CN110962722A - Space truss type rocket erecting arm - Google Patents
Space truss type rocket erecting arm Download PDFInfo
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- CN110962722A CN110962722A CN201811564714.XA CN201811564714A CN110962722A CN 110962722 A CN110962722 A CN 110962722A CN 201811564714 A CN201811564714 A CN 201811564714A CN 110962722 A CN110962722 A CN 110962722A
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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
Abstract
The invention discloses a space truss type rocket erecting arm, and belongs to ground launch guarantee equipment of a carrier rocket. The vertical arm is designed into a five-section variable cross-section structure according to the stress condition of each action in the whole operation process, and the five-section variable cross-section structure comprises a first section, a middle section, a tail section, a head transition section between the first section and the middle section, and a tail transition section between the middle section and the tail section; each section adopts a uniform cross-section structure; the lower bottom surface of the first section part is of an inwards concave structure, and the height of the bottom surface of the inwards concave structure is higher than that of the lower bottom surface of the main body structure of the vertical arm, so that an auxiliary supporting structure can be conveniently arranged below the inwards concave structure; the whole cross section of the vertical arm is designed into a V-shaped structure. The erecting arm has enough rigidity and strength and can realize large-tonnage reliable bearing.
Description
Technical Field
The invention relates to a vertical arm used on a rocket launching transportation support vehicle, and belongs to the technical field of ground launching support equipment of carrier rockets.
Background
Before the rocket is launched, in the processes of assembling, parking, transporting, erecting and withdrawing, an integrated special guarantee barrier can be adopted to finish all the actions, one of the main structures of the special equipment is an erecting arm, and the main functions of the special equipment are as follows: the supporting device supports the product and bears the inertia load of the product such as gravity and the like, provides an installation foundation for each supporting and adjusting device, and connects the rocket and the chassis vehicle.
In the prior art, a tower crane is adopted for rocket overturning and core-level butt joint to complete preparation operation before launching, and a truss structure on a transport vehicle only plays a role in parking and transporting and cannot realize integrated erection and withdrawal.
The prior equipment which partially adopts a special vehicle with a vertical arm device to complete the preparation operation before launching has the following problems:
(1) at present, because core stages of a multi-stage rocket are separately transported, the length of a vertical arm is correspondingly smaller, when the preparation time for launching is required to be shortened and the launching process is required to be optimized, the core stage is required to be integrally transported and integrally erected, so that the length of the vertical arm is increased, the length of a cantilever in the erecting process is increased, the self weight of the vertical arm is increased, the deflection of the integral erecting process is difficult to control, and a large additional bending moment is generated on a rocket body;
(2) the section of a common vertical arm is generally of a regular rectangular structure, while the loading object of the rocket vertical arm is cylindrical, the structure between the vertical arm and the rocket is not compact, the space waste is large, and the whole vehicle height control is not facilitated;
(3) if the vertical arm adopts a solid web type structure and is formed by welding steel plates together, the number of welding seams is more, and the dead weight of the solid web type structure with the same bearing capacity is much larger than that of a truss type structure.
Disclosure of Invention
In view of the above, the invention provides a space truss type rocket erector arm, which has enough rigidity and strength and can realize large-tonnage reliable bearing.
A space truss type rocket erecting arm is designed into a five-section variable cross section structure according to the stress condition of each action in the whole operation process, wherein the five-section variable cross section comprises a first section, a middle section, a tail section, a head transition section between the first section and the middle section, and a tail transition section between the middle section and the tail section; each section adopts a uniform cross-section structure; the lower bottom surface of the first section part is of an inwards concave structure, and the height of the bottom surface of the inwards concave structure is higher than that of the lower bottom surface of the main body structure of the vertical arm, so that an auxiliary supporting structure can be conveniently arranged below the inwards concave structure; the whole cross section of the vertical arm is designed into a V-shaped structure.
Furthermore, the space truss structure of the vertical arm forms a stable space truss structure by four main chords, four longitudinal beams and corresponding connecting rod systems; the four main chords form the outermost structure of the erecting arm, the four longitudinal beams penetrate through the whole length direction of the erecting arm, the four longitudinal beams form a rectangle in space and are positioned inside a rectangular frame formed by the four main chords, and the rectangular bottom surfaces of the longitudinal beams are coplanar with the rectangular frame bottom surfaces of the main chords.
