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CN-121589595-B - Assembly process for strengthening target drone

CN121589595BCN 121589595 BCN121589595 BCN 121589595BCN-121589595-B

Abstract

The application provides an assembly process for a reinforced target drone, which relates to the technical field of assembly of composite material target drone bodies, and comprises the steps of assembling the reinforced target drone by an assembly fixture, wherein the assembly fixture comprises a lower fixing device, an upper fixing device, a mold clamping device, a wing positioning device, a horizontal tail positioning device and a fuselage limiting device, and the assembly process comprises the steps of pre-treating an upper fuselage skin and a lower fuselage skin after demolding; and (3) positioning the lower fixing device and the machine body limiting device through a positioning pin, then connecting through a bolt, reserving a clamping gap of 5mm, and placing the pretreated lower machine body skin into the lower fixing device. The application provides an assembly process for a reinforced target drone, which effectively reduces the total manual consumption in the assembly process, has high overall strength of the assembled reinforced target drone and high use reliability, and does not need secondary grinding.

Inventors

  • DING FENG
  • YANG YISHUO
  • LI BAOLU

Assignees

  • 北京海利天梦科技有限公司
  • 天津锋明无人机科技有限公司

Dates

Publication Date
20260512
Application Date
20260130

Claims (7)

  1. 1. An assembly process for a reinforcement target machine, wherein the assembly process assembles the reinforcement target machine (200) through an assembly fixture (100), the assembly fixture (100) comprising a lower fixing device (110), an upper fixing device (120), a mold clamping device (130), a wing positioning device (140), a horizontal tail positioning device (150) and a fuselage limiting device (160), the assembly process comprising: The upper fuselage skin (210) and the lower fuselage skin (220) are subjected to pretreatment after being demoulded; connecting the lower fixing device (110) with the machine body limiting device (160) through a positioning pin, connecting the lower fixing device with the machine body limiting device (160) through a bolt (170) and reserving a 5mm clamping gap, placing the pretreated lower machine body skin (220) into the lower fixing device (110) so as to support the lower machine body skin (220) through a support bracket (111) of the lower fixing device (110), and locking the 5mm clamping gap between the lower fixing device (110) and the machine body limiting device (160); The method comprises the steps of performing bonding pretreatment on a plurality of first connecting metal pieces and a plurality of first partition frames, bonding the first connecting metal pieces and the first partition frames on the inner surface of a lower fuselage skin (220) after the bonding pretreatment is finished, respectively connecting and clamping a plurality of first connecting metal pieces and the first partition frames with a lower fuselage skin (220) through a plurality of positioning frames (121) of an upper fixing device (120) and a flat tail positioning device (150) by using positioning pins and positioning rear bolts (170), and simultaneously connecting a plurality of fuselage limiting devices (160) with a first partition frame by bolts; curing the device which is positioned by the positioning pin and is connected and clamped by the bolt (170) at room temperature according to a preset time, and detaching the upper fixing device (120) from the horizontal tail positioning device (150) after the curing is finished; Coating glue on the inner surface of the upper fuselage skin (210), and then bonding the upper fuselage skin with a plurality of first connecting metal pieces and a plurality of first separation frames so as to be in butt joint with the lower fuselage skin (220) placed on the lower fixing device (110); the die clamping device (130) is clamped and connected with the lower fixing device (110) through bolts (170) after being positioned by using positioning pins; Connecting a plurality of positioning frames (121) with the mold clamping device (130) from the upper part of the upper fuselage skin (210) to mold the upper fuselage skin (210) and the lower fuselage skin (220), wherein two positioning frames (121) in the plurality of positioning frames (121) are respectively in clamping connection with the horizontal tail positioning device (150) and the wing positioning device (140) through bolts (170) after being positioned by using positioning pins; the horizontal tail positioning device (150) is connected with the horizontal tail connecting metal piece through a positioning pin; And after the devices of the assembly fixture (100) are positioned and clamped by bolts (170), performing room-temperature curing according to preset time, and after the curing is finished, removing the devices of the assembly fixture (100) so as to take out the reinforcement target machine (200) from the assembly fixture (100).
  2. 2. The assembly process according to claim 1, wherein said applying glue to the inner surface of said upper fuselage skin (210) is followed by bonding with a plurality of first connecting metal pieces and a plurality of first formers to interface with said lower fuselage skin (220) placed on said lower fixture (110), previously comprising: and carrying out bonding pretreatment on the plurality of first connecting metal pieces, the plurality of first bulkhead frames and the upper fuselage skin (210).
  3. 3. The assembly process according to claim 1, wherein said clamping connection of said clamping device (130) to said lower fixture (110) by means of bolts (170) after positioning using positioning pins, comprises: the clamping device (130) and the two matching plates (112) of the lower fixing device (110) are clamped and connected through bolts (170) after being positioned through positioning pins.
  4. 4. The assembly process according to claim 1, wherein the horizontal tail positioning device (150) is connected to the horizontal tail connecting metal piece by a positioning pin, comprising: positioning the horizontal tail positioning device (150) and the lower fixing device (110) through positioning pins; And positioning the horizontal tail positioning device (150) positioned with the lower fixing device (110) through a positioning pin, positioning the horizontal tail connecting metal piece through the positioning pin, and connecting and clamping through a bolt (170).
  5. 5. The assembly process of claim 1, wherein the predetermined time of room temperature curing is at least 12 hours.
  6. 6. The assembly process according to claim 1, wherein the pretreatment is to trim burrs or burrs of the upper fuselage skin (210) and the lower fuselage skin (220) after demolding, and to polish the bonding surfaces of the upper fuselage skin (210) and the lower fuselage skin (220).
  7. 7. The assembly process according to claim 1, characterized in that the connection gap between the plurality of devices of the assembly fixture (100) is not more than 0.1mm.

