Search

CN-119826643-B - Missile full-missile double-platform parallel excitation reliability test device based on comprehensive stress

CN119826643BCN 119826643 BCN119826643 BCN 119826643BCN-119826643-B

Abstract

The invention provides a missile full-missile double-platform parallel excitation reliability test device based on comprehensive stress, and relates to the technical field of missile testing. The device comprises a plurality of vibration test tables and clamping mechanisms, wherein the test walls of the vibration test tables are abutted with the side walls of the guided missiles along the length direction of the test walls, the clamping mechanisms are arranged on one side, close to the guided missiles, of the vibration test tables, the feeding assemblies comprise lifting mechanisms, moving parts and feeding parts, the feeding parts are used for placing guided missiles to be tested, the lifting mechanisms can be lifted to the positions, located on the test walls of the vibration test tables, of the moving parts, the feeding parts can be moved to the positions, located on the test walls of the vibration test tables, of the lifting mechanisms can be lowered to the positions, located on the test walls of the vibration test tables, of the guided missiles to be tested, along the length direction of the side walls of the guided missiles to be tested, are abutted with the test walls of the guided missiles. The device can greatly simplify the complicated steps of feeding, discharging and the like during testing, so that the testing efficiency is effectively improved, and the device has the advantage of high automation degree.

Inventors

  • CHEN WEI
  • ZHU GUANGYU
  • DING DANDAN

Assignees

  • 贵州航天计量测试技术研究所

Dates

Publication Date
20260508
Application Date
20241126

Claims (6)

  1. 1. The missile full-bullet double-platform parallel excitation reliability test device based on the comprehensive stress is used for testing a missile and is characterized by comprising a test component and a feeding component; The test assembly comprises a vibration test bed and a clamping mechanism, the test wall of the vibration test bed is abutted with the side wall of the missile along the length direction of the missile, and the clamping mechanism is arranged on one side, close to the missile, of the vibration test bed; The feeding assembly comprises a lifting mechanism, a moving part and a feeding part, wherein the feeding part is used for placing a missile to be tested, the lifting mechanism can be lifted to be above a testing wall of the vibration test bench, the moving part can move the feeding part to the position of the testing wall of the vibration test bench, and the lifting mechanism can be lowered to the position of the testing wall of the vibration test bench so that the side wall of the missile to be tested along the length direction of the missile is abutted to the testing wall; The test assembly comprises a first vibration test bed and a second vibration test bed, the first vibration test bed and the second vibration test bed are arranged at intervals along the length direction of the missile, and the test walls of the first vibration test bed and the second vibration test bed are respectively abutted with two ends of the missile along the length direction of the missile; Two bent strips are symmetrically arranged at one end of the vibration test bed, which is close to the missile, the two bent strips are matched to clamp the missile, a rotating shaft is arranged at one end of the bent strip, which is far away from the missile, the rotating shaft penetrates through the vibration test bed along the length direction of the missile, and two ends of the rotating shaft are respectively connected with fixed ends of the bent strips, which are positioned at two sides of the vibration test bed; A transmission rod, a clamping gear and a control gear are arranged between the two vibration test tables, the clamping gear is sleeved outside the transmission rod, the clamping gear is meshed with the control gear, two ends of the transmission rod are respectively connected with two opposite ends of a rotating shaft arranged on the two vibration test tables, the clamping gear rotates under the driving of the control gear to drive the transmission rod to rotate, and the transmission rod can drive the rotating shaft to rotate so that the bent strip clamps or loosens the missile; The moving piece comprises a first supporting part, a second supporting part and a moving part, wherein the arrangement direction of the first supporting part is consistent with the length direction of the missile, two ends of the second supporting part are respectively connected with the first supporting part and the moving part, the moving part can reciprocate linearly along the length direction of the missile, and the second supporting part can reciprocate linearly under the action of the moving part; The lifting mechanism comprises a lifting frame, a lifting through hole is formed in a first supporting portion, one end of the lifting frame penetrates through the lifting through hole and is connected with a feeding piece, a control rack is arranged on one side, away from the first supporting portion, of the feeding piece, the control rack can be meshed with the control gear when the feeding piece moves to two positions between the vibration test tables, the lifting frame drives the control rack to descend to one side, deviating from the missile, of the lifting frame, and the control rack drives the control gear to rotate under the descending action of the lifting frame so as to drive the bent strips to clamp the missile to be tested.
  2. 2. The comprehensive stress-based missile full-bullet double-platform parallel excitation reliability test device according to claim 1, wherein a limit column is arranged on a rotating path of the bent strip, which deviates from the missile.
  3. 3. The comprehensive stress-based missile full-bullet double-platform parallel excitation reliability test device according to claim 1, wherein the lifting frame comprises a vertical portion and a transverse portion, one end of the vertical portion is connected with the transverse portion, and the other end of the vertical portion penetrates through the lifting through hole to be connected with the feeding piece.
  4. 4. The comprehensive stress-based missile full-bullet double-platform parallel excitation reliability test device according to claim 3, wherein a driving motor is arranged on the first supporting portion, a lifting rack is arranged on the vertical portion, the lifting rack is meshed with a driving gear of the driving motor, and the vertical portion moves in a lifting mode along the height direction of the vibration test platform under the meshing action of the driving motor and the lifting rack.
  5. 5. The comprehensive stress-based missile full-bullet double-platform parallel excitation reliability test device is characterized in that the feeding piece is in a horizontal frame shape, and the central hollowed-out area of the feeding piece corresponds to the position of the clamping gear.
  6. 6. The comprehensive stress-based missile full-elastic double-platform parallel excitation reliability test device is characterized by further comprising a test box, wherein the test assembly and the feeding assembly are arranged in the test box, one side, far away from the missile, of the vibration test bed is fixed on the side wall of the test box, a temperature control unit and a humidity control unit are further arranged in the test box, and the temperature control unit and the humidity control unit can respectively control the temperature and the humidity in the test box.

