CN110186325A - A kind of Solid Launch Vehicle multi-point support system - Google Patents
A kind of Solid Launch Vehicle multi-point support system Download PDFInfo
- Publication number
- CN110186325A CN110186325A CN201910435544.3A CN201910435544A CN110186325A CN 110186325 A CN110186325 A CN 110186325A CN 201910435544 A CN201910435544 A CN 201910435544A CN 110186325 A CN110186325 A CN 110186325A
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- CN
- China
- Prior art keywords
- oil cylinder
- auxiliary support
- launch vehicle
- vertical arm
- support apparatus
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F3/00—Rocket or torpedo launchers
- F41F3/04—Rocket or torpedo launchers for rockets
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Vehicle Cleaning, Maintenance, Repair, Refitting, And Outriggers (AREA)
Abstract
The present invention provides a kind of Solid Launch Vehicle multi-point support systems, including play vertical arm；One group of main supporting mechanism and multiple groups auxiliary support apparatus are set in described vertical arm, main supporting mechanism and auxiliary support apparatus are located at along the middle line distribution and main supporting mechanism for playing vertical arm is distributed rear end, and the auxiliary support apparatus positioned at distribution front end also has been located at the front position of vertical arm；Each group auxiliary support apparatus provides lifting drive by an oil cylinder respectively.The present invention can be realized rocket body during level is parked, transition is transported, plays perpendicular with any main support, the demand of remaining multiple spot Auxiliary support, ensure that each auxiliary support apparatus reaction of bearing is impartial；It can be realized the requirement of each Auxiliary support counter-force equalization.
Description
Technical field
The present invention relates to a kind of Solid Launch Vehicle multi-point support systems, belong to Launch Vehicle Ground supports guarantee skill
Art field.
Background technique
In recent years, China's Space Industry has stepped into commercialization process in multiple fields, and the development of business space flight is to ground
Transmitting guarantee field proposes new demand.Horizontal transhipment in the past plays perpendicular carrier rocket or weapon system use front and back two o'clock
Fixed supporting way, support rocket body is parked, transition is transported or plays perpendicular function, and the support force of two o'clock might not be equal, and with
The development of business space flight, the rocket body that slenderness ratio is big, intensity is weak are badly in need of being guaranteed the safety of rocket body using multi-point support, be wanted simultaneously
The reaction of bearing of each Auxiliary support point is asked to want equal.Therefore Solid Launch Vehicle multi-point support technology carrier rocket or force at home
Device system has no using precedent, the equal technology of multi-point support device counter-force in the urgent need to address, and solution level is parked, transition is transported
Defeated, perpendicular the problem of guaranteeing rocket body safety in the process.
Summary of the invention
In order to solve the above technical problems, the present invention provides a kind of Solid Launch Vehicle multi-point support system, solid fortune
Carrying rocket multi-point support system can guarantee that rocket body uses multi-point support, while the counter-force of each Auxiliary support point is equal.
The present invention is achieved by the following technical programs.
A kind of Solid Launch Vehicle multi-point support system provided by the invention, including play vertical arm；It is arranged in described vertical arm
One group of main supporting mechanism and multiple groups auxiliary support apparatus, main supporting mechanism and auxiliary support apparatus along the middle line distribution for playing vertical arm and
Main supporting mechanism is located at distribution rear end, and the auxiliary support apparatus positioned at distribution front end also has been located at the front position of vertical arm；Each group
Auxiliary support apparatus provides lifting drive by an oil cylinder respectively.
The auxiliary support apparatus is made of guiding device, rack, curved support seat, and guiding device has been fixed on vertical arm
Interior and be located at the top of oil cylinder, rack is fixed on the top movable end of oil cylinder and is limited in vertical direction, arc by guiding device
Support base is fixed on the rack end.
Connection between the bottom of the frame and oil cylinder top movable end is to be rotatably connected.
The oil cylinder oil outlet is connected with fluid pressure line.
Shut-off valve is provided on the pipeline of the oil cylinder.
The rodless cavity side of the oil cylinder is connected with accumulator.
