阅读说明：本技术 一种测量涵道式飞行器舵面升力的装置 (Device for measuring lift force of control surface of ducted aircraft ) 是由 张汝康 于 2020-04-13 设计创作，主要内容包括：本发明涉及一种测量涵道式飞行器舵面升力的装置,该装置包括气流发生机构、舵面测试机构和支撑底座,所述支撑底座平置底面上,所述气流发生机构通过紧固件固定在所述支撑底座上表面；所述舵面测试机构固定在所述气流发生机构的正上方,该装置中的舵面测试机构利用静态扭矩传感器测出舵面对旋转装置产生的转矩,然后通过所测得的转矩除以舵面中心到旋转中心的距离得出舵面升力,本发明解决了现有技术中舵面测量误差高,且无法同时测量不同偏角不同位置下的舵面升力,提高了测量精度,且适用多条件下进行测量,通用性高,为飞行器设计研发提供了理论支撑。(The invention relates to a device for measuring the lift force of a control surface of a ducted aircraft, which comprises an airflow generating mechanism, a control surface testing mechanism and a supporting base, wherein the supporting base is horizontally arranged on the bottom surface, and the airflow generating mechanism is fixed on the upper surface of the supporting base through a fastening piece; the control surface testing mechanism is fixed right above the airflow generating mechanism, the control surface testing mechanism in the device measures torque generated by a control surface to the rotating device by using the static torque sensor, and then the control surface lift force is obtained by dividing the measured torque by the distance from the center of the control surface to the rotating center.)

1. The utility model provides a measure device of duct formula aircraft control surface lift, includes control surface accredited testing organization, its characterized in that: the control surface testing mechanism comprises a control surface deflection mechanism and a control surface rotating mechanism, the control surface deflection mechanism is fixedly connected with the control surface rotating mechanism, the control surface deflection mechanism comprises a control surface, a rotatable component with a supporting function and a steering engine, the windward surface of the control surface is vertical to the horizontal direction, the control surface is provided with a plurality of groups, each group of control surfaces are arranged side by side, the upper end and the lower end of each group of control surfaces are respectively connected and fixed through a fixing block to form a control surface unit, the upper end and the lower end of the control surface unit are respectively connected with a group of rotatable component, and one group of rotatable component is fixedly connected with the steering engine; the control surface rotating mechanism comprises a static torque sensor and a sensor transmission shaft, one end of the static torque sensor is fixedly connected with the control surface deflection mechanism through the sensor transmission shaft, and the axial direction of the sensor transmission shaft is perpendicular to the axial direction of the rotatable component.

2. The apparatus of claim 1, wherein: the control surface testing mechanism further comprises a transverse adjusting mechanism and a vertical adjusting mechanism, wherein the transverse adjusting mechanism is located below the vertical adjusting mechanism and fixedly connected with the vertical adjusting mechanism, and the control surface rotating mechanism is fixedly connected below the transverse adjusting mechanism.

3. The apparatus of claim 2, wherein: the vertical adjusting mechanism adopts a plurality of groups of linear bearings with locks, the linear bearings with locks can be respectively sleeved on the test supporting stand column in a vertically sliding manner, and the heights of the linear bearings with locks are always kept consistent.

4. The apparatus of claim 3, wherein: the lower surface of the transverse adjusting mechanism is provided with a groove-shaped structure, a plurality of groups of strip-shaped holes for fixing are arranged in the groove-shaped structure, and the control surface rotating mechanism is fixedly connected in the groove-shaped structure.

5. The apparatus of claim 4, wherein: rotatable parts in the control surface deflection mechanism are provided with control surface fixing seats in the horizontal direction, the control surface fixing seats are mutually fixed through vertically arranged connecting plates, and a steering engine fixing seat is arranged on one group of control surface fixing seats.

6. The apparatus of claim 5, wherein: the steering engine is fixedly connected with the rotatable part through a first coupler.

