CN110745056B - Rocket transfer supporting device and rocket transfer trolley - Google Patents
Rocket transfer supporting device and rocket transfer trolley Download PDFInfo
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- CN110745056B CN110745056B CN201910959977.9A CN201910959977A CN110745056B CN 110745056 B CN110745056 B CN 110745056B CN 201910959977 A CN201910959977 A CN 201910959977A CN 110745056 B CN110745056 B CN 110745056B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60P—VEHICLES ADAPTED FOR LOAD TRANSPORTATION OR TO TRANSPORT, TO CARRY, OR TO COMPRISE SPECIAL LOADS OR OBJECTS
- B60P3/00—Vehicles adapted to transport, to carry or to comprise special loads or objects
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60P—VEHICLES ADAPTED FOR LOAD TRANSPORTATION OR TO TRANSPORT, TO CARRY, OR TO COMPRISE SPECIAL LOADS OR OBJECTS
- B60P7/00—Securing or covering of load on vehicles
- B60P7/06—Securing of load
- B60P7/135—Securing or supporting by load bracing means
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Abstract
The application relates to a rocket transport supporting device includes: the device comprises a front elastic component, a rear elastic component and at least three oil cylinders; the lower cavity of each oil cylinder is communicated with each other through a lower oil way, and the upper cavity of each oil cylinder is communicated with each other through an upper oil way; a front elastic component with the deformation direction the same as the extension direction of a piston rod of the oil cylinder is arranged around the oil cylinder at the forefront; a rear elastic component with the deformation direction the same as the extension direction of a piston rod of the oil cylinder is arranged around the oil cylinder at the last side; the piston rod of each oil cylinder extends upwards and is connected with the bracket, and the bracket is contacted with the rocket shell at the position of the equipment to be protected in the rocket to be transported. The rocket body structure solves the problem that the local surface pressure of the traditional rocket transportation cannot be solved due to the overlarge rocket mass, avoids designing an additional bearing structure of the rocket, and reduces the requirement of the rocket body structure for transportation through a load dispersing mode.
Description
Technical Field
The application relates to the field of rocket transportation, in particular to a rocket transfer supporting device and a rocket transfer trolley.
Background
With the continuous development of aerospace technology, rockets have also been greatly developed as an aerospace tool for delivering artificial earth satellites, manned spacecraft, space stations, space detectors, and the like into predetermined orbits. At present, due to the continuous development of loads such as satellites, airships, space stations, space detectors and the like which need to be transported, the weight of the load is continuously increased, the scale of the rocket is larger and larger, and the weight of the rocket is also continuously increased.
By adopting the traditional rocket transportation and transshipment supporting mode, the surface pressure of the supporting position can be continuously increased due to the continuous increase of the weight of the rocket. Various coatings such as heat protection, heat preservation and the like coated on the surface of the rocket body can be damaged due to the increase of the surface pressure, so that the rocket body structure fails.
Therefore, how to reduce the transportation difficulty caused by the weight of the carrier rocket and avoid the additional mass added by the rocket for being specially used for transporting and supporting the rocket is a technical problem which needs to be solved urgently by technical personnel in the field at present.
Disclosure of Invention
The application provides a supporting device and rocket transfer car (buggy) are transported to rocket to reduce the transportation degree of difficulty that carrier rocket brought because of weight, avoid leading to the inefficacy of rocket body structure because of transporting.
In order to solve the technical problem, the application provides the following technical scheme:
a rocket transport support device comprising: the device comprises a front elastic component, a rear elastic component and at least three oil cylinders; the lower cavity of each oil cylinder is communicated with each other through a lower oil way, and the upper cavity of each oil cylinder is communicated with each other through an upper oil way; a front elastic component with the deformation direction the same as the extension direction of a piston rod of the oil cylinder is arranged around the oil cylinder at the forefront; a rear elastic component with the deformation direction the same as the extension direction of a piston rod of the oil cylinder is arranged around the oil cylinder at the last side; the piston rod of each oil cylinder extends upwards and is connected with the bracket, and the bracket is contacted with the rocket shell at the position of the equipment to be protected in the rocket to be transported.
The rocket transporting support device as described above, wherein preferably, the positions of the front elastic component and the rear elastic component are both arranged at positions corresponding to the positions of the devices to be protected of the transported rocket.