Further, the main chords comprise an upper left main chord, a lower left main chord, an upper right main chord and a lower right main chord; the upper left main chord and the lower left main chord are connected by a triangular unit consisting of a vertical web member and an inclined web member; the connecting structure between the upper right main chord and the lower right main chord is symmetrical to the left side structure.
Furthermore, a web member for connecting the upper chord member and the vertical web member is additionally arranged at the middle section of the vertical arm, and the web member transmits the supporting force of the main vertical oil cylinder to the chord member and other connected rod systems; the tail sections of the upper left main chord and the upper right main chord are provided with a section of concave structure to prevent interference with the arrow body arm embracing device when the arrow body arm embracing device is opened, and an inclined web member is arranged between the upper chord and the lower chord at the section.
Furthermore, the four longitudinal beams are connected through vertical rods, upper cross rods and lower cross rods to form horizontal trusses, horizontal oblique rods are connected among the upper cross rods, and the horizontal oblique rods and the upper cross rods form triangular unit trusses; the four longitudinal beams are connected with the corresponding positions of the main chord members through the rods and the space rods to form a space truss structure.
Has the advantages that:
1. the vertical jib is designed into a five-section variable cross-section structure according to the stress condition of each action in the whole operation flow to realize the optimization of the whole structure, the whole appearance is designed to be adaptive to a bending moment diagram borne by the vertical jib, so that the internal forces of all sections of chords are approximately equal, and the chords with equal cross-sections are adopted, thereby reducing the weight of the section; the cross section of the middle section is designed to be the highest, so that the deflection deformation can be controlled with the greatest benefit; the cross section is designed into a V-shaped structure, so that the bending resistance of the vertical arm is improved to the maximum extent; the front end is designed with a concave inward-contracting type slide rail to realize compact arrangement with the auxiliary supporting device.
2. In the spatial truss structure, the triangular units are formed by the vertical web members and the diagonal web members between the main chords, and in the horizontal truss formed by the four longitudinal beams, the horizontal diagonal members and the upper cross members also form a triangular unit truss, and the triangular units are a geometric invariant system, so that the overall structure rigidity of the vertical arm is better.
Drawings
FIG. 1 is a schematic perspective view of the present invention
FIG. 2 is a front view of the present invention (left side is a traveling direction, and upper side is an upper portion)
FIG. 3 is a schematic view of the main body outline of the front view angle of the present invention
FIG. 4 is a left side view of the spatial truss type riser of FIG. 2
FIG. 5 is a top plan view of the spatial truss type riser of FIG. 2
FIG. 6 is a cross-sectional view of the spatial truss type riser arm A-A of FIG. 2
FIG. 7 is a cross-sectional view of the spatial truss type riser B-B of FIG. 2
FIG. 8 is a cross-sectional view of the spatial truss type riser arm C-C of FIG. 2
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
As shown in attached figures 1 and 2, the invention provides a space truss type rocket erector arm, and an outermost structure of a main body of the erector arm consists of an upper left main chord 1, a lower left main chord 2, an upper right main chord 3 and a lower right main chord 4.
The outline of the space truss type vertical arm structure consisting of the upper left main chord 1, the lower left main chord 2, the upper right main chord 3 and the lower right main chord 4 is shown in fig. 3. The space truss type erecting arm structure is designed into a variable cross section according to the stress condition of each action in the whole operation flow, the whole appearance of the space truss type erecting arm structure is designed to be adaptive to a bending moment graph borne by the erecting arm, so that the internal force of each chord is approximately equal, the chords with equal cross sections can be adopted, and the weight of the section is reduced. The chord structure can be divided into a first section, a middle section and a tail section. In order to ensure that the structure is stressed reasonably, a head transition section is designed between the first section and the middle section, and a tail transition section is designed between the middle section and the tail section.
In order to control the deformation in the erecting process, according to the calculation and analysis result, the supporting part and the front and rear areas of the main erecting oil cylinder are the parts with the largest stress, the part is the middle section, the cross section of the middle section is designed to be the highest, and the deflection deformation can be controlled with the greatest benefit.