7. The apparatus of claim 6, wherein: the static torque sensor is characterized in that sensor fixing seats are vertically arranged at two ends of the static torque sensor respectively, the sensor fixing seats are fixed to each other through a connecting plate horizontally arranged, and the static torque sensor is fixedly connected with the sensor transmission shaft through a second coupler.

8. The apparatus of claim 7, wherein: the rotatable part adopts shaft parts or bearing parts.

9. The apparatus of claim 8, wherein: the device is characterized by further comprising an airflow generation mechanism and a supporting base, wherein the supporting base is horizontally arranged on the ground, the upper part of the supporting base is fixedly connected with the airflow generation mechanism, and the control surface testing mechanism is located above the airflow generation mechanism and fixedly connected with the supporting base.

10. The apparatus of claim 9, wherein: control surface accredited testing organization still includes control surface supporting mechanism, control surface supporting mechanism fixes mechanism top takes place for the air current, and it includes multiunit test support post and top mounting panel, the top mounting panel level sets up control surface supporting mechanism's top, the test support post is located respectively under the corner of top mounting panel, and one end with the corner vertical fixation of top mounting panel, the other end with mechanism fixed connection takes place for the air current.

Technical Field

The invention relates to the technical field of lift measurement, in particular to a device for measuring lift of a control surface of a ducted aircraft.

Background

The ducted aircraft is powered by propellers in a duct, a control surface for controlling the posture of an aircraft body is arranged below the propellers in the ducted aircraft body, and the control surface generates lift force and resistance by airflow flowing through the control surface. In the design of the ducted aircraft, the lift force generated by the control surface is used for controlling the attitude and the flight track of the unmanned aerial vehicle and balancing the reaction torque generated by the propeller, and the lift force measurement of the control surface is particularly important. In order to measure the lift generated by the control surface as a result of the air flow over the control surface, a measuring device is required which is dedicated to the control surface measurement.

Chinese patent document CN106289710B discloses an airfoil model force measuring system, comprising: a pair of brackets which are vertically arranged; a pair of connecting seats, each connecting seat is arranged on each bracket in a mode of sliding along the bracket without friction loss; a resistance measuring balance connected to one of the connecting seats; a resistance and pitching moment measuring balance connected to the other connecting seat; one end of one connecting rod is connected to the resistance measuring balance, one end of the other connecting rod is connected to the resistance and pitching moment measuring balance, and the other end of each connecting rod is connected to the front end of the wing profile model so as to support the wing profile model between the pair of brackets; and the lift force measuring devices are arranged on the brackets, and the lift force transmission component of each lift force measuring device is connected to each connecting seat. The invention adopts a double-support system, the airfoil model is supported between the pair of supports, the system support rigidity is high, the airfoil model has small deformation under the action of self weight and wind load, the device can measure the lift force of the control surface, but the device has large volume and more occupied space, and the measured lift force data is increased by receiving the interference error of the resistance of the control surface.

Chinese patent document CN209085816U discloses a ducted propeller lift force combination measurement test system, which comprises a propeller lift force measurement device and a ducted lift force measurement device; the propeller lift force measuring device comprises a propeller, a torque sensor, a first pressure sensor, a slideway rod and a first fixing plate, and can measure the lift force and the torque generated by the propeller; the duct lift force measuring device comprises an electric push rod, a second pressure sensor, a support rod and a displacement sensor, the height of the duct can be changed, so that the gap between the duct and the propeller is changed, and meanwhile, the duct lift force measuring device can measure the lift force generated by the duct. The utility model discloses control simply, use high-efficient, measure the accuracy, not only be used for measuring the size that the duct screw produced lift, can also measure the change of lift under the different clearance size between screw and the duct simultaneously, the lift of screw is measured to this system measurable quantity many conditions, nevertheless is not suitable for to the control surface measurement.

Disclosure of Invention

Aiming at the problems in the prior art, the invention discloses a device for measuring the lift force of the control surface of a ducted aircraft, which solves the problems that the measurement error of the control surface is high and the lift force of the control surface at different deflection angles and different positions cannot be measured simultaneously in the prior art, improves the measurement precision, is suitable for measurement under multiple conditions and has high universality.

