阅读说明：本技术 一种飞行器动力系统转矩和升力的测量装置 (Measuring device for torque and lift of aircraft power system ) 是由 张汝康 于 2020-04-21 设计创作，主要内容包括：本发明涉及是一种飞行器动力系统转矩和升力的测量装置,包括支撑底座、测试支撑机构、发动机动力机构和发动机测试机构,所述支撑底座水平放置,其上固定连接所述测试支撑机构,所述发动机动力机构和发动机测试机构均固定在所述测试支撑机构上,其中测试支撑机构设有上下分层结构,避免了发动机对传感器的振动影响,且发动机动力机构中采用两组支撑机构,使得发动机重心在两支撑机构之间,避免了悬臂结构,本发明解决了现有技术的测量过程中转矩和升力测量结果的误差较大的问题,提升了测量精度,避免了测试过程中发动机对测量结果的影响。(The invention relates to a device for measuring torque and lift force of an aircraft power system, which comprises a supporting base, a testing supporting mechanism, an engine power mechanism and an engine testing mechanism, wherein the supporting base is horizontally arranged and fixedly connected with the testing supporting mechanism, and the engine power mechanism and the engine testing mechanism are both fixed on the testing supporting mechanism, wherein the testing supporting mechanism is provided with an upper layered structure and a lower layered structure, so that the vibration influence of an engine on a sensor is avoided.)

1. An aircraft power system torque and lift measuring device comprises an engine testing mechanism and a testing support mechanism, and is characterized in that:

the test support mechanism comprises an engine support seat and a sensor support seat, the engine support seat and the sensor support seat are arranged in a layered mode, the engine support seat is located on the upper layer, an engine fixing seat used for fixing an engine is arranged above the engine support seat, and the engine support seat is in rolling connection with the engine fixing seat;

the engine testing mechanism comprises a torque testing mechanism and a lift force testing mechanism, the torque testing mechanism comprises a pressure block and a rotary pressure sensor, the pressure block is positioned below the engine and fixedly connected with the engine, the rotary pressure sensor is fixedly connected with the sensor fixing seat, and the pressure block is in rolling connection with the rotary pressure sensor; the lift force testing mechanism comprises two groups of pressure sensors which are oppositely arranged at the tail part of the engine fixing seat and are respectively and fixedly connected with the sensor supporting seat.

2. An aircraft power system torque and lift measurement device as defined in claim 1, wherein: the engine fixing seat is provided with a plurality of groups of supporting seats, the supporting seats are provided with shaft holes with coincident axes, the engine is rotatably fixed in the shaft holes, and the engine and the shaft holes are coaxial.

3. An aircraft power system torque and lift measurement device as defined in claim 2, wherein: the engine with all be provided with rotatable part and engine mounting panel between the supporting seat, the engine mounting panel is fixed correspond the position of corresponding supporting seat on the engine, rotatable part is fixed in the clearance of engine mounting panel and corresponding supporting seat.

4. An aircraft power system torque and lift measurement device as defined in claim 3, wherein: an engine mounting plate positioned at the head of the engine is provided with a vertical flange extending downwards, and the surface of the vertical flange is fixedly connected with the pressure block; and a cam follower is arranged between the pressure block and the rotary pressure sensor, and the cam follower is fixed on the pressure block and clings to the surface of the rotary pressure sensor.

5. An aircraft power system torque and lift measurement device as defined in claim 4, wherein: the engine mounting plate positioned in the middle and at the tail of the engine comprises an upper mounting plate and a lower mounting plate of the engine body, wherein the upper mounting plate of the engine body and the lower mounting plate of the engine body clamp and fix the engine through fastening bolts.

6. An aircraft power system torque and lift measurement device as defined in claim 5, wherein: a horizontal flange extends out of the middle of the engine fixing seat, two groups of limiting blocks for limiting displacement of the engine unit are arranged on the engine supporting seat and located on two sides of the horizontal flange, and the engine unit is fixed on the surface of the engine supporting seat through fastening bolts.

