CN103134394A - Rocket projectile control wing ejection control device - Google Patents
Rocket projectile control wing ejection control device Download PDFInfo
- Publication number
- CN103134394A CN103134394A CN2013100670070A CN201310067007A CN103134394A CN 103134394 A CN103134394 A CN 103134394A CN 2013100670070 A CN2013100670070 A CN 2013100670070A CN 201310067007 A CN201310067007 A CN 201310067007A CN 103134394 A CN103134394 A CN 103134394A
- Authority
- CN
- China
- Prior art keywords
- rocket projectile
- power transmission
- power output
- power
- aerofoil
- 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.)
- Granted
Links
Images
Landscapes
- Toys (AREA)
Abstract
A rocket projectile control wing ejection control device main comprises a rocket projectile ejection wall, power supply pipes, power output rods, power transmission rods, power output connecting rods, motors, airfoil power output transmission rods and airfoils. When a rocket projectile is ignited for launching, time delay is reserved, after a rocket flies out of a canister launcher, electronic ignition devices in the power supply pipes ignite to fire black powder, the black powder generates a large amount of gas to propel the power output rods to jack upwards, further the power transmission rods and the power output connecting rods are pushed to enable the airfoils to be pushed to be on the same line with the airfoil power output transmission rods, and at the moment, the power output rods are perpendicular to the airfoils, the power transmission rods are parallel to the airfoils, and the motors can control the airfoils through rotation. The airfoils are fixed at specific positions under the action of external fluid resistance and self-locking, so that short-time jamming of the motors caused by vibration of the airfoils is prevented. Ejection of powered rocket projectile control wings is controllable, the rocket projectile control wing ejection control device has self-locking capability, and control reliability is improved.
Description
Technical field
The invention belongs to a kind of rocket projectile and control wing ejection control device, belong to especially a kind of rear controlled rocket projectile control wing ejection control device that ejects.
Background technology
at present, most rocket projectile is controlled the wing and is ejected rear uncontrollable, or control the wing based on a kind of motorless rocket projectile, controllable device after ejecting, also or a kind of rocket projectile control device without ejecting, above-mentioned the first ejects the uncontrollable wing and mostly is applied in accuracy less demanding, to obtain cheapness, the rocket projectile that large tracts of land is killed and wounded, the second is mainly used in the precise guidance of unpowered section of rocket projectile, above-mentioned the third is mainly used in does not need often to transport or answer the large rocket bullet, above-mentioned ejection is controlled the wing and is cut both ways, can't realize simultaneously the advantage that they are all.
Summary of the invention
The object of the present invention is to provide a kind of rocket projectile to control the wing and eject control device, a kind of rear controlled rocket projectile control wing ejection control device that ejects particularly is provided.
The technical problem to be solved in the present invention is to provide a kind of dynamic rocket projectile and controls wing ejection control device, and it mainly comprises rocket projectile bullet wall, power supply pipe, power output rod, power transmission bar, power output connecting rod, motor, profile power transmission pole, aerofoil.Rocket projectile bullet wall has four aerofoils to skid off groove, and to coordinate the ejection of aerofoil, the inside of rocket projectile bullet wall is four motor installing ports of distribution evenly, power supply pipe installing port, profile power transmission pole installing port, there is guide groove the centre of rocket projectile bullet wall, so that the parts of rocket projectile power set to be installed; The power supply pipe is installed in the corresponding installing port of rocket projectile bullet wall, power supply pipe one end opening, so that power output rod can be in interior slip, power supply pipe bottom has electronic lighter, bottom that appropriate black powder is arranged; The external diameter of power output rod is identical with the internal diameter of power supply pipe, and an end has axle, to coordinate the hole on the power transmission bar; The power transmission bar is porose near an end of power output rod, and the other end has an axle, and axle matches with the hole on power output connecting rod; Power output connecting rod has near an end of power transmission bar the hole that coordinates with it, and the other end has the hole of matching with aerofoil, so that power output connecting rod can slide on aerofoil; Worm gear is arranged on motor, be installed in four installing ports of rocket projectile bullet wall, turbine matches with the worm screw on the profile power transmission pole; Profile power transmission pole one end has worm gear, the other end has an axle, match with the hole of aerofoil one end, the profile power transmission pole is installed in the installing port of the profile power transmission pole on rocket projectile bullet wall, so that the profile power transmission pole can not move forward and backward in interior rotation; Aerofoil one end has the hole of matching with the profile power transmission pole, and the other end is used for launching to control air-flow.
