CN108759588B - Missile mass and mass center adjusting device and method - Google Patents
Missile mass and mass center adjusting device and method Download PDFInfo
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- CN108759588B CN108759588B CN201810425416.6A CN201810425416A CN108759588B CN 108759588 B CN108759588 B CN 108759588B CN 201810425416 A CN201810425416 A CN 201810425416A CN 108759588 B CN108759588 B CN 108759588B
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- counterweight
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
Abstract
A missile mass center adjusting device and an adjusting method are provided, the missile mass center adjusting device comprises balance weight pipes (2, 3) positioned in a missile cabin (1), a plurality of balance weight blocks (4) positioned in the balance weight pipes (2, 3), end caps (5, 7, 8, 9) detachably connected with two ends of the balance weight pipes (2, 3) respectively, and the balance weight pipes (2, 3) are connected with the missile cabin through flange plates (6, 10, 11); when the missile mass center adjusting device is assembled, the end cap at one end is connected with the cabin body or one flange plate (10) of the cabin body, one end of the counterweight pipe is connected with the end cap, the other end of the counterweight pipe is fixed through the other flange plate (6, 11), the end cap at the other end of the counterweight pipe is assembled, and the cabin body without the counterweight is assembled; after the equipment in the equal cabin is installed and debugged, the initial value of the mass center of the missile is measured, and a counterweight scheme is formulated by comparing the initial value with the theoretical mass center of mass to realize the accurate adjustment of the mass center of mass.
Description
Technical Field
The invention relates to the technical field of missiles, in particular to a missile mass center adjusting device; the invention also relates to a missile mass center adjusting method.
Background
The missile needs to adjust the mass through the balance weight, and meanwhile, the relative position of the mass center and the pneumatic pressure center is adjusted to improve the stability and the maneuverability of the missile. Traditional mode of regulation carries out mechanical connection with the balancing weight and the cabin body through bolt, screw, and the operating space of counter weight installation need be reserved to this kind of mode, and space utilization is low, and quality barycenter adjusting efficiency is poor. There is also a "lead pouring" method in the prior art, which, according to design, molds first and then pours molten liquid lead water into the mold. This approach suffers mainly from the following drawbacks: the process is complicated; generally, the balance weight is firstly and then assembled, and the weight is increased after the balance weight is assembled, so that the assembly among cabin sections is inconvenient; the "lead filled" weight is cured after completion and is often difficult to remove.
CN105737687A discloses a capsule body structure for adjusting mass and mass center in 2016, month 07 and 06, wherein the capsule body and a weight part are designed into an integral structure, and a lead block embedding hole is formed in the weight part; the number of the lead block embedding holes is multiple, and a connecting cover plate is arranged above the embedding holes; and the lead block embedding hole is filled with a lead block. The cabin body adopts the casting integrated into one piece, measures the initial value of quality barycenter after the machine adds, through the contrast with theoretical quality barycenter, formulates the adjustment scheme, including the distribution position and the quality of lead block, imbeds the accurate regulation of lead block realization to the quality barycenter in the hole.
The technical scheme has at least one of the following defects:
1. the cabin body and the counterweight are designed into an integral structure, so that the manufacturing difficulty of the cabin body is increased;
2. when the lead block is embedded, the calculation workload is large, the configuration is complex and the difficulty is large;
3. the lead block is embedded into the hole and is difficult to take out when solidified together with the hole; when the lead block is not solidified with the hole, the stability in the flying process is easily influenced along with the movement of the lead block in the hole in the moving process.
Disclosure of Invention
The invention aims to provide a missile mass center of mass adjusting device and method which are ingenious in structure, convenient to install, easy to adjust and capable of repeatedly utilizing a balancing weight.
In order to solve the technical problem, according to one aspect of the invention, the invention provides a missile mass center adjusting device, which comprises at least one counterweight pipe positioned in a missile shell; a plurality of balancing weights arranged in the balancing pipe; the end caps are detachably connected with two ends of the counterweight pipe respectively; the counterweight pipe is connected with the missile cabin through a flange plate.
As an improved technical scheme, the missile mass center adjusting device provided by the invention comprises a front end counterweight pipe and a rear end counterweight pipe which are positioned in a missile cabin; the front end counterweight pipe is fixed in the first cabin section through a first front end cap embedded in the first cabin section and a first flange plate connected with the first cabin section; the rear end counterweight pipe is fixed in the second cabin section through a second flange plate and a third flange plate which are connected with the second cabin section, and a second front end cap connected with the rear end counterweight pipe is connected with the second flange plate.