The accumulator oil outlet is provided with shut-off valve.
The oil cylinder oil outlet is connected with valve member, and the rod chamber of oil cylinder is interconnected by valve member with rodless cavity.
The beneficial effects of the present invention are: it can be realized rocket body during level is parked, transition is transported, plays perpendicular with a bit
Main support, remaining multiple spot Auxiliary support demand, ensure that each auxiliary support apparatus reaction of bearing is impartial；It can be realized each auxiliary
The requirement of reaction of bearing equalization.
Detailed description of the invention
Fig. 1 is structural schematic diagram of the invention；
Fig. 2 is the top view of Fig. 1；
Fig. 3 is the cross section structure schematic diagram of auxiliary support apparatus in Fig. 2.
In figure: 1- plays vertical arm, 2- oil cylinder, 3- guiding device, 4- rack, 5- curved support seat, 6- accumulator, 7- hydraulic tube
Road, 8- valve member, the main supporting mechanism of 9-, 10- auxiliary support apparatus.
Specific embodiment
Be described further below technical solution of the present invention, but claimed range be not limited to it is described.
A kind of Solid Launch Vehicle multi-point support system as shown in Figure 1 to Figure 3, including play vertical arm 1；Described vertical arm 1
One group of main supporting mechanism 9 of upper setting and multiple groups auxiliary support apparatus 10, main supporting mechanism 9 and auxiliary support apparatus 10 are along a vertical arm
1 middle line is distributed and main supporting mechanism 9 is located at distribution rear end, and the auxiliary support apparatus 10 positioned at distribution front end also has been located at vertical arm
1 front position；Each group auxiliary support apparatus 10 provides lifting drive by an oil cylinder 2 respectively.
The auxiliary support apparatus 10 is made of guiding device 3, rack 4, curved support seat 5, and guiding device 3 is fixed on
It rises in vertical arm 1 and is located at 2 top of oil cylinder, rack 4 is fixed on the top movable end of oil cylinder 2 and is limited in by guiding device 3 vertical
Histogram is to curved support seat 5 is fixed on 4 upper end of rack.
Connection between 2 top movable end of 4 bottom of rack and oil cylinder is to be rotatably connected.
2 oil outlet of oil cylinder is connected with fluid pressure line 7.
Shut-off valve is provided on the pipeline of the oil cylinder 2.
The rodless cavity side of the oil cylinder 2 is connected with accumulator 6.
6 oil outlet of accumulator is provided with shut-off valve.
2 oil outlet of oil cylinder is connected with valve member 8, and the rod chamber of oil cylinder 2 is interconnected by valve member 8 with rodless cavity.
Each supporting point in vertical arm 1 that rises of the invention is respectively arranged with oil cylinder 2 as a result, and 2 upper end of oil cylinder passes through guiding device 3
It is connect with rack 4, guiding device 3 can be provided with curved support in 4 upper end of rack with relative motion with the guide rail risen in vertical arm 1
Seat 5, is used to support rocket body, and 2 oil outlet of oil cylinder connects fluid pressure line 7 and valve member 8, is provided with cut-off on the pipeline of each oil cylinder 2
The rod chamber of each oil cylinder 2 is interconnected by valve, valve member 8 with rodless cavity, and accumulator 6 is connected to the rodless cavity side of oil cylinder 2, and
6 oil outlet of accumulator is provided with shut-off valve.