Description

Missile full-missile double-platform parallel excitation reliability test device based on comprehensive stress Technical Field The specification relates to the technical field of missile testing, in particular to a missile full-missile double-platform parallel excitation reliability test device based on comprehensive stress. Background It is known that among many types of missiles, ground-air missiles and air-air missiles (missiles launched from aircrafts to attack aerial targets) are one of the most complex missiles in the encountered vibration environment, the ground-air missiles and the air-air missiles can encounter power environments such as hanging vibration in the process of launching to flying, the complex external force is one of important factors causing the failure of missile launching, and as the ground-air missiles and the air-air missiles generally pass through the stages of transportation, storage and use in the whole life time from delivery to launching to flying to targets, the ground-air missiles and the air-air missiles can be influenced by various environmental factors, besides the factors such as temperature, damp and heat, the power such as inevitable vibration and impact, the severity and durability caused by the hanging vibration are most important, and if the missiles are stationary, various parameters of the ground-air missiles are normal, and once the missiles are launched, whether the performance is still good or not can be predicted, and an instrument capable of simulating the various power environments suffered after the missiles are launched is needed. The function exerted by the vibration platform is exactly a simulation test device; at present, the use steps of the device for missile testing in the prior art comprise a plurality of steps of feeding, clamping, testing, clamping releasing, discharging and the like, and when testing is performed, a plurality of missiles in each batch are usually required to be sampled for testing, a large number of missiles are required to be tested every day, and the use steps are troublesome in operation, so that the testing efficiency is greatly reduced. Disclosure of Invention The purpose of this specification is to provide a missile full-bullet double-platform parallel excitation reliability test device based on comprehensive stress, and it can solve. The embodiments of the present specification are implemented as follows: the missile full-bullet double-platform parallel excitation reliability test device based on comprehensive stress is used for testing a missile and comprises a test component and a feeding component; The test assembly comprises a plurality of vibration test tables and a clamping mechanism, the test wall of each vibration test table is abutted with the side wall of the missile along the length direction of the missile, and the clamping mechanism is arranged on one side, close to the missile, of each vibration test table; The feeding assembly comprises a lifting mechanism, a moving part and a feeding part, wherein the feeding part is used for placing a missile to be tested, the lifting mechanism can be lifted to the position above the testing wall of the vibration test bench, the moving part can be used for moving the feeding part to the position of the testing wall of the vibration test bench, and the lifting mechanism can be lowered to the position of the testing wall of the vibration test bench so that the lateral wall of the missile to be tested along the length direction of the missile is abutted to the testing wall. Embodiments of the present description have at least the following advantages or benefits: Compared with the prior art, the missile full-elastic double-platform parallel excitation reliability test device based on comprehensive stress has the advantages that the feeding assembly is arranged, the lifting mechanism and the moving part are matched to move for feeding and discharging, the steps of feeding, discharging and the like during testing can be greatly simplified, and accordingly the testing efficiency is effectively improved. Moreover, through setting up material loading subassembly and test module, can be at the in-process that a guided missile carries out vibration test, material loading subassembly still can carry out the unloading to the guided missile that last test was accomplished and carry out the material loading preparation to next guided missile that awaits measuring, and it is apparent that the above-mentioned device has degree of automation height and the advantage that test efficiency is high. Drawings In order to more clearly illustrate the technical solutions of the embodiments of the present description, the drawings that are needed in the embodiments will be briefly described below, it being understood that the following drawings only illustrate some embodiments of the present description and should therefore not be considered as limiting the scope, and that other related drawings m