CN106114907A - Servo control mechanism erecting device and installation method in the section tight space of a kind of rocket cabin - Google Patents
Servo control mechanism erecting device and installation method in the section tight space of a kind of rocket cabin Download PDFInfo
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- CN106114907A CN106114907A CN201610695188.5A CN201610695188A CN106114907A CN 106114907 A CN106114907 A CN 106114907A CN 201610695188 A CN201610695188 A CN 201610695188A CN 106114907 A CN106114907 A CN 106114907A
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- control mechanism
- servo control
- clip
- suspender belt
- hanging beam
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Abstract
The present invention relates to erecting device and the installation method of servo control mechanism in the section tight space of a kind of rocket cabin, this device includes hanging beam, hanging apparatus, hoop component and go-cart, on entablature in wherein hanging beam is arranged on rocket cabin section, hanging apparatus one end is connected with hanging beam, and hanging apparatus can move along hanging beam, the hanging apparatus other end is connected with hoop component, and hoop component is arranged on servo control mechanism, and servo control mechanism is placed in go-cart；Hoop component includes the first clip, the second clip, hanger, the first attachment means and the second attachment means, this device is simple to operate, easy for installation, effectively prevent the risk of a dead lift, improve efficiency and reduce human cost, the servo control mechanism installation requirements in tight space can be met, it is simultaneously suitable for large volume, the installation of big quality servo control mechanism, in addition installation process more specification, significantly improves installation reliability and safety.
Description
Technical field
The present invention relates to a kind of servo control mechanism erecting device and method, in particular relate in the section tight space of a kind of rocket cabin
Servo control mechanism erecting device and installation method.
Background technology
Along with the development of China's Aerospace Technology, manned space flight, manned moon landing are to starting the demand of grade thrust increasingly
Greatly, high thrust motor is applied on a new generation's carrier rocket, grinds for realizing high thrust motor thruster vector control
The high-power servo control mechanism weight and volume of system significantly increases, and active service carrier rocket supporting servo control mechanism weight is about
55kg, length is about 1365mm；And a new generation of China carrier rocket high thrust motor supporting servo control mechanism weight is maximum
Being about 105Kg, length is about 1843mm.
It is big that active service delivery has Duan Nei space, rocket cabin, the feature that servo control mechanism is lightweight, volume is little, and servo control mechanism is installed
The method using a dead lift, rocket cabin section outer personnel transmitted servo control mechanism by the window of 500mmX500mm in the section of rocket cabin
To personnel in the section of rocket cabin, in the section of rocket cabin, servo control mechanism is carried to installation place on electromotor by personnel, completes on servo control mechanism
The installation of lower fulcrum.
Traditional servo mechanism a dead lift installation method is only applicable to large space inside dimension servo control mechanism little, lightweight peace
Dress, has certain limitation, and a dead lift process operation is complicated simultaneously, and risk is bigger.
A new generation's carrier rocket uses high thrust oxygen kerosene electromotor, and engine tube line structure is complicated, volume is big, rocket
Duan Nei space, cabin and anxiety thereof.A new generation's carrier rocket supporting servo control mechanism weight and volume all significantly increases, and a dead lift is stranded
Difficulty, poor stability, servo control mechanism is difficult to be entered in the section of rocket cabin by 500mmX500mm window in the section of rocket cabin simultaneously.Therefore
The a dead lift method used is installed by traditional servo mechanism can not meet a new generation's carrier rocket servo control mechanism installation requirement.
Summary of the invention
It is an object of the invention to overcome the above-mentioned deficiency of prior art, it is provided that servo in the section tight space of a kind of rocket cabin
Mechanism mounting device, this device is simple to operate, easy for installation, effectively prevent the risk of a dead lift, improves efficiency and reduces
Human cost, can meet the servo control mechanism installation requirements in tight space.
Another object of the present invention is to provide servo control mechanism erecting device in the section tight space of a kind of rocket cabin
Installation method.