In the rocket transport supporting device according to the above, preferably, the front elastic member is provided in front of the foremost cylinder, and the rear elastic member is provided behind the rearmost cylinder.
In the rocket transport supporting device as described above, it is preferable that the supporting force of each part of the rocket to be transported is set according to the weight of each part of the rocket to be transported, and the cross-sectional area of the cylinder corresponding to each part of the rocket to be transported is set in the same proportion according to the proportion of the supporting force of each part.
The rocket transport supporting device is characterized in that each oil cylinder is provided with a damping system.
The rocket transport supporting device as described above, wherein preferably, each cylinder is vertically connected to the frame of the rocket transport supporting device.
The rocket transporting and supporting device is characterized in that the piston rod of each of the front group of oil cylinders and the rear group of oil cylinders is hinged to the lower end of the bracket, and the bracket is in sliding fit with the vertically through sliding hole of the frame of the rocket transporting and supporting device.
The rocket transport supporting device is characterized in that the end surface of the upper end of the bracket is a concave surface matched with the shape of the shell of the rocket to be transported.
The rocket transporting and supporting device is characterized in that a lower oil way consisting of a front lower oil way and a rear lower oil way is preferably connected with a lower oil way stop valve, the lower oil way stop valve is connected with a lower oil way hydraulic control one-way valve, and the lower oil way hydraulic control one-way valve is connected with a lower oil way quick connector so as to be connected with an oil tank; an upper oil way consisting of a front upper oil way and a rear upper oil way is connected with an upper oil way stop valve, the upper oil way stop valve is connected with an upper oil way hydraulic control one-way valve, and the upper oil way hydraulic control one-way valve is connected with an upper oil way quick connector so as to realize connection with an oil tank; the lower oil way quick connector is also connected with a control oil way of the upper oil way hydraulic control one-way valve, and the upper oil way quick connector is connected with the control oil way of the lower oil way hydraulic control one-way valve.
A rocket transfer car (buggy), comprising: the rocket transport supporting device comprises a carrier vehicle body and the rocket transport supporting device, wherein the rocket transport supporting device is installed on the carrier vehicle body.
Compared with the background technology, the rocket transfer supporting device and the rocket transfer trolley provided by the invention fully utilize the part of the shell with high strength in the rocket structure to carry under the condition of ensuring that the rocket is stably loaded on the rocket supporting device and ensuring that the rocket is uniformly stressed during transfer, and can effectively reduce the weight of the rocket, thereby reducing the surface pressure of the rocket supporting position, avoiding the damage of transfer to the rocket body caused by weight increase, and further avoiding the failure of the rocket body structure caused by transfer.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments described in the present invention, and other drawings can be obtained by those skilled in the art according to the drawings.
FIG. 1 is a schematic structural view of a rocket transport support device provided in an embodiment of the present application;
fig. 2 is an enlarged view of a portion a in fig. 1.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. In addition, spatial relationship terms such as "upper", "above", "lower", "below", "front", "rear", and the like are used for convenience of description to explain a positional relationship between two components. The embodiments described below with reference to the drawings are illustrative only and should not be construed as limiting the invention.
During the transportation of the rocket, a support is generally used for supporting the rocket so as to keep the rocket in a horizontal state, and the surface of the rocket bears pressure and bending moment.
In addition, two supports are usually used for supporting the rocket, and the two supports support the rocket, wherein each supporting point can bear huge load, and in order to avoid the damage of the rocket shell caused by the huge load, the thickness of the shell is inevitably increased, particularly the thickness of the shell near the supporting point is increased, so that the strength of the rocket shell is increased.
If a plurality of supports are used for supporting the rocket, for example, three supports are used for supporting the rocket, when the rocket is going to pass through a bumpy road surface, the three supports support the rocket to form over-constraint, so that one support does not actually bear load, and the other two supports bear the load exceeding the design preset, in order to overcome the damage caused by the over-constraint, the thickness of the shell is further increased, particularly the thickness of the shell near the supporting point is increased, so that the strength of the shell of the rocket is increased.
In addition, not only the rocket case but also the devices inside the rocket need to be protected, so the rocket case where the devices need to be protected are arranged to be thicker, so that the devices are protected by increasing the strength of the rocket case at the devices, and when the rocket is placed on the support, the support needs to be far away from the position where the devices are located because the support applies huge load to the rocket, so that the devices are prevented from bearing huge load from the support, and the devices are protected. For example: the rocket case where the engine is located is set to be thick, and the pedestal is in contact with the rocket case at a position away from the engine to support the rocket.
