CN103317486A - Adjustable satellite protection bracket - Google Patents
Adjustable satellite protection bracket Download PDFInfo
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- CN103317486A CN103317486A CN201310200036XA CN201310200036A CN103317486A CN 103317486 A CN103317486 A CN 103317486A CN 201310200036X A CN201310200036X A CN 201310200036XA CN 201310200036 A CN201310200036 A CN 201310200036A CN 103317486 A CN103317486 A CN 103317486A
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- rod
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- protective cradle
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Abstract
The invention provides an adjustable satellite protection bracket which comprises a right-angle connecting rod (1), an upper bearing installation plate (5), a steel wire check ring (6) for a shaft, a bearing installation base (7), a thrust ball bearing (8), an adjustable screw (9), a screw locking check ring (10) with a locking ring and a base (11). The adjustable satellite protection bracket solves the problem of safety of tests of centroid and rotational inertia of satellites, can be adjusted along the Z direction, can perform movement adjustment along the X direction and the Y direction through the base and an installation connecting plate, and can be suitable for tests of the rotational inertia and centroid positions of satellites of various types. The adjustable satellite protection bracket enables the satellites to be adjusted rapidly along Z-directional installation positions, adjustment can be achieved as long as the adjustable screw is rotated slightly, and the operation process is convenient.
Description
Technical field
The present invention relates to protective cradle, more particularly, relate to a kind of adjustable satellite protective cradle, especially a kind of highly reliable, and can Fast Installation, adjustable device for the satellite protection, key is that this device has high safety, Fast Installation.
Background technology
At present both at home and abroad the experimental rig of instrumented satellite mass property mainly adopts: satellite mass characteristic test fixture (being commonly called as the L-type beam), frame frock, vertical frock and and other tooling combination test.Test around rotary inertia and the centroid position of Z axis, adopt L-type beam mass property frock to realize, level at the test process Satellite, be subject to so a very large moment of flexure on the structural member of satellite, also do not had suitable supporting tool to address this problem on the domestic and international market at present.
So the sagging problem of satellite front end is extremely urgent when solving under level test.Although also taked a lot of measures to solve in the satellite assembly process, effect is all not obvious.Have a strong impact on like this safety of satellite, brought very large hidden danger to assemble of the satellite.Therefore be necessary to develop a kind of adjustable satellite protective cradle, to solve the needs of general assembly operating personnel in process of the test.
Do not find at present explanation or the report of technology similar to the present invention, not yet collect both at home and abroad similarly data yet.
Summary of the invention
For deficiency of the prior art, the technical problem to be solved in the present invention is: when testing for the test of doing rotary inertia around Z axis, centroid position at satellite and other tooling combination, and the problem that the satellite front end is sagging.Safety problem when having solved test in the process.A kind of adjustable satellite protective cradle device is provided, improved the safety of assemble of the satellite, experiment work.
The adjustable satellite protective cradle that provides according to this invention; but comprise right angle connecting rod 1, upper bearing (metal) installing plate 5, axle-steel silk back-up ring 6, bearing mounting base 7, thrust ball bearing 8 adjusting screw(rod)s 9, the screw lock baffle ring 10 with retainer, base 11, wherein:
But right angle connecting rod 1, upper bearing (metal) installing plate 5, bearing mounting base 7 adjusting screw(rod)s 9, base 11 connect successively, but an end of adjusting screw(rod) 9 is installed in the bearing mounting base 7 by thrust ball bearing 8, but axle-steel silk back-up ring 6 is arranged between the end and upper bearing (metal) installing plate 5 of adjusting screw(rod) 9, but the inner ring of thrust ball bearing 8 is connected with an end of adjusting screw(rod) 9, the outer ring of thrust ball bearing 8 and bearing mounting base 7 tight fit connections, but the other end of adjusting screw(rod) 9 is installed in the base 11 by the screw lock baffle ring 10 with retainer.
Preferably, also comprise high-strength large hexagon head bolt used for steel structure 2, single coil spring lock washer light type 3, plain washer 4, wherein, described right angle connecting rod 1 is installed on upper bearing (metal) installing plate 5 by high-strength large hexagon head bolt used for steel structure 2, single coil spring lock washer light type 3, the plain washer 4 that connects successively.