The above-mentioned purpose of the present invention is mainly achieved by following technical solution:
The erecting device of servo control mechanism in the section tight space of a kind of rocket cabin, including hanging beam, hanging apparatus, hoop component and
Go-cart, on the entablature in wherein hanging beam is arranged on rocket cabin section, hanging apparatus one end is connected with hanging beam, and hanging apparatus
Can move along hanging beam, the hanging apparatus other end is connected with hoop component, and hoop component is arranged on servo control mechanism, and servo
Structure is placed in go-cart；Described hoop component includes that the first clip, the second clip, hanger, the first attachment means and second connect
Device, wherein the two ends of the first clip and the second clip are connected with the second attachment means by the first attachment means respectively, and first
Clip and the second clip can rotate along the first attachment means, are connected by the second attachment means and servo control mechanism are fixing, and
The inner space formed after first clip and the second clamp connection matches with the external surface shape of servo control mechanism installation position, hangs
Ear is arranged on the first clip and the second clip both sides.
In the section tight space of above-mentioned rocket cabin in the erecting device of servo control mechanism, also include some studs, some nuts,
First suspender belt and the second suspender belt, the most some studs, some nuts be connected fixing to hanging beam and entablature, the first suspender belt set
Being contained on hanging beam, be connected with hanging beam by hanging apparatus, second suspender belt one end is connected with hanging apparatus, and the other end is with hoop component even
Connect.
In the section tight space of above-mentioned rocket cabin in the erecting device of servo control mechanism, some studs are separately positioned on hanging beam
Two ends, some nuts are for being connected with some studs；In addition uniform multiple through holes on hanging beam, stud is with nut as required
It is arranged on different lead to the hole site.
In the section tight space of above-mentioned rocket cabin in the erecting device of servo control mechanism, the first suspender belt is flat sling；Described
The length ratio of the first suspender belt and the second suspender belt is 0.5～0.8:1.
In the section tight space of above-mentioned rocket cabin in the erecting device of servo control mechanism, the length of the second suspender belt is more than servo
Structure front band component mounting position and the distance of upper fulcrum A.
In the section tight space of above-mentioned rocket cabin in the erecting device of servo control mechanism, the first attachment means includes rotating shaft, spiral shell
Mother and split pin, described first clip one end is provided with groove, and second clip one end is provided with and the boss of described matching grooves, and institute
Stating groove and all offer coaxial through-hole on boss, after groove coordinates with boss, rotating shaft passes through hole, and nut and opening are passed through in two ends
Pin connects.
In the section tight space of above-mentioned rocket cabin in the erecting device of servo control mechanism, the second attachment means includes screw, bullet
Spring packing ring and plain washer, described first clip one end is provided with through hole, and second clip one end is provided with screwed hole, and screw is through the first card
Being connected with the screwed hole of the second clip after the through hole of hoop, spring washer and plain washer are arranged between screw and the first clip.
In the section tight space of a kind of rocket cabin, the installation method of servo control mechanism, comprises the steps:
(1), being passed from the through hole at hanging beam two ends by stud, nut is fixed with screwing up stud, thus is arranged on by hanging beam and sends out
In motivation frame；
(2), being sleeved on hanging beam by the first suspender belt, hanging apparatus one end is connected with the first suspender belt；Adjust the first suspender belt to exist
Position on hanging beam, makes hanging apparatus be positioned on electromotor above the position of servo control mechanism to be installed；
(3), servo control mechanism is placed in go-cart, after fixing to hoop component and servo control mechanism connection, will by go-cart
Servo control mechanism is pushed into below the section of rocket cabin；
(4), the second suspender belt two ends are connected with two hangers of hoop component respectively after, by the interposition of the second suspender belt
Put and be connected with hanging apparatus；
(5), adjusting hanging apparatus makes servo control mechanism slowly rise, until it reaches position to be installed on electromotor, completes to watch
Take mechanism's installation on the engine；
(6), the second suspender belt is disconnected with hoop component, hoop component is removed from servo control mechanism, by hanging beam, lifting dress
Put, the first suspender belt, nut and stud are removed.
In the section tight space of above-mentioned rocket cabin in the installation method of servo control mechanism, in step (5), servo control mechanism rises
Speed is 0.05m/s～0.1m/s.
In the section tight space of above-mentioned rocket cabin in the installation method of servo control mechanism, hoop component and servo in step (3)
The method of connection is fixed by mechanism:
(3.1), by after the boss of second clip one end and the groove fit of first clip one end, rotating shaft passes described boss
With the through hole on groove, rotating shaft two ends are connected by bolt and nut of clip；
(3.2), servo control mechanism installation site being wrapped up by the first clip and the second clip, screw is through the first clip
After through hole, the screwed hole with the second clip is connected, and spring washer and plain washer are arranged between screw and the first clip, it is achieved the
One clip and the connection of the second clip.
