40results about How to "Easy to disassemble repeatedly" patented technology

The invention discloses a spacecraft fluid path breakout connector dual-set synchronous separation device and belongs to the technical field of spacecrafts. The spacecraft fluid path breakout connector dual-set synchronous separation device comprises two sets of separation power components, a fixed base, a separation bracket, an outer guiding barrel, an inner guiding barrel, a separation nut and a connecting screw rod; the separation power components are used for providing power for separating the bracket from the fixed base; an installation plate of the separation bracket is tightly pressed on the fixed base; the inner guiding barrel is fixed into a rectangular frame body of the separation bracket, and the outer guiding barrel is installed on the outer circumferential face of the inner guiding barrel in a sleeving mode; the separation nut is installed in the inner guiding barrel, one end of the separation nut is fixed to the top of the rectangular frame body of the separation bracket, and the other end of the separation nut is connected with the connecting screw rod; and the two separation power components are symmetrically installed on the two sides of the separation nut, and the two ends of each separation power component are fixedly connected with the separation bracket and the fixed base correspondingly. The spacecraft fluid path breakout connector dual-set synchronous separation device can autonomously achieve whole translation pull-disengagement separation of cabin liquid path detachable connectors in advance before cabin section separation of a spacecraft.

The invention relates to a test detection device for a joint bearing, belonging to the technical field of engineering machine test equipment. The joint bearing and a connecting shaft are arranged in an inner hole of a loading bracket in an interference fit way; two ends of the connecting shaft are fixed inside a following shaft sleeve and a rotary sleeve by using an expansion sleeve; the following shaft sleeve and the rotary sleeve are arranged in inner holes of double-row conical roller bearings; the double-row conical roller bearings are arranged on bearing seats at the two ends; and the bearing seats at the two ends are fixed on a base through guide blocks. The test detection device has the advantages of novel structure, high reliability, convenience for repeated assembly and disassembly, suitability for testing bearings of different specifications and capability of detecting the friction coefficient and the service life of the joint bearing and measuring the temperature change of the joint bearing under repeated load.

A device for connecting two components, comprising at least one foot (12) having a fastening hole (14) to which at least one bracket (16) is connected, said device also comprising means for receiving a fastening pin (54 ) of the pin socket (22), the fastening pin (54) can pass through the fastening hole (14), wherein a receiving groove (30) for receiving the first component is formed between the leg and the pin socket (22), wherein , the foot (12) has at least one engaging surface (52) for engaging the second assembly on its side facing away from the receiving groove (30), wherein in each case there are at least two guide rods (34, 36) Extending along opposite sides of the pin socket (22), these guide rods connect the pin socket to the bracket so that the pin socket can move elastically axially.

The invention provides a wire clamp and an electronic device using the wire clamp. The wire clamp is used for holding a wire. The wire clamp comprises a main body, a wire hook structure and an elastic sheet part, wherein the wire hook structure is connected with the main body, the elastic sheet part is connected with the main body and has a through-hole, and the elastic sheet part can be bended relative to the main body to move towards the main body, so as to allow the wire hook structure to partially pass through the through-hole. The wire is clamped between the elastic sheet part and the wire hook structure which partially passes through the through-hole. The wire clamp is mainly applied to the common wire arrangement as well as wire layout in electronic devices. The wire clamp has simple structure and low requirements for structure and material, therefore, the forming difficulty is low, the fabrication is facilitated and the occurrenceof structural function failures can be avoided mostly. The wire clamp provided by the invention can be used as a standard part.

The invention discloses a connector fixing structure and a fan fixing frame. The connector fixing structure comprises a structural wall, an elastic limiting piece and a connector body. The structure wall is provided with an installation hole and a sliding connection structure located on the edge of the installation hole. The elastic limiting piece is arranged on the structural wall close to the mounting hole. The connector body is provided with another sliding connection structure and a limiting part. The two sliding connection structures are connected in a sliding mode so that the connector body can be arranged at a preset position, the elastic limiting piece can restrain the limiting part, and the connector body can be fixed to the installation hole. Afterwards, the elastic limiting piece can be operated so that the elastic limiting piece can be separated from the limiting part, and the connector body is allowed to slide away from the preset position. A fan fixing frame forms a fan installation space and comprises the connector fixing structure. The connector body is exposed out of the fan installation space.

The invention provides a landing gear aerodynamic load test device and a design method thereof. The landing gear aerodynamic load test device includes a mounting frame and a loading device; the loading device is provided with an application point, and the mounting frame is provided with a loading point; in static state, the loading point is aligned with the center of the landing gear axle. The position of the point on the lateral and vertical projection planes corresponds; driven by the applied point, the loading point can be displaced laterally, heading, and vertically, and the displacement track of the loading point is consistent with the landing gear Displacement trajectory matching. Compared with the related technology, the aerodynamic load test device of the landing gear provided by the present invention truly simulates the retraction and retraction of the landing gear under the influence of the aerodynamic load; the structure is novel, the reliability is high, and repeated disassembly and assembly are convenient.