The specific technical scheme disclosed by the invention is as follows: the device for measuring the lift force of the control surface of the ducted aircraft comprises a control surface testing mechanism, wherein the control surface testing mechanism comprises a control surface deflection mechanism and a control surface rotating mechanism, and the control surface deflection mechanism is fixedly connected with the control surface rotating mechanism.

The rudder surface deflection mechanism comprises a rudder surface, rotatable components with a supporting function and a steering engine, wherein the windward surface of the rudder surface is vertical to the horizontal direction, the rudder surface is provided with a plurality of groups, each group of rudder surfaces are arranged side by side, the upper end and the lower end of each group of rudder surface are respectively connected and fixed through a fixing block to form a rudder surface unit, the upper end and the lower end of the rudder surface unit are respectively connected with one group of rotatable components, one group of rotatable components are fixedly connected with the steering engine, and the steering engine controls the rotatable components to rotate to drive the whole rudder surface to deflect;

the control surface rotating mechanism comprises a static torque sensor and a sensor transmission shaft, one end of the static torque sensor is fixedly connected with the control surface deflection mechanism through the sensor transmission shaft, the axial direction of the sensor transmission shaft is vertical to the axial direction of the rotatable component, when airflow passes through the control surface, lift force is generated in the left and right directions of the control surface, the whole control surface deflection mechanism can deflect around the axial direction of the sensor transmission shaft, the torque generated by the control surface deflection mechanism to the sensor transmission shaft can be measured through the static torque sensor fixedly connected with the sensor transmission shaft, and simultaneously, because the airflow generates resistance to the front surface of the control surface and lift force is generated on the left and right sides when the airflow passes through the control surface, when the axial direction of the sensor transmission shaft is vertical to the axial direction of the rotatable component, the resistance generated by the airflow to the control surface can not be transmitted to the static torque, the influence of the resistance on the static torque sensor is avoided.

The control surface testing mechanism further comprises a transverse adjusting mechanism and a vertical adjusting mechanism, the transverse adjusting mechanism is positioned below the vertical adjusting mechanism and is fixedly connected with the vertical adjusting mechanism, and the control surface rotating mechanism is fixedly connected below the transverse adjusting mechanism; the vertical adjusting mechanism preferably adopts a plurality of groups of linear bearings with locks, the linear bearings with locks can be respectively sleeved on the test supporting stand columns in a vertically sliding manner, and the heights of the linear bearings with locks are always kept consistent; the lower surface of the transverse adjusting mechanism is provided with a groove-shaped structure, a plurality of groups of strip-shaped holes for fixing are arranged in the groove-shaped structure, and the control surface rotating mechanism is fixedly connected in the groove-shaped structure. Because the lower side of the propeller in the ducted unmanned aerial vehicle is provided with a plurality of groups of control surfaces for controlling the attitude and the flight track of the aircraft, the lift force of the propeller axis and the control surface structure at different distances in the ducted unmanned aerial vehicle can be simulated and measured by adjusting the height of the vertical adjusting mechanism and adjusting the distance between the whole center of the control surface and the axis of the propeller in the airflow generating mechanism. Meanwhile, by adjusting the transverse adjusting mechanism to simulate different distances between the control plane and the propeller rotation plane, lift force data of the propeller plane and the control plane at different distances can be measured, so that the optimal distance is found out, and data support is provided for research and development of the aircraft.

Furthermore, rotatable part horizontal direction in the rudder surface deflection mechanism is equipped with the rudder surface fixing base, the connecting plate reciprocal anchorage of rudder surface fixing base through vertical setting, be equipped with the steering wheel fixing base on one of them set of rudder surface fixing base, this structure can provide the support for rudder surface and steering wheel structure, reduces the rudder surface and rocks the impact that produces the steering wheel, extension measuring mechanism's life.

