13 and the corresponding force arm is balanced with the direction torque acting on the rotary flange 8 by the motor. Furthermore, the propeller torque can be estimated from the values of the tension/pressure torque sensor 14 and the geometric dimensions of the rotary flange 8.
The principle of propeller thrust measurement is as follows: the plane of the supporting plate 7 is vertical to the thrust direction of the propeller, the thrust of the propeller is equivalent to the axis of the inner hole of the supporting plate 7 through a propeller motor 10, and a torque rotating along the cylindrical guide shaft 3 is formed. Because the rotation angle of the supporting plate 7 along the cylindrical guide shaft 3 is very small, the rotation torque generated by the propeller thrust along the direction of the cylindrical guide shaft 3 is equal to the product of the stress at the joint of the bottom of the supporting plate 7 and the corresponding force arm. Therefore, the propeller thrust can be calculated by the values of the tension and pressure force measuring sensors 12 at the bottoms of the supporting plates 7 and the geometrical parameters of the force arm.
The invention has the advantages and characteristics that:
(1) the novel axial compact structural design is adopted, the axial length of the testing device is shortened, and when the two testing devices are axially and symmetrically installed, the coaxial double-propeller dynamic characteristic test can be realized. (2) The synchronous measurement of the torque and the thrust of the propeller is realized, and the efficiency of testing the dynamic characteristics of the propeller is greatly improved. (3) The decoupling measurement of the torque and the thrust of the propeller is realized, the interference among different degrees of freedom is reduced, and the improvement of the test precision is facilitated. (4) The propeller torque measurement adopts a force balance mode, a torque value is equivalently obtained by a low-cost pull pressure sensor, a relatively expensive torque sensor is avoided, and the test cost is favorably reduced.
Drawings
Fig. 1 is a schematic structural diagram of a propeller dynamic characteristic testing device of the present invention.
Fig. 2 is a front schematic view (front view) of the propeller dynamic characteristic testing apparatus according to the present invention.
Fig. 3 is a schematic reverse side view (rear view) of the structure of the propeller dynamic characteristic testing device of the present invention.
Fig. 4 is a schematic diagram of the measurement of the propeller torque according to the present invention.
Fig. 5 is a schematic diagram of the propeller thrust measurement of the present invention.
FIG. 6 is a schematic structural diagram of a coaxial double-paddle dynamic characteristic testing device.
Detailed Description
As shown in fig. 1-3, the device for synchronously testing the dynamic characteristics of the propellers of the axial compact aircraft comprises a fixed base 1, a side bracket 2, a cylindrical guide shaft 3, a guide shaft support frame 4, a guide shaft slide block 5, a slide block adapter 6, a support plate 7, a rotary flange 8, a stop block 9, a propeller motor 10, a force sensor support block 11, a tension and pressure force sensor 12, a rod end joint bearing 13, a tension and pressure torque sensor 14 and a torque sensor support block 15.
First, the rotary flange 8 can be inserted through the support plate 7, the rotary flange 8 is axially fixed to the support plate 7 by the stopper block 9, and the rotary flange 8 can freely rotate relative to the axial direction. And next, connecting the bearing end of the rod end joint bearing 13 with the rotary flange 8, fixing the rod end of the rod end joint bearing 13 with a tension pressure torque measuring sensor 14, and fixing the tension pressure torque measuring sensor 14 on the support plate 7 through a torque measuring sensor support block 15. And next, mechanically fixing the sliding block adapter 6 on the supporting plate 7, and mechanically fixing the guide shaft sliding block 5 and the sliding block adapter 6.
Then the side bracket 2 is mechanically connected on the fixed base 1, and the cylindrical guide shaft 3 passes through the guide shaft slide block 5 and is fixed on the side bracket 2 through the guide shaft support frame 4. And next, mechanically connecting the load cell supporting block 11 with the fixed base 1, and respectively connecting the two ends of the tension and pressure load cell 12 with the load cell supporting block 11 and the supporting plate 7.
Finally, the propeller motor 10 is mounted on the rotary flange 8. The propeller motor 10 is started, the propeller torque is transmitted to the rotary flange 8 through the motor 10, and the torque is applied to the tension/compression torque sensor 14 through the rod end joint bearing 13 fixed to the rotary flange 8. The propeller thrust is transmitted to the rotary flange 8 through the motor 10 and forces are applied to the tension-compression load cell 12 through the support plate 7. The values of the tension and compression force torque sensor 14 and the tension and compression force sensor 12 are read or recorded by corresponding display instruments.
The principle of measuring the propeller torque is shown in fig. 4, the propeller torque is equivalent to a torque MZ acting on a center line point O of a rotating flange 8, a point a is an equivalent connection point of a rod end joint bearing 13 and the rotating flange 8, and a tension Fm is measured from a tension pressure torque measuring sensor 14. Because the rotating angle of the rotary flange plate 8 is very small, the propeller torque can be calculated according to the torque balance principle: MZ ═ Fm × r, where r is the moment arm of Fm, i.e. the distance between AO and o points.
The principle of measuring the propeller thrust is shown in fig. 5, the propeller tension is equivalent to an axial force FZ acting on a center line point O of a rotating flange 8, a point P is the center of the section of a cylindrical guide shaft 3, a point B is an equivalent connection point of a support plate 7 and a tension and pressure force measuring sensor 12, and the tension and pressure force measuring sensor 12 measures the tension force Fb. The point G is the equivalent gravity center point of the propeller motor 10 and the rotary flange 8, and the equivalent gravity of the propeller motor 10 and the rotary flange 8 is Fg. Because the angle of the supporting plate 7 rotating around the point P is very small, the propeller thrust can be calculated according to the torque balance principle: FZ ═ (Fb × b — Fg × g)/a, where a is the moment arm of FZ, i.e., the distance between two points PO; b is the moment arm of Fb, i.e. the distance between two points PB; g is the moment arm of Fg, i.e. the distance between two points of GO.
