CN115127773B

CN115127773B - Aerodynamic force load measuring device capable of rapidly replacing test state

Info

Publication number: CN115127773B
Application number: CN202211058692.6A
Authority: CN
Inventors: 李勇; 王晨; 张傲男; 刘力夫; 张平; 许文格; 王碧玲
Original assignee: AVIC Shenyang Aerodynamics Research Institute
Current assignee: AVIC Shenyang Aerodynamics Research Institute
Priority date: 2022-08-31
Filing date: 2022-08-31
Publication date: 2022-11-15
Anticipated expiration: 2042-08-31
Also published as: CN115127773A

Abstract

The invention discloses a aerodynamic force load measuring device capable of rapidly changing a test state, belongs to the field of aerospace aerodynamic force test measuring equipment, and aims to solve the problem that a measuring rudder of a hinge moment balance is difficult to assemble and disassemble when load measurement is carried out at different angles. The moment balance comprises a moment balance and a plurality of right-angle trapezoidal wedge blocks, wherein an angle limiting groove is formed in the peripheral surface of a moment balance base, a rectangular groove and a hinge hole which are vertically communicated are formed in a model body, and the base is in running fit with the hinge hole; the inner end faces of the right trapezoid wedge blocks have various included angles with the axial direction of the right trapezoid wedge blocks, any right trapezoid wedge block is inserted into the rectangular groove, the inner end face abuts against the bottom face of the angle limiting groove, different right trapezoid wedge blocks are replaced, the inner end faces of the right trapezoid wedge blocks are abutted against and matched with the angle limiting groove, the rotating state of the moment balance can be changed quickly and accurately, and the occupied model body space is small.

Description

Aerodynamic force load measuring device capable of rapidly replacing test state

Technical Field

The invention belongs to the field of aeronautical and astronautic aerodynamic force test measuring equipment, and particularly relates to an aerodynamic force load measuring device capable of rapidly changing a test state.

Background

Wind tunnel balances are used in wind tunnel tests to measure aerodynamic loads acting on an aircraft and can be classified into mechanical balances, optical fiber balances, piezoelectric balances and the like according to the working principle. At present, a strain balance is commonly used, a strain gauge is adhered to a balance element by adopting a strain electric measurement principle to form an electric bridge, and the strain of the loaded deformation of the balance element is converted into an electric signal for measurement. And calibrating the mapping relation between the load and the electric signal in advance, and calculating the aerodynamic load of the aircraft according to the measured electric signal according to the mapping relation.

The column beam type hinge moment balance is one kind of strain balance and is mainly used for measuring the pneumatic hinge moment load of the control surface of an aircraft model. In order to facilitate calculation and arrangement of test data, the position relationship between the balance element and the measuring rudder needs to be kept unchanged during testing. When the measuring rudder carries out aerodynamic load measurement in different angle states, the balance element and the measuring rudder need to be subjected to integral angle transformation at the same time. In the prior art, the angle state is changed by installing a positioning pin on a base of the balance, and in order to ensure that the rotation angle of a control surface of a rudder is accurate, the base needs to be large enough to be provided with enough pin holes, and the positioning pin and the pin holes need to be tightly matched, so that the problems that the hinge moment balance occupies a large space and is difficult to assemble and disassemble are caused.

Disclosure of Invention

The invention aims to provide an aerodynamic load measuring device capable of rapidly changing a test state, and aims to solve the problems that when a measuring rudder of a hinge moment balance measures aerodynamic load in different angle states, a base needs to be large enough, a positioning pin and a pin hole need to be tightly matched, and the hinge moment balance occupies a large space and is difficult to assemble and disassemble. The technical scheme adopted by the invention is as follows:

a aerodynamic force load measuring device capable of rapidly changing a test state comprises a moment balance and a plurality of right-angle trapezoidal wedge blocks;

the moment balance comprises a measuring rudder, a balance element and a base which are sequentially connected from top to bottom, the base is cylindrical, and an angle limiting groove which is communicated along the horizontal direction is arranged on the peripheral surface of the base;

the model body is provided with a rectangular groove and a hiding hole, the bottom surface of the hiding hole is provided with a hinge hole, the rectangular groove is vertically communicated with the hinge hole, a base of the moment balance is in rotating fit with the hinge hole, and a working space is arranged between the balance element and the hiding hole;

the inclined plane of the right-angle trapezoidal wedge block is an inner end face, the outer periphery of the right-angle trapezoidal wedge block is matched with the inner periphery of the rectangular groove, and a plurality of included angles are formed between the inner end face and the outer end face of the right-angle trapezoidal wedge blocks and range from 25 degrees to 75 degrees;

any right trapezoid wedge block is inserted into the rectangular groove, the inner end of the right trapezoid wedge block is clamped in the angle limiting groove, the inner end face of the right trapezoid wedge block abuts against the bottom face of the angle limiting groove, the jackscrew is in threaded fit with the outer end of the rectangular groove, and the jacking end face of the jackscrew abuts against and is matched with the outer end face of the right trapezoid wedge block.