The course of work of the present invention are as follows: before rocket body lifting, it is hydraulic first to open 2 oil outlets of each 10 lower end oil cylinder of auxiliary support apparatus
The shut-off valve of 6 oil outlet of shut-off valve and accumulator on pipeline 7 drives each Auxiliary support by hydraulic system to 2 fuel feeding of oil cylinder
Device 10 slowly rises, and when some Auxiliary support height and consistent 9 height of main support device, it is fuel-displaced to close the support cylinder 2
The shut-off valve of mouth continues fuel feeding and stretches other high support devices so that the support device height no longer changes, other support devices
The cut-off on the 2 oil outlet fluid pressure line 7 of support device oil cylinder is equally closed when some bearing height is consistent with main bearing height
Valve, with same method until all support device height are adjusted to cut-off consistent with main bearing height, and closing accumulator 6
Valve, to guarantee that rocket body axis is parallel to the horizontal plane after rocket body has been lifted into vertical arm 1.After rocket body lifting, it is fuel-displaced to open each oil cylinder 2
The shut-off valve of 6 oil outlet of valve member 8 and accumulator on mouthful fluid pressure line 7, make each 10 lower end oil cylinder 2 of auxiliary support apparatus without bar
Chamber, rod chamber are respectively communicated with, while accumulator 6 carries out repairing to each oil cylinder 2, with the leakage of compensating cylinder 2, realize Auxiliary support
The pressure holding function of device, i.e. reaction of bearing can remain unchanged, and accumulator should be inflated before lifting.In auxiliary support apparatus
In 10 height adjustment process, guiding device 3 takes guiding role, and rack 4 and curved support seat 5 take supporting role.Rocket body is in level
Park, transition transport, rise it is perpendicular during, each oil cylinder 2 that is connected to is risen or fallen automatically according to the case where support device stress to protect
Card reaction of bearing is consistent, the amount of deflection of vertical arm 1 from each oil cylinder 2 is suitable for rough road and rises when erecting.It ensure that rocket body exists
Level is parked, transition is transported, safety when playing perpendicular.
Claims (8)
1. a kind of Solid Launch Vehicle multi-point support system, including play vertical arm (1), it is characterised in that: it is set on described vertical arm (1)
One group of main supporting mechanism (9) and multiple groups auxiliary support apparatus (10) are set, main supporting mechanism (9) and auxiliary support apparatus (10) edge are risen
The middle line of vertical arm (1) is distributed and main supporting mechanism (9) is located at distribution rear end, the auxiliary support apparatus (10) positioned at distribution front end
Positioned at the front position for playing vertical arm (1)；Each group auxiliary support apparatus (10) provides lifting drive by an oil cylinder (2) respectively.
2. Solid Launch Vehicle multi-point support system as described in claim 1, it is characterised in that: the auxiliary support apparatus
(10) it is made of guiding device (3), rack (4), curved support seat (5), guiding device (3) has been fixed in vertical arm (1) simultaneously
At the top of oil cylinder (2), rack (4) is fixed on the top movable end of oil cylinder (2) and is limited in Vertical Square by guiding device (3)
To curved support seat (5) is fixed on rack (4) upper end.
3. Solid Launch Vehicle multi-point support system as claimed in claim 2, it is characterised in that: rack (4) bottom and
Connection between oil cylinder (2) top movable end is to be rotatably connected.
4. Solid Launch Vehicle multi-point support system as described in claim 1, it is characterised in that: oil cylinder (2) oil outlet
It is connected with fluid pressure line (7).
5. Solid Launch Vehicle multi-point support system as described in claim 1, it is characterised in that: the pipeline of the oil cylinder (2)
On be provided with shut-off valve.
6. Solid Launch Vehicle multi-point support system as described in claim 1, it is characterised in that: the oil cylinder (2) without bar
Chamber side is connected with accumulator (6).
7. Solid Launch Vehicle multi-point support system as claimed in claim 6, it is characterised in that: the accumulator (6) is fuel-displaced
Mouth is provided with shut-off valve.