After the test apparatus of the present invention is mounted in place, the value of the tension/compression force sensor 12 is read in a stationary state of the propeller motor 10 and is set as Fb 0. The gravity equivalent torque is: fg — g — Fb0 — b, the propeller thrust equation can be expressed as: FZ is (Fb-Fb0) × b/a.
The two propeller dynamic characteristic testing devices are axially and symmetrically arranged, so that synchronous testing of coaxial double-propeller dynamic characteristics can be performed, as shown in fig. 6. Two testing devices are installed on the common base 16, and the coaxial double-propeller power characteristic test of different propeller rotating surface distances can be realized by adjusting the installation positions of the two testing device fixing bases 1 on the common base 16, so that the testing device is used for evaluating the pneumatic coupling influence between the coaxial double propellers.
Those skilled in the art will appreciate that the invention may be practiced without these specific details. The above-described embodiments of the present invention are illustrative of the scheme and are not intended to limit the present invention, and any changes within the meaning and range equivalent to the protection range of the present invention should be considered to be included in the protection range of the present invention.
Claims (2)
1. An axial compact type aircraft propeller dynamic characteristic synchronous testing device is characterized by comprising a fixed base (1), a side support (2), a cylindrical guide shaft (3), a guide shaft support frame (4), a guide shaft slide block (5), a slide block adapter (6), a support plate (7), a rotary flange plate (8), a stop baffle block (9), a propeller motor (10), a force measuring sensor support block (11), a pull pressure and thrust measuring sensor (12), a rod end joint bearing (13), a pull pressure and torque measuring sensor (14) and a torque measuring sensor support block (15); the connection and matching relationship of the components is as follows: the side support (2) is mechanically connected to the fixed base (1), two ends of the cylindrical guide shaft (3) are fixed through a guide shaft support frame (4) arranged on the side support (2), the force measuring sensor support block (11) is mechanically connected with the fixed base (1), and two ends of the tension and pressure measuring and thrust sensor (12) are respectively connected with the force measuring sensor support block (11) and the support plate (7); install guide shaft slider (5) on cylinder guide shaft (3), guide shaft slider (5) have along the axial displacement and the rotational degree of freedom of cylinder guide shaft (3), guide shaft slider (5) pass through slider adapter (6) with backup pad (7) mechanical connection, hole and rotatory ring flange (8) excircle slip or bearing cooperation are gone up in backup pad (7), screw motor (10) mechanical mounting in rotatory ring flange (8), through locking rotatory ring flange (8) and backup pad (7) on axial displacement in stop block piece (9), the axial of rotatory ring flange (8) receives stop block piece (9) restriction, and the screw moment of torsion passes through screw motor (10) transmit rotatory ring flange (8) to through fixing rod end joint bearing (13) on rotatory ring flange (8), applying a torsion force to the tension pressure torsion measuring sensor (14) so as to measure the torque of the propeller; the propeller thrust is transmitted to the rotary flange plate (8) through the propeller motor (10), and the force acts on the tension and pressure force measuring sensor (12) through the supporting plate (7) so as to realize measurement of the propeller thrust.
2. A method for synchronously testing the dynamic characteristics of the propellers of an aircraft by using the device for synchronously testing the dynamic characteristics of the propellers of the axially compact aircraft according to claim 1, characterized in that two devices for synchronously testing the dynamic characteristics of the propellers are axially symmetrically arranged, and the torque of the propellers is obtained according to the value of a tension-pressure torque measuring sensor (14) and the geometric dimension of the rotating flange plate (8); meanwhile, the propeller thrust can be calculated by the values of a tension and pressure measuring thrust sensor (12) at the bottom of the supporting plate (7) and the geometrical parameters of the force arm; the synchronous test of the propeller dynamic characteristics of the coaxial double-propeller aircraft is realized.
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| CN104019968B (en) * | 2014-05-20 | 2016-06-15 | 北京航空航天大学 | A kind of pilot system testing screw blade fatigue property |
| CN104483053B (en) * | 2014-12-25 | 2017-02-08 | 深圳市博尔创意文化发展有限公司 | Torque measuring device of small engine |
| US9829407B2 (en) * | 2015-07-24 | 2017-11-28 | Snap-On Equipment Srl A Unico Socio | Measuring unit and measuring assembly for measuring unbalance forces |
| RU163306U1 (en) * | 2015-11-18 | 2016-07-10 | Федеральное государственное бюджетное образовательное учреждение высшего образования "Приокский государственный университет" (ФГБОУ ВО "ПГУ") | TEST STAND FOR RESEARCH OF ROTARY SYSTEMS |
| CN105547676B (en) * | 2015-12-25 | 2018-01-12 | 北京航空航天大学 | A kind of arm-type rotor model.test system of multifunctional rotary |
| CN106017891B (en) * | 2016-06-29 | 2018-12-28 | 湖南航天机电设备与特种材料研究所 | A kind of propeller dynamic characteristics test device |
| CN205971888U (en) * | 2016-07-07 | 2017-02-22 | 顺丰科技有限公司 | Aircraft driving system testing arrangement |
| CN106516160B (en) * | 2016-12-12 | 2018-11-23 | 哈尔滨理工大学 | A kind of remote-controlled test device of rotor lift parameter |
| CN107117331B (en) * | 2017-05-11 | 2019-06-07 | 安阳全丰航空植保科技股份有限公司 | A kind of device and detection method detecting rotor wing unmanned aerial vehicle aerodynamic characteristic |
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