Obviously, when the launch vehicle is used for running the rocket, especially a large launch vehicle, under the condition of avoiding the damage of the rocket caused by the pressure and bending moment born by the rocket, the weight of the rocket is difficult to reduce, and the surface pressure of a supporting position is difficult to reduce, so the damage of the transportation to the rocket body caused by the weight increase is difficult to overcome by the existing rocket transportation mode. In addition, it is less likely to both secure the strength and reduce the weight of the rocket under full load of solid fuel.
Based on this, the present application provides a rocket transporting support device, please refer to fig. 1, and fig. 1 is a schematic structural diagram of the rocket transporting support device provided in the embodiments of the present application.
The rocket transport supporting device comprises: at least three oil cylinders (specifically, the oil cylinders can be 4, 5, 7 and the like, and the acting force of each oil cylinder on the rocket shell is reduced by a plurality of oil cylinders, such as the oil cylinder 111, the oil cylinder 112, the oil cylinder 113 … …, the oil cylinder 11n-2, the oil cylinder 11n-1 and the oil cylinder 11n) and two elastic components (a front elastic component 121 and a front elastic component 122).
The elastic member may be a spring, but is not limited to a spring. The lower cavity of each oil cylinder is communicated with each other through a lower oil way, for example: the lower cavities of the oil cylinder 111, the oil cylinder 112, the oil cylinder 113 … …, the oil cylinder 11n-2, the oil cylinder 11n-1 and the oil cylinder 11n are communicated with each other through a lower oil way; the upper cavity of each oil cylinder is communicated with each other through an upper oil way, for example: the upper cavities of the oil cylinder 111, the oil cylinder 112, the oil cylinder 113 … …, the oil cylinder 11n-2, the oil cylinder 11n-1 and the oil cylinder 11n are communicated with each other through an upper oil way; a front elastic member 121 having the same deformation direction as the extension and contraction direction of the piston rod of the cylinder is provided around the foremost cylinder 111, and preferably, the front elastic member 121 is provided in front of the foremost cylinder 111; a rear elastic member 122 having the same deformation direction as the extension and contraction direction of the piston rod of the cylinder is provided around the rearmost cylinder 11n, and the rear elastic member 122 is preferably provided behind the rearmost cylinder 11 n.
In addition, as shown in fig. 2, each cylinder may be provided with a damping system 130 to alleviate impact caused by a small load applied instantaneously, thereby preventing a rotation angle from being generated. In addition, each oil cylinder is vertically arranged, and specifically, the oil cylinders can be vertically and fixedly connected to the frame 140 of the rocket transfer supporting device, for example: the frame 140 of the rocket transfer supporting device is provided with an oil cylinder mounting hole 141 which extends in the vertical direction and has an opening facing upwards, the oil cylinder is placed in the oil cylinder mounting hole 141, a piston rod of the oil cylinder penetrates through the flange 150 to extend upwards, and the flange 150 is fixed with the frame 140 of the rocket transfer supporting device towards the oil cylinder.
On the basis of the above, the piston rod of each cylinder extends upwards and is connected with the bracket 160 so as to support and release the rocket through the bracket 160. Specifically, a vertically through sliding hole 142 is formed in the frame 140 of the rocket transfer supporting device, the bracket 160 is in sliding fit with the sliding hole 142 of the frame 140 in the vertical direction, the lower end of the bracket 160 is hinged to a piston rod of the oil cylinder, and in order to ensure that the bracket 160 is in sufficient contact with the rocket, the end face of the upper end of the bracket 160 is a concave face matched with the shape of the shell of the rocket 210 to be transferred. The piston rod of the oil cylinder is hinged with the bracket 160, and the bracket 160 slides in the vertical direction relative to the sliding hole 142 of the frame 140, so that the guiding effect is achieved, the force applied to the oil cylinder and the rocket placed on the bracket 160 is vertical, and the oil cylinder is prevented from inclining due to the counter-acting force, and the rocket is prevented from being damaged due to the inclined counter-acting force.