As an improved technical scheme, the missile mass center of mass adjusting device provided by the invention comprises a counterweight box body detachably connected with the inner cavity of a counterweight pipe; the box cover is connected with one end of the counterweight box body; a plurality of counterweight plates connected with the inner cavity of the counterweight box; the counterweight plates calculate the mass and gravity center offset requirements of the counterweight blocks at different positions according to a counterweight scheme, and different materials are selected to be made into corresponding shapes and sizes, so that the counterweight mass and the gravity center offset can be adjusted, and the actual mass center of the missile meets the mass center requirement of the missile design; the counterweight box body is detachably connected with the counterweight pipe through a pin, a key or a screw, and the position and the direction of the counterweight box body are fixed.
According to another aspect of the invention, the invention provides a missile mass center adjusting method, wherein the missile is provided with a missile mass center adjusting device, the missile mass center adjusting device comprises at least one balance weight pipe positioned in a missile cabin, a plurality of balance weights placed in the balance weight pipe, end caps detachably connected with two ends of the balance weight pipe respectively, and the balance weight pipe is connected with the missile cabin through a flange plate; when the missile mass center adjusting device is assembled, the end cap at one end is connected with the cabin body or one of the flange plates, one end of the counterweight pipe is connected with the end cap, the other end of the counterweight pipe is fixed through the other flange plate, the end cap at the other end of the counterweight pipe is assembled, and the cabin body without the counterweight is assembled; after the equipment in the equal cabin is installed and debugged, measuring an initial value of the mass center of mass of the missile, and making a counterweight scheme by comparing the initial value with the theoretical mass center of mass, wherein the counterweight scheme comprises the mass of each counterweight block at each position and the offset of the gravity center, so that the mass center of mass can be accurately adjusted; and after the end cap at the other end of the counterweight pipe is taken down, the counterweight block is installed according to the counterweight scheme, and the end cap of the counterweight pipe is covered again.
As an improved technical scheme, the missile mass center adjusting method provided by the invention is characterized in that the missile is provided with a missile mass center adjusting device, and the missile mass center adjusting device comprises a front end counterweight pipe and a rear end counterweight pipe which are positioned in a missile cabin; a plurality of balancing weights arranged in the front end balancing weight pipe or the rear end balancing weight pipe; the first front end cap and the first rear end cap are detachably connected with two ends of the front end counterweight pipe respectively; the second front end cap and the second rear end cap are detachably connected with two ends of the rear end counterweight pipe respectively; the front end counterweight pipe is fixed in the first cabin section through a first front end cap embedded in the first cabin section and a first flange plate connected with the first cabin section; the rear end counterweight pipe is fixed in the second cabin section through a second flange plate and a third flange plate which are connected with the second cabin section, and a second front end cap connected with the rear end counterweight pipe is connected with the second flange plate; when the missile mass center adjusting device is assembled, the first front end cap is connected with the first cabin section, one end of the front end counterweight pipe is connected with the first front end cap, the other end of the front end counterweight pipe is fixed through a first flange plate connected with the first cabin section, the first rear end cap at the other end of the front end counterweight pipe is assembled, and the counterweight-free first cabin section is assembled; connecting a second flange plate with the second cabin section, connecting a second front end cap with the second flange plate, connecting one end of the rear end counterweight pipe with the second front end cap, fixing the other end of the rear end counterweight pipe through a third flange plate connected with the second cabin section, installing the second rear end cap at the other end of the rear end counterweight pipe, and assembling the counterweight-free second cabin section; after the equipment in the first cabin section and the second cabin section is installed and debugged, measuring initial values of mass centers of the first cabin section and the second cabin section respectively, and making a counterweight scheme by comparing the initial values with theoretical mass centers, wherein the counterweight scheme comprises the mass of each counterweight block and the gravity center offset, so that the mass centers are accurately adjusted; after the first rear end cap of the front end counterweight pipe is taken down, the counterweight block of the front end counterweight pipe is installed, and then the first rear end cap of the front end counterweight pipe is covered again; after the second rear end cap of the rear end counterweight pipe is taken down, the counterweight block of the rear end counterweight pipe is installed, and then the second rear end cap of the rear end counterweight pipe is covered again; assembling the sections into a missile; measuring the mass center of the missile, judging whether the integral balance weight of the missile needs to be adjusted or not by comparing the mass center of the missile with the theoretical mass center of mass, and if the integral balance weight needs to be adjusted, formulating an adjustment balance weight scheme which comprises the mass and the gravity center offset of each adjusted balance weight block to realize the accurate adjustment of the mass center of mass; when dismantling the change balancing weight, take off the first rear end cap of front end counter weight pipe or the second rear end cap of rear end counter weight pipe, take out the balancing weight, after the balancing weight of renewal, cover first rear end cap and second rear end cap again.