Furthermore, the outer end face of the right-angled trapezoid wedge block is provided with a dismounting screw hole.

Furthermore, the upper end face and the lower end face of the rectangular groove are provided with integrated thread structures, and the diameter of each thread structure is smaller than the horizontal width of the rectangular groove.

Compared with the prior art, the invention has the beneficial effects that:

moment balance's base and hinge hole normal running fit, hinge hole is spacing to moment balance's circumference, arbitrary right trapezoid voussoir inserts the rectangular channel, its inner end joint is in angle spacing inslot, right trapezoid voussoir and rectangular channel cooperate, still cooperate with angle spacing groove simultaneously, the up end of right trapezoid voussoir supports with the last lateral wall in angle spacing groove and leans on, the lower terminal surface of right trapezoid voussoir supports with the lower lateral wall in angle spacing groove and leans on, right trapezoid voussoir is spacing to moment balance's axial, and it is spacing to moment balance's turned angle, change different right trapezoid voussoirs, make its inner end face support with angle spacing groove and lean on the cooperation, the rotational state of change moment balance that can be quick accurate, and the model body space that occupies is little.

Drawings

FIG. 1 is a cut-away isometric view of the present invention;

FIG. 2 is an isometric view of the present invention;

FIG. 3 is an isometric view of a model body;

FIG. 4 is a partial half-sectional view of the model body;

FIG. 5 is an isometric view of a torque balance;

FIG. 6 is an isometric view of a right angle trapezoidal wedge;

FIG. 7 is an isometric view of another perspective of the right angle trapezoidal wedge.

In the figure: 1-model body, 11-hinge hole, 12-rectangular groove, 13-thread structure, 14-avoiding hole, 2-moment balance, 21-measuring rudder, 22-balance element, 23-base, 24-angle limiting groove, 3-right-angle trapezoidal wedge block, 31-disassembling screw hole and 4-jackscrew.

Detailed Description

In order that the objects, aspects and advantages of the invention will become more apparent, the invention will be described by way of example only, and with reference to the accompanying drawings. It is to be understood that such description is merely illustrative and not intended to limit the scope of the present invention. Moreover, in the following description, descriptions of well-known structures and techniques are omitted so as to not unnecessarily obscure the concepts of the present invention.

The connection mentioned in the invention is divided into fixed connection and detachable connection, the fixed connection is non-detachable connection and comprises but is not limited to folding edge connection, rivet connection, bonding connection, welding connection and other conventional fixed connection modes, the detachable connection comprises but is not limited to bolt connection, buckle connection, pin connection, hinge connection and other conventional detaching modes, when the specific connection mode is not clearly limited, the skilled person can select at least one connection mode from the existing connection modes to realize the function by default, and the skilled person can select the connection mode according to the needs. For example: the fixed connection selects welded connection, and the detachable connection selects bolted connection.

The present invention will be described in further detail with reference to the accompanying drawings, and the following examples are illustrative of the present invention, but the present invention is not limited to the following examples.

The embodiment is as follows: as shown in fig. 1-7, the aerodynamic force load measuring device capable of rapidly changing the test state comprises a moment balance 2 and a plurality of right-angle trapezoidal wedges 3;

the moment balance 2 comprises a measuring rudder 21, a balance element 22 and a base 23 which are sequentially connected from top to bottom, the base 23 is cylindrical, and an angle limiting groove 24 which is communicated along the horizontal direction is formed in the peripheral surface of the base 23;

the model body 1 is provided with a rectangular groove 12 and an avoiding hole 14, the bottom surface of the avoiding hole 14 is provided with a hinge hole 11, the rectangular groove 12 is vertically communicated with the hinge hole 11, a base 23 of the moment balance 2 is in running fit with the hinge hole 11, and a working space is arranged between the balance element 22 and the avoiding hole 14;

the inclined plane of the right-angle trapezoidal wedge block 3 is an inner end face, the outer periphery of the right-angle trapezoidal wedge block 3 is matched with the inner periphery of the rectangular groove 12, and a plurality of included angles are formed between the inner end face and the outer end face of the right-angle trapezoidal wedge blocks 3, and the included angles range from 25 degrees to 75 degrees;

any one right-angle trapezoidal wedge 3 is inserted into the rectangular groove 12, the inner end of the right-angle trapezoidal wedge is clamped in the angle limiting groove 24, the inner end face of the right-angle trapezoidal wedge abuts against the bottom face of the angle limiting groove 24, the jackscrew 4 is in threaded fit with the outer end of the rectangular groove 12, and the jacking end face of the jackscrew 4 abuts against and is matched with the outer end face of the right-angle trapezoidal wedge 3.