In the section tight space of above-mentioned rocket cabin in the installation method of servo control mechanism, the first suspender belt is flat sling: described
The length ratio of the first suspender belt and the second suspender belt is 0.5～0.8:1.
In the section tight space of above-mentioned rocket cabin in the installation method of servo control mechanism, the length of the second suspender belt is more than servo
Structure front band component mounting position and the distance of upper fulcrum A；Described hanging apparatus is chain block.
Present invention advantage compared with prior art is:
(1), the present invention is directed to servo control mechanism in prior art the problem existed is installed, a kind of novel watching of innovative design
Take mechanism mounting device, this erecting device simple in construction, easy for installation, it is adaptable to servo control mechanism in tight space in the section of rocket cabin
Installation, be simultaneously suitable for large volume, the installation of big quality servo control mechanism；
(2), servo control mechanism installation method of the present invention is simple to operate, easy for installation, effectively prevent the risk of a dead lift,
Improve efficiency and reduce human cost, the servo control mechanism installation requirements in tight space can be met.
(3), servo control mechanism installation method of the present invention by hanging apparatus and hoop component complete install, installation process is more
Specification, significantly improves installation reliability and safety；
(4), servo control mechanism installation method of the present invention can be completed the installation of multiple servo control mechanism by a set of erecting device,
Improve installation effectiveness, reduce installation cost simultaneously；
(5), the present invention version and the proportional sizes of each building block in servo control mechanism are optimized design, can
Control lifting speed with reliable, and make hoisting process more reliable and more stable.
(6), the present invention carries out innovative design to the hoop component structure of servo control mechanism erecting device, it is ensured that servo control mechanism
The balance and stability of hoisting process, and the simpler convenience of hoop component assembling and disassembling, improve lifting efficiency further.
Accompanying drawing explanation
Fig. 1 is servo control mechanism erecting device structural representation of the present invention；
Fig. 2 is hoop component structural representation of the present invention, and wherein Fig. 2 a is front view, and Fig. 2 b is left view.
Detailed description of the invention
The present invention is described in further detail with specific embodiment below in conjunction with the accompanying drawings:
Being illustrated in figure 1 servo control mechanism erecting device structural representation of the present invention, rocket cabin the most of the present invention section is tight
Gather the erecting device of servo control mechanism in space, including hanging beam 1, hanging apparatus 5, some studs 2, some nuts the 3, first suspender belt 4,
Second suspender belt 6, hoop component 7 and go-cart 8, what hanging beam 1 was arranged in the section of rocket cabin by the most some studs 2, some nuts 3 sends out
In motivation frame, some studs 2 are separately positioned on the two ends of hanging beam 1, and some nuts 3 are for being connected with some studs 2.Hang
Uniform multiple through holes on beam 1, stud 2 is arranged as required to be arranged on different lead to the hole site from nut 3.
First suspender belt 4 is sleeved on hanging beam 1, is connected with hanging beam 1 by hanging apparatus 5, and the first suspender belt 4 is flat sling.The
One suspender belt 4 can drive hanging apparatus 5 to move along hanging beam 1.
Second suspender belt 6 one end is connected with hanging apparatus 5, and the other end is connected with hoop component 7.First suspender belt 4 hangs with second
Length ratio with 6 is 0.5～0.8:1.And second suspender belt 6 length more than servo control mechanism 9 front band assembly 7 installation site with upper
The distance of fulcrum A.Hanging apparatus can reliably control to lift speed, and the hoisting process made is more reliable and more stable.Hanging apparatus 5 can
Think chain block.
Hoop component 7 is arranged on servo control mechanism 9, and servo control mechanism 9 is placed in go-cart 8, and go-cart 8 can be that flat board is little
Car.
Being illustrated in figure 2 hoop component structural representation of the present invention, wherein Fig. 2 a is front view, and Fig. 2 b is left view.Card
Hoop assembly 7 includes first clip the 11, second clip 12, hanger the 14, first attachment means and the second attachment means, wherein the first card
Hoop 11 is connected with the second attachment means by the first attachment means respectively with the two ends of the second clip 12, the first clip 11 and second
Clip 12 can carry out rotating (13 rotating around the shaft) along the first attachment means, is fixed with servo control mechanism 9 by the second attachment means
Connect, and the first clip 11 is connected with the second clip 12 after the inner space of formation and the outer surface of servo control mechanism 9 installation position
Mating shapes, hanger 14 is arranged on the first clip 11 and the second clip 12 both sides.