7. An aircraft power system torque and lift measurement device as defined in claim 6, wherein: the test supporting mechanism further comprises a base, an engine supporting stand column and a sensor supporting stand column, wherein the engine supporting stand column and the sensor supporting stand column are vertically fixed on the surface of the base, the engine supporting stand column is vertically connected with the engine supporting seat, and the sensor supporting stand column is vertically connected with the sensor supporting seat.

8. An aircraft power system torque and lift measurement device as defined in claim 7, wherein: the lower surface of the engine fixing seat is connected with the upper surface of the engine supporting seat through a rolling linear guide rail.

9. An aircraft power system torque and lift measurement device as defined in claim 8, wherein: the tail of the engine fixing seat is provided with a square hole, a narrow edge is arranged on the square hole, and the narrow edge is located between the two groups of pressure sensors.

10. An aircraft power system torque and lift measurement device as defined in claim 9, wherein: the rotatable part is a bearing part.

Technical Field

The invention relates to the technical field of measurement, in particular to a device for measuring torque and lift of an aircraft power system.

Background

In recent years, with the rapid development of civil unmanned aerial vehicles, aircraft power systems are applied more and more, but the methods for testing the torque and the lift force of an engine are not many, and the testing effect is not good. In the conventional technology, a rotating shaft is additionally arranged at the tail part of an engine, then the rotating shaft is arranged in a linear bearing seat, the rotating shaft can rotate and axially move, and due to the cantilever structure, a large moment can be generated at the position of the linear bearing, so that the friction force is large, and the errors of the measured torque and the lift force are large. When this conventional technique is applied to an engine having a long length, a large moment is generated due to the long installation position from the tail.

Chinese patent document CN104483053B discloses a small engine torque measuring device, belonging to the technical field of engine performance tests. The device comprises a propeller, an engine to be tested, a connecting screw rod, a double-arm steel plate, a supporting bearing, a supporting polished rod, a pressure sensor, a main supporting plate, a rack with a sliding guide rail, a pressure plate, a steering engine and a tension meter; the propeller, the engine to be tested, the connecting screw rod, the double-arm steel plate and the support polished rod form a cantilever system, the support bearing, the main support plate and the rack with the sliding guide rail form the support system, and the cantilever system can freely rotate around the axis of the support polished rod. The device can accurately measure the torque characteristic of the low-power model airplane engine which cannot be accurately measured by a common torque measuring instrument, and can measure the thrust of the engine, but the device adopts a cantilever structure, and a linear bearing is subjected to a large moment, so that the friction force is increased, and the errors of the measured torque and the lift force are increased.

Chinese patent document CN106828971B discloses an experimental device for measuring lift force of a single duct and a single duct aircraft, which mainly comprises a duct experimental prototype, an experimental vehicle base, a guide pillar chute, a plurality of guide pillars, a screw perforation, a fixed sleeve, a tension measurer and a mooring cable. The method is characterized in that: the duct experimental prototype is of a single duct type and is arranged on a base of the test vehicle; the base of the test vehicle is triangular, and guide posts and sliding grooves are formed in three beams of the base of the test vehicle; the three guide posts are respectively arranged on three guide post sliding grooves of the test vehicle base; each guide post is provided with a screw through hole at a certain distance; the fixing sleeve is sleeved on each guide post, and the fixing sleeve is fixed by the screw through hole; a tension measurer is arranged between the fixed sleeve and the duct experimental prototype; the mooring cable is connected to the ducted experimental prototype. The device has a simple structure, can improve the test efficiency and reduce the test cost, but has larger shaking and larger measurement error in the test process, and the device can not measure the torque of the engine.

Disclosure of Invention

Aiming at the problems in the prior art, the invention discloses a device for measuring the torque and the lift force of an aircraft power system, which solves the problem of large error of the torque and the lift force measurement result in the measurement process in the prior art, avoids the measurement error increased by the vibration of an engine in the test process, and improves the measurement precision.

The specific technical scheme disclosed by the invention is as follows: the measuring device for the torque and the lift of the aircraft power system comprises an engine testing mechanism and a testing supporting mechanism.

The test supporting mechanism comprises an engine supporting seat and a sensor supporting seat, the engine supporting seat is arranged in a layered mode with the sensor supporting seat, the engine supporting seat is located on the upper layer, an engine fixing seat used for fixing an engine is arranged above the engine supporting seat, the engine supporting seat is connected with the engine fixing seat in a rolling mode, and a sliding connection mode with small friction force can be adopted.

