CN-122009477-A - Unmanned aerial vehicle undercarriage buffer

CN122009477ACN 122009477 ACN122009477 ACN 122009477ACN-122009477-A

Abstract

The invention discloses an unmanned aerial vehicle landing gear buffer which comprises a buffer support column module, a damping module and an inflation valve, wherein the buffer support column module comprises an outer cylinder end cover, an outer cylinder comprising an upper section of the outer cylinder, more than one lengthened section of the outer cylinder, a piston rod and a lower shaft sleeve, one end of the lengthened section of the outer cylinder is fixed with the upper section of the outer cylinder through sealing threads, the other end of the lengthened section of the outer cylinder is fixed with the upper section of the outer cylinder through sealing threads, the lower shaft sleeve is tightly assembled with the upper section of the outer cylinder through a sealing ring I, the piston rod is slidably connected with the lower shaft sleeve through a plurality of sealing rings II, the inflation valve is fixed on a port of the piston rod, which is positioned at the outer end of the outer cylinder, the damping module is fixed on a port of the inner end of the outer cylinder through threads, and hydraulic oil and nitrogen which are mutually communicated are filled in an inner cavity of the outer cylinder and an inner cavity of the piston rod. The invention has the advantages of modularized design, flexibility in the aspects of manufacturing, maintaining, upgrading, adapting to different machine types, and the like, strong universality, low production cost, high production efficiency, simple and convenient maintenance and replacement and low cost.

Inventors

GAO JIANQIANG

Assignees

保定向阳航空精密机械有限公司

Dates

Publication Date: 20260512
Application Date: 20251226

Claims (6)

1. The landing gear buffer of the unmanned aerial vehicle is characterized by comprising a buffer support column module, a damping module and an inflatable valve, wherein the buffer support column module comprises an outer cylinder, an outer cylinder end cover, a piston rod and a lower shaft sleeve, the outer cylinder comprises an upper section of the outer cylinder and more than one outer cylinder extension section, when the number of the outer cylinder extension sections is more than 2, the outer cylinder extension sections are sequentially fixed together in a sealing threaded mode, one end of the outer cylinder extension section or the outer cylinder extension section fixed together is fixed together with the upper section of the outer cylinder in a sealing threaded mode, the other end of the outer cylinder extension section or the outer cylinder extension section fixed together is fixed together with the outer cylinder end cover in a sealing threaded mode, the lower shaft sleeve is tightly assembled with the upper section of the outer cylinder through a sealing ring I, the piston rod is slidably connected with the lower shaft sleeve through a plurality of sealing rings II, the inflatable valve is fixed on the opening of the piston rod, the damping module is fixed on the opening of the outer cylinder, and the inner cavity of the outer cylinder of the buffer support column module is filled with hydraulic oil and nitrogen which are mutually communicated.
2. The unmanned aerial vehicle landing gear buffer of claim 1, wherein the damping module comprises a damping valve and a bolt, the damping valve is a blanking cover with external threads matched with the internal threads of the end part of the piston rod, and an oil through hole which is vertically communicated with the inside is formed in the center of the blanking cover.
3. The landing gear buffer of the unmanned aerial vehicle of claim 2, wherein an electric regulating valve capable of regulating the size of the oil through hole is arranged in the oil through hole of the bolt.
4. The landing gear buffer for the unmanned aerial vehicle according to claim 1, 2 or 3, wherein the air charging valve comprises an end plug provided with external threads matched with the internal threads of the end part of the piston rod, an end plug cover and a one-way valve, the end plug is provided with a central oil hole, the one-way valve is arranged in the central oil hole, the end plug threads are sealed and fixed on the piston rod, and the end plug cover is detachably fixed on the end plug.
5. The unmanned aerial vehicle landing gear buffer of claim 4, wherein a dust ring is further installed between the end of the lower shaft sleeve and the piston rod.
6. The unmanned aerial vehicle landing gear buffer of claim 1, 2 or 3, wherein a dust ring is further installed between the end of the lower shaft sleeve and the piston rod.