First attachment means includes that rotating shaft 13, nut 15 and split pin 19, first clip 11 one end are provided with groove, the second card
Bind round 12 one end to be provided with and the boss of described matching grooves, and described groove all offers coaxial through-hole, groove and boss on boss
After cooperation, rotating shaft 13 is connected through through hole, two ends by nut 15 and split pin 19.
Second attachment means includes that screw 16, spring washer 17 and plain washer 18, first clip 11 one end are provided with through hole, the
Two clip 12 one end are provided with screwed hole, and screw 16 is connected with the screwed hole of the second clip 12 after the through hole of the first clip 11,
Spring washer 17 and plain washer 18 are arranged between screw 16 and the first clip 11.
Wherein nut 15 can be hex nut, screw 16 can be hexagon socket cap head screw.
In the section tight space of rocket cabin of the present invention, the installation method of servo control mechanism comprises the steps:
(1), being passed from the through hole at hanging beam 1 two ends by stud 2, nut 3 is tightened fixing with stud 2, thus is installed by hanging beam 1
On entablature.
(2), being sleeved on hanging beam 1 by the first suspender belt 4, hanging apparatus 5 one end is connected with the first suspender belt 4；Adjust first to hang
With 4 positions on hanging beam 1, hanging apparatus 5 is made to be positioned on electromotor above the position of servo control mechanism 9 to be installed.
(3), servo control mechanism 9 is placed in go-cart 8, after fixing with servo control mechanism 9 for hoop component 7 connection, by pushing away
Servo control mechanism 9 is pushed into below the section of rocket cabin by car 8.
Hoop component 7 fixes, with servo control mechanism 9, the method being connected:
(3.1), by after the boss of second clip 12 one end and the groove fit of first clip 11 one end, rotating shaft 13 is through institute
Stating boss and the through hole on groove, rotating shaft 13 two ends are connected by nut 15 and split pin 19；
(3.2), servo control mechanism 9 installation site being wrapped up by the first clip 11 and the second clip 12, screw 16 is through the
After the through hole of one clip 11, the screwed hole with the second clip 12 is connected, and spring washer 17 and plain washer 18 are arranged on screw 16 and
Between one clip 11, it is achieved the first clip 11 and connection of the second clip 12.
(4), the second suspender belt 6 two ends are connected with two hangers of hoop component 7 respectively after, by the second suspender belt 6
Between position be connected with hanging apparatus 5；
(5), adjusting hanging apparatus 5 makes servo control mechanism 9 slowly rise, until it reaches position to be installed on electromotor, completes
Servo control mechanism 9 installation on the engine, i.e. completes lower fulcrum on servo control mechanism and installs.The speed that servo control mechanism 9 rises is
0.05m/s～0.1m/s.
(6), the second suspender belt 6 is disconnected with hoop component 7, clip group assembly 7 is removed from servo control mechanism 9, by hanging beam
1, hanging apparatus the 5, first suspender belt 4, nut 3 and stud 2 is removed and in the section of rocket cabin take out.
Embodiment 1
The length of the first suspender belt 4 and the second suspender belt 6 is respectively 0.5m and 0.8m.
First suspender belt 4 is fixed on left end 2/5 position of hanging beam 1, the i.e. first suspender belt 4 fixed position distance hanging beam left end away from
From for the 2/5 of hanging beam 1 length.
Hanging beam 1 is the cylinder type steel pipe being distributed several through holes, a length of 1.75m of hanging beam 1, the spacing of through hole on hanging beam 1
For 0.2m.Each 2 studs 2 in hanging beam 1 two ends.
The degree of depth of the boss height of second clip 12 one end and the groove of first clip 11 one end is 18mm, left and right after assembling
Gap is 0.2～0.5mm.
The material of hanging beam 1 and hoop component 7 is rustless steel.
The above, the detailed description of the invention that only present invention is optimal, but protection scope of the present invention is not limited thereto,
Any those familiar with the art in the technical scope that the invention discloses, the change that can readily occur in or replacement,
All should contain within protection scope of the present invention.
