阅读说明：本技术 航天器分离插头的机械分离钢锁机构及安装方法 (Mechanical separation steel lock mechanism of spacecraft separation plug and installation method ) 是由 王益军 张朋松 徐天水 刘未科 于 2020-06-11 设计创作，主要内容包括：本发明提供了一种航天器分离插头的机械分离钢锁机构,包括钢丝绳、压接套和分离挂钩,所述钢丝绳的第一端与航天器分离插头连接后通过第一压接套压紧固定,第二端与分离挂钩连接后通过第二压接套压紧固定；所述分离挂钩通过紧固件和运载仪器舱的机械装置连接；当航天器与运载仪器舱分离时通过机械分离钢锁机构拉开分离插头,实现航天器和运载仪器舱的机械分离。本发明的航天器分离插头的机械分离钢锁机构不但具有结构简单、成本低、可靠性高、安装操作简便的优点,而且通过在钢丝绳两端增加压接套来控制拉力方向,能够使得分离插头瞬时所受的拉力最大化,比传统钢丝绳直接连接方式更可靠。(The invention provides a mechanical separation steel lock mechanism of a spacecraft separation plug, which comprises a steel wire rope, a crimping sleeve and a separation hook, wherein the first end of the steel wire rope is connected with the spacecraft separation plug and then is fixedly crimped by the first crimping sleeve, and the second end of the steel wire rope is connected with the separation hook and then is fixedly crimped by the second crimping sleeve; the separation hook is connected with a mechanical device of the carrier cabin through a fastener; when the spacecraft is separated from the carrier instrument cabin, the separation plug is pulled open through the mechanical separation steel lock mechanism, so that the mechanical separation of the spacecraft and the carrier instrument cabin is realized. The mechanical separation steel lock mechanism of the spacecraft separation plug has the advantages of simple structure, low cost, high reliability and simplicity and convenience in installation and operation, and the tension direction is controlled by adding the crimping sleeves at the two ends of the steel wire rope, so that the instantaneous tension borne by the separation plug can be maximized, and the mechanical separation steel lock mechanism is more reliable than a traditional direct connection mode of the steel wire rope.)

1. The mechanical separation steel lock mechanism of the spacecraft separation plug is characterized by comprising a steel wire rope (1), a crimping sleeve (2) and a separation hook (3), wherein the first end of the steel wire rope (1) is connected with the spacecraft separation plug (8) and then is pressed and fixed through a first crimping sleeve (21), and the second end of the steel wire rope is connected with the separation hook (3) and then is pressed and fixed through a second crimping sleeve (22);

the separation hook (3) is connected with a mechanical device of the carrier cabin through a fastener; when the spacecraft is separated from the carrier cabin, the separation plug (8) is pulled open through the mechanical separation steel lock mechanism, so that the mechanical separation of the spacecraft and the carrier cabin is realized.

2. A mechanical separation steel lock mechanism of a spacecraft separation plug according to claim 1, characterized in that one end of the first crimp sleeve (21) close to the separation plug (8) is an a-end and the other end is a B-end; the first end of the steel wire rope (1) penetrates in from the end B of the first crimping sleeve (21), penetrates out from the end A, penetrates in from the end B, penetrates out from the end A, penetrates in from the end A after penetrating through the separating plug (8), penetrates out from the end B, penetrates in from the end A, and penetrates out from the end B; the length of the first end which finally penetrates out of the end B is controlled to be 5 mm-10 mm.

3. A mechanical separation steel lock mechanism of a spacecraft separation plug according to claim 1, characterized in that one end of the second crimp sleeve (22) close to the separation hook (3) is a C-end and the other end is a D-end; the second end of the steel wire rope (1) penetrates in from the end D of the second crimping sleeve (22), penetrates out from the end C, penetrates in from the end D, penetrates out from the end C, penetrates in from the end C after penetrating through the separating hook (3), penetrates out from the end D, penetrates in from the end C, and penetrates out from the end D; the length of the second end which finally penetrates out of the D end is controlled to be 5 mm-10 mm.

