JPH0337542A - Apparatus for testing dynamic stability of aircraft - Google Patents

Abstract

PURPOSE:To make it possible to hold a model at the parts other than the lower surface and the side surface of the model by holding the aircraft model at the rear side, and providing an oscillating sting which is connected to the rear end part so that the sting can be slidden in the axial direction with respect to a moving plate and which is held with a hinge at the intermediate part so that the sting can be swung. CONSTITUTION:The initial attitude of a testing apparatus before oscillation is applied is determined with the attaching position of a sting pod 22, and the apparatus is fixed. The rotation of a motor 4 after the start of operation is reduced with a speed reducer 3, and a rotary disk 6 is rotated. A cam follower 7 provided on the disk 6 performs eccentric turning motion and horizontal reciprocal motion relatively in the long-hole shaped groove in a vertical moving plate 8. The vertical moving plate 8, which is retained so that the plate can be moved in the up and down direction with bearings for linear motion, is driven up and down. The tip of a shaking sting 1 is vertically reciprocated in an arc pattern by the motion through a sliding connecting part 10. The sting 1 supported with a hinge 2 performs swinging motion indicated by an arrow F. Therefore, a model 19 which is held at the tip of the sting 1 through a balance 23 performs swinging motion with the hinge 2 as a center.

Description

DETAILED DESCRIPTION OF THE INVENTION [Industrial Application Field] The present invention relates to a dynamic stability testing device used for determining the dynamic stability performance of an aircraft through wind tunnel testing.

[Conventional technology]

Figure 3(a) is a front view of a conventional aircraft dynamic stability test device.
Figure (b) shows a side view of the device. In the figure, 11 is an electric motor, 12 is a reduction gear connected to the electric motor, 13 is a crankshaft connected to the reduction gear, 14 is a connecting rod that is eccentrically connected to the crankshaft and performs reciprocating motion, and 15 is a connecting rod provided on a fixed part. A 1:16kia strut is rotatably held at the top of the strut, and the connecting rod 14 is attached to one of its two arms to swing the swinging arm, 17 is rotatable at the top of the strut. A swing shaft that is held movably and swings about axis 1b in conjunction with the center of rotation of the swing arm, and is attached to a different arm of the two 18Fi swing arms. 19 is an aircraft model for wind tunnel testing attached to the tip of the swing shaft 17, 2o is a wind tunnel, arrow A is the direction of airflow, and arrow F is an excitation cylinder. It is the direction.

In this device, after the rotation of the electric motor 11 is decelerated by the reducer 12, the connecting rod 14 is rotated by the crankshaft 13.
This is converted into a reciprocating motion of the swinging shaft 17 via the swinging arm 16, which is transmitted to the model 19, and the model 19 performs a swinging motion. In this device, the excitation frequency is adjusted by changing the rotational speed of the electric motor 11, and the amplitude of the vibration movement is adjusted by changing the mounting position of the connecting rod 14 with respect to the crankshaft 13.

[Problem to be solved by the invention]

When it is desired to apply yaw vibration to an aircraft model for wind tunnel testing, conventional dynamic stability test equipment applies pitch vibration to the lower surface of the model's fuselage, and when fcl The moving shaft 17 was installed. The model holder including this swing axis disturbs the shape of the lower or side surface of the fuselage, increasing aerodynamic interference. Furthermore, in the former case, when attempting to attach a payload to the underside of the fuselage, it would interfere with the holding part, making it impossible to conduct wind tunnel tests on aircraft with payloads attached.

The purpose of the present invention is to provide an aircraft dynamic stability test device that can hold a model facing the area of the vehicle.

[Means to solve the problem]

The present invention has solved the above-mentioned problems, and includes an aircraft dynamic stability test device that provides swinging motion to an aircraft model for wind tunnel testing. , an eccentric shaft that is driven by the electric motor to perform an eccentric orbiting motion by firing the shaft, a moving plate that engages with the eccentric shaft and reciprocates in a direction perpendicular to the shaft, and a front portion of the device. bz, which is provided approximately along the longitudinal direction of the device, has a button at the front end of the sled, holds the aircraft model from the rear of the model, and is connected to the movable plate at the rear end so as to be slidable in the axial direction. The present invention relates to an aircraft dynamic stability testing device characterized in that it is equipped with a vibrating sting that is swingably held by a hinge bin in the intermediate portion.

[Effect]

In the test apparatus of the present invention, an eccentric shaft driven eccentrically around the longitudinal axis of the apparatus by an electric motor causes the moving plate to perform linear reciprocating motion in a direction perpendicular to the longitudinal axis. The rear end of the excitation sting, which is slidably connected to the movable plate in the axial direction, performs an arcuate reciprocating motion as the hinge bin rotates as the movable plate moves, thereby moving the excitation sting around the bin. Rock around.

The aircraft model held at the tip of the sting also swings accordingly.

In wind tunnel tests, the aircraft model is placed with its center line almost parallel to the airflow and its front section facing the airflow, but with this device, the model is held from the rear of the model. , the entire device will be located at the rear of the model, and there will be no aerodynamic interference caused by the test device. Since the model is held from the rear, it is possible to carry out wind tunnel tests by adding payloads to the underside of the model's fuselage.

〔Example〕

FIG. 1 shows a side view of an embodiment of the present invention.

>1% in the figure, 19 is an aircraft model for wind tunnel testing, 20 is a wind tunnel, 21 is a sting support device of existing equipment normally used during static characteristic tests of aircraft, and 22 is a sting installed in the sting support device. This is the part of the body where the dynamic stability test equipment described below is attached. 23 is model 1
This is an aerodynamic load measuring balance that is interposed between the model and the dynamic stability testing device described below in the interior of the model.