When rocket projectile is not launched, power output rod is inserted in the power supply pipe, power output rod thereby be pulled to low side, then hold the power transmission bar, power output connecting rod is held aerofoil, and an angle is arranged between profile power transmission pole and aerofoil, the uncontrollable electric machine rotation of motor prevents from because of the rotation of aerofoil, aerofoil being ejected.
When rocket projectile igniting emission, a time delay is arranged, after rocket flies out from launching tube, black powder is lighted in electronic lighter sparking in the power supply pipe, black powder produces a large amount of gases, propulsion power take-off lever make progress jack-up, propulsion power transmission pole then, power output connecting rod, aerofoil is pushed to the profile power transmission pole on a line, and power output rod is perpendicular to aerofoil at this moment, and the power transmission bar is parallel to aerofoil, at this moment, motor can be controlled aerofoil by rotation; Because effect and the mechanical self-latching of external fluid resistance makes aerofoil be fixed on ad-hoc location, prevent from causing motor stuck in short-term because of the vibrations of aerofoil.
In summary, the present invention has realized can controlling in the ejection of the dynamic rocket projectile control wing.
In addition, structure of the present invention also has the ability of mechanical self-latching, makes aerofoil be fixed on a specific position, has improved the reliability of controlling.
Description of drawings
Fig. 1 arrow bullet is controlled the front view that the wing ejects the power supply pipe of control device
This rocket projectile of Fig. 2 is controlled the stereogram that the wing ejects the power supply pipe of control device
This rocket projectile of Fig. 3 is controlled the front view that the wing ejects the power output rod of control device
This rocket projectile of Fig. 4 is controlled the elevation view that the wing ejects the power output rod of control device
This rocket projectile of Fig. 5 is controlled the front view that the wing ejects the power transmission bar of control device
This rocket projectile of Fig. 6 is controlled the elevation view that the wing ejects the power transmission bar of control device
This rocket projectile of Fig. 7 is controlled the front view that the wing ejects the power output connecting rod of control device
This rocket projectile of Fig. 8 is controlled the elevation view that the wing ejects the power output connecting rod of control device
This rocket projectile of Fig. 9 is controlled the stereogram figure that the wing ejects the control device motor
This rocket projectile of Figure 10 is controlled the front view that the wing ejects the profile power take-off lever of control device
This rocket projectile of Figure 11 is controlled the stereogram that the wing ejects the profile power take-off lever of control device
This rocket projectile of Figure 12 is controlled the stereogram that the wing ejects the aerofoil of control device
This rocket projectile of Figure 13 is controlled the wing and is ejected the profile power take-off lever of control device and the installation diagram of aerofoil
This rocket projectile of Figure 14 control the wing eject control device rocket projectile bullet wall just wait shaft side figure
This rocket projectile of Figure 15 is controlled the certain viewing angles stereogram that the wing ejects the rocket projectile bullet wall of control device
General assembly drawing when this rocket projectile of Figure 16 control wing ejection control device aerofoil is packed up
When this rocket projectile of Figure 17 control wing ejection control device aerofoil is packed up, the master looks cutaway view
General assembly drawing when this rocket projectile of Figure 18 control wing ejection control device aerofoil is opened
Master when this rocket projectile of Figure 19 control wing ejection control device aerofoil is opened looks cutaway view
The specific embodiment
Below by example and accompanying drawing thereof, the present invention is described in further details;
Referring to Fig. 1-Fig. 2, this rocket projectile is controlled the power supply pipe 1 that the wing ejects control device, power supply pipe 1 is installed in the corresponding installing port 20 of rocket projectile bullet wall 17, power supply pipe 1 one end openings, so that power output rod 3 can be in interior slip, electronic lighter 2 is arranged at power supply pipe 1 bottom, and appropriate black powder is arranged at the bottom.
Referring to Fig. 3-Fig. 4, this rocket projectile is controlled the power output rod 3 that the wing ejects control device, and the external diameter of power output rod 3 is identical with the internal diameter of power supply pipe 1, and an end has axle 4, to coordinate the hole 6 on power transmission bar 5.
