CN201993222U - Measuring device for wind tunnel large-amplitude roll oscillation experiment - Google Patents

Abstract

The utility model relates to a measuring device for a wind tunnel large-amplitude roll oscillation experiment, wherein the motor is connected with a dual-sine mechanism support through a speed reducer; a U-shaped block is fixed on sliding blocks; slideways are fixed on upper and lower frames of the support; an eccentric wheel is arranged at the front end of the output shaft of the speed reducer and inserted into a rear slideway of the U-shaped block; an eccentric wheel is also arranged at rear end of a balance supporting rod and inserted into a front slideway of the U-shaped block. The measuring device for the wind tunnel large-amplitude roll oscillation experiment can realize the large-amplitude roll oscillation of a flight vehicle through the design of the special dual-sine roll oscillation mechanism, and measures the dynamic and pneumatic characteristics of the large-amplitude roll oscillation of the flight vehicle through the six-component force balance at the front end of the supporting rod, thereby meeting the requirements of the tunnel experiment.

Description

A kind of measurement mechanism that is used for wind-tunnel large amplitude lift-over vibration test

Technical field

The utility model relates to the lift-over vibrating device, can measure significantly a kind of measurement mechanism that is used for wind-tunnel large amplitude lift-over vibration test of lift-over when vibration aerodynamic characteristic of aircraft specifically exactly.Belong to aviation aerodynamic force wind-tunnel technique field.

Background technology

Modern combat aircraft is in order to adapt to the requirement that short range combat and comprehensive enforcement are attacked, pursue super maneuverability and agility highlightedly, the former main with significantly, the angular speed motion morphology is relevant greatly, the latter refers to that mainly aircraft transfers the transient response ability of another kind of state apace to from a kind of state of flight.These two subject matter of bringing to Flight Vehicle Design is that the two all has substantial connection with aerodynamic force non-permanent, non-linear, and under specific state of flight, the non-permanent and non-linear effects of aerodynamic force dominates.Therefore, in order to hold the aerodynamic characteristics of modern combat aircraft, solve key aerodynamic power problem, it is very necessary and urgent carrying out the development of model large amplitude dynamic test in wind-tunnel.In the wind-tunnel pre-stage test, find, come driving model lift-over vibration with the reciprocating mode of programmed control servomotor self, when setting low-angle amplitude and frequency, the motor output torque still can satisfy the demands, and model actual amplitude angular error is also being accepted within the scope; But when the motor set angle reached the large amplitude lift-over and tests desired angle and frequency, because model rotation inertia is excessive, the output torque of motor was difficult to satisfy the requirement that model is done sinusoidal lift-over vibration.Existing lift-over equipment is difficult to satisfy the test needs.

The utility model content

The utility model is the problem that occurs in the above-mentioned large amplitude lift-over test in order to solve, overlap the lift-over vibrating mechanism and design one, by the large amplitude lift-over sinusoidal vibration that rotatablely moving continuously of motor changed into model in this mechanism, can satisfy the measurement mechanism of a kind of wind-tunnel large amplitude lift-over vibration test of wind tunnel test needs.

The technical scheme that adopts is:

A kind of measurement mechanism that is used for wind-tunnel large amplitude lift-over vibration test comprises motor, speed reduction unit, vibrating mechanism, Π type support, balance pole, six COMPONENT BALANCE; Described vibrating mechanism comprises bearing, last slide rail, glidepath, top shoe, sliding block, U type piece, described motor output shaft is connected with speed reduction unit, fixedly connected with bearing by the reducer shell front end, the front end of bearing is fixedlyed connected with the rear end of Π type support, the front end of balance pole is fixedlyed connected with six COMPONENT BALANCE, balance props up rod rear end and inserts in the Π type rack bore, and supported by the clutch shaft bearing and second bearing, U type piece is fixed on, on the sliding block, on, glidepath is fixed on the bearing, it is characterized in that described reducer output shaft front end is provided with the motor eccentric wheel, the motor eccentric wheel inserts in the rear slide of U type piece; Balance props up rod rear end and is provided with the pole eccentric wheel, and the pole eccentric wheel inserts in the preceding slideway of U type piece.

Principle of work of the present utility model:

If the want sense aircraft aerodynamic characteristic in lift-over when vibration significantly need a kind of lift-over vibrating mechanism of design can make model do large amplitude lift-over vibration, and vibration wants steady.This mechanism can the implementation model amplitude be the sinusoidal wave lift-over vibrations of 60 degree.