Preferably, also comprise connecting plate 12 is installed, wherein, the bottom of described base 11 connects described installation connecting plate 12.
Preferably, the procedure of processing of described right angle connecting rod 1 comprises the steps:
Step 1): cast and completely foundry goods is carried out temper eliminate casting stress afterwards, temperature is 720 ℃, and the time is 6 hours, takes out product with the stove cooling after 24 hours;
Step 2): foundry goods is carried out roughing, remove more allowance from the foundry goods cutting, and put the allowance of 2mm～3mm, reach preliminary machining accuracy and lower processing fineness;
Step 3): carry out a de-stress after roughing is complete and process;
Step 4): roughing and de-stress are carried out the semifinishing between roughing and fine finishining after processing;
Step 5): carry out again one time stabilization processes after the semifinishing;
Step 6): carry out again fine finishining after being disposed, make the machining accuracy of each grade size all will reach designing requirement;
Step 7): carry out again at last hard anodized and process to provide case hardness.
Preferably, but the procedure of processing of described adjusting screw(rod) 9 comprise the steps:
Shape requirement by drawing carries out roughing first, puts allowance 1mm～2mm, then carries out modifier treatment, makes the institutional framework of material become the tempered sorbite tissue; After modifier treatment, carry out again semifinishing, in process, put grinding allowance 0.2mm～0.3mm, in order to improve wearability and stability, before fine finishining, adopt nitrogen treatment; Carry out at last grinding fine finishining.
Preferably, the procedure of processing of described installation connecting plate 12 comprises the steps:
After machining was complete, integral body was carried out the surface chill anodization, and wherein, chill anodization is specifically in 25% sulfuric acid solution, and temperature is in the situation that 10, through powered anode processing in 2.5 hours; After chill anodization, make piece surface generate the corrosion-resistant oxide-film of one deck, oxidation film layer is: 45～50 microns alundum (Al2O3) hard layer.
Preferably, the upper end of described right angle connecting rod 1 has a plurality of mounting holes, and the wide of mounting hole is 12.5 ㎜, and length is 16 ㎜, and the connecting bolt of guaranteeing M12 has the adjusting space of 4 ㎜ when installing.
Preferably, but described adjusting screw(rod) 9 comprises a primary structural component and a nut, and nut spot welding is welded in primary structural component.
Preferably, on the described base 11 a plurality of mounting holes are arranged, the wide of mounting hole is 12.5 ㎜, and length is 28 ㎜, and the adjusting space of 16 ㎜ is arranged along Y direction when the connecting bolt of guaranteeing M12 is installed.
Preferably, the screw that a plurality of M12 are arranged on the connecting plate 12 is installed, is guaranteed the installation of the connecting bolt of M12, to satisfy the plurality of installation forms along directions X.
Compared with prior art, beneficial effect of the present invention is as follows:
1. reliability, the security of Satellite Experiment have been improved;
2. can save time and the manpower of test;
3. adapt to the satellite rotary inertia of different sizes and the test of centroid position;
4. operating process is convenient.
Description of drawings
By reading the detailed description of non-limiting example being done with reference to the following drawings, it is more obvious that other features, objects and advantages of the present invention will become:
Fig. 1 is the adjustable protective rack assumption diagram;
Fig. 2 is right angle connecting rod structure chart;
Fig. 3 is for can regulate screw-rod structure figure;
Fig. 4 is understructure figure;
Fig. 5 is for installing connecting board structure figure;
Fig. 6 is the processing process of right angle connecting rod;
But Fig. 7 is the processing process of adjusting screw(rod).
Among the figure:
1 is the right angle connecting rod;
2 is high-strength large hexagon head bolt used for steel structure;
3 is single coil spring lock washer light type;
4 is plain washer;
5 is the upper bearing (metal) installing plate;
6 is axle-steel silk back-up ring;
7 is bearing mounting base
8 is thrust ball bearing;
But 9 is adjusting screw(rod);
10 are the screw lock baffle ring with retainer
11 is base;
12 for installing connecting plate.
The specific embodiment
The present invention is described in detail below in conjunction with specific embodiment.Following examples will help those skilled in the art further to understand the present invention, but not limit in any form the present invention.Should be pointed out that to those skilled in the art, without departing from the inventive concept of the premise, can also make some distortion and improvement.These all belong to protection scope of the present invention.