During the process of turning the vertical arm from a horizontal (0 degree) state to a vertical (90 degree) state, the two stages are divided: in the process of 0-30 degrees, the auxiliary support is used as a component for mainly providing turning force, and the main vertical oil cylinder is in a follow-up state in the stage; in the process of 30-90 degrees, the main vertical oil cylinder provides the turning force. From this, the bottom surface designs into indent formula structure under left lower main chord 2 and the 4 first parts of right lower main chord, and the lower bottom surface of than erecting arm major structure is high, is convenient for arrange auxiliary stay structure, and secondly left lower main chord 2 and the 4 first parts of right lower main chord bottom surface also regard as the slide rail with auxiliary stay contact for erect the arm whole and arrange the compactness.
The upper left main chord 1 and the lower left main chord 2 are connected by triangular units formed by web members, and the triangular units are of a geometric invariant system and have better structural rigidity. As shown in fig. 2, the head part upper chord member and the head part lower chord member are connected by a vertical web member 6 and a diagonal web member 7, the head part transition part upper chord member and the head part transition part lower chord member are connected by a vertical web member 8 and a diagonal web member 9, the middle part upper chord member and the head part transition part lower chord member are connected by a vertical web member 10 and a diagonal web member 11, the tail part transition part upper chord member and the tail part transition part lower chord member are connected by a vertical web member 8 and a diagonal web member 9, and the tail part upper chord member and the tail part lower chord member are connected by a vertical web member 14 and a diagonal web member 13.
And a web member 12 is added at the supporting position of the main vertical oil cylinder at the middle section part and is used for connecting the upper chord member and the vertical web member and transmitting the supporting force of the main vertical oil cylinder to the chord member and other rod systems. The tail section part of the upper left chord 1 is designed with a section of concave structure to prevent interference with the arrow body arm embracing device when opening, and an inclined web member 15 is arranged between the upper chord and the lower chord at the section part. The connecting structure between the upper right main chord 3 and the lower left main chord 4 is symmetrical to the left side structure.
As shown in fig. 4, four longitudinal beams 5 are designed in the middle of the vertical arm and penetrate the vertical arm along the whole length direction. As shown in fig. 6, 7, and 8: the longitudinal beam 5 (upper left) is connected with the lower left main chord 2 through a rod 17 and a rod 18, and the longitudinal beam 5 (upper left) is connected with the upper left main chord 1 at the first section, the middle section and the tail section through a space rod 22, a space rod 23 and a space rod 24 respectively; the longitudinal beam 5 (lower left) is connected with a lower left main chord through a rod 17 and a rod 18; the longitudinal beam 5 (upper right) is connected with the lower right main chord through a rod 17 and a rod 18, and the longitudinal beam 5 (upper right) is connected with the upper right main chord 3 at the first section, the middle section and the tail section through a space rod 22, a space rod 23 and a space rod 24 respectively; the longitudinal beam 5 (lower right) is connected with a lower right main chord through a rod 17 and a rod 18; the four longitudinal beams 5 are connected through vertical rods 19, upper cross rods 20 and lower cross rods 21. As shown in fig. 5, horizontal diagonal rods 25 are designed between the upper cross rods 20 to form a triangular unit truss with the upper cross rods 20, so that the horizontal truss also becomes a geometrically invariable system.
A supporting seat bracket 16 is designed at the rearmost part of the truss structure, so that the weight of the supporting seat is borne by the supporting seat bracket 16 on the vertical arm when the truss structure is in a running state, and the supporting seat is prevented from generating large bending moment load on an arrow body.
Thus, four main chords (the upper left main chord 1, the lower left main chord 2, the upper right main chord 3 and the lower right main chord 4) and four longitudinal beams 5 form a stable space truss structure through the chord systems.
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (5)
1. A space truss type rocket erector arm is characterized in that the erector arm is designed into a five-section variable cross-section structure according to the stress condition of each action in the whole operation process, and the five-section variable cross-section structure comprises a first section, a middle section, a tail section, a head transition section between the first section and the middle section, and a tail transition section between the middle section and the tail section; each section adopts a uniform cross-section structure; the lower bottom surface of the first section part is of an inwards concave structure, and the height of the bottom surface of the inwards concave structure is higher than that of the lower bottom surface of the main body structure of the vertical arm, so that an auxiliary supporting structure can be conveniently arranged below the inwards concave structure; the whole cross section of the vertical arm is designed into a V-shaped structure.