As an improved technical scheme, the missile mass center of mass adjusting method provided by the invention is characterized in that the balancing weight comprises a balancing weight box body detachably connected with the inner cavity of the balancing weight pipe; the box cover is connected with one end of the counterweight box body; a plurality of counterweight plates connected with the inner cavity of the counterweight box; the counterweight plates calculate the mass and gravity center offset requirements of the counterweight blocks at different positions according to a counterweight scheme, and different materials are selected to be made into corresponding shapes and sizes, so that the counterweight mass and the gravity center offset can be adjusted, and the actual mass center of the missile meets the mass center requirement of the missile design; the counterweight box body is detachably connected with the counterweight pipe through a pin, a key or a screw, and the position and the direction of the counterweight box body are fixed.
The foregoing improvements can be practiced alone or in combination without conflict.
According to the technical scheme provided by the invention, the outer diameter, the length, the setting position and the configuration of the counterweight block of the counterweight pipe can be flexibly and conveniently adjusted according to the actual design requirement, and the actual overall parameter requirements can be met, such as: polar moment of inertia, equatorial moment of inertia, three coordinates of center of gravity, etc. The counterweight pipe and the missile cabin are connected and fastened through a flange plate, and the fixing mode is flexible and various. The surface of the cabin body does not need to be provided with a complex counterweight mechanism, so that the cabin body is more convenient to process and manufacture and has a better structure.
During the installation of the equipment in the cabin, the counterweight pipe can be installed firstly, then the electronic components and the connecting circuit are installed, then the counterweight is carried out, and the assembly difficulty is effectively reduced.
Because the counterweight pipe and the counterweight block are mechanically assembled, the counterweight block can be prepared outside the missile cabin, and the counterweight block can be disassembled and reassembled, so that the counterweight block can flexibly adapt to the change of design parameters.
Drawings
The accompanying drawings are included to provide a further understanding of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the invention without limiting the invention. In the drawings:
FIG. 1 is a schematic structural diagram of a missile mass center adjusting device according to an embodiment;
fig. 2 is a schematic structural principle diagram of a counterweight of the missile mass center-of-mass adjusting device according to the embodiment.
Detailed Description
The invention will be further explained with reference to the drawings.
The missile mass center of mass adjusting device shown in fig. 1 comprises a front end counterweight pipe 2 and a rear end counterweight pipe 3 which are positioned in a missile cabin 1, a plurality of counterweight blocks 4 which are arranged in the front end counterweight pipe 2 or the rear end counterweight pipe 3, a first front end cap 7 and a first rear end cap 5 which are respectively detachably connected with two ends of the front end counterweight pipe 2, a second front end cap 8 and a second rear end cap 9 which are respectively detachably connected with two ends of the rear end counterweight pipe 3, the front end counterweight pipe 2 is fixed in a first cabin section through the first front end cap 7 which is embedded into the first cabin section and a first flange plate 6 which is connected with the first cabin section, the rear end counterweight pipe 3 is fixed in a second cabin section through a second flange plate 10 and a third flange plate 11 which are connected with the second cabin section, and the second front end cap 8 which is connected with the rear end counterweight pipe 3 is connected with the second flange plate 10.