The pressure block is a T-shaped structure and is a component for transmitting the torque of the engine to the rotary pressure sensor so as to measure the torque of the engine.

The engine testing mechanism comprises a torque testing mechanism and a lift force testing mechanism, the torque testing mechanism comprises a pressure block and a rotary pressure sensor, the pressure block is positioned below the engine and fixedly connected with the engine, the rotary pressure sensor is fixedly connected with the sensor fixing seat, and the pressure block is in rolling connection with the rotary pressure sensor; the lift force testing mechanism comprises two groups of pressure sensors which are oppositely arranged at the tail part of the engine fixing seat and are respectively and fixedly connected with the sensor supporting seat.

Because the engine produces vibration in the operation process, can cause the sensor measurement in-process reading unstable, damage sensor inner structure even, make the sensor life-span reduce, consequently through adopting double-deck fixed knot structure in this device, it is fixed with the engine and sensor layering, avoid engine vibration to cause the influence to the sensor, improve measurement accuracy, prolong sensor life simultaneously. Meanwhile, the torque and the lift force generated by the engine can be respectively measured by a rotary pressure sensor and a pressure sensor arranged in the device.

Furthermore, be equipped with the multiunit supporting seat on the engine fixing base, be provided with the shaft hole of axis coincidence on the supporting seat, the engine is rotatable to be fixed in the shaft hole, and the engine with the shaft hole is coaxial.

Furthermore, the engine with all be provided with rotatable part and engine mounting panel between the supporting seat, the engine mounting panel is fixed the position of corresponding supporting seat on the engine, rotatable part preferably adopts the bearing part, fixes in the clearance of engine mounting panel and corresponding supporting seat.

The engine fixing seat has the advantages that the multiple groups of supporting seats are adopted in the structure, the whole body of the engine is fixed on the engine fixing seat, the suspension of the engine is avoided, the phenomenon that the engine falls down due to the gravity of the engine is avoided, the moment is generated on the fixing device, the moment generated on sensors around the engine is also avoided, the friction force is increased, and the torque or pressure measurement is not accurate.

The torque measurement principle in the structure is as follows: when a propeller in an engine moves, reaction torque can be generated on a body of the engine, so that the engine tends to rotate, but due to the limitation of a rotating pressure sensor, the rotating tendency of the engine is converted into the pressure action of a pressure block fixed on the engine on the rotating pressure sensor, so that the pressure data of the pressure block is measured, meanwhile, the distance between the rotating axis of the engine and the rotating pressure sensor is fixed and can be directly measured, and therefore, the torque of the engine can be obtained by multiplying the pressure data measured by the rotating pressure sensor by the distance between the rotating axis of the engine and the rotating pressure sensor.

The lift force measuring principle in the structure is as follows: the engine fixing seat for fixing the engine is fixed with the engine supporting seat in a sliding mode, when the propeller on the engine runs to generate lift force, the engine fixing seat can be driven to move forwards, the tail of the engine fixing seat generates pressure action on a group of pressure sensors arranged at the tail, and a group of lift force data, namely the lift force of the engine, is measured.

Furthermore, an engine mounting plate positioned at the head of the engine is provided with a vertical flange extending downwards, and the surface of the vertical flange is fixedly connected with the pressure block; the cam follower is arranged between the pressure block and the rotary pressure sensor, the cam follower is fixed on the pressure block and is tightly attached to the surface of the rotary pressure sensor, and the friction of the cam follower in the rolling process of the surface of the rotary pressure sensor is extremely small, so that the measurement error of the tail pressure sensor is further reduced, and the measurement precision is improved.

Furthermore, the engine mounting plate that is located middle part and afterbody on the engine includes mounting panel and fuselage down mounting panel on the fuselage, mounting panel on the fuselage with mounting panel presss from both sides tight fixed engine through fastening bolt under the fuselage.