Description

Unmanned aerial vehicle undercarriage buffer Technical Field The invention belongs to the technical field of manufacturing of unmanned aerial vehicle landing gears, and relates to an unmanned aerial vehicle landing gear buffer. Background The landing gear is a special device for running and parking an airplane, and needs to bear static load and dynamic load generated by contact of the airplane with the ground, so as to play a role in supporting and protecting the machine body. Landing gear relies on the buffer to absorb landing impact energy, and the performance of the landing gear has a decisive influence on the taking-off and landing performance of the aircraft. Most aircraft use oil-gas type buffers, which have the highest efficiency and the best work load absorbing capacity among all types of buffers, but the structure of the existing oil-gas type buffers is suitable for large aircraft and is not suitable for small unmanned aircraft. Unmanned aerial vehicle is explosive development in recent years, and the wide application is in each field, and the model is more, but current unmanned aerial vehicle undercarriage buffer structure often is integrated design, has a great deal of inconvenience in aspects such as manufacturing, maintenance, upgrading and adaptation different models, need disassemble the maintenance to whole buffer when a certain subassembly damages, and maintenance time is long and with high costs. When buffer parameter adjustment or function upgrade is performed for different aircraft models, the whole buffer structure is often required to be redesigned, and flexibility and universality are lacking. Disclosure of Invention The invention aims to solve the problems in the prior art and provide the unmanned aerial vehicle landing gear buffer which is of modular design, flexible in manufacturing, maintenance, upgrading, adapting to different machine types and the like, high in universality, low in production cost, high in production efficiency, simple and convenient to maintain and replace and low in cost. The technical scheme is that the unmanned aerial vehicle landing gear buffer comprises a buffer support column module, a damping module and an air inflation valve, wherein the buffer support column module comprises an outer cylinder, an outer cylinder end cover, a piston rod and a lower shaft sleeve, the outer cylinder comprises an upper outer cylinder section and more than one outer cylinder extension section, when the number of the outer cylinder extension sections is more than 2, the outer cylinder extension sections are sequentially fixed together in a sealing threaded mode, one end of the outer cylinder extension sections or one end of the outer cylinder extension sections fixed together are fixed together in a sealing threaded mode with the upper outer cylinder section, the other end of the outer cylinder extension sections or the other end of the outer cylinder extension sections fixed together in a sealing threaded mode with the outer cylinder end cover, the lower shaft sleeve is tightly assembled with the upper outer cylinder section through a sealing ring I, the piston rod is slidably connected with the lower shaft sleeve through a plurality of sealing rings II, the air inflation valve is fixed on the opening of the outer end of the piston rod, the damping module is fixed on the opening of the inner cylinder in a threaded mode, and the inner cavity of the outer cylinder and the inner cavity of the buffer support column module is filled with hydraulic oil and nitrogen which are mutually communicated. Further preferably, the damping module comprises a damping valve and a bolt, wherein the damping valve is a blanking cover with external threads matched with the internal threads at the end part of the piston rod, the center of the blanking cover is provided with a center hole with an internal threaded hole and an external oil passing hole, the bolt is installed in the threaded hole of the blanking cover in a threaded mode, and the bolt is provided with an oil passing hole which is vertically communicated with the center hole of the blanking cover. The damping module is fixed on the piston rod through threads, is easy to detach, and is simple and convenient to maintain and replace and low in cost. Preferably, an electric regulating valve capable of regulating the size of the oil through hole is arranged in the oil through hole of the bolt. The electric regulating valve adopts an electric control mode, and can automatically regulate the size of the damping hole according to the landing state of the aircraft according to a preset control logic. Further preferably, the inflation valve comprises an end plug, an end plug cover and a one-way valve, wherein the end plug is provided with an external thread matched with the internal thread at the end part of the piston rod, the end plug is provided with a central oil hole, the one-way valve is arranged in the central oil hole, the end plug thread