Adjustable satellite protective cradle of the present invention is that a kind of height can be regulated, length can increase, the installation site can change, has characteristics lightweight, easy for installation, has reached a kind of device of safeguard protection effect in assemble of the satellite, test.The general assembly operating personnel can install the satellite protective cradle rapidly, have the characteristics of installation, adjusting, convenient disassembly, can guarantee like this safety of Satellite Experiment.
According to adjustable protective supporting structure provided by the invention as shown in Figure 1, described adjustable protective support mainly by right angle connecting rod 1, high-strength large hexagon head bolt used for steel structure 2, single coil spring lock washer light type 3, plain washer 4, upper bearing (metal) installing plate 5, axle-steel silk back-up ring 6, bearing mounting base 7, thrust ball bearing (51106) but 8 adjusting screw(rod)s 9, the screw lock baffle ring 10 with retainer, base 11, the part such as connecting plate 12 be installed formed.Wherein, plain washer is preferably plain washer-C level.
Described right angle connecting rod 1 is vital part, and right angle connecting rod 1 directly contacts with satellite, so material adopts Birmasil, because Birmasil is lightweight, machinability is good, and is not yielding, easily processing.Processing process is seen Fig. 6, and processing technology is: 1) casting is complete carries out temper to foundry goods and eliminates casting stress afterwards, and temperature is about 720 ℃, and the time is 6 hours, takes out product with the stove cooling after 24 hours.2) foundry goods is carried out roughing, remove more allowance from the foundry goods cutting, and put the allowance of 2mm～3mm, reach preliminary machining accuracy and lower processing fineness.3) roughing is carried out a de-stress after complete and is processed 4) after roughing and de-stress process, carry out the semifinishing between roughing and fine finishining, accurately machined machining accuracy can be guaranteed.5) carry out again one time stabilization processes after the semifinishing.6) carry out fine finishining after being disposed, fine finishining all will reach designing requirement for the machining accuracy of each grade size again.7) carry out at last hard anodized again and process, after the employing hard anodized is processed after the processing, overcome the not wear-resisting defective of cast aluminium, case hardness improves greatly.
It is 1Cr18Ni9Ti titaniferous stainless steel that described high-strength large hexagon head bolt used for steel structure 2 is selected the high trade mark of corrosion resistance.
Described single coil spring lock washer light type 3 selects the board with enough plasticity and toughness to be: the 65Mn/GB/T3078-1994 spring steel wire.
It is 45(GB702-86 that described plain washer 4 is selected the trade mark with enough plasticity and toughness) carbon constructional quality steel make.
It is 45(GB702-86 that described upper bearing (metal) installing plate 5 is selected the trade mark with enough plasticity and toughness) carbon constructional quality steel make.
Described axle-steel silk back-up ring 6 selects the board with enough plasticity and toughness to be: the 65Mn/GB/T3078-1994 spring steel wire.
It is 45(GB702-86 that described bearing mounting base 7 is selected the trade mark with enough plasticity and toughness) carbon constructional quality steel make.
Described thrust ball bearing (51106) but 8 be installed between bearing mounting base 7 and the adjusting screw(rod) 9, the outer ring of thrust ball bearing 8 and bearing mounting base 7 tight fit connections, but the inner ring of thrust ball bearing 8 is connected with adjusting screw(rod) 9, but a pair of thrust ball bearing is supported on the two ends of adjusting screw(rod) 9, but realized the rotation of adjusting screw(rod) 9 and improved the rigidity of this mechanism, but made adjusting screw(rod) 9 can bear barycenter and the rotary inertia test of large weight satellite.
But described adjusting screw(rod) 9 is critical components in the support provided by the present invention, it is again a main stressed part, but for the requirements such as intensity, wearability and toughness that guarantee adjusting screw(rod) 9, but adjusting screw(rod) 9 carries out roughing by the shape requirement of drawing first, in order to prevent distortion, put allowance 1mm～2mm, then carry out modifier treatment, make the institutional framework of material become tempered sorbite and organize to improve the intensity of body, plasticity and toughness.After modifier treatment, carry out again semifinishing, in process, put grinding allowance 0.2mm～0.3mm, in order to improve wearability and stability, before fine finishining, adopt nitrogen treatment.Loop bar case hardness (being Rockwell hardness) after via nitride is processed reaches RC50, has very strong wearability, improves simultaneously its fatigue strength (improving about 25%).Carry out at last grinding fine finishining.But in order to strengthen adjusting screw(rod) 9 intensity and wearability, but concrete processing process operates by the adjusting screw(rod) processing process shown in Fig. 7.