Furthermore, a horizontal flange extends out of the middle position of the engine fixing seat, two groups of limiting blocks for limiting displacement of the engine unit are arranged on the engine supporting seat and located on two sides of the horizontal flange, the limiting blocks are fixed on the surface of the engine supporting seat through fastening bolts, and the structure is a safety limiting device and prevents the engine from sliding out and falling after the bolts are loosened.

Furthermore, test supporting mechanism still includes base, engine support post and sensor support post, engine support post with the equal vertical fixation of sensor support post is on the base surface, engine support post connects perpendicularly the engine supporting seat, sensor support post connects perpendicularly the sensor supporting seat adopts the double-column structure in the device, the at utmost has reduced the influence that engine vibration caused to the sensor.

Further, the lower surface of the engine fixing seat is connected with the upper surface of the engine supporting seat through a rolling linear guide rail, and the linear guide rail also adopts other linear guide rails with small friction force.

Further, the afterbody of engine fixing base is equipped with the quad slit, be equipped with the narrow limit on the quad slit, the narrow limit is located between two sets of pressure sensor, and wherein the two sets of pressure sensor of installation is because will test different screws, and some screws are positive oar, and some are anti-oar, and the direction of the direction that positive oar and anti-oar produced is different. The lift force of the engine can be calculated by directly reading a group of pressure data through the pressure generated by the narrow-edge structure to one group of pressure sensors.

Compared with the prior art, the invention has the following advantages:

1) the engine is fixed on the engine body through the plurality of groups of supporting seats, so that the center of gravity of the engine is positioned between the supporting seats, the moment and the additional friction force brought by a cantilever structure are avoided, the damage to the fixing device and the sensor is also avoided, the measurement error is reduced, the accuracy of measured data is improved, and the service life of the device is prolonged.

2) According to the invention, the sensor and the engine are separated independently, and the engine and the sensor are respectively installed by adopting an upper and lower layered structure, so that the influence of the vibration of the engine on the sensor is avoided, and the measurement precision is further improved.

3) According to the invention, the rotatable part is arranged between the engine and the supporting seat, so that the direct contact between the engine and the supporting seat is avoided to generate friction force, and the torque measurement precision is reduced.

4) The whole mechanism for measuring the torque is arranged on the linear guide rail, so that the engine keeps a rotating trend, and meanwhile, the whole mechanism for measuring the torque has a trend of moving along the direction of the linear guide rail, so that the torque and the tension can be measured simultaneously, and the practicability of the device is enhanced.

5) The single linear guide rail is adopted, so that the problem of large friction resistance caused by non-parallel two guide rails and non-uniform installation height when the two guide rails are installed is solved, and the lift force measurement precision of the engine is further improved.

Drawings

FIG. 1 is a perspective view of an aircraft power system torque and lift measurement device in accordance with an embodiment of the present invention;

FIG. 2 is a side view block diagram of an aircraft power system torque and lift measurement device in an embodiment of the present invention;

FIG. 3 is a cross-sectional view taken along the line A in FIG. 2;

FIG. 4 is a partial view of portion B of FIG. 3;

FIG. 5 is a side cross-sectional view of an aircraft powertrain torque and lift measurement arrangement in an embodiment of the present invention;

FIG. 6 is a partial view of portion C of FIG. 5

FIG. 7 is a block diagram of an engine mounting plate in an embodiment of the present invention;

1-supporting base, 2-testing supporting mechanism, 201-base, 202-engine supporting column, 203-sensor supporting column, 204-engine supporting base, 20411-limiting block, 205-sensor supporting base, 3-engine power mechanism, 301-propeller, 302-first supporting base, 303-engine mounting plate, 304-engine, 305-second supporting base, 306-upper body mounting plate, 307-lower body mounting plate, 308-engine fixing base, 309-first bearing, 310-second bearing, 4-engine testing mechanism, 401-pressure sensor mounting plate, 402-pressure sensor, 403-pressure block, 404-rotating pressure sensor mounting plate, 405-rotating pressure sensor, 406-cam follower, 5-linear guide.

Detailed Description

The preferred embodiments of the present invention will be described below with reference to the accompanying drawings, and it should be understood that the embodiments described herein are merely for the purpose of illustrating and explaining the present invention and are not intended to limit the present invention.