Aircraft lift force test platform

Abstract

The utility model discloses an aircraft lift force test platform which comprises a workbench and a tension sensor, the workbench is fixedly connected with an arc-shaped seat, the arc-shaped seat is provided with a convex groove, the convex groove is internally provided with a convex seat in a sliding manner, the convex seat is fixedly connected with a mounting seat, and the tension sensor is mounted on the mounting seat. The tension sensor is connected with a flexible rope, the other end of the flexible rope is fixedly connected with a mounting plate used for mounting an aircraft, the convex seat is in threaded connection with a fixing screw, the arc seat is provided with an arc groove communicated with the convex groove, the fixing screw is located in the arc groove, and the side end of the arc seat is provided with angle scale marks. An arc-shaped plate is fixedly connected to the side end of the arc-shaped seat, and a plurality of reference lines are arranged at the side end of the arc-shaped plate, so that the lift force of the aircraft at different inclination angles can be conveniently detected, lift force data of the aircraft under various conditions can be conveniently detected, and the accuracy of lift force detection of the aircraft can be ensured.

Description

TECHNICAL FIELD

[0001] The utility model relates to unmanned aerial vehicle performance detection technical field more specifically, it relates to a kind of aircraft lift test platform. BACKGROUND

[0002] Human flight dream and its inspiration source from animal free flight, flapping wing aircraft is one of the ways to realize human flight dream, flapping wing aerodynamics research is an important content of flapping wing aircraft research. Establish the mapping relationship of flight structure parameters, aerodynamic parameters and power parameters, carry out joint optimization of design parameter space, it is an important direction of flapping wing aircraft flapping wing lift research, and it is the basis of aircraft light weight and high efficiency research, when the lift of aircraft is tested, it is usually tested on corresponding test platform.

[0003] Through searching, the utility model discloses a kind of flapping wing aircraft lift and thrust test platform, including workbench, tension sensor, tension sensor installation pillar, flexible rope and test frame;Tension sensor installation pillar and test frame are installed on workbench;Tension sensor includes first tension sensor and second tension sensor, and is connected with test frame by flexible rope;Test frame includes vertical pillar, crossbeam, first sliding assembly, tension spring, second sliding assembly, angle adjusting assembly and clamping piece;Vertical pillar and crossbeam are connected by first sliding assembly and tension spring together;Crossbeam center is fixed with second sliding assembly, and crossbeam is connected with angle adjusting assembly by second sliding assembly;Angle adjusting assembly is connected with clamping piece, and flapping wing aircraft is fixed by clamping piece.

[0004] When using, flexible rope is pulled by aircraft, and the tension of flexible rope is detected by tension sensor, so as to detect the lift of aircraft, it can detect the lift of aircraft in vertical direction, it is inconvenient to check the lift of aircraft in inclined direction, and the data of aircraft lift detection is less, which affects the accuracy of aircraft lift detection. UTILITY MODEL CONTENT

[0005] (1) technical problem solved

[0006] In view of the problems existing in the prior art, the utility model provides a kind of aircraft lift test platform to solve the technical problems that inconvenient to check the lift of aircraft in inclined direction, and the data of aircraft lift detection is less, which affects the accuracy of aircraft lift detection mentioned in background art.

[0007] (2) technical scheme

[0008] In order to achieve the above object, the utility model provides the following technical scheme: a kind of aircraft lift testing platform, including workbench and tension sensor, the workbench is fixedly connected with arc seat, arc seat is provided with convex groove, the inside of convex groove is slidably provided with convex seat, the fixedly connected with mounting seat of convex seat, the tension sensor is installed on mounting seat, tension sensor is connected with flexible rope, the other end of flexible rope is fixedly connected with mounting plate for installing aircraft, the fixed screw is threadedly connected on the convex seat, arc seat is provided with arc slot in communication with convex groove, fixed screw is located in the inside of arc slot, the side end of arc seat is provided with angle scale, the side end of arc seat is fixedly connected with arc plate, the side end of arc plate is provided with multiple reference lines, it is convenient to detect the lift of different inclination angles of aircraft, it is convenient to detect the lift data of aircraft under multiple conditions, the accuracy of aircraft lift detection can be guaranteed.

[0009] The utility model further sets up, the top of workbench is fixedly connected with L type seat, L type seat is provided with slot, the mounting plate is placed on L type seat, the flexible rope is located in the inside of slot, it is convenient to place mounting plate, it is convenient to dismount and assemble aircraft.