It is 45(GB702-86 that described screw lock baffle ring 10 with retainer is selected the trade mark with enough plasticity and toughness) carbon constructional quality steel make.Guarantee that but adjusting screw(rod) 9 does not break away from base 11, the screw lock baffle ring 10 of locking belt retainer after installing, but can be locked at securely on the adjusting screw(rod) 9 with the screw lock baffle ring 10 of retainer.
Described base 11 selects that corrosion resistance is high, the little trade mark of distortion is that 3Cr18Ni7Si2 martensite type stainless steel carries out processing and fabricating, and accessory size is stable fine behind the processing and fabricating, and the processing afterwards precision of accessory size does not descend.
It is the 7A04 extra super duralumin alloy that described installation connecting plate 12 is selected the trade mark of good stability, and the air-tightness of 7A04 extra super duralumin alloy is good, lightweight, machinability is all good, and after machining was complete, integral body was carried out the surface chill anodization.Chill processing is in 25% sulfuric acid solution, and temperature is in the situation that 10, after powered anode processing in 2.5 hours.After chill anodization, make piece surface generate the corrosion-resistant oxide-film of one deck, oxidation film layer is: 45～50 microns alundum (Al2O3) (AL
2O
3) hard layer, can not produce scuffing with the delineation of pocket knife yet.Fineness through chill anodization rear surface also improves one-level (5 microns) simultaneously, and its hardness reaches HRC45～50.
The structure chart of described right angle connecting rod as shown in Figure 2, the upper end of right angle connecting rod 1 has two mounting holes, the wide of mounting hole is 12.5 ㎜, length is 16 ㎜, the connecting bolt of guaranteeing M12 has the adjusting space of 4 ㎜ when installing.Lower end has the circular hole of four φ 12.5 ㎜ to be connected with installation connecting plate 12.The right angle connecting rod has 5 kinds of specifications, and the length of right angle connecting rod is respectively: 138 ㎜, 218 ㎜, 280 ㎜, 358 ㎜ and 468 ㎜ can adapt to barycenter and the rotary inertia test of the different model satellite of 5 kinds of sizes.
But the structure chart of described adjusting screw(rod) 9 as shown in Figure 3, but adjusting screw(rod) 9 is critical components in the support provided by the present invention, be again a main stressed part, but adjusting screw(rod) 9 mainly is comprised of a primary structural component and a nut.Installation process is: the first step is installed in two thrust ball bearings (51106) 8 on bearing mounting base 7 and the primary structural component; Second step is installed in axle-steel silk back-up ring 6 on the primary structural component, and assurance thrust ball bearing (51106) 8 is installed securely; The 3rd step was installed in upper bearing (metal) installing plate 5 on the bearing mounting base 7 and used spot-welded on; The 4th step was installed in a nut on the primary structural component and used spot-welded on; But the adjusting screw(rod) 9 that the 5th step will assemble is installed to base 11; But the 5th step will be installed to the screw lock baffle ring 10 of retainer lower end and the locking of adjusting screw(rod) 9.
The structure chart of described base 11 has four mounting holes as shown in Figure 4 on the base 11, the wide of mounting hole is 12.5 ㎜, and length is 28 ㎜, and the adjusting space of 16 ㎜ is arranged along Y direction when the connecting bolt of guaranteeing M12 is installed.
The structure chart of described installation connecting plate 12 is installed the screw that 12 M12 are arranged on the connecting plate 12 as shown in Figure 5, guarantees the installation of the connecting bolt of M12.Can satisfy along directions X simultaneously 5 kinds of installation forms are arranged.