Balance pole front end is provided with conventional six COMPONENT BALANCE, suffered aerodynamic force load when the electric bridge of forming by the foil gauge pasted on balance measurement element diverse location can be measured the dummy vehicle test.

Two sine mechanism motion principle math equations are:

Motor eccentric wheel eccentric arm is that r, pole eccentric wheel eccentric arm are R.Each all concerns motor eccentric wheel and pole eccentric wheel just like minor function constantly:

（r<R）

When

The time

So

The rolling movement curve of model is an inverse function curve

It is the inverse function curve

With the standard sine function

Comparison diagram

Explanation

With

Be very approaching, the roll angle Changing Pattern can be used as sine wave curve.

Characteristics of the present utility model:

(1) the utility model adopts large amplitude the test two topology layout of sinusoidal lift-over vibration measurement device overall vibration, i.e. motor, speed reduction unit, vibrating mechanism, Π frame middle part, balance pole, six COMPONENT BALANCE

Whole type of attachment has been finished the measurement of the aerodynamic characteristic of dummy vehicle large amplitude lift-over vibration test exactly.

(2) the utility model has adopted " two sinusoidal vibration mechanism " to make the lift-over vibrating mechanism be special construction.

(3) the utility model design science, reasonable, original, compact overall structure, volume is little, low-power consumption, with low cost, stable performance, reliable, environment applicability and practicality are stronger, have development prospect preferably.

Description of drawings

Fig. 1 is a structural representation of the present utility model.

Fig. 2 is " two sine " of the present utility model movement conversion mechanism partial structurtes synoptic diagram.

Fig. 3 is motor eccentric wheel of the present utility model and pole eccentric wheel differential seat angle synoptic diagram.

Embodiment

A kind of measurement mechanism that is used for wind-tunnel large amplitude lift-over vibration test comprises motor 1, speed reduction unit 2, vibrating mechanism, Π type support 9, balance pole 11, six COMPONENT BALANCE 12; Described vibrating mechanism comprises bearing 8, last slide rail 4, glidepath 15, top shoe 5, sliding block 16, U type piece 6, described motor 1 output shaft is connected with speed reduction unit 2, fixedly connected with bearing 8 by speed reduction unit 2 housing front ends, the front end of bearing 8 is fixedlyed connected with the rear end of Π type support 9, the front end of balance pole 11 is fixedlyed connected with six COMPONENT BALANCE 12, insert in Π type support 9 inner chambers balance pole 11 rear ends, and supported by the clutch shaft bearing 10 and second bearing 17, U type piece 6 is fixed on, sliding block 5, on 16, on, glidepath 4,15 are fixed on the bearing 8, it is characterized in that described reducer output shaft front end is provided with motor eccentric wheel 3, motor eccentric wheel 3 inserts in the rear slide 13 of U type piece 6; Balance pole 11 rear ends are provided with pole eccentric wheel 7, and pole eccentric wheel 7 inserts in the preceding slideway 14 of U type piece.

Claims (1)

1. a measurement mechanism that is used for wind-tunnel large amplitude lift-over vibration test comprises motor (1), speed reduction unit (2), vibrating mechanism, Π type support (9), balance pole (11), six COMPONENT BALANCE (12); Described vibrating mechanism comprises bearing (8), last slide rail (4), glidepath (15), top shoe (5), sliding block (16), U type piece (6), described motor (1) output shaft is connected with speed reduction unit (2), fixedly connected with bearing (8) by speed reduction unit (2) housing front end, the front end of bearing (8) is fixedlyed connected with the rear end of Π type support (9), the front end of balance pole (11) is fixedlyed connected with six COMPONENT BALANCE (12), insert in Π type support (9) inner chamber balance pole (11) rear end, and supported by clutch shaft bearing (10) and second bearing (17), U type piece (6) is fixed on, sliding block (5), (16) on, on, glidepath (4), (15) be fixed on the bearing (8), it is characterized in that described reducer output shaft front end is provided with motor eccentric wheel (3), motor eccentric wheel (3) inserts in the rear slide (13) of U type piece (6); Balance pole (11) rear end is provided with pole eccentric wheel (7), and pole eccentric wheel (7) inserts in the preceding slideway (14) of U type piece.

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