Referring to Fig. 5-Fig. 6, this rocket projectile is controlled the power transmission bar 5 that the wing ejects control device, and power transmission bar 5 is porose 6 near an end of power output rods 3, and the other end has an axle 7, and axle 7 matches with the hole 8 that power is exported on connecting rod 9.
Referring to Fig. 7-Fig. 8, this rocket projectile is controlled the power output connecting rod 9 that the wing ejects control device, power output connecting rod 9 has near an end of power transmission bar 5 hole 8 that coordinates with it, and the other end has the hole 10 of matching with aerofoil 15, so that power output connecting rod 9 can slide on aerofoil 15.
Referring to Fig. 9, this rocket projectile is controlled the motor 12 that the wing ejects control device, and worm gear 11 is arranged on motor 12, is installed in four installing ports 21 of rocket projectile bullet wall 17, and turbine 11 matches with the worm screw on profile power transmission pole 13.
Referring to Figure 10-Figure 11, this rocket projectile is controlled the profile power transmission pole 13 that the wing ejects control device, profile power transmission pole 13 1 ends have worm gear, the other end has an axle 14, match with the hole 16 of aerofoil 15 1 ends, profile power transmission pole 13 is installed in the installing port 23 of the profile power transmission pole 13 on rocket projectile bullet wall 17, so that profile power transmission pole 13 can not move forward and backward in interior rotation.
Referring to Figure 12, this rocket projectile is controlled the aerofoil 15 that the wing ejects control device, and aerofoil 15 1 ends have the hole 16 of matching with profile power transmission pole 13, and the other end is used for launching to control air-flow.
Referring to Figure 14-Figure 15, this rocket projectile is controlled the rocket projectile bullet wall 17 that the wing ejects control device, rocket projectile bullet wall 17 has four aerofoils to skid off groove 18, to coordinate the ejection of aerofoil 15, the inside of rocket projectile bullet wall 17 is four motor installing ports 20 of distribution evenly, power supply pipe installing port 21, profile power transmission pole installing port 23, there is guide groove 19 centre of rocket projectile bullet wall, so that the parts of rocket projectile power set to be installed.
Referring to Figure 16-Figure 17, general assembly drawing when this rocket projectile control wing ejection control device aerofoil 15 is packed up, when rocket projectile was not launched, power output rod 3 was inserted in power supply pipe 1, power output rod 3 thereby be pulled to low side, then hold power transmission bar 5, power output connecting rod 9 is held aerofoil 15, between profile power transmission pole 13 and aerofoil 15, an angle is arranged, the uncontrollable aerofoil 15 of motor 12 rotates, and prevents from because of the rotation of aerofoil 15, aerofoil 15 being ejected.
referring to Figure 18-Figure 19, general assembly drawing when this rocket projectile control wing ejection control device aerofoil 15 is opened, when rocket projectile igniting emission, a time delay is arranged, after rocket flies out from launching tube, black powder is lighted in electronic lighter 2 sparkings in power supply pipe 1, black powder produces a large amount of gases, propulsion power take-off lever 3 is jack-up upwards, then the propulsion power transmission pole 5, power output connecting rod 9, aerofoil 15 is pushed to profile power transmission pole 13 on a line, power output this moment connecting rod 9 is perpendicular to profile power transmission pole 13, power transmission bar 5 is parallel to aerofoil 15, at this moment, motor 12 can be controlled aerofoil 15 by rotation, because effect and the mechanical self-latching of external fluid resistance makes aerofoil 15 be fixed on ad-hoc location, prevent from causing motor 12 stuck in short-term because of the vibrations of aerofoil 15.
The present invention has realized can controlling in the ejection of the dynamic rocket projectile control wing.
The above is only one embodiment of the present invention; should be understood that; for the those of ordinary skill in field, place of the present invention under the prerequisite that does not break away from the principle of the invention; can also make a lot of remodeling; such as, the riding position of plus-minus number of surface or change aerofoil, the kind of drive of adjustment motor and profile power take-off lever; change the length of each bar etc., these also should belong to protection scope of the present invention.