The invention solves the barycenter of satellite and the safety of rotary inertia test, the present invention can realize can regulating along Z-direction, can move adjusting along X, Y both direction by base and installation connecting plate, can adapt to the test of Multiple Type satellite rotary inertia and centroid position, and the present invention can realize satellite along the quick adjustment of Z-direction installation site, but during adjusting if rotation adjusting screw(rod) gently just can realize.The more important thing is that the general assembly operating personnel are more convenient when satellite is installed, saved a large amount of time and personnel, a satellite is installed in the past needs 5～6 people, and installation in 3～4 hours just can be finished.Only need now 2 people, just can install in 20～30 minutes.This device is subject to general assembly operating personnel's welcome.Therefore the present invention has guaranteed the safety of Satellite Experiment, and the reliability, the security that have improved Satellite Experiment can adapt to the satellite rotary inertia of different sizes and the test of centroid position simultaneously, and operating process is convenient.
Above specific embodiments of the invention are described.It will be appreciated that, the present invention is not limited to above-mentioned specific implementations, and those skilled in the art can make various distortion or modification within the scope of the claims, and this does not affect flesh and blood of the present invention.
Claims (10)
1. adjustable satellite protective cradle; it is characterized in that; comprise right angle connecting rod (1), upper bearing (metal) installing plate (5), axle-steel silk back-up ring (6), bearing mounting base (7), thrust ball bearing (8) but adjusting screw(rod) (9), the screw lock baffle ring (10) with retainer, base (11), wherein:
Right angle connecting rod (1), upper bearing (metal) installing plate (5), bearing mounting base (7), but adjusting screw(rod) (9), base (11) connects successively, but an end of adjusting screw(rod) (9) is installed in the bearing mounting base (7) by thrust ball bearing (8), axle-steel silk back-up ring (6) but be arranged between the end and upper bearing (metal) installing plate (5) of adjusting screw(rod) (9), thrust ball bearing (8) but inner ring be connected with an end of adjusting screw(rod) (9), the outer ring of thrust ball bearing (8) and bearing mounting base (7) tight fit connection, but the other end of adjusting screw(rod) (9) is installed in the base (11) by the screw lock baffle ring (10) with retainer.
2. adjustable satellite protective cradle according to claim 1; it is characterized in that; also comprise high-strength large hexagon head bolt used for steel structure (2), single coil spring lock washer light type (3), plain washer (4); wherein, described right angle connecting rod (1) is installed on upper bearing (metal) installing plate (5) by high-strength large hexagon head bolt used for steel structure (2), single coil spring lock washer light type (3), the plain washer (4) that connects successively.
3. adjustable satellite protective cradle according to claim 1 is characterized in that, also comprises connecting plate (12) is installed, and wherein, the bottom of described base (11) connects described installation connecting plate (12).
4. adjustable satellite protective cradle according to claim 1 is characterized in that, the procedure of processing of described right angle connecting rod (1) comprises the steps:
Step 1): cast and completely foundry goods is carried out temper eliminate casting stress afterwards, temperature is 720 ℃, and the time is 6 hours, takes out product with the stove cooling after 24 hours;
Step 2): foundry goods is carried out roughing, remove more allowance from the foundry goods cutting, and put the allowance of 2mm～3mm, reach preliminary machining accuracy and lower processing fineness;
Step 3): carry out a de-stress after roughing is complete and process;
Step 4): roughing and de-stress are carried out the semifinishing between roughing and fine finishining after processing;
Step 5): carry out again one time stabilization processes after the semifinishing;
Step 6): carry out again fine finishining after being disposed, make the machining accuracy of each grade size all will reach designing requirement;
Step 7): carry out again at last hard anodized and process to provide case hardness.
5. adjustable satellite protective cradle according to claim 1 is characterized in that, but the procedure of processing of described adjusting screw(rod) (9) comprises the steps:
Shape requirement by drawing carries out roughing first, puts allowance 1mm～2mm, then carries out modifier treatment, makes the institutional framework of material become the tempered sorbite tissue; After modifier treatment, carry out again semifinishing, in process, put grinding allowance 0.2mm～0.3mm, in order to improve wearability and stability, before fine finishining, adopt nitrogen treatment; Carry out at last grinding fine finishining.
6. adjustable satellite protective cradle according to claim 3 is characterized in that, the procedure of processing of described installation connecting plate (12) comprises the steps:
After machining was complete, integral body was carried out the surface chill anodization, and wherein, chill anodization is specifically in 25% sulfuric acid solution, and temperature is in the situation that 10, through powered anode processing in 2.5 hours; After chill anodization, make piece surface generate the corrosion-resistant oxide-film of one deck, oxidation film layer is: 45～50 microns alundum (Al2O3) hard layer.