4. The mechanical separation steel lock mechanism of the spacecraft separation plug according to claim 1, characterized in that the separation hook (3) is of a U-shaped structure and comprises two side edges (31) and a bowtie-shaped connecting portion (32), a through hole (311) with the diameter of 3.2mm is formed in each of the two side edges (31) for installing a fastener, the length of each side edge (31) is 18mm, the width of each side edge is 8mm, the thickness of each side edge is 4mm, and arc-shaped grooves are formed in two sides of the bowtie-shaped connecting portion (32) in a concave manner so as to fix the steel wire rope (1).

5. A mechanical release steel lock mechanism of a spacecraft release plug according to claim 4, wherein the release hook (3) is made of 1Cr18Ni9 Ti.

6. The mechanical separation steel lock mechanism of the spacecraft separation plug of claim 4, characterized in that the fastening piece is a nut (4) and a screw (7), and the screw (7) passes through the through hole (311) on the two sides (31) of the separation hook and the mechanical device of the carrier bay and then is fixed with the nut (4);

between the outer sides of the through hole (311) and the nuts (4) and the screws (7), flat washers (5) and spring washers (6) are arranged, and between the outer sides of the through hole (311) and the spring washers (6), the flat washers (5) are arranged.

7. The mechanical separation steel lock mechanism of the spacecraft separation plug according to claim 1, wherein the steel wire rope (1) is made of stainless steel, the length of the steel wire rope (1) is 20mm to 30mm longer than the actual required length when the steel wire rope is installed, and the material of the crimping sleeve (2) is titanium alloy.

8. Mechanical release steel lock mechanism of a spacecraft release plug according to claim 1 or 7, characterised in that the crimp sleeve (2) is a tubular cylinder with a length of 50mm, an inner bore diameter of 2.6mm and a wall thickness of 1.2 mm.

9. A mechanical release steel lock mechanism of a spacecraft release plug according to claim 8, wherein the material of the crimping sleeve (2) is 1Cr18Ni9 Ti.

10. A method for installing a mechanical separation steel lock mechanism of a spacecraft separation plug is characterized by comprising the following steps:

s1, hanging a weight of 20kg +/-2 kg for 30S on the steel wire rope (1), after detection, shearing a section of steel wire rope not more than 1m to be assembled with the crimping sleeve (2) to form a forced demoulding mechanism for tensile test, wherein the steel wire rope is qualified when the steel wire rope is not less than 50kg, and shearing a qualified steel wire rope (1) into a section for later use;

s2, the separation hook (3) is connected with the delivery instrument cabin through a nut (4), a flat washer (5), a spring washer (6) and a screw (7);

s3, connecting the first end of the steel wire rope (1) with a separation plug (8) of the spacecraft through a first crimping sleeve (21), controlling the final penetrating length of the first end of the steel wire rope (1) to be 5-10 mm, and winding a blue adhesive tape on the penetrating part of the first end of the steel wire rope (1);

s4, vertically pulling down the second end of the steel wire rope (1), connecting the second end of the steel wire rope (1) to the separation hook (3) through a second crimping sleeve (22), controlling the final penetrating length of the second end of the steel wire rope (1) to be 5-10 mm, and winding a blue adhesive tape on the penetrating part of the second end of the steel wire rope (1);

s5, measuring the length of the steel wire rope (1) which is vertically pulled down, and controlling the length allowance within the range of 20 mm-30 mm.

Technical Field

The invention relates to the technical field of aerospace assembly processes, in particular to a mechanical separation steel lock mechanism of a spacecraft separation plug and an installation method.

Background

The separation plug is used as an important device for wired signal transmission between the spacecraft and the ground test equipment, and has the function of playing a role. During the on-orbit period, once the separation fails, the spacecraft and the carrier cannot be separated, and the result is extremely heavy, which can cause the failure of the whole launching task.

At present, two guarantee measures of electrical separation and mechanical separation are adopted for separation of the separation plug, the mechanical separation is used as one guarantee measure for separation of the separation plug between the spacecraft and the carrier, normal separation of the separation plug can be guaranteed under the condition that the electrical separation of the separation plug fails, and the separation plug has an extremely important function.

The traditional mechanical separation steel cable mechanism generally directly adopts a steel cable to connect a separation plug and a carrying instrument cabin, and the mechanical separation is realized by transmitting the carried pulling force to the separation plug through the steel cable in the mechanical separation process. In the mode, the steel wire rope is only restrained by the fixing points at the two ends, and the tension acted by the carrying does not act on the separation plug vertically in the tension transmission process (the length allowance of the steel wire rope and the vibration in the launching process can influence the direction of the instantaneous tension), so that the maximization of the instantaneous tension borne by the separation plug cannot be realized.