Furthermore, the steering engine is fixedly connected with the rotatable component through a first coupler, the coupler can compensate offset (including axial offset, radial offset, angular offset or comprehensive offset) between the two shafts due to manufacturing and installation inaccuracy, deformation or thermal expansion in working and the like, and torque is accurately transmitted, so that the steering engine accurately controls the deflection angle of the control surface.

Further, static torque sensor both ends are equipped with the sensor fixing base along vertical respectively, the sensor fixing base passes through the connecting plate reciprocal anchorage that the level set up, static torque sensor with the sensor transmission shaft passes through second coupling fixed connection, and this structure supports sensor transmission shaft and static torque sensor's position fixedly, has avoided the sensor transmission shaft to produce radial moment of torsion to static torque sensor, the damage sensor.

The device is characterized by further comprising an airflow generation mechanism and a supporting base, wherein the supporting base is horizontally arranged on the ground, the upper part of the supporting base is fixedly connected with the airflow generation mechanism, and the control surface testing mechanism is located above the airflow generation mechanism and fixedly connected with the supporting base.

Further, rudder surface accredited testing organization still includes rudder surface supporting mechanism, rudder surface supporting mechanism fixes mechanism top takes place for the air current, and it includes multiunit test support post and top mounting panel, the top mounting panel level sets up rudder surface supporting mechanism's top, the test support post is located respectively under the corner of top mounting panel, and one end with the corner vertical fixation of top mounting panel, the other end with mechanism fixed connection takes place for the air current.

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

1) the steering engine can control the deflection angle of the control surface, so that lift force data of the control surface under different deflection angles can be obtained, and theoretical data are provided for attitude control of the aircraft.

2) The invention can adjust the distance from the center of the control surface to the center of the rotating shaft through the vertical adjusting mechanism and adjust the distance from the control surface to the rotating plane of the propeller through the transverse adjusting mechanism, thereby providing important data for the design of the single duct type unmanned aerial vehicle.

3) According to the whole testing device, the influence of the resistance and vibration of the control surface on the torque sensor is reduced through the structural design between the control surface and the sensor and the offset compensation effect of the coupler, and the measurement accuracy is further improved.

4) The invention can be compatible with control surfaces of various different airfoil shapes and control surfaces of various different sizes, and the control surfaces can be measured a plurality of times, thereby having stronger applicability.

Drawings

FIG. 1 is a block diagram of a device for measuring lift of a control surface of a ducted aircraft according to an embodiment of the present invention;

FIG. 2 is a block diagram of an airflow generating mechanism in an embodiment of the invention;

FIG. 3 is a block diagram of a control surface test mechanism according to an embodiment of the invention;

FIG. 4 is a side view structural diagram of a control surface deflection mechanism and a control surface rotation mechanism in the embodiment of the invention;

fig. 5 is a perspective structural view of a control surface deflecting mechanism and a control surface rotating mechanism in the embodiment of the invention;

the specific meanings of the reference numbers in the drawings are:

1-airflow generation mechanism, 101-propeller, 102-engine, 103-side mounting plate, 104-mounting plate, 105-first base plate, 106-engine support column, 107-second base plate, 2-control surface testing mechanism, 201-control surface deflection mechanism, 20111-control surface, 20112-control surface rotating shaft, 20113-control surface bearing seat, 20114-bearing seat mounting plate, 20115-connecting plate, 20116-first coupler, 20117-small rotating shaft, 20118-rudder horn, 20119-steering engine, 20120-steering engine mounting plate, 20121-total rotating shaft connecting plate, 202-control surface rotating mechanism, 20211-sensor transmission shaft, 20212-large shaft bearing seat, 20213-top plate, 20214-second coupler, 20215-static torque sensor, 20216-sensor connecting plate, 203-a transverse adjusting mechanism, 204-a vertical adjusting mechanism, 205-a control surface supporting mechanism, 20511-a test supporting upright post, 20512-a top mounting plate and a 3-a supporting base.

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.