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A device for simulating the variation of drag rudder deflection angle and stiffness of tailless aircraft

A technology of tailless aircraft and stiffness change, which is applied in the direction of measuring devices, machine/structural component testing, aerodynamic testing, etc. It can solve the problems of not considering the rigid body model of elastic deformation, and there is no resistance rudder, so as to improve the design level Effect

Active Publication Date: 2020-12-25
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Generally speaking, wind tunnel tests are indispensable in obtaining the vibration characteristics of drag rudders. However, since the traditional tailless aircraft wind tunnel model mainly studies the mechanical characteristics of the aircraft at different attitudes and flight speeds, the adopted It is a rigid body model that does not consider elastic deformation, and an elastic model that considers deformation must be used to study vibration characteristics, so there is no model design scheme for studying the vibration characteristics of drag rudders

Method used

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  • A device for simulating the variation of drag rudder deflection angle and stiffness of tailless aircraft
  • A device for simulating the variation of drag rudder deflection angle and stiffness of tailless aircraft
  • A device for simulating the variation of drag rudder deflection angle and stiffness of tailless aircraft

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Embodiment 1

[0036] like Figure 1-9 As shown, a device for simulating the deflection angle and stiffness change of a tailless aircraft resistance rudder includes a basic model, a rudder surface model, a connecting device, a deflection angle control system and a stiffness control system, wherein: the basic model is selected as no The aeroelastic model of tail plane wing, i.e. wing 1; Described rudder surface model is resistance rudder 2, and described resistance rudder 2 comprises rudder leading edge 4 and rudder surface trailing edge 10, and described rudder leading edge 4 and rudder surface The two ends of trailing edge 10 are respectively connected by end frames 8 and dimension-shaped frames 5 on the left and right sides of the rudder surface; shaped frame 5, the rotating shaft 12 is sleeved on the connection support 7 located outside the end frame 8, and the connection support 7 is connected to the rear beam of the wing 1 through the connection support arm 3; the deflection control sys...

Embodiment 2

[0043]Since the separation vortex produced when the drag rudder is opened will directly affect the aeroelastic characteristics of the wing part where the rudder surface is located, the present invention can be used on the basis of the aeroelastic model of the wing to study the impact of drag rudders with different stiffnesses on the aircraft at different deflection angles. The influence of wing vibration characteristics.

[0044] A device for simulating the variation of drag rudder deflection angle and stiffness of tailless aircraft includes a basic model, a rudder surface model, a connecting device, a deflection angle control system and a stiffness control system. The basic model selects the aeroelastic model of the tailless aircraft wing, and the model adopts a structural dynamics similarity scheme to satisfy the aerodynamic shape, stiffness distribution and mass distribution similarity. The wing includes a beam frame, a dimensional frame and a skin, where: the stiffness of ...

Embodiment 3

[0051] In the embodiment, the wing span of the test model is determined according to the diameter of the test wind tunnel, and then the basic parameters of the model such as the stiffness scale and mass of the wing model are determined. According to the relative position of the drag rudder and the wing, the position of the rotation axis of the rudder surface and the plane size of the rudder surface can be determined.

[0052] Since the rudder surface is installed on the wing rear beam by means of the connecting device, the height of one end of the connecting support arm is determined according to the height of the wing rear beam. The chord length of the connecting support arm is determined according to the distance from the leading edge of the rudder to the rotating shaft, and then the height of the airfoil at the corresponding position is obtained from the length, and then the height of the other end of the connecting support arm is obtained. This essentially determines the d...

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Abstract

The invention discloses a device for simulating tailless aircraft drag rudder deflection angle and rigidity change. The device comprises a basic model, a control surface model, a connecting apparatus,a deflection angle control system and a rigidity control system. Specifically, an aeroelastic model of a tailless aircraft wing is selected as the basic model, namely a wing 1; the control surface model is a resistance rudder 2; the connecting apparatus comprises a connecting support 7 and a connecting supporting arm 3, the resistance rudder 2 is installed on a rotating shaft 12, the rotating shaft 12 is sleeved on a connecting support 7 located outside an end frame 8, and the connecting support 7 is connected to a rear beam of the wing 1 through the connecting supporting arm 3; the deflection angle control system comprises a steering engine, a locking apparatus and an angle measurement sensor; and rigidity control is achieved by adjusting the leaf spring rigidity. The device is applied to a wind tunnel test model of the tailless aircraft, helps engineering personnel to further know the change conditions of vibration characteristics of the drag rudder in deflection angle and rigiditychanges, and the design level of the tailless aircraft drag rudder is improved.

Description

technical field [0001] The invention belongs to the technical field of aeroelastic wind tunnel models, and in particular relates to a device for simulating the variation of drag rudder deflection angle and stiffness of tailless aircraft. Background technique [0002] In order to obtain better stealth performance, the tailless aircraft adopts wing-body fusion technology, and abandons the vertical and horizontal tails. At the same time, the disadvantage is that its directional control characteristics are insufficient. At present, drag rudder is one of the most effective directional control methods for tailless aircraft, which generally refers to the trailing edge cracked drag rudder installed on the wingtip. Therefore, for a tailless aircraft with a large aspect ratio flying wing layout, the small resistance on the drag rudder can generate enough yaw moment; in addition, when the drag rudder angle is opened to the maximum, there is also the function of the drag plate; When th...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M9/08G01M9/02
CPCG01M9/02G01M9/08
Inventor 周丽周大恒邱涛
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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