[0010] The utility model further sets up, the bottom of mounting plate is provided with two installation grooves, and the position corresponding to installation groove is screw connected with fixed screw on mounting plate, and the side end of fixed screw extends to the inside of installation groove, so that counterweight is installed and fixed.

[0011] The utility model further sets up, the side end of fixed screw is fixedly connected with first handle, so as to rotate fixed screw.

[0012] The utility model further sets up, the top of mounting plate is fixedly connected with two fixed plates, and the first screw rod is screw connected in two fixed plates, and the side end of first screw rod is fixedly connected with clamping plate, and the bottom of clamping plate is slidably connected with the top of mounting plate, so as to clamp and fix different models of aircraft.

[0013] The utility model further sets up, the side end of first screw rod is fixedly connected with second handle, so as to rotate first screw rod by second handle.

[0014] The utility model further sets up, two slide rods are fixedly connected on clamping plate, and the slide rod is slidably connected with corresponding fixed plate, so as to improve the stability of clamping plate.

[0015] The utility model further sets up, support seat is connected between arc seat and workbench, so as to improve the stability of arc seat and workbench connection.

[0016] (Three) beneficial effects

[0017] Compared with the prior art, the aircraft lift test platform has the following beneficial effects:

[0018] 1、When the lift of the aircraft at different inclination angles needs to be detected, the convex seat slides in the convex groove, the convex seat is adjusted to the corresponding position through the angle scale line, then the convex seat is fixed by screwing the fixing screw, then the aircraft flies obliquely, the flexible rope pulls the tension sensor, the flexible rope and the reference line perpendicular to the tension sensor are leveled, the lift of the aircraft in the direction of inclination is judged through the data detected by the tension sensor, so that the lift of the aircraft at different inclination angles is conveniently detected, the lift data of the aircraft under various conditions is conveniently detected, and the accuracy of the aircraft lift detection can be ensured.

[0019] 2、By setting the fixing plate, the first screw rod and the clamping plate and the like structure, the positions of the two clamping plates are adjusted, the aircraft on the mounting plate is clamped and fixed by adjusting the spacing between the two clamping plates, so that the aircraft of different sizes and models can be clamped and fixed.

[0020] 3、By setting the mounting groove at the bottom end of the mounting plate, the two counterweights are conveniently placed in the two mounting grooves, the fixed screw rod is made to abut against the side end of the counterweight by screwing the fixing screw rod, the counterweight is fixed, the counterweight of the aircraft is increased through the counterweight, so that the lift of the aircraft under the counterweight condition is conveniently detected. DETAILED DESCRIPTION

[0021] Figure 1 It is a front structure schematic view of the aircraft lift test platform in the utility model;

[0022] Figure 2 It is a structure schematic view of the cooperation of the arc-shaped seat, the convex seat, the mounting seat and the tension sensor and the like structure in the utility model;

[0023] Figure 3 It is a structure schematic view of the connection of the mounting plate, the fixed screw rod and the first handle in the utility model;

[0024] Figure 4 It is a structure schematic view of the connection of the mounting plate, the two fixing plates and the two clamping plates and the like structure in the utility model;

[0025] Figure 5 It is a structure schematic view of the connection of the arc-shaped seat and the supporting seat in the utility model.

[0026] In the figure: 1, workbench; 2, tension sensor; 3, arc seat; 4, convex groove; 5, convex seat; 6, mounting seat; 7, flexible rope; 8, mounting plate; 9, fixing screw; 10, arc groove; 11, angle scale; 12, arc plate; 13, reference line; 14, L-shaped seat; 15, missing groove; 16, mounting groove; 17, fixing screw rod; 18, first rotating handle; 19, fixing plate; 20, first screw rod; 21, clamping plate; 22, second rotating handle; 23, sliding rod; 24, support seat. DETAILED DESCRIPTION

[0027] It should be noted that the embodiments in the present application and the features in the embodiments can be combined with each other without conflict. The present application will be described in detail below with reference to the drawings and in combination with the embodiments.

[0028] It should be noted that, unless otherwise specified, all technical and scientific terms used in the present application have the same meaning as generally understood by those skilled in the art to which the present application belongs.

[0029] In the present application, unless otherwise specified, the directions used such as "up, down" are generally with respect to the directions shown in the drawings, or with respect to the vertical, perpendicular or gravity directions; similarly, for the convenience of understanding and description, "left, right" are generally with respect to the left and right shown in the drawings; "inner, outer" refer to the inner and outer with respect to the contour of each component itself, but the above directional words are not used to limit the present application.

[0030] Please refer to Figures 1-5 A kind of aircraft lift test platform, including workbench 1 and tension sensor 2, workbench 1 is fixedly connected with arc seat 3, arc seat 3 is connected with support seat 24 between workbench 1, improve the stability of arc seat 3 with workbench 1 connection, arc seat 3 is provided with convex groove 4, convex groove 4 is slidably arranged with convex seat 5 in the inside, convex seat 5 is fixedly connected with mounting seat 6, tension sensor 2 is installed on mounting seat 6, tension sensor 2 is connected with flexible rope 7, the other end of flexible rope 7 is fixedly connected with mounting plate 8 for installing aircraft, convex seat 5 is threadedly connected with fixing screw 9, arc seat 3 is provided with arc groove 10 that communicates with convex groove 4, fixing screw 9 is located in the inside of arc groove 10, the side end of arc seat 3 is provided with angle scale 11, the side end of arc seat 3 is fixedly connected with arc plate 12, the side end of arc plate 12 is provided with multiple reference lines 13, the top of workbench 1 is fixedly connected with L-shaped seat 14, L-shaped seat 14 is provided with missing groove 15, mounting plate 8 is placed on L-shaped seat 14, flexible rope is located in the inside of missing groove 15, it is convenient to place mounting plate 8, it is convenient to disassemble and assemble aircraft.

[0031] Specifically, when the lift of the aircraft at different inclination angles needs to be detected, the convex seat 5 is slid in the convex groove 4, and the convex seat 5 is adjusted to the corresponding position through the angle scale line 11, then the convex seat 5 is fixed by screwing the fixing screw 9, then the aircraft is flown obliquely, the aircraft drives the mounting plate 8 and the flexible rope 7 to fly, the flexible rope 7 pulls the tension sensor 2, and the flexible rope 7 is leveled with the reference line 13 perpendicular to the tension sensor 2, the lift of the aircraft in the inclination direction is judged through the data detected by the tension sensor 2, so that the lift of the aircraft at different inclination angles is conveniently detected, the lift data of the aircraft in multiple situations is conveniently detected, and the accuracy of the aircraft lift detection can be ensured.

[0032] Please refer to Figure 3 The bottom end of the mounting plate 8 is symmetrically provided with two mounting grooves 16, and the mounting plate 8 is threadedly connected with a fixed screw rod 17 at a position corresponding to the mounting grooves 16, the side end of the fixed screw rod 17 extends into the mounting groove 16, and the side end of the fixed screw rod 17 is fixedly connected with a first handle 18, so as to conveniently rotate the fixed screw rod 17.

[0033] Specifically, when the lift of the aircraft needs to be detected when carrying a load, two counterweights of a corresponding weight are respectively placed in the two mounting grooves 16, and then the fixed screw rod 17 is screwed to abut the side end of the counterweight, so as to fix the counterweight, and the lift is detected by flying the aircraft with the counterweight, so that the lift of the aircraft flying in the load state is conveniently detected.

[0034] Please refer to Figure 1 and Figure 4 The top end of the mounting plate 8 is fixedly connected with two fixed plates 19, the two fixed plates 19 are threadedly connected with a first screw rod 20, the side end of the first screw rod 20 is fixedly connected with a clamping plate 21, the bottom end of the clamping plate 21 is in sliding fit with the top end of the mounting plate 8, the side end of the first screw rod 20 is fixedly connected with a second handle 22, the first screw rod 20 is conveniently rotated through the second handle 22, two slide rods 23 are fixedly connected to the clamping plate 21, and the two slide rods 23 are in sliding fit with the corresponding fixed plates 19, so as to improve the stability of the clamping plate 21.

[0035] Specifically, the aircraft is placed on the mounting plate 8, and then the first screw rod 20 is rotated clockwise, the first screw rod 20 drives the clamping plate 21 to move, the aircraft is clamped and fixed by the two clamping plates 21, and the interval between the two clamping plates 21 is adjusted, so as to conveniently clamp and fix the aircraft of different sizes and models.

[0036] In summary, when the overall device is used:

[0037] The aircraft is placed on the mounting plate 8, and then the first screw rod 20 is turned clockwise, the first screw rod 20 drives the clamping plate 21 to move, and the aircraft is clamped and fixed by the two clamping plates 21; when the lift of the aircraft at different inclination angles needs to be detected, the convex seat 5 is slid in the convex groove 4, and the convex seat 5 is adjusted to the corresponding position through the angle scale line 11, then the fixing screw 9 is screwed to fix the convex seat 5, then the aircraft is flown obliquely, the aircraft drives the mounting plate 8 and the flexible rope 7 to fly, the flexible rope 7 pulls the tension sensor 2, and the flexible rope 7 is leveled with the reference line 13 perpendicular to the tension sensor 2, the lift of the oblique flight of the aircraft is detected through the data detected by the tension sensor 2;

[0038] When the lift of the aircraft under load needs to be detected, the two counterweights of the corresponding weight are respectively placed in the two mounting grooves 16, then the fixed screw rod 17 is screwed, the side end of the fixed screw rod 17 is tightly abutted with the side end of the counterweight, the counterweight is fixed, the lift is detected by flying the aircraft with the counterweight, so that the lift of the aircraft flying under load is detected.

[0039] In all the schemes mentioned above, the connection between the two components can be selected according to the actual situation, such as welding, bolt and nut cooperation connection, bolt or screw connection or other known connection mode, which is not described one by one, whenever the fixed connection is mentioned in the above, the welding is preferred, although the embodiments of the utility model have been shown and described, for those skilled in the art, it can be understood that the embodiments can be changed, modified, replaced and modified in various ways without departing from the principles and spirits of the utility model, the scope of the utility model is defined by the appended claims and their equivalents.

Claims

1. An aircraft lift test platform comprising a workbench (1) and a tension sensor (2), characterized in that: The workbench (1) is fixedly connected with an arc-shaped seat (3), the arc-shaped seat (3) is provided with a convex groove (4), the convex groove (4) is slidably provided with a convex seat (5), the convex seat (5) is fixedly connected with a mounting seat (6), the tensile sensor (2) is mounted on the mounting seat (6), the tensile sensor (2) is connected with a flexible rope (7), the other end of the flexible rope (7) is fixedly connected with a mounting plate (8) for mounting an aircraft, the convex seat (5) is threadedly connected with a fixing screw (9), the arc-shaped seat (3) is provided with an arc-shaped groove (10) in communication with the convex groove (4), the fixing screw (9) is located in the arc-shaped groove (10), the side end of the arc-shaped seat (3) is provided with an angle scale line (11), the side end of the arc-shaped seat (3) is fixedly connected with an arc-shaped plate (12), the side end of the arc-shaped plate (12) is provided with a plurality of reference lines (13).

2. The aircraft lift testing platform of claim 1, wherein: The top end of the workbench (1) is fixedly connected with an L-shaped seat (14), the L-shaped seat (14) is provided with a missing groove (15), the mounting plate (8) is placed on the L-shaped seat (14), and the flexible rope (7) is located in the missing groove (15).

3. The aircraft lift testing platform of claim 1, wherein: The bottom end of the mounting plate (8) is symmetrically provided with two mounting grooves (16), the mounting plate (8) is threadedly connected with a fixed screw rod (17) at a position corresponding to the mounting groove (16), and the side end of the fixed screw rod (17) extends into the mounting groove (16).

4. The aircraft lift testing platform of claim 3, wherein: The side end of the fixed screw rod (17) is fixedly connected with a first handle (18).

5. The aircraft lift testing platform of claim 1, wherein: The top end of the mounting plate (8) is fixedly connected with two fixed plates (19), the two fixed plates (19) are both threadedly connected with a first screw rod (20), the side end of the first screw rod (20) is fixedly connected with a clamping plate (21), and the bottom end of the clamping plate (21) is in sliding fit with the top end of the mounting plate (8).

6. A flying vehicle lift testing platform according to claim 5, wherein: The side end of the first screw rod (20) is fixedly connected with a second handle (22).

7. The aircraft lift testing platform of Claim 5, wherein: The clamping plate (21) is fixedly connected with two slide rods (23), and the two slide rods (23) are in sliding fit with the corresponding fixed plates (19).

8. The aircraft lift testing platform of claim 1, wherein: The arc-shaped seat (3) and the workbench (1) are connected with a support seat (24).

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