When the missile mass center adjusting device is assembled, the first front end cap 7 is connected with the first cabin section, one end of the front end counterweight pipe 2 is connected with the first front end cap 7, the other end of the front end counterweight pipe 2 is fixed through the first flange plate 6 connected with the first cabin section, the first rear end cap 5 at the other end of the front end counterweight pipe 2 is assembled, and the counterweight-free first cabin section is assembled; connecting a second flange plate 10 with the second cabin section, connecting a second front end cap 8 with the second flange plate 10, connecting one end of the rear end counterweight pipe 3 with the second front end cap 8, fixing the other end of the rear end counterweight pipe 3 through a third flange plate 11 connected with the second cabin section, installing a second rear end cap 9 at the other end of the rear end counterweight pipe 3, and assembling the second cabin section without counterweight; after the equipment in the first cabin section and the second cabin section is installed and debugged, measuring initial values of mass centers of the first cabin section and the second cabin section respectively, and making a counterweight scheme by comparing the initial values with theoretical mass centers, wherein the counterweight scheme comprises the mass of each counterweight block and the gravity center offset, so that the mass centers are accurately adjusted; after the first rear end cap 5 of the front end counterweight pipe 2 is taken down, the counterweight block of the front end counterweight pipe 2 is installed, and then the first rear end cap 5 of the front end counterweight pipe 2 is covered again; after the second rear end cap 9 of the rear end counterweight pipe 3 is taken down, the counterweight block of the rear end counterweight pipe 3 is installed, and then the second rear end cap 9 of the rear end counterweight pipe 3 is covered again; assembling the sections into a missile; measuring the mass center of the missile, judging whether the integral balance weight of the missile needs to be adjusted or not by comparing the mass center of the missile with the theoretical mass center of mass, and if the integral balance weight needs to be adjusted, formulating an adjustment balance weight scheme which comprises the mass and the gravity center offset of each adjusted balance weight block to realize the accurate adjustment of the mass center of mass; when dismantling the change balancing weight, take off the first rear end cap 5 of front end counter weight pipe 2 or the second rear end cap 9 of rear end counter weight pipe 3, take out the balancing weight, after the balancing weight of renewal, cover first rear end cap 5 and second rear end cap 9 again.
In other schemes, the missile mass center of mass adjusting device can be provided with one or more balance weight pipes positioned in the missile cabin 1, a plurality of balance weight blocks 4 arranged in the balance weight pipes, end caps detachably connected with two ends of each balance weight pipe respectively, and the balance weight pipes are connected with the missile cabin 1 through flange plates.
When the missile mass center adjusting device is assembled, the end cap at one end is connected with the cabin body or one of the flange plates, one end of the counterweight pipe is connected with the end cap, the other end of the counterweight pipe is fixed through the other flange plate, the end cap at the other end of the counterweight pipe is assembled, and the cabin body without the counterweight is assembled; after the equipment in the equal cabin is installed and debugged, measuring an initial value of the mass center of mass of the missile, and making a counterweight scheme by comparing the initial value with the theoretical mass center of mass, wherein the counterweight scheme comprises the mass of each counterweight block at each position and the offset of the gravity center, so that the mass center of mass can be accurately adjusted; and after the end cap at the other end of the counterweight pipe is taken down, the counterweight block is installed according to the counterweight scheme, and the end cap of the counterweight pipe is covered again.
Optionally, as shown in fig. 2, in the missile mass center adjusting device provided by the present invention, the counterweight block 4 includes a counterweight box body 12 detachably connected to the inner cavity of the counterweight pipes 2 and 3, a box cover 13 connected to one end of the counterweight box body 12, and a plurality of counterweight plates 14 connected to the inner cavity of the counterweight box body 12, the counterweight plates 14 calculate the mass and the center-of-gravity offset requirements of the counterweight block 4 at different positions according to a counterweight scheme, and are made of different materials into corresponding shapes and sizes, so as to achieve the adjustability of the counterweight mass and the center-of-gravity offset, thereby achieving the actual mass center of the missile meeting the designed mass center requirement of the missile; the weight box 14 is detachably connected to the weight tubes 2, 3 by pins, keys, or screws to fix the position and orientation of the weight box 12.
According to the technical scheme provided by the invention, the outer diameter, the length, the setting position and the configuration of the counterweight block of the counterweight pipe can be flexibly and conveniently adjusted according to the actual design requirement, and the actual overall parameter requirements can be met, such as: polar moment of inertia, equatorial moment of inertia, three coordinates of center of gravity, etc. The counterweight pipe is connected and fastened with the missile cabin 1 through a flange plate, and the fixing mode is flexible and various. The surface of the cabin body does not need to be provided with a complex counterweight mechanism, so that the cabin body is more convenient to process and manufacture and has a better structure.
During the installation of the equipment in the cabin, the counterweight pipe can be installed firstly, then the electronic components and the connecting circuit are installed, then the counterweight is carried out, and the assembly difficulty is effectively reduced.
Because the balance weight pipe and the balance weight block 4 are assembled mechanically, the balance weight block 4 can be prepared outside the missile cabin 1, and the balance weight block can be disassembled and reassembled, thereby flexibly adapting to the change of design parameters.
Various modifications and alterations to this invention will become apparent to those skilled in the art. Any modification, equivalent replacement, improvement and the like made within the spirit and principle of the claims of the present invention should be included in the protection scope of the present invention.
