CN111750039B - Mechanical separation steel lock mechanism of spacecraft separation plug and installation method - Google Patents
Mechanical separation steel lock mechanism of spacecraft separation plug and installation method Download PDFInfo
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- CN111750039B CN111750039B CN202010531668.4A CN202010531668A CN111750039B CN 111750039 B CN111750039 B CN 111750039B CN 202010531668 A CN202010531668 A CN 202010531668A CN 111750039 B CN111750039 B CN 111750039B
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- 238000000926 separation method Methods 0.000 title claims abstract description 146
- 229910000831 Steel Inorganic materials 0.000 title claims abstract description 124
- 239000010959 steel Substances 0.000 title claims abstract description 124
- 230000007246 mechanism Effects 0.000 title claims abstract description 43
- 238000000034 method Methods 0.000 title claims description 13
- 238000009434 installation Methods 0.000 title abstract description 11
- 238000002788 crimping Methods 0.000 claims abstract description 50
- 230000000149 penetrating effect Effects 0.000 claims description 14
- 230000006835 compression Effects 0.000 claims description 10
- 238000007906 compression Methods 0.000 claims description 10
- 239000002390 adhesive tape Substances 0.000 claims description 5
- 229910001069 Ti alloy Inorganic materials 0.000 claims description 4
- 239000010936 titanium Substances 0.000 claims description 4
- 238000004804 winding Methods 0.000 claims description 3
- 238000001514 detection method Methods 0.000 claims description 2
- 239000010935 stainless steel Substances 0.000 claims description 2
- 229910001220 stainless steel Inorganic materials 0.000 claims description 2
- 238000009864 tensile test Methods 0.000 claims description 2
- 239000000463 material Substances 0.000 description 7
- 239000004831 Hot glue Substances 0.000 description 4
- 238000010438 heat treatment Methods 0.000 description 3
- 238000003825 pressing Methods 0.000 description 3
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000010008 shearing Methods 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000005485 electric heating Methods 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 238000007781 pre-processing Methods 0.000 description 1
- 239000002994 raw material Substances 0.000 description 1
- 230000008054 signal transmission Effects 0.000 description 1
- 238000007711 solidification Methods 0.000 description 1
- 230000008023 solidification Effects 0.000 description 1
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16G—BELTS, CABLES, OR ROPES, PREDOMINANTLY USED FOR DRIVING PURPOSES; CHAINS; FITTINGS PREDOMINANTLY USED THEREFOR
- F16G11/00—Means for fastening cables or ropes to one another or to other objects; Caps or sleeves for fixing on cables or ropes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B45/00—Hooks; Eyes
- F16B45/04—Hooks with sliding closing member
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Ropes Or Cables (AREA)
Abstract
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.
Description
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.
Example 1
The utility model provides a mechanical separation steel lock mechanism of spacecraft separation plug, includes wire rope 1, crimping cover 2 and separation couple 3, and wire rope 1 is used for and separates plug 8, separation couple 3 and connects, and crimping cover 2 is used for the crimping at 1 both ends of wire rope, and is concrete, compresses tightly fixedly through first crimping cover 21 after the first end of wire rope 1 is connected with spacecraft separation plug 8, and it is fixed to compress tightly through second crimping cover 22 after the second end of wire rope 1 is connected with separation couple 3. 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, and when the spacecraft is separated from the delivery instrument cabin, a separation plug is pulled through a mechanical separation steel lock mechanism, so that the mechanical separation of the spacecraft and the delivery instrument cabin is realized.
The material of the crimping sleeve 2, the separating hook 3, the nut 4, the flat washer 5, the spring washer 6 and the screw 7 is titanium alloy, the specification of the nut 4 and the screw 7 is M3, and the specification of the flat washer 5 and the spring washer 6 is matched with that of the nut 4 and the screw 7.
When the steel wire rope is installed, the length of the steel wire rope 1 is 20 mm-30 mm longer than the actual required length, and the material of the pressure welding sleeve 2 is titanium alloy. Preferably, the material of the crimping sleeve 2 is 1Cr18Ni9Ti, the crimping sleeve 2 is a tubular cylinder, the length L11 is 50mm, the chamfer radius R3 is 0.2mm, the inner hole diameter phi 5 is 2.6mm, and the outer diameter phi 4 is 3.8mm (which can be processed according to the actual diameter of the selected steel wire rope).