7. adjustable satellite protective cradle according to claim 1; it is characterized in that, the upper end of described right angle connecting rod (1) has a plurality of mounting holes, and the wide of mounting hole is 12.5 ㎜; length is 16 ㎜, and the connecting bolt of guaranteeing M12 has the adjusting space of 4 ㎜ when installing.
8. adjustable satellite protective cradle according to claim 1 is characterized in that, but described adjusting screw(rod) (9) comprises a primary structural component and a nut, and nut spot welding is welded in primary structural component.
9. adjustable satellite protective cradle according to claim 1; it is characterized in that, described base has a plurality of mounting holes on (11), and the wide of mounting hole is 12.5 ㎜; length is 28 ㎜, and the adjusting space of 16 ㎜ is arranged along Y direction when the connecting bolt of guaranteeing M12 is installed.
10. adjustable satellite protective cradle according to claim 1 is characterized in that, the screw that a plurality of M12 are arranged on the connecting plate (12) is installed, and guarantees the installation of the connecting bolt of M12, to satisfy the plurality of installation forms along directions X.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310200036.XA CN103317486B (en) | 2013-05-24 | 2013-05-24 | Adjustable satellite protection bracket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310200036.XA CN103317486B (en) | 2013-05-24 | 2013-05-24 | Adjustable satellite protection bracket |
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| Publication Number | Publication Date |
|---|---|
| CN103317486A true CN103317486A (en) | 2013-09-25 |
| CN103317486B CN103317486B (en) | 2015-11-18 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310200036.XA Active CN103317486B (en) | 2013-05-24 | 2013-05-24 | Adjustable satellite protection bracket |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103935531A (en) * | 2014-04-15 | 2014-07-23 | 北京控制工程研究所 | Two-dimensional vector adjusting mechanism |
| CN104374520A (en) * | 2014-10-31 | 2015-02-25 | 上海卫星装备研究所 | Light adjusting device capable of vertically moving |
| CN109604957A (en) * | 2018-12-14 | 2019-04-12 | 中国航空工业集团公司北京航空精密机械研究所 | A kind of processing method of the open thin-wall titanium alloy part of high-precision configuration |
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| CN2781063Y (en) * | 2004-12-02 | 2006-05-17 | 上海卫星工程研究所 | Rolling bearing for satellite rotation platform |
| CN102601781A (en) * | 2012-03-30 | 2012-07-25 | 苏州光福冶金铸造有限责任公司 | Height-adjustable working platform |
| CN102642190A (en) * | 2011-12-15 | 2012-08-22 | 上海卫星工程研究所 | Separation preventing device for screw |
| CN102642191A (en) * | 2011-12-15 | 2012-08-22 | 上海卫星工程研究所 | Device for satellite assembly |
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| US4213330A (en) * | 1977-10-28 | 1980-07-22 | Kurt Beckel | Machine for measuring the moments of inertia |
| DE29916650U1 (en) * | 1999-09-22 | 2000-03-02 | Maier, Hubert, 83052 Bruckmühl | Adjustable trestle, for holding reinforcement stirrups |
| JP2002265189A (en) * | 2001-03-06 | 2002-09-18 | Mitsubishi Materials Corp | Television set disassembling work bench and method therefor |
| CN2781063Y (en) * | 2004-12-02 | 2006-05-17 | 上海卫星工程研究所 | Rolling bearing for satellite rotation platform |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103935531A (en) * | 2014-04-15 | 2014-07-23 | 北京控制工程研究所 | Two-dimensional vector adjusting mechanism |
| CN103935531B (en) * | 2014-04-15 | 2016-01-20 | 北京控制工程研究所 | A kind of two-dimensional vector regulating mechanism |
| CN104374520A (en) * | 2014-10-31 | 2015-02-25 | 上海卫星装备研究所 | Light adjusting device capable of vertically moving |
| CN109604957A (en) * | 2018-12-14 | 2019-04-12 | 中国航空工业集团公司北京航空精密机械研究所 | A kind of processing method of the open thin-wall titanium alloy part of high-precision configuration |
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| Publication number | Publication date |
|---|---|
| CN103317486B (en) | 2015-11-18 |
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