Claims (5)
1. A missile mass center of mass adjusting device comprises at least one counterweight pipe (2, 3) positioned in a missile cabin (1); a plurality of balancing weights (4) arranged in the balancing weight pipes (2, 3); end caps (5, 7, 8, 9) detachably connected to both ends of the weight tubes (2, 3), respectively; the counterweight pipes (2 and 3) are connected with the missile cabin (1) through flanges (6, 10 and 11), and the counterweight is characterized in that the counterweight block (4) comprises a counterweight box body (12) detachably connected with the inner cavities of the counterweight pipes (2 and 3); a box cover (13) connected with one end of the counterweight box body (12); a plurality of counterweight plates (14) connected with the inner cavity of the counterweight box body (12); the counterweight plates (14) calculate the mass and gravity center offset requirements of the counterweight blocks (4) at different positions according to a counterweight scheme, and different materials are selected to be made into corresponding shapes and sizes, so that the counterweight mass and the gravity center offset can be adjusted, and the actual mass center of the missile meets the mass center requirement of the missile design; the counterweight box body (12) is detachably connected with the counterweight pipes (2 and 3) through pins, keys or screws, and the position and the direction of the counterweight box body (12) are fixed.
2. The missile mass center of mass adjustment device of claim 1, comprising a front counterweight tube (2) and a rear counterweight tube (3) located in the missile bay (1); the front end counterweight pipe (2) is fixed in the first cabin section through a first front end cap (7) embedded in the first cabin section and a first flange plate (6) connected with the first cabin section; the rear end counterweight pipe (3) is fixed in the second cabin section through a second flange plate (10) and a third flange plate (11) which are connected with the second cabin section, and a second front end cap (8) connected with the rear end counterweight pipe (3) is connected with the second flange plate (10).
3. The missile mass center adjusting method is characterized in that a missile is provided with a missile mass center adjusting device, the missile mass center adjusting device comprises at least one balance weight pipe (2, 3) positioned in a missile cabin (1), a plurality of balance weight blocks (4) placed in the balance weight pipe (2, 3), end caps (5, 7, 8 and 9) detachably connected with two ends of the balance weight pipe (2, 3) respectively, and the balance weight pipe (2, 3) is connected with the missile cabin through flange plates (6, 10 and 11); when the missile mass center adjusting device is assembled, the end cap at one end is connected with the cabin body or one flange plate (10) of the cabin body, one end of the counterweight pipe is connected with the end cap, the other end of the counterweight pipe is fixed through the other flange plate (6, 11), the end cap at the other end of the counterweight pipe is assembled, and the cabin body without the counterweight is assembled; after the equipment in the equal cabin is installed and debugged, measuring an initial value of the mass center of mass of the missile, and making a counterweight scheme by comparing the initial value with the theoretical mass center of mass, wherein the counterweight scheme comprises the mass of each counterweight block at each position and the offset of the gravity center, so that the mass center of mass can be accurately adjusted; and after the end cap at the other end of the counterweight pipe is taken down, the counterweight block is installed according to the counterweight scheme, and the end cap of the counterweight pipe is covered again.
4. The missile mass center adjusting method is characterized in that the missile is provided with a missile mass center adjusting device, and the missile mass center adjusting device comprises a front end counterweight pipe (2) and a rear end counterweight pipe (3) which are positioned in a missile cabin (1); a plurality of balancing weights (4) arranged in the front end balancing pipe (2) or the rear end balancing pipe (3); the first front end cap (7) and the first rear end cap (5) are detachably connected with two ends of the front end counterweight pipe (2) respectively; a second front end cap (8) and a second rear end cap (9) which are detachably connected with two ends of the rear end counterweight pipe (3) respectively; the front end counterweight pipe (2) is fixed in the first cabin section through a first front end cap (7) embedded in the first cabin section and a first flange plate (6) connected with the first cabin section; the rear end counterweight pipe (3) is fixed in the second cabin section through a second flange plate (10) and a third flange plate (11) which are connected with the second cabin section, and a second front end cap (8) connected with the rear end counterweight pipe (3) is connected with the second flange plate (10); when the missile mass center adjusting device is assembled, a first front end cap (7) is connected with a first cabin section, one end of a front end counterweight pipe (2) is connected with the first front end cap (7), the other end of the front end counterweight pipe (2) is fixed through a first flange