The material of separation couple 3 is 1Cr18Ni9Ti, for U type structure, connecting portion 32 including two sides 31 and bowtie shape, set up diameter phi 1 on two sides 31 and be used for the installation fastener for 3.2 mm's through-hole 311, the distance L7 of through-hole 311 center and side bottom is 5mm, connecting portion 32 is 14mm with the distance L6 of side bottom, the length L5 of side 31 is 18mm, width L10 is 8mm, thickness L8 is 4mm, distance L9 between the outside of two sides 31 is 12.1mm, the concave arc recess that forms in the connecting portion 32 both sides of bowtie shape, the radius R2 of recess is 2mm and is convenient for fixed wire rope 1.
The fasteners are nuts 4 and screws 7, the screws 7 penetrate through holes 311 on two side edges 31 of the separation hook 3 and mechanical devices of the transport instrument cabin and then are fixed with the nuts 4, flat washers 5 and spring washers 6 are arranged between the nuts 4 and the screws 7 and the outer sides of the through holes 311, and the flat washers 5 are arranged between the spring washers 6 and the outer sides of the through holes 311.
Example 2
Example 2 is a preferred example of example 1.
In example 2, the connection relationship between the two ends of the steel wire rope 1, the separation hook 3 and the separation plug 8 is as follows: the first end of the steel wire rope 1 is connected with the spacecraft separation plug 8 and then is compressed and fixed through a first compression joint sleeve 21, one end, close to the separation plug 8, of the first compression joint sleeve 21 is an A end, and the other end of the first compression joint sleeve 21 is a B end; the first end of the steel wire rope 1 penetrates through the end B of the first crimping sleeve 21, 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 separating plug 8, penetrates out of the end B, penetrates through the end A and penetrates out of the end B; the length L2 of the first end which finally penetrates out of the end B is controlled to be 5 mm-10 mm. The distance L1 between end a and the separation plug 8 is 5 mm.
The second end of the steel wire rope 1 is connected with the separation hook 3 and then is pressed and fixed through the second pressing sleeve 22. One end of the second pressure welding 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 through the end D of the second crimping sleeve 22, penetrates out of the end C, penetrates through the end D and penetrates out of the end C, penetrates through the separating hook 3 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 L3 of the second end which finally penetrates out of the D end is controlled to be 5 mm-10 mm. The distance L4 between the end C and the separating hook 3 was 5 mm.
The other structure is the same as embodiment 1.
Example 3
Example 3 is an application example of example 1 or example 2.
And (3) pre-processing the separation hook 3 and the crimping sleeve 2 according to requirements, and then installing the mechanical separation steel lock mechanism of the spacecraft separation plug.
The specific installation method comprises the following steps:
(1) a weight of 20kg +/-2 kg is hung on the steel wire rope 1 for 30s, a steel wire rope with one end not more than 1m is cut after the steel wire rope is cut, the steel wire rope and the crimping sleeve 2 are assembled into a forced demoulding mechanism to be tested in a tension test, the steel wire rope is qualified when the weight is not less than 50kg, and a qualified steel wire rope 1 is cut into a section for standby application;
(2) 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;
(3) the first end of the steel wire rope 1 is connected to a spacecraft separation plug 8, the separation plug 8 is connected with the steel wire rope 1 to be knotted by double buckles (namely, one end of the single end of;
(4) the second end of the steel wire rope 1 is vertically pulled down and connected to the separation hook 3, the separation hook 3 is connected with the steel wire rope 1 to be knotted by using double buckles, the steel wire rope 1 is required to be tightly attached to the second crimping sleeve 22 in the knotting process, a ring formed by the double buckles of the steel wire rope 1 is tensioned before being compressed, the length of the penetrating end is controlled to be 5-10 mm according to the graph after being compressed, and a blue adhesive tape is wound on the part of the penetrating steel wire rope 1;
(5) and measuring the length of the steel wire rope 1 which is vertically pulled down, and controlling the length allowance within the range of 20-30 mm.