The content not being described in detail in description of the invention belongs to the known technology of professional and technical personnel in the field.
Claims (12)
1. the erecting device of servo control mechanism in a rocket cabin section tight space, it is characterised in that: include hanging beam (1), lifting dress
Put (5), hoop component (7) and go-cart (8), on the entablature in wherein hanging beam (1) is arranged on rocket cabin section, hanging apparatus
(5) one end is connected with hanging beam (1), and hanging apparatus (5) can be mobile along hanging beam (1), hanging apparatus (5) other end and clip group
Part (7) connects, and hoop component (7) is arranged on servo control mechanism (9), and servo control mechanism (9) is placed in go-cart (8)；Described card
Hoop assembly (7) includes the first clip (11), the second clip (12), hanger (14), the first attachment means and the second attachment means, its
In the first clip (11) be connected with the second attachment means by the first attachment means respectively with the two ends of the second clip (12), first
Clip (11) can rotate along the first attachment means with the second clip (12), by the second attachment means and servo control mechanism (9)
Fixing connect, and the first clip (11) is connected with the second clip (12) after the inner space of formation and servo control mechanism (9) installation portion
The external surface shape of position matches, and hanger (14) is arranged on the first clip (11) and the second clip (12) both sides.
The erecting device of servo control mechanism in the section tight space of a kind of rocket cabin the most according to claim 1, it is characterised in that:
Also include some studs (2), some nuts (3), the first suspender belt (4) and the second suspender belt (6), the most some studs (2), some spiral shells
Female (3) are connected fixing to hanging beam (1) and entablature, and the first suspender belt (4) is sleeved on hanging beam (1), by hanging apparatus (5) and
Hanging beam (1) connects, and the second suspender belt (6) one end is connected with hanging apparatus (5), and the other end is connected with hoop component (7).
The erecting device of servo control mechanism in the section tight space of a kind of rocket cabin the most according to claim 2, it is characterised in that:
Described some studs (2) are separately positioned on the two ends of hanging beam (1), and some nuts (3) are for being connected with some studs (2)；
In addition the upper uniform multiple through holes of hanging beam (1), stud (2) is arranged on different lead to the hole site as required from nut (3).
The erecting device of servo control mechanism in the section tight space of a kind of rocket cabin the most according to claim 2, it is characterised in that:
Described first suspender belt (4) is flat sling；Described first suspender belt (4) is 0.5～0.8:1 with the length ratio of the second suspender belt (6).
5., according to the erecting device of servo control mechanism in a kind of rocket cabin section tight space one of claim 2～4 Suo Shu, it is special
Levy and be: the length of described second suspender belt (6) is more than servo control mechanism (9) front band assembly (7) installation site and upper fulcrum (A)
Distance.
The erecting device of servo control mechanism in a kind of rocket cabin section tight space the most according to claims 1 to 4, its feature exists
In: described first attachment means includes that rotating shaft (13), nut (15) and split pin (19), described first clip (11) one end are provided with
Groove, the second clip (12) one end is provided with and the boss of described matching grooves, and described groove all offers coaxial leading on boss
Hole, after groove coordinates with boss, rotating shaft (13) passes through hole, and two ends are connected by nut (15) and split pin (19).
The erecting device of servo control mechanism in a kind of rocket cabin section tight space the most according to claims 1 to 4, its feature exists
In: described second attachment means includes screw (16), spring washer (17) and plain washer (18), described first clip (11) one end
Being provided with through hole, the second clip (12) one end is provided with screwed hole, and screw (16) blocks with second after the through hole of the first clip (11)
The screwed hole of hoop (12) connects, and spring washer (17) and plain washer (18) are arranged between screw (16) and the first clip (11).