In order to ensure that the acting force of each bracket 160 on the rocket shell is uniform, the supporting force of each part of the rocket 210 to be transported is set according to the weight of each part of the rocket 210 to be transported, the cross-sectional area of the oil cylinder corresponding to each part of the rocket 210 to be transported is set according to the proportion of the supporting force of each part in the same proportion, namely, the mass of the rocket 210 to be transported at the part is heavier, the cross-sectional area of the oil cylinder at the corresponding position is larger, the mass of the rocket 210 to be transported at the part is lighter, and the cross-sectional area of the oil cylinder at the corresponding position is smaller.
The rocket shell of the position of the equipment needing to be protected in the rocket is generally thicker to protect the equipment, the position of each oil cylinder is arranged at the position corresponding to the position of the equipment needing to be protected in the rocket 210 to be transported in the application, so that the bracket 160 of the rocket transporting support device is contacted with the rocket shell of the position of the equipment needing to be protected in the rocket 210 to be transported, and the load of the rocket 210 to be transported is borne by the rocket transporting support device by utilizing the strength of the thicker shell while the equipment is protected by the thicker shell. On the basis, the positions of the front elastic part 121 and the rear elastic part 122 are also arranged at the positions corresponding to the positions of the devices to be protected of the transported rocket 210, and the rotation direction of the rocket is changed by using the strength of the thicker shell.
In addition, the lower oil way is connected with a lower oil way stop valve 171, the lower oil way stop valve 171 is connected with a lower oil way hydraulic control one-way valve 181, and the lower oil way hydraulic control one-way valve 181 is connected with a lower oil way quick joint 191 to realize connection with an oil tank; the upper oil way is connected with the upper oil way stop valve 172, the upper oil way stop valve 172 is connected with the upper oil way hydraulic control one-way valve 182, and the upper oil way hydraulic control one-way valve 182 is connected with the upper oil way quick joint 192 to realize connection with an oil tank; the lower oil way quick connector 191 is also connected with a control oil way of the upper oil way hydraulic control one-way valve 182, and the upper oil way quick connector 192 is connected with a control oil way of the lower oil way hydraulic control one-way valve 181; the upper oil way and the lower oil way are locked to prevent oil liquid in the loop from flowing, so that the state of the rocket to be transported, which is placed on the rocket transporting and supporting device, cannot be changed due to backflow of the oil liquid.
The application also provides a rocket transfer car (buggy), include: the rocket transport supporting device is installed on the carrier vehicle body and specifically installed in a hopper of the carrier vehicle body.
When the rocket to be transported is supported by the rocket transporting and supporting device and the rocket transporting vehicle, firstly, the rocket 210 to be transported is lifted and placed on the bracket 160, and the bracket 160 is contacted with the rocket shell at the position of the device to be protected in the rocket 210 to be transported, so that the wall thickness of the rocket shell at other positions can be reduced, and the weight of the rocket is further reduced. Because a plurality of oil cylinders (the oil cylinder 111, the oil cylinder 112, the oil cylinder 113 … …, the oil cylinder 11n-2, the oil cylinder 11n-1 and the oil cylinder 11n) are used for carrying the rocket together, the load of each oil cylinder to the rocket is small, the small load can prevent equipment at the position from being damaged, and the load of the rocket can be carried by a thicker shell arranged in the rocket for protecting the equipment.
In the rocket production process, certain errors exist between the position of the actual centroid of the rocket after production and the position of the design centroid G of the rocket due to unavoidable factors (such as engine shell winding errors and manufacturing errors), and the errors (such as +/-300 mm) are necessarily within a controllable range and are generally small relative to the length (such as 30m and 50m) of the rocket because the rocket is a precisely manufactured aerospace device. When the rocket 210 to be transferred is lifted and placed on the bracket 160, the design centroid G of the rocket 210 to be transferred is necessarily placed at a predetermined position (for example, between two adjacent fuel tanks) because the lifting and placing of the rocket 210 to be transferred are also highly precise operations.