plate (6) connected with the first cabin section, a first rear end cap (5) at the other end of the front end counterweight pipe (2) is assembled, and the first cabin section without counterweight is assembled; connecting a second flange plate (10) with the second cabin section, connecting a second front end cap (8) with the second flange plate (10), then connecting one end of the rear end counterweight pipe (3) with the second front end cap (8), then fixing the other end of the rear end counterweight pipe (3) through a third flange plate (11) connected with the second cabin section, installing a second rear end cap (9) at the other end of the rear end counterweight pipe (3), and assembling the counterweight-free second cabin section; after the equipment in the first cabin section and the second cabin section is installed and debugged, measuring initial values of mass centers of the first cabin section and the second cabin section respectively, and making a counterweight scheme by comparing the initial values with theoretical mass centers, wherein the counterweight scheme comprises the mass of each counterweight block and the gravity center offset, so that the mass centers are accurately adjusted; after the first rear end cap (5) of the front end counterweight pipe (2) is taken down, the counterweight block of the front end counterweight pipe (2) is installed, and then the first rear end cap (5) of the front end counterweight pipe (2) is covered again; after the second rear end cap (9) of the rear end counterweight pipe (3) is taken down, the counterweight block of the rear end counterweight pipe (3) is installed, and then the second rear end cap (9) of the rear end counterweight pipe (3) is covered again; assembling the sections into a missile; measuring the mass center of the missile, judging whether the integral balance weight of the missile needs to be adjusted or not by comparing the mass center of the missile with the theoretical mass center of mass, and if the integral balance weight needs to be adjusted, formulating an adjustment balance weight scheme which comprises the mass and the gravity center offset of each adjusted balance weight block to realize the accurate adjustment of the mass center of mass; when dismantling the change balancing weight, take off first rear end cap (5) of front end counter weight pipe (2) or second rear end cap (9) of rear end counter weight pipe (3), take out the balancing weight, after the balancing weight of renewal, cover first rear end cap (5) and second rear end cap (9) again.
5. The missile mass center of mass adjustment method according to claim 3 or 4, wherein the counterweight block (4) comprises a counterweight box body (12) detachably connected with the inner cavity of the counterweight pipe (2, 3); a box cover (13) connected with one end of the counterweight box body (12); a plurality of counterweight plates (14) connected with the inner cavity of the counterweight box body (12); the counterweight plate (14) is made of different materials according to the position, mass and gravity center offset requirements of the counterweight block (4) calculated according to the counterweight scheme, and the corresponding shape and size are realized, so that the counterweight mass, the position and the gravity center offset can be adjusted, and the actual mass center of the missile meets the mass center requirement of the missile design; the counterweight box body (12) is detachably connected with the counterweight pipes (2 and 3) through pins, keys or screws, and the position and the direction of the counterweight box body (12) are fixed.
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| CN201810425416.6A CN108759588B (en) | 2018-05-07 | 2018-05-07 | Missile mass and mass center adjusting device and method |
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| CN201810425416.6A CN108759588B (en) | 2018-05-07 | 2018-05-07 | Missile mass and mass center adjusting device and method |
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| CN108759588B true CN108759588B (en) | 2020-04-03 |
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| CN112007305B (en) * | 2020-08-13 | 2021-07-27 | 西安近代化学研究所 | Ten-ton-level liquid phase material filling shell capable of automatically overturning through mass center position adjustment |
| CN114322682A (en) * | 2021-11-30 | 2022-04-12 | 湖南航天机电设备与特种材料研究所 | Test system and method based on patrol missile launching impact overload |
| CN116379843B (en) * | 2023-06-02 | 2023-08-01 | 北京航天众信科技有限公司 | Mass center adjusting device of target projectile |
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| GB2382782A (en) * | 2001-12-07 | 2003-06-11 | Yang Jian Kuo | Changing centre of gravity of object, eg sports racket, bat or club |
| CN2635149Y (en) * | 2003-07-03 | 2004-08-25 | 张荣士 | Improved wood based baseball bat |
| CN103175653A (en) * | 2011-12-23 | 2013-06-26 | 中国船舶重工集团公司七五○试验场 | Weight simulator of cylinder with slenderness ratio |
| CN202511716U (en) * | 2012-03-07 | 2012-10-31 | 中国人民解放军总参谋部工程兵科研三所 | Large-caliber supersonic target bullet for tests or training |
| CN205412174U (en) * | 2016-03-17 | 2016-08-03 | 宁若峰 | Novel billiard cue |
| CN206634190U (en) * | 2017-03-31 | 2017-11-14 | 大鹏高科（武汉）智能装备有限公司 | A kind of underwater robot with gravity adjusting device |
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