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Free mode testing system in guided missile rotation state

A modal test and missile technology, applied in the direction of ammunition test, ammunition, weapon accessories, etc., can solve problems such as inapplicability, and achieve the effects of convenient control, easy installation and maintenance, and good signal-to-noise ratio.

Pending Publication Date: 2017-11-24
TIANJIN AEROSPACE RELIA TECH +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] However, the existing free modal test system is only aimed at the modal parameter identification of missile products in a static state and cannot be applied to the situation in a rotating state

Method used

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  • Free mode testing system in guided missile rotation state
  • Free mode testing system in guided missile rotation state
  • Free mode testing system in guided missile rotation state

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Embodiment Construction

[0031] Figure 1-4 Show a kind of free mode test system under the self-rotation state of missile, comprise suspension device A, excitation device B, data acquisition and analysis device C, it is characterized in that missile rotary drive device E and connected to said missile rotary drive device are also provided with E and the rotary transmission device D between the tail end of the missile test sample 4. The suspension device A includes at least two sets of suspension frames. In this example, two sets of suspension frames are used. The suspension frame is mainly composed of a mounting frame 1, a hoop bearing 3 supporting a missile test sample 4 in a horizontal position and freely rotating state, and an elastic rope 2 fixing the hoop bearing 3; the missile rotation driving device E includes The variable frequency motor 8 and the frequency converter 7 connected to it have a frequency range of 5Hz-20Hz. In actual construction, the variable frequency motor 8 is supported on a ...

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Abstract

The invention relates to a free mode testing system in a guided missile rotation state. The free mode testing system in the guided missile rotation state comprises a suspension device, an excitation device and a data acquiring and analyzing device, and is characterized by further comprising a guided missile rotation driving device and a rotation transmission device; the suspension device comprises suspension frames; each suspension frame consists of a mounting frame, a hoop bearing and an elastic rope; the guided missile rotation driving device comprises a variable frequency motor and a frequency converter with the frequency range of 5Hz-20Hz; the rotation transmission device comprises a transmission shaft; one end of the transmission shaft is universally connected with a rotating shaft of the variable frequency motor while the other end of the transmission shaft is universally connected with a clamping piece at the tail end of a guided missile testing sample piece; the data acquiring and analyzing device comprises an acceleration sensor, a force sensor, a charge amplifier, a data recording instrument, a wireless signal transmitter, a wireless base station and a computer terminal; the acceleration sensor is arranged on the guided missile testing sample piece and is wirelessly connected with the wireless base station through the wireless signal transmitter; the force sensor is connected with the data recording instrument through the charge amplifier; and the wireless base station and the data recording instrument are connected to a computer terminal.

Description

technical field [0001] The invention relates to a missile modal test system, in particular to a free modal test system under the self-rotation state of the missile. Background technique [0002] Due to the characteristics of low cost, fast response, miniaturization and good adaptability, rotating missiles have great development potential and application prospects in the field of guided weapons. In order to improve rapidity and reduce flight resistance, rotating missiles are usually designed with a large slenderness ratio, so the structural rigidity is low; at the same time, with the improvement of maneuverability requirements, the flight overload of missiles is getting bigger and bigger. Under the condition of large angle of attack, the projectile will produce severe elastic deformation. Taking the American Ram missile as an example, its slenderness ratio exceeds 20, the maximum flight overload is more than 45g, and the longitudinal and lateral elastic vibration is signific...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F42B35/00
CPCF42B35/00
Inventor 李杰张呈波朱正邦李克勇王辉
Owner TIANJIN AEROSPACE RELIA TECH
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