Because the actual barycenter of rocket does not coincide with the design barycenter, use the place ahead of actual barycenter at the design barycenter as an example, place rocket 210 to be transported on bracket 160 after, rocket 210 to be transported can use actual barycenter as the center of rotation, the front end of rocket 210 to be transported rotates downwards and pushes down the bracket, the rear end of rocket 210 to be transported rotates upwards and keeps away from the bracket, the lower cavity of each hydro-cylinder carries out the complementation of fluid through lower oil circuit each other in this process, the upper cavity of each hydro-cylinder carries out the complementation of oil circuit through last oil circuit each other. After the rocket 210 to be transported rotates to a predetermined range, the shell at the front end of the rocket 210 to be transported contacts with the front elastic part 121 arranged around the foremost oil cylinder 111, and presses down the front elastic part 121, and the front elastic part 121 exerts a counterforce on the shell at the front end of the rocket 210 to be transported, so that the front end of the rocket 210 to be transported tilts upwards.
Just after the rocket 210 to be transported is hoisted and placed, the front elastic part 121 acts in the process of pressing down the front end of the rocket 210 to be transported, so that the front end of the rocket 210 to be transported has a tendency of rising, the oil quantity of the upper cavity and the lower cavity of each oil cylinder is adjusted in a smaller range, the stability of the rocket 210 to be transported in the hoisting and placing process is further ensured, and the rocket 210 to be transported is prevented from being unstable and falling due to the fact that the rotating amplitude of the rocket 210 to be transported is too large due to the actual center of mass deviation of the rocket 210 to be transported; in the process, a plurality of components (the front elastic component 121, the oil cylinder 111, the oil cylinder 112, the oil cylinder 113 … …, the oil cylinder 11n-2, the oil cylinder 11n-1 and the oil cylinder 11n) for applying loads to the rocket 210 to be transported are arranged, so that the loads applied to the shell of the rocket 210 to be transported by the front elastic component 121 are smaller, the equipment to be protected is protected, meanwhile, the thicker shell at the position where the elastic component is arranged is used for bearing, the shell wall thickness of the rocket at other positions can be reduced, and the weight of the rocket is reduced.
Through the above-mentioned continuous adjustment in a small range, the rocket 210 to be transported is horizontally and stably placed, each cylinder uniformly loads the shell of the rocket 210 to be transported, and the front elastic component 121 and the rear elastic component 122 do not apply a load to the shell of the rocket 210 to be transported. At this time, the rocket 210 to be transported can be transported, and when the rocket is going to go uphill, downhill or bumpy road surface in the transportation process, because the upper cavities of the oil cylinders are communicated and the lower cavities of the oil cylinders are communicated, the hydraulic oil of the oil cylinders can be supplemented with each other, thereby ensuring that the bracket connected with the piston rod of the oil cylinder is always contacted with the shell of the rocket 210 to be transported and applying even load to the shell of the rocket 210 to be transported, each of the plurality of rams thus uniformly loads the hull of the rocket 210 to be transported, therefore, the phenomenon of load sharp increase caused by over-constraint formed by impact is avoided, thereby further ensuring that the equipment needing to be protected is protected and simultaneously the thicker shell at the position is utilized for carrying, further, the wall thickness of the rocket shell at other positions can be reduced, and the weight of the rocket is further reduced.
Because guaranteed to load rocket steady to rocket strutting arrangement to guaranteed to under the even atress's of rocket the condition during transportation, make full use of the position of the big shell of intensity itself in the rocket structure bears, so can effectual reduction rocket's weight, consequently just reduced the face pressure of rocket supporting position, thereby avoided the transportation that leads to because of the weight increase to the destruction of rocket body, and then avoided leading to the inefficacy of rocket body structure because of transporting. In addition, the weight of the rocket can be effectively reduced, so that the rocket can be transported under the condition of full load of solid fuel, thereby avoiding filling fuel in a rocket launching site and reducing the occupied time of the rocket for the launching site.
It will be evident to those skilled in the art that the invention is not limited to the details of the foregoing illustrative embodiments, and that the present invention may be embodied in other specific forms without departing from the spirit or essential attributes thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
Furthermore, it should be understood that although the present description refers to embodiments, not every embodiment may contain only a single embodiment, and such description is for clarity only, and those skilled in the art should integrate the description, and the embodiments may be combined as appropriate to form other embodiments understood by those skilled in the art.