8. Solid Launch Vehicle multi-point support system as described in claim 1, it is characterised in that: oil cylinder (2) oil outlet
It is connected with valve member (8), and the rod chamber of oil cylinder (2) and rodless cavity are interconnected by valve member (8).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910435544.3A CN110186325A (en) | 2019-05-23 | 2019-05-23 | A kind of Solid Launch Vehicle multi-point support system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910435544.3A CN110186325A (en) | 2019-05-23 | 2019-05-23 | A kind of Solid Launch Vehicle multi-point support system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110186325A true CN110186325A (en) | 2019-08-30 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910435544.3A Pending CN110186325A (en) | 2019-05-23 | 2019-05-23 | A kind of Solid Launch Vehicle multi-point support system |
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| Country | Link |
|---|---|
| CN (1) | CN110186325A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111023900A (en) * | 2019-11-05 | 2020-04-17 | 蓝箭航天空间科技股份有限公司 | Rocket supporting and holding device |
| CN111043905A (en) * | 2019-11-05 | 2020-04-21 | 蓝箭航天空间科技股份有限公司 | Rocket rear supporting point supporting and adjusting system |
| CN114872932A (en) * | 2022-07-11 | 2022-08-09 | 东方空间技术(山东)有限公司 | Control system for controlling spacecraft to launch at sea |
| CN115231008A (en) * | 2022-08-18 | 2022-10-25 | 北京中科宇航技术有限公司 | Stable governing system is all carried |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104776754A (en) * | 2015-04-15 | 2015-07-15 | 北京航天发射技术研究所 | Eight-supporting-point leveling method for rocket launching platform |
| CN106372355A (en) * | 2016-09-14 | 2017-02-01 | 北京航空航天大学 | Universal erection load simulation device |
| CN205979029U (en) * | 2016-08-23 | 2017-02-22 | 成都航天万欣科技有限公司 | Leveling strutting arrangement |
| CN107764133A (en) * | 2017-09-29 | 2018-03-06 | 北京航天发射技术研究所 | A kind of truss-like Missile Erecting Arm |
| CN107796266A (en) * | 2017-09-29 | 2018-03-13 | 北京航天发射技术研究所 | A kind of lighting plays perpendicular insulated hold and preparation method thereof |
| CN108502727A (en) * | 2018-03-28 | 2018-09-07 | 北京蓝箭空间科技有限公司 | Play perpendicular device and hoisting machine |
-
2019
- 2019-05-23 CN CN201910435544.3A patent/CN110186325A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104776754A (en) * | 2015-04-15 | 2015-07-15 | 北京航天发射技术研究所 | Eight-supporting-point leveling method for rocket launching platform |
| CN205979029U (en) * | 2016-08-23 | 2017-02-22 | 成都航天万欣科技有限公司 | Leveling strutting arrangement |
| CN106372355A (en) * | 2016-09-14 | 2017-02-01 | 北京航空航天大学 | Universal erection load simulation device |
| CN107764133A (en) * | 2017-09-29 | 2018-03-06 | 北京航天发射技术研究所 | A kind of truss-like Missile Erecting Arm |
| CN107796266A (en) * | 2017-09-29 | 2018-03-13 | 北京航天发射技术研究所 | A kind of lighting plays perpendicular insulated hold and preparation method thereof |
| CN108502727A (en) * | 2018-03-28 | 2018-09-07 | 北京蓝箭空间科技有限公司 | Play perpendicular device and hoisting machine |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111023900A (en) * | 2019-11-05 | 2020-04-17 | 蓝箭航天空间科技股份有限公司 | Rocket supporting and holding device |
| CN111043905A (en) * | 2019-11-05 | 2020-04-21 | 蓝箭航天空间科技股份有限公司 | Rocket rear supporting point supporting and adjusting system |
| CN111043905B (en) * | 2019-11-05 | 2020-09-01 | 蓝箭航天空间科技股份有限公司 | Rocket rear supporting point supporting and adjusting system |
| WO2021088817A1 (en) * | 2019-11-05 | 2021-05-14 | 蓝箭航天空间科技股份有限公司 | Rocket rear fulcrum support adjustment system |
| CN114872932A (en) * | 2022-07-11 | 2022-08-09 | 东方空间技术(山东)有限公司 | Control system for controlling spacecraft to launch at sea |
| CN115231008A (en) * | 2022-08-18 | 2022-10-25 | 北京中科宇航技术有限公司 | Stable governing system is all carried |
| CN115231008B (en) * | 2022-08-18 | 2024-05-17 | 北京中科宇航技术有限公司 | Uniform load stable adjusting system |
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Application publication date: 20190830 |