Base 23 and the 11 normal running fit of hinge hole of moment balance 2, hinge hole 11 is spacing to the circumference of moment balance 2, arbitrary right trapezoid voussoir 3 inserts the rectangular channel, its inner end joint is in angle spacing groove 24, right trapezoid voussoir 3 cooperatees with rectangular channel 12, still cooperate with angle spacing groove 24 simultaneously, the up end of right trapezoid voussoir 3 supports with the last lateral wall of angle spacing groove 24 and supports, the lower terminal surface of right trapezoid voussoir 3 supports with the lower lateral wall of angle spacing groove 24 and supports, right trapezoid voussoir 3 is spacing to the axial of moment balance 2, and spacing to the turned angle of moment balance 2, change different right trapezoid voussoir 3, make its inner end support with angle spacing groove 24 and support the cooperation, the rotation state of change moment balance that can be accurate fast, and the model balance body 1 space that occupies is little.

The outer end face of the right-angle trapezoidal wedge block 3 is provided with a dismounting screw hole 31. When the rectangular wedge 3 is replaced, the rectangular wedge 3 can be removed from the rectangular groove 12 by screwing a screw, which is matched with the screw hole 31, into the screw hole 31.

The upper end face and the lower end face of the rectangular groove 12 are provided with an integrated thread structure 13, and the diameter of the thread structure 13 is smaller than the horizontal width of the rectangular groove 12. The thread structure 13 is tapped along the axial direction by the outer end notch of the rectangular groove 12, so that a incomplete threaded hole is overlapped in the axial direction of the rectangular groove 12, the small-size jackscrew 4 can be selected as far as possible, and the diameter of the jackscrew 4 is slightly larger than the vertical height of the rectangular groove 12.

The above embodiments are merely illustrative of the present patent and do not limit the scope of the patent, and those skilled in the art can make modifications to the parts thereof without departing from the spirit and scope of the patent.

Claims

1. The utility model provides a quick replacement test condition's aerodynamic force load measuring device which characterized in that: comprises a moment balance (2) and a plurality of right-angle trapezoidal wedges (3);

the moment balance (2) comprises a measuring rudder (21), a balance element (22) and a base (23) which are sequentially connected from top to bottom, the base (23) is cylindrical, and an angle limiting groove (24) which is communicated along the horizontal direction is formed in the peripheral surface of the base (23);

the model body (1) is provided with a rectangular groove (12) and a hiding hole (14), the bottom surface of the hiding hole (14) is provided with a hinge hole (11), the rectangular groove (12) is vertically communicated with the hinge hole (11), a base (23) of the moment balance (2) is in running fit with the hinge hole (11), and a working space is arranged between the balance element (22) and the hiding hole (14);

the inclined plane of the right-angle trapezoidal wedge block (3) is an inner end face, the outer periphery of the right-angle trapezoidal wedge block (3) is matched with the inner periphery of the rectangular groove (12), and a plurality of included angles are formed between the inner end face and the outer end face of the right-angle trapezoidal wedge blocks (3), and the included angles range from 25 degrees to 75 degrees;

any one right trapezoid wedge (3) is inserted into the rectangular groove (12), the inner end of the right trapezoid wedge is clamped in the angle limiting groove (24), the inner end face of the right trapezoid wedge abuts against the bottom face of the angle limiting groove (24), the jackscrew (4) is in threaded fit with the outer end of the rectangular groove (12), the jacking end face of the jackscrew (4) abuts against the outer end face of the right trapezoid wedge (3) to be matched, the right trapezoid wedge (3) is limited to the axial direction of the torque balance (2), the rotating angle of the torque balance (2) is limited, different right trapezoid wedges (3) are replaced, the inner end face of the right trapezoid wedge is abutted against the angle limiting groove (24) to be matched, the rotating state of the torque balance can be changed quickly and accurately, and the occupied space of the model body (1) is small.

2. A rapid test condition change aerodynamic force load measuring device according to claim 1, wherein: the outer end surface of the right-angle trapezoidal wedge block (3) is provided with a disassembly screw hole (31).

3. A rapid test condition change aerodynamic force load measuring device according to claim 1 or 2, wherein: the upper end face and the lower end face of the rectangular groove (12) are provided with integrated thread structures (13), and the diameter of each thread structure (13) is smaller than the horizontal width of the rectangular groove (12).