8. the installation method of servo control mechanism in a rocket cabin section tight space, it is characterised in that: comprise the steps:
(1), being passed from the through hole at hanging beam (1) two ends by stud (2), nut (3) is tightened fixing with stud (2), thus by hanging beam
(1) it is arranged on entablature；
(2), being sleeved on hanging beam (1) by the first suspender belt (4), hanging apparatus (5) one end is connected with the first suspender belt (4)；Adjust the
One suspender belt (4) position on hanging beam (1), makes hanging apparatus (5) be positioned on electromotor on the position of servo control mechanism to be installed (9)
Side；
(3), servo control mechanism (9) is placed in go-cart (8), after fixing to hoop component (7) and servo control mechanism (9) connection, logical
Cross go-cart (8) to be pushed into below the section of rocket cabin by servo control mechanism (9)；
(4), the second suspender belt (6) two ends are connected with two hangers (14) of hoop component (7) respectively after, by the second suspender belt
(6) centre position is connected with hanging apparatus (5)；
(5), adjusting hanging apparatus (5) makes servo control mechanism (9) slowly rise, until it reaches position to be installed on electromotor, completes
Servo control mechanism (9) installation on the engine；
(6), the second suspender belt (6) is disconnected with hoop component (7), hoop component (7) is removed from servo control mechanism (9), will hang
Beam (1), hanging apparatus (5), the first suspender belt (4), nut (3) and stud (2) are removed.
The installation method of servo control mechanism in the section tight space of a kind of rocket cabin the most according to claim 8, it is characterised in that:
The speed that in described step (5), servo control mechanism (9) rises is 0.05m/s～0.1m/s.
The installation method of servo control mechanism in the section tight space of a kind of rocket cabin the most according to claim 8, its feature exists
In: in described step (3), the fixing method that is connected of hoop component (7) and servo control mechanism (9) is:
(3.1), by after the boss of the second clip (12) one end and the groove fit of the first clip (11) one end, rotating shaft (13) passes
Described boss and the through hole on groove, rotating shaft (13) two ends are connected by nut (15) and split pin (19)；
(3.2), servo control mechanism (9) installation site being wrapped up by the first clip (11) and the second clip (12), screw (16) is worn
After crossing the through hole of the first clip (11), the screwed hole with the second clip (12) is connected, and spring washer (17) and plain washer (18) are arranged
Between screw (16) and the first clip (11), it is achieved the first clip (11) and the connection of the second clip (12).
The installation method of servo control mechanism in 11. a kind of rocket cabin according to claim 8 section tight spaces, its feature exists
In: described first suspender belt (4) is flat sling: described first suspender belt (4) is 0.5～0.8 with the length ratio of the second suspender belt (6):
1。
The installation method of servo control mechanism in 12. a kind of rocket cabin according to claim 8 section tight spaces, its feature exists
In: the length of described second suspender belt (6) more than servo control mechanism (9) front band assembly (7) installation site and upper fulcrum (A) away from
From；Described hanging apparatus (5) is chain block.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610695188.5A CN106114907A (en) | 2016-08-19 | 2016-08-19 | Servo control mechanism erecting device and installation method in the section tight space of a kind of rocket cabin |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610695188.5A CN106114907A (en) | 2016-08-19 | 2016-08-19 | Servo control mechanism erecting device and installation method in the section tight space of a kind of rocket cabin |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106114907A true CN106114907A (en) | 2016-11-16 |
Family
ID=57278932
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610695188.5A Pending CN106114907A (en) | 2016-08-19 | 2016-08-19 | Servo control mechanism erecting device and installation method in the section tight space of a kind of rocket cabin |
Country Status (1)
| Country | Link |
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| CN (1) | CN106114907A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112638775A (en) * | 2018-08-31 | 2021-04-09 | 赛峰短舱公司 | Operating assembly and method for operating an aircraft propulsion unit |
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| CN204279977U (en) * | 2014-09-26 | 2015-04-22 | 中国商用飞机有限责任公司 | For the hoisting mechanism of civil aircraft auxiliary power unit |
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| EP2915768A1 (en) * | 2014-03-04 | 2015-09-09 | Step Technology s.r.l. | Portal crane |
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| WO2006062414A1 (en) * | 2004-12-06 | 2006-06-15 | T. Kverneland & Sønner As | A travelling crane |
| EP2915768A1 (en) * | 2014-03-04 | 2015-09-09 | Step Technology s.r.l. | Portal crane |
| CN104310198A (en) * | 2014-09-25 | 2015-01-28 | 北京航星机器制造有限公司 | Large-mass initiating explosive device safe hoisting and transfer device and use method thereof |
| CN204279977U (en) * | 2014-09-26 | 2015-04-22 | 中国商用飞机有限责任公司 | For the hoisting mechanism of civil aircraft auxiliary power unit |
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Application publication date: 20161116 |
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| RJ01 | Rejection of invention patent application after publication |