Claims (9)
1. A rocket transfer support device, comprising: the device comprises a front elastic component, a rear elastic component and at least three oil cylinders; the lower cavity of each oil cylinder is communicated with each other through a lower oil way, and the upper cavity of each oil cylinder is communicated with each other through an upper oil way; a front elastic component with the deformation direction the same as the extension direction of a piston rod of the oil cylinder is arranged around the oil cylinder at the forefront; a rear elastic component with the deformation direction the same as the extension direction of a piston rod of the oil cylinder is arranged around the oil cylinder at the last side; a piston rod of each oil cylinder extends upwards to be connected with a bracket, and the bracket is contacted with a rocket shell at the position of equipment to be protected in the rocket to be transported; the lower oil way consisting of the front lower oil way and the rear lower oil way is connected with a lower oil way stop valve, the lower oil way stop valve is connected with a lower oil way hydraulic control one-way valve, and the lower oil way hydraulic control one-way valve is connected with a lower oil way quick connector to realize connection with an oil tank; an upper oil way consisting of a front upper oil way and a rear upper oil way is connected with an upper oil way stop valve, the upper oil way stop valve is connected with an upper oil way hydraulic control one-way valve, and the upper oil way hydraulic control one-way valve is connected with an upper oil way quick connector so as to realize connection with an oil tank; the lower oil way quick connector is also connected with a control oil way of the upper oil way hydraulic control one-way valve, and the upper oil way quick connector is connected with the control oil way of the lower oil way hydraulic control one-way valve.
2. A rocket transfer supporting device according to claim 1, wherein the positions of the front elastic member and the rear elastic member are both set at positions corresponding to the positions of the devices to be protected of the rocket to be transferred.
3. A rocket transfer support device according to claim 1, wherein the front resilient member is disposed forward of the forwardmost cylinder and the rear resilient member is disposed rearward of the rearwardmost cylinder.
4. A rocket transfer supporting device according to any one of claims 1-3, wherein the supporting force of each part of the rocket to be transferred is set according to the weight of each part of the rocket to be transferred, and the cross-sectional area of the oil cylinder corresponding to each part of the rocket to be transferred is set according to the ratio of the supporting force of each part and the same ratio.
5. A rocket transfer support device according to any one of claims 1-3, wherein each cylinder is provided with a damping system.
6. A rocket transfer support according to any one of claims 1-3 wherein each cylinder is vertically attached to a frame of the rocket transfer support.
7. A rocket transfer support device according to claim 6, wherein the piston rod of each cylinder is hinged to the lower end of a bracket which is in sliding engagement with a vertically through sliding hole of the frame of the rocket transfer support device.
8. A rocket transport support device according to claim 7, wherein the end surface of the upper end of the bracket is a concave surface matching the shape of the housing of the rocket to be transported.
9. A rocket transfer car (buggy), comprising: a vehicle body and a rocket transport support device of any of claims 1-8, said rocket transport support device mounted on said vehicle body.
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| CN201910959977.9A CN110745056B (en) | 2019-10-10 | 2019-10-10 | Rocket transfer supporting device and rocket transfer trolley |
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| CN201910959977.9A CN110745056B (en) | 2019-10-10 | 2019-10-10 | Rocket transfer supporting device and rocket transfer trolley |
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| CN110745056B true CN110745056B (en) | 2020-06-16 |
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| CN111959386B (en) * | 2020-07-28 | 2021-10-15 | 北京航天发射技术研究所 | Lock arrow mechanism with direction function |
| CN113218246B (en) | 2021-05-20 | 2022-11-08 | 鲁东大学 | Offshore rocket thermal launching erecting device and erecting method |
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| RU2141906C1 (en) * | 1997-11-26 | 1999-11-27 | Центральное конструкторское бюро транспортного машиностроения | Carrier |
| CN107042785B (en) * | 2016-11-30 | 2019-11-15 | 北京特种机械研究所 | A kind of fixed mechanism for aircraft various states |
| CN207955444U (en) * | 2018-03-01 | 2018-10-12 | 北京爱尔达电子设备有限公司 | Sounding rocket with protective device emits transport vehicle |
| CN108502727B (en) * | 2018-03-28 | 2023-12-05 | 蓝箭航天技术有限公司 | Lifting device and crane |
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Address after: 511400 room 1702, No. 1, Cuiying street, Nansha District, Guangzhou, Guangdong Province Patentee after: Guangzhou Zhongke Aerospace Exploration Technology Co.,Ltd. Address before: 100176 1201, 12 / F, building 6, yard 18, Kechuang 13th Street, Beijing Economic and Technological Development Zone, Daxing District, Beijing Patentee before: Beijing Zhongke Aerospace Exploration Technology Co.,Ltd. |