Through the search of the prior art, the invention patent with application publication number CN 103615450A discloses a spacecraft unlocking and separating device, which mainly comprises a full-thread hexagon head bolt and a stud with one end provided with an external thread and the other end provided with a threaded hole, wherein a section of blind hole is drilled on the bolt from the center of the hexagon head, a heating rod is placed in the blind hole of the bolt, the bolt can be inserted into the internal thread of the stud, hot melt adhesive is filled between the external thread of the bolt and the internal thread of the stud, and the bolt and the stud are fixedly connected together through the hot melt adhesive. The hot melt adhesive is melted in an electric heating mode to unlock the two connecting pieces during separation, and the mode of separation is realized in a hot melt adhesive solidification and melting mode, so that the reliability is poor, a heating device is required to be added for heating and unlocking, the structure is complicated, and the separation plug is not suitable for separation of the spacecraft separation plug.

Disclosure of Invention

Aiming at the defects in the prior art, the invention aims to provide a mechanical separation steel lock mechanism of a spacecraft separation plug and an installation method.

The purpose of the invention is realized by the following scheme:

the invention provides a mechanical separation steel lock mechanism of a spacecraft separation plug, which comprises a steel wire rope, a crimping sleeve and a separation hook, wherein the first end of the steel wire rope is connected with the spacecraft separation plug and then is fixedly crimped by the first crimping sleeve, and the second end of the steel wire rope is connected with the separation hook and then is fixedly crimped by the second crimping sleeve;

the separation hook is connected with a mechanical device of the carrier cabin through a fastener; when the spacecraft is separated from the carrier instrument cabin, the separation plug is pulled open through the mechanical separation steel lock mechanism, so that the mechanical separation of the spacecraft and the carrier instrument cabin is realized.

Preferably, one end of the first crimping sleeve, which is close to the separation plug, is an end a, and the other end of the first crimping sleeve is an end B; the first end of the steel wire rope penetrates through the end B of the first crimping sleeve, penetrates out of the end A, penetrates through the end B, penetrates out of the end A, penetrates through the end A after penetrating through the separation plug, penetrates out of the end B, penetrates through the end A, and penetrates out of the end A and the end B; the length of the first end which finally penetrates out of the end B is controlled to be 5 mm-10 mm.

Preferably, one end of the second crimping sleeve, which is close to the separation hook, is a C end, and the other end of the second crimping sleeve is a D end; the second end of the steel wire rope penetrates through the end D of the second crimping sleeve, penetrates out of the end C, penetrates through the end D, penetrates out of the end C, penetrates through the separating hook and penetrates through the end C, penetrates out of the end D, penetrates through the end C and penetrates out of the end D; the length of the second end which finally penetrates out of the D end is controlled to be 5 mm-10 mm.

Preferably, the separation couple is U type structure, including the connecting portion of two sides and bowknot shape, two set up the through-hole that the diameter is 3.2mm on the side and be used for the installation fastener, the length of side is 18mm, and the width is 8mm, and thickness is 4mm, the interior concave arc recess that forms in connecting portion both sides of bowknot shape is convenient for fixed wire rope.

Preferably, the material of the separation hook is 1Cr18Ni9 Ti.

Preferably, the fastening pieces are nuts and screws, and the screws penetrate through holes in two side edges of the separation hook and mechanical devices of the delivery instrument cabin and are fixed with the nuts;

between the outer sides of the nut, the screw and the through hole, a flat washer and a spring washer are arranged, and between the spring washer and the outer side of the through hole, a flat washer is arranged.

Preferably, the steel wire rope is made of stainless steel, the length of the steel wire rope is 20-30 mm longer than the actually required length during installation, and the crimping sleeve is made of titanium alloy.

Preferably, the crimping sleeve is a tubular cylinder, the length of the crimping sleeve is 50mm, the diameter of an inner hole of the crimping sleeve is 2.6mm, and the wall thickness of the crimping sleeve is 1.2 mm.

Preferably, the material of the crimping sleeve is 1Cr18Ni9 Ti.