Description

Assembly process for strengthening target drone Technical Field The application relates to the technical field of assembly of composite material target drone bodies, in particular to an assembly process for reinforcing a target drone. Background There are currently two general ways in which conventional composite drones, i.e. reinforced drones, are assembled. One is the positioning and folding of the forming die. The other is that the free state is closed after the machine body is demolded. The forming die is positioned and folded to be a matrix which uses the die body as an assembly tool and is used for fixing the target machine body. And then scribing and positioning the setting position of the inner bulkhead by using a caliper and a tape measure. And then guiding and positioning the upper machine body and the lower machine body through forming dies, and closing the upper machine body and the lower machine body by using the self weight of the dies. Because this kind of organism forming die is steel generally, and the mould weight is more than 1T generally, consequently the present traditional assembly organism folds the mode and has the potential safety hazard when folding, causes the volume task volume of product processing volume huge moreover, and the cost is higher. And the machine body is assembled by tools such as a steel plate ruler, a caliper and the like, so that the positioning accuracy is inaccurate, and when the subsequent machine body is matched with other target machine body components such as wings, tail wings and the like, the one-time assembly can not be successfully realized due to the size deviation. And the body parts are subjected to a grinding treatment, thereby causing a scrapping risk. And the upper and lower machine body is once only closed, and the bulkhead after scribing and positioning is freely placed in the closing process, and when the forming die is closed, the reinforcing bulkhead can run due to the weight of the die, so that the overall strength of the reinforced target machine after closing is reduced. The free state closure after the machine body is demolded is that the traditional composite material target machine body is assembled, after the product is demolded, the upper machine body and the lower machine body of the product are positioned and reserved for positioning closure under the free state, the upper machine body and the lower machine body are pressurized by using clamps such as F clamps, C clamps and the like, a plurality of machine body inner partition frames are used for marking and positioning the inner partition frames by using calipers or measuring tape, and then the positioning and bonding are carried out by quick-drying glue. The assembly mode causes inaccurate positioning accuracy of the bulkhead through tools such as a steel plate ruler, a caliper and the like, can not be assembled at one time when a subsequent machine body is adapted to other target machine body components such as wings, tail wings and the like, and even has scrapping risks through grinding treatment. And the quick-drying adhesive is used for fixing the spacer frame, so that the spacer frame can possibly deviate due to external pressure in the die assembly process, and the overall strength of the reinforced target aircraft after die assembly is reduced. Disclosure of Invention The application aims at solving the problems and provides an assembly process for a reinforced target machine, wherein a plurality of devices of an assembly tool are accurately positioned and stably connected, the reinforced target machine can be separated from a forming die to be folded, the overall strength of the assembled reinforced target machine is high, the use reliability is high, and secondary grinding is not needed to be carried out subsequently. The application provides an assembly process for a reinforcement target aircraft, which comprises the steps of assembling the reinforcement target aircraft through an assembly tool, wherein the assembly tool comprises a lower fixing device, an upper fixing device, a mold clamping device, a wing positioning device, a horizontal tail positioning device and a fuselage limiting device, the assembly process comprises the steps of pre-treating an upper fuselage skin and a lower fuselage skin after demolding, connecting the lower fixing device with the fuselage limiting device through positioning pins and reserving a 5mm clamping gap after positioning through bolts, placing the lower fuselage skin after the pre-treatment into the lower fixing device so as to support the lower fuselage skin through a support bracket of the lower fixing device, locking a 5mm clamping gap between the lower fixing device and the fuselage limiting device, bonding a plurality of first connecting metal pieces and a plurality of first spacer frames after the bonding pretreatment is finished, bonding a plurality of positioning frames of the upper fixing device with the lower fuselage skin t