2. A space truss rocket erector arm as in claim 1 wherein the space truss structure of said erector arm is formed as a stable space truss structure from four main chords, four longitudinal beams and corresponding tie rods; the four main chords form the outermost structure of the erecting arm, the four longitudinal beams penetrate through the whole length direction of the erecting arm, the four longitudinal beams form a rectangle in space and are positioned inside a rectangular frame formed by the four main chords, and the rectangular bottom surfaces of the longitudinal beams are coplanar with the rectangular frame bottom surfaces of the main chords.
3. A space truss rocket riser according to claim 1 or 2 wherein said main chords include an upper left main chord, a lower left main chord, an upper right main chord, and a lower right main chord; the upper left main chord and the lower left main chord are connected by a triangular unit consisting of a vertical web member and an inclined web member; the connecting structure between the upper right main chord and the lower right main chord is symmetrical to the left side structure.
4. The space truss rocket erector arm of claim 3 wherein a web member connecting the upper boom member and the vertical web member is added to the midsection of said erector arm, said web member transmitting the main vertical cylinder support force to the boom member and other connected linkages; the tail sections of the upper left main chord and the upper right main chord are provided with a section of concave structure to prevent interference with the arrow body arm embracing device when the arrow body arm embracing device is opened, and an inclined web member is arranged between the upper chord and the lower chord at the section.
5. The space truss type rocket erector arm of claim 4 wherein said four stringers are connected together by vertical rods, upper cross-rods and lower cross-rods to form horizontal trusses, horizontal diagonals are connected between the upper cross-rods, and the horizontal diagonals and the upper cross-rods form triangular unit trusses; the four longitudinal beams are connected with the corresponding positions of the main chord members through the rods and the space rods to form a space truss structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811564714.XA CN110962722A (en) | 2018-12-20 | 2018-12-20 | Space truss type rocket erecting arm |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811564714.XA CN110962722A (en) | 2018-12-20 | 2018-12-20 | Space truss type rocket erecting arm |
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| Publication Number | Publication Date |
|---|---|
| CN110962722A true CN110962722A (en) | 2020-04-07 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811564714.XA Pending CN110962722A (en) | 2018-12-20 | 2018-12-20 | Space truss type rocket erecting arm |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115649039A (en) * | 2022-12-22 | 2023-01-31 | 山西全城联动环保科技有限公司 | Waste transport motor vehicle |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8701539B1 (en) * | 2013-03-15 | 2014-04-22 | General Electrodynamics International, LLC | Expandable electromagnetic launcher |
| CN104930915A (en) * | 2015-06-08 | 2015-09-23 | 北京航天发射技术研究所 | Truss type erecting arm |
| CN105235578A (en) * | 2015-11-04 | 2016-01-13 | 北京航天发射技术研究所 | Highway transport vehicle |
| CN107554823A (en) * | 2017-08-09 | 2018-01-09 | 湖北航天技术研究院总体设计所 | A kind of large scale segmented rocket has transported perpendicular transmitting girder structure |
| CN108562189A (en) * | 2018-03-20 | 2018-09-21 | 西安航天动力技术研究所 | A kind of sounding rocket emitter |
-
2018
- 2018-12-20 CN CN201811564714.XA patent/CN110962722A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8701539B1 (en) * | 2013-03-15 | 2014-04-22 | General Electrodynamics International, LLC | Expandable electromagnetic launcher |
| CN104930915A (en) * | 2015-06-08 | 2015-09-23 | 北京航天发射技术研究所 | Truss type erecting arm |
| CN105235578A (en) * | 2015-11-04 | 2016-01-13 | 北京航天发射技术研究所 | Highway transport vehicle |
| CN107554823A (en) * | 2017-08-09 | 2018-01-09 | 湖北航天技术研究院总体设计所 | A kind of large scale segmented rocket has transported perpendicular transmitting girder structure |
| CN108562189A (en) * | 2018-03-20 | 2018-09-21 | 西安航天动力技术研究所 | A kind of sounding rocket emitter |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115649039A (en) * | 2022-12-22 | 2023-01-31 | 山西全城联动环保科技有限公司 | Waste transport motor vehicle |
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Application publication date: 20200407 |