The invention provides a method for installing a mechanical separation steel lock mechanism of a spacecraft separation plug, which specifically comprises the following steps:

s1, hanging a weight of 20kg plus or minus 2kg on the steel wire rope for 30S, after detection, shearing a section of steel wire rope not more than 1m and assembling the steel wire rope and the crimping sleeve into a forced demoulding mechanism to carry out a tensile test, wherein the steel wire rope is qualified when the steel wire rope is not less than 50kg, and shearing a section of qualified steel wire rope for later use;

s2, the separation hook is connected with the delivery instrument cabin through a nut, a flat washer, a spring washer and a screw;

s3, connecting the first end of the steel wire rope with a separation plug of the spacecraft through a first crimping sleeve in a double-buckle knotting mode, wherein in the knotting process, the steel wire rope is required to be tightly attached to the first crimping sleeve, a ring formed by double buckles of the steel wire rope is tensioned before the steel wire rope is compressed, after the steel wire rope is compressed, the final penetrating length of the first end of the steel wire rope is controlled to be 5-10 mm, and a blue adhesive tape is wound on the penetrating part of the first end of the steel wire rope;

s4, vertically pulling down the second end of the steel wire rope, connecting the second end of the steel wire rope to a separation hook through a second crimping sleeve in a double-buckle knotting mode, in the knotting process, requiring the steel wire rope to be tightly attached to the second crimping sleeve, tensioning a ring formed by double buckles of the steel wire rope before compression, controlling the final penetrating length of the second end of the steel wire rope to be 5-10 mm after compression, and winding a blue adhesive tape on the penetrating part of the second end of the steel wire rope;

and S5, measuring the length of the steel wire rope which is vertically pulled down, and controlling the length allowance within the range of 20 mm-30 mm.

Compared with the prior art, the invention has the following beneficial effects:

1. the mechanical separation steel lock mechanism of the spacecraft separation plug is simple and easy to assemble and low in cost, only steel wire ropes, the crimping sleeve, the separation hook, the nut, the flat washer, the spring washer and the screw are needed, the common materials are low in cost, the whole assembly process is simple and easy, and the operation is convenient.

2. According to the mechanical separation steel lock mechanism of the spacecraft separation plug, raw materials used for installation are all space mature products, the tensile force borne by the steel wire rope far exceeds the tensile force required by mechanical separation of the separation plug, the two ends of the steel wire rope of the separation steel lock mechanism are both buckled and knotted and then are pressed by the pressing sleeve, and the pressing sleeves at the two ends can ensure that the instantaneous tensile force can be maximally vertically acted on the separation plug, so that the tensile force instantaneously borne by the separation plug is maximized, the separation of the spacecraft and the carrying machine is realized, and the reliability is high. In addition, the length allowance of the steel wire rope is controlled in place, and the problems of breakage, sliding and the like of the steel wire rope are solved.

3. According to the mechanical separation steel lock mechanism of the spacecraft separation plug, the compression joint sleeve and the separation hook are self-made products, the steel wire rope, the nut, the flat washer, the spring washer and the screw are conventional devices, and the devices related to the whole set of mechanism are simple and compact in structure and do not have complex mechanisms and devices.

Drawings

Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:

FIG. 1 is a schematic structural view of a mechanical separation steel lock mechanism of the spacecraft separation plug of the present invention;

FIG. 2 is an enlarged view of a portion of FIG. 1;

FIG. 3 is a front view of a separation hook in the mechanical separation steel lock mechanism of the spacecraft separation plug of the present invention;

FIG. 4 is a side view of a release hook in the mechanical release steel lock mechanism of the spacecraft release plug of the present invention;

FIG. 5 is a top view of a separation hook in the mechanical separation steel lock mechanism of the spacecraft separation plug of the present invention;

FIG. 6 is a perspective view of a separation hook in the mechanical separation steel lock mechanism of the spacecraft separation plug of the present invention;

FIG. 7 is a front view of a press fit sleeve in the mechanically separating steel locking mechanism of the spacecraft separation plug of the present invention;

FIG. 8 is a top view of a crimp sleeve in the mechanically decoupled steel lock mechanism of the spacecraft separation plug of the present invention;

fig. 9 is a perspective view of the crimp sleeve in the mechanical release steel lock mechanism of the spacecraft release plug of the present invention.

Detailed Description

The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.

As shown in fig. 1 to 9, the present invention will be described in further detail with reference to specific embodiments.