1 is an excitation sting attached to the model via the aerodynamic load measuring flat balance 23; 2 is a hinge pin that swingably holds the sting at the intermediate portion between its front and rear ends; 3 is a deceleration 4 is an electric motor, and 5 is an outer frame. Although details are omitted from the drawing, the dynamic stability test apparatus of this embodiment consists of a series of parts designated by the above-mentioned numerals 1 to 5.

Arrow F indicates the direction in which the model is vibrated by this device, and the center of the swing is at the position of the hinge pin 2 that is spaced rearward from the model. Bo is the direction of airflow. In addition, the posture of the device indicated by B in the figure can be changed by attaching the sting bod 22 to a different position of the sting support device 21 (dynamic stability test device) and the posture of the model before excitation. It shows.

FIG. 2 is a partially detailed perspective view of the above embodiment.

This shows the part between the vibration sting 1 supported by the hinge pin 2 and the speed reducer 3, that is, the device that gives swing to the vibration sting 1. 6
7 is a rotating disk connected to the rotating shaft of the speed reducer 30; 7 is a cam follower provided at an eccentric position on the disk; 8 is a vertically movable plate having an elongated groove in its upper part for receiving the outer ring of the cam follower 7; Reference numeral 9 denotes a linear motion bearing provided on the vertically movable plate 8 to permit only vertical movement; 10 represents a linear reciprocating motion of the vertically movable plate 8 and an excitation sting supported by the hinge bin 2; This is a sliding connection consisting of a pin and an elongated hole to gently connect the ends that move up and down in an arc shape.

In this device, the initial posture before vibration is determined by the mounting position of the sting bod 22 and the device is fixed. The 40 rotations of the electric motor caused by the start of operation of this device are reduced by the reducer 3 and rotate the rotary disk 6. At this time, the cam follower 7 provided on the circular plate 6 performs an eccentric orbital movement, performs a horizontal reciprocating movement relatively within the elongated groove provided in the vertically movable plate 8, and also performs a linear movement. A vertically movable plate 8 restrained by bearings so that it can only move vertically is reciprocated in the vertical direction. This vertical reciprocating motion of the vertically movable plate 8 is carried out by the excitation sting 1 via the sliding connection part 10.
The end of the machine moves up and down in an arc. As a result, the excitation sting 1 supported by the hinge bin 2 performs a rocking motion as indicated by the arrow F. Along with this, the model 19 held at the tip of the sting 1 via the aerodynamic load measuring balance 23 also performs a swinging motion about the hinge bin 2 . The excitation frequency is adjusted by changing the rotational speed of the electric motor 40, and the amplitude of the swinging motion is adjusted by changing the mounting position of the cam follower 7 on the rotary disk 6 and changing the eccentricity 't. In addition, in this device, the model is held and vibrated via the aerodynamic load measurement balance 23 at the tip of the excitation sting, so the dynamic characteristics of the model can be directly grasped. It is also possible to easily change from pitching vibration to yaw vibration by rotating the model by 90°.

As detailed above, in this testing device, the model is held from behind, so aerodynamic interference due to the testing device does not occur. Furthermore, since the model is not held on the underside of the fuselage, wind tunnel tests can be performed on aircraft models that have objects mounted on the underside of the fuselage.

〔Effect of the invention〕

The aircraft dynamic stability testing device of the present invention includes a motor that rotates around the longitudinal axis of the device, an eccentric shaft that performs all eccentric orbital movements by the motor, and a button that engages with the eccentric shaft and rotates in a direction perpendicular to the shaft. There is a movable plate that reciprocates in the middle, and a hinge pin that holds the aircraft model from the rear of the model at the front end. Equipped with a swinging sting, wind tunnel tests are conducted by holding and swinging the aircraft model from behind, so there is no aerodynamic interference to the test equipment, -1:
Wind tunnel tests can be conducted by adding payloads to the underside of the model's fuselage.

[Brief explanation of drawings]

FIG. 1 is a top view of an embodiment of the present invention, FIG. 2 is a partially detailed perspective view of the above embodiment, FIG. 3(a) is a front view of a conventional aircraft dynamic stability test device, and FIG. ) is a side view of the device. 1... Vibration sting, 2... Hinge bin,
3...Reducer, 4...Electric motor, 5...Outer frame, 6...Rotating disk, 7...Cam follower, 8...
・・Vertical movement plate, 9 ・・Vertical ring for linear motion,
10...Sliding connection part, jl...Electric motor, I2...
...Deceleration R11,3...Crank: FIl,14...
- Connecting rod, 15... Strut, 16... Rocking arm, 17... Rocking shaft, 18... Air cylinder for backlash prevention, 19... Model, 20... Wind tunnel,
21... Sting support device, 22... Sting bod, 23... 4X force load measurement large pestle.

Claims (1)

[Claims] In an aircraft dynamic stability testing device that applies rocking motion to an aircraft model for wind tunnel testing, an electric motor generates a rotational driving force around a longitudinal axis of the device, and an eccentric orbiting motion is caused by the electric motor with respect to said axis. an eccentric shaft that engages with the eccentric shaft and reciprocates in a direction perpendicular to the axis; A vibrating stay is provided which holds the aircraft model from the rear of the model, is connected to the movable plate at its rear end so as to be slidable in the axial direction, and is held swingably by a hinge pin at an intermediate portion thereof. An aircraft dynamic stability test device featuring: