CN101354226A - Cannonball with rocket capable of rotating after transmitting - Google Patents
Cannonball with rocket capable of rotating after transmitting Download PDFInfo
- Publication number
- CN101354226A CN101354226A CNA2007101307695A CN200710130769A CN101354226A CN 101354226 A CN101354226 A CN 101354226A CN A2007101307695 A CNA2007101307695 A CN A2007101307695A CN 200710130769 A CN200710130769 A CN 200710130769A CN 101354226 A CN101354226 A CN 101354226A
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- China
- Prior art keywords
- shell
- emission
- rocket
- empennage
- ballistic trajectory
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention discloses an artillery shell which is provided with a rocket and can rotate after being launched. The artillery shell consists of a shell which can rotate after being launched and a tail part which does not rotate after being launched and is provided with a rocket or a tailing spout which can deflect; the rocket or the tailing spout can function to fire the rocket in the process after the shell is launched for a certain distance or a certain time, or to deflect the tailing spout so as to push the shell off the original ballistic trajectory; and the deflected ballistic trajectory is in the detection scope of counter battery radar of the enemy while the former ballistic trajectory is not in the detection scope, therefore the enemy can not calculate the actual position of the artillery shell according to the deflected ballistic trajectory, thus being beneficial to preserving the military strength.
Description
Technical field
The present invention relates to the shell that rotates after a kind of emission with rocket.
Background technology
The shell of existing various emissions back rotation, as long as an emission enemy fire-finder counter-battery radar can be accomplished first location basically, promptly utilize the flight path of shell can calculate the position of cannon, thereby the safety of prestige rib cannon, common way is once being to have played race, the 2nd, develop stealthy shell, run out of the strike of enemy's artillery fire surely but run to differ, stealthy shell then differs real surely stealthy.
Summary of the invention
The purpose of this invention is to provide a kind of shell that rotates after the emission of the band rocket of putting in the emplacement that do not fire that calculates from its flight path.
But the present invention is achieved in that the shell that rotates after the emission of this band rocket and comprises the shell that various emissions back rotates and stablize non-rotary empennage part after the emission that has rocket or deflection nozzle, it is characterized in that but rocket or deflection nozzle are to launch in a segment distance or the flight course after the time at shell to work, make shell depart from former ballistic trajectory, and depart from the investigative range of later ballistic trajectory at enemy's fire-finder counter-battery radar, ballistic trajectory before is not then in the investigative range of opposing fire-finder counter-battery radar.
After adopting said structure, because but shell has rocket or deflection nozzle, and but rocket or deflection nozzle are launched in a segment distance or the flight course after the time at shell and are worked, make shell depart from former ballistic trajectory, so enemy's fire-finder counter-battery radar is according to departing from the later cannon position that ballistic trajectory calculated just not in the physical location of cannon, can exempt from enemy firepower and hit, help preserving strength.
Description of drawings
Fig. 1 is the shell structural representation that rotates after a kind of emission with rocket of the present invention;
Fig. 2 is the shell structural representation that rotates after the emission of another kind of band rocket of the present invention;
Fig. 3 is the shell structural representation that rotates after the emission of a kind of band rocket that has radar emission recorder, a computer of the present invention;
Fig. 4 is the shell structural representation that rotates after the emission of the another kind of the present invention band rocket that has radar emission recorder, computer.
Among the figure: 1 shell, 2 rotatable jockeys, 3 empennage sections, 4 empennages, 5 rockets, 6 nozzles, 7 radar emission recorders, 8 computers.
The specific embodiment
Below in conjunction with drawings and Examples the present invention is further described.
With reference to accompanying drawing, the shell that rotates after a kind of emission of the present invention with rocket, comprising that shell 1, rotatable jockey 2, empennage section 3, empennage 4, the rocket 5 that is positioned at empennage section 3 or nozzle 6, radar are auxilliary penetrates recorder 7, computer 8, and radar emission recorder 7, computer 8 can not comprise yet.The empennage part of being made up of empennage section 3, empennage 4 and rocket 5 or nozzle 6, radar emission recorder 7, computer 8 is stable after emission does not rotate, be connected with shell 1 by rotatable jockey 2, radar emission recorder 7 is formed automatic control system with computer 8.
In the present embodiment, shell 1 is the shell of various emissions back rotation, also can be rocket projectile, rocket assisted cartridge, and empennage 4 can be various empennages, and its population size can suitably be selected; Rocket 5 can be various solids or liquid rocket, its nozzle can be fixed, but also deflection, its quantity, nozzle direction, the big I of thrust are suitably selected, and the igniter fuse that has in it can be set before emission or control igniter fuses by radar emission recorder 7, computer 8 awing, when but its nozzle was the deflection nozzle, its deflection period can be set before emission, or awing by radar emission recorder 7, computer 8 control deflections; Have bearing in the rotatable jockey 2, when Fig. 1 was rocket projectile or rocket assisted cartridge, its nozzle did not omit among Fig. 1 and draws in the empennage part yet.
In the present embodiment, when shell 1 was rocket projectile or rocket assisted cartridge, rocket can be its original rocket, as shown in Figure 2, change direction but but nozzle 6 is deflection, the direction of its change and time can be set before emission, or are awing controlled automatically by radar emission recorder 7, computer 8.
The shell that rotates after a kind of emission with rocket of the present invention need be adjusted rocket 5 or nozzle 6 before emission position, also can on gun tube, do suitable design, but head for target emission, when making shell 1, rocket 5 or nozzle 6 depart from vertical direction, the emission that also can depart from objectives is when rocket 5 or nozzle 6 depart from shell 1 in the horizontal direction.
Claims (4)
1. the shell that rotates after the emission with rocket, the shell (1) and the rocket (5) that comprise the rotation of emission back, it is characterized in that, also comprise by empennage section (3), empennage (4), stablize non-rotary empennage part after the emission that rocket (5) is formed, and empennage part is connected with shell (1) by rotatable jockey (2), and rocket (5) can be set in before emission in the flight course after shell (1) emission one segment distance or time and works, it can make shell (1) depart from original ballistic trajectory, and depart from the investigative range of later ballistic trajectory, and ballistic trajectory before is not in the investigative range of opposing fire-finder counter-battery radar at enemy's fire-finder counter-battery radar.
2. the shell that rotates after the emission with rocket, the shell (1) that comprises the rotation of emission back, shell (1) is rocket projectile or rocket assisted cartridge, it is characterized in that, also comprise by empennage section (3) empennage (4), stablize non-rotary empennage part after the emission that nozzle (6) is formed, and empennage part is connected with shell (1) by rotatable jockey (2), nozzle (6) can be set deflection and change direction before emission, deflection changes direction in shell (1) emission one segment distance or the flight course after the time, it can make shell (1) depart from original ballistic trajectory, and depart from the investigative range of later ballistic trajectory at enemy's fire-finder counter-battery radar, ballistic trajectory before is not then in the investigative range of opposing fire-finder counter-battery radar.
3. the shell that rotates after the emission with rocket, the shell (1) and the rocket (5) that comprise the rotation of emission back, it is characterized in that, also comprise by empennage section (3), empennage (4), rocket (5), radar emission recorder (7), stablize non-rotary empennage part after the emission that computer (8) is formed, and they are connected by rotatable jockey (2), and rocket (5) is controlled it by radar emission recorder (7) and computer (8) and is worked in shell (1) emission one segment distance or the process after the time, make shell (1) depart from original trajectory track, and the ballistic trajectory that departs from is in the investigative range of enemy's fire-finder counter-battery radar, and ballistic trajectory before is not in its scope.
4. the shell that rotates after the emission with rocket, the shell (1) that comprises the rotation of emission back, shell (1) is rocket projectile or rocket assisted cartridge, it is characterized in that, also comprise by empennage section (3), empennage (4), nozzle (6), stablize non-rotary empennage part after the emission that radar emission recorder (7) and computer (8) are formed, and by rotatable jockey (2), shell (1) partly is connected with empennage, and nozzle (6) is launched in a segment distance or the process after the time by radar emission recorder (7) at shell (1), computer (8) can be controlled and depart from, make shell (1) depart from original ballistic trajectory, and depart from the investigative range of later ballistic trajectory at enemy's fire-finder counter-battery radar, ballistic trajectory does not before then exist.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2007101307695A CN101354226A (en) | 2007-07-24 | 2007-07-24 | Cannonball with rocket capable of rotating after transmitting |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2007101307695A CN101354226A (en) | 2007-07-24 | 2007-07-24 | Cannonball with rocket capable of rotating after transmitting |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101354226A true CN101354226A (en) | 2009-01-28 |
Family
ID=40307154
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNA2007101307695A Pending CN101354226A (en) | 2007-07-24 | 2007-07-24 | Cannonball with rocket capable of rotating after transmitting |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN101354226A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111141183A (en) * | 2020-01-10 | 2020-05-12 | 蓝箭航天空间科技股份有限公司 | Power tail cabin and rocket |
-
2007
- 2007-07-24 CN CNA2007101307695A patent/CN101354226A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111141183A (en) * | 2020-01-10 | 2020-05-12 | 蓝箭航天空间科技股份有限公司 | Power tail cabin and rocket |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Open date: 20090128 |