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.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (8)
1. The mechanical separation steel lock mechanism of the spacecraft separation plug is characterized by comprising a steel wire rope (1), a separation hook (3), a first compression sleeve (21) and a second compression sleeve (22), wherein the first end of the steel wire rope (1) is connected with the spacecraft separation plug (8) and then is compressed and fixed through the first compression sleeve (21), and the second end of the steel wire rope is connected with the separation hook (3) and then is compressed and fixed through the second compression 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 instrument 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 instrument cabin is realized;
one end of the first crimping sleeve (21) close to the separation plug (8) is an A end, and the other end of the first crimping sleeve 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 5-10 mm;
one end of the second crimping sleeve (22) close to the separating 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.
2. 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).
3. A mechanical release steel lock mechanism of a spacecraft release plug according to claim 2, wherein the release hook (3) is made of 1Cr18Ni9 Ti.
4. The mechanical separation steel lock mechanism of the spacecraft separation plug of claim 2, characterized in that the fastening piece is a nut (4) and a screw (7), and the screw (7) passes through a through hole (311) on two sides (31) of the separation hook and a mechanical device of a 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.
5. A mechanical release steel lock mechanism of a spacecraft release 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 first crimping sleeve (21) and the second crimping sleeve (22) are made of titanium alloy.
6. A mechanical release steel lock mechanism for a spacecraft release plug according to claim 1 or 5, characterised in that the first (21) and second (22) crimp sleeves are tubular cylinders with a length of 50mm, an inner bore diameter of 2.6mm and a wall thickness of 1.2 mm.
7. A mechanical release lock mechanism according to claim 6, wherein the first (21) and second (22) crimp sleeves are made of 1Cr18Ni9 Ti.
8. A method of installing a mechanical breakaway steel lock mechanism for a spacecraft separation plug as claimed in any one of claims 1 to 7, comprising the steps of:
s1, hanging a weight of 20kg plus or minus 2kg on the steel wire rope (1) for 30S, assembling the steel wire rope with a length not more than 1m, the first crimping sleeve (21) and the second crimping sleeve (22) into a forced separation mechanism to perform a tensile test after detection, wherein the steel wire rope with a length not less than 50kg is qualified, and cutting a section of the qualified steel wire rope (1) for standby;
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.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010531668.4A CN111750039B (en) | 2020-06-11 | 2020-06-11 | Mechanical separation steel lock mechanism of spacecraft separation plug and installation method |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010531668.4A CN111750039B (en) | 2020-06-11 | 2020-06-11 | Mechanical separation steel lock mechanism of spacecraft separation plug and installation method |
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| CN111750039A CN111750039A (en) | 2020-10-09 |
| CN111750039B true CN111750039B (en) | 2021-09-14 |
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| US20110308049A1 (en) * | 2008-03-18 | 2011-12-22 | Wen-Wei Sun | Wire fastening band |
| US8205922B1 (en) * | 2011-04-07 | 2012-06-26 | The Crosby Group LLC | Grommet shackle |
| US8790370B2 (en) * | 2012-03-30 | 2014-07-29 | Depuy Mitek, Llc | Surgical filament assemblies |
| CN103280665A (en) * | 2013-05-03 | 2013-09-04 | 北京空间飞行器总体设计部 | Electrical connector forced separation device for separation of spacecrafts |
| CN203774600U (en) * | 2013-10-16 | 2014-08-13 | 北京特种机械研究所 | Unmanned plane plug automatic-separating mechanism |
| CN105024227B (en) * | 2015-08-12 | 2017-06-13 | 杭州航天电子技术有限公司 | One kind can oblique pull electro-magnetic release mechanism |
| CN105626779A (en) * | 2015-12-30 | 2016-06-01 | 建峰索具有限公司 | Combined type pulling cable for membrane structure |
| CN106004526A (en) * | 2016-06-27 | 2016-10-12 | 王文芳 | Composite hanger wire and electric railway catenary hanger |
| CN207320473U (en) * | 2017-04-11 | 2018-05-04 | 沈阳兴华航空电器有限责任公司 | A kind of fixedly separated CA cable assembly |
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2020
- 2020-06-11 CN CN202010531668.4A patent/CN111750039B/en active Active
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