Claims (1)
1. rocket projectile is controlled the wing and is ejected control device, and it mainly comprises rocket projectile bullet wall, the power supply pipe, and power output rod, the power transmission bar, power output connecting rod, motor, the profile power transmission pole, aerofoil is characterized in that:
Rocket projectile bullet wall has four aerofoils to skid off groove, and to coordinate the ejection of aerofoil, the inside of rocket projectile bullet wall is four motor installing ports of distribution evenly, power supply pipe installing port, profile power transmission pole installing port, there is guide groove the centre of rocket projectile bullet wall, so that the parts of rocket projectile power set to be installed;
The power supply pipe is installed in the corresponding installing port of rocket projectile bullet wall, power supply pipe one end opening, so that power output rod can be in interior slip, power supply pipe bottom has electronic lighter, bottom that appropriate black powder is arranged; The external diameter of power output rod is identical with the internal diameter of power supply pipe, and an end has axle, to coordinate the hole on the power transmission bar;
The power transmission bar is porose near an end of power output rod, and the other end has an axle, and axle matches with the hole on power output connecting rod;
Power output connecting rod has near an end of power transmission bar the hole that coordinates with it, and the other end has the hole of matching with aerofoil, so that power output connecting rod can slide on aerofoil;
Worm gear is arranged on motor, be installed in four installing ports of rocket projectile bullet wall, turbine matches with the worm screw on the profile power transmission pole;
Profile power transmission pole one end has worm gear, the other end has an axle, match with the hole of aerofoil one end, the profile power transmission pole is installed in the installing port of the profile power transmission pole on rocket projectile bullet wall, so that the profile power transmission pole can not move forward and backward in interior rotation;
Aerofoil one end has the hole of matching with the profile power transmission pole, and the other end is used for launching to control air-flow.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310067007.0A CN103134394B (en) | 2013-03-04 | 2013-03-04 | Rocket projectile control wing ejection control device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310067007.0A CN103134394B (en) | 2013-03-04 | 2013-03-04 | Rocket projectile control wing ejection control device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103134394A true CN103134394A (en) | 2013-06-05 |
| CN103134394B CN103134394B (en) | 2014-10-29 |
Family
ID=48494551
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310067007.0A Expired - Fee Related CN103134394B (en) | 2013-03-04 | 2013-03-04 | Rocket projectile control wing ejection control device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103134394B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103644765A (en) * | 2013-12-12 | 2014-03-19 | 中国兵器工业第二0二研究所 | Synchronously opening device used for guided cartridge rudder sheet |
| CN104089546A (en) * | 2014-04-29 | 2014-10-08 | 北京理工大学 | Variable pneumatic layout structure for projectile body |
| CN105292410A (en) * | 2015-10-30 | 2016-02-03 | 北京精密机电控制设备研究所 | Pop-up decelerating wing system driven by initiating explosive device and provided with locking function |
| CN106813537A (en) * | 2016-12-13 | 2017-06-09 | 中国航天空气动力技术研究院 | A kind of four axle combines the helm gear of precision actuation |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100147992A1 (en) * | 2007-01-10 | 2010-06-17 | Hr Textron Inc. | Eccentric drive control actuation system |
| CN102226671A (en) * | 2011-05-26 | 2011-10-26 | 浙江理工大学 | Redundant locking folding wing longitudinal deployment mechanism |
| CN203083451U (en) * | 2013-03-04 | 2013-07-24 | 丁云广 | Rocket projectile control wing ejection control device |
-
2013
- 2013-03-04 CN CN201310067007.0A patent/CN103134394B/en not_active Expired - Fee Related
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100147992A1 (en) * | 2007-01-10 | 2010-06-17 | Hr Textron Inc. | Eccentric drive control actuation system |
| CN102226671A (en) * | 2011-05-26 | 2011-10-26 | 浙江理工大学 | Redundant locking folding wing longitudinal deployment mechanism |
| CN203083451U (en) * | 2013-03-04 | 2013-07-24 | 丁云广 | Rocket projectile control wing ejection control device |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103644765A (en) * | 2013-12-12 | 2014-03-19 | 中国兵器工业第二0二研究所 | Synchronously opening device used for guided cartridge rudder sheet |
| CN103644765B (en) * | 2013-12-12 | 2015-07-08 | 中国兵器工业第二0二研究所 | Synchronously opening device used for guided cartridge rudder sheet |
| CN104089546A (en) * | 2014-04-29 | 2014-10-08 | 北京理工大学 | Variable pneumatic layout structure for projectile body |
| CN104089546B (en) * | 2014-04-29 | 2015-09-30 | 北京理工大学 | The variable aerodynamic arrangement structure of body |
| CN105292410A (en) * | 2015-10-30 | 2016-02-03 | 北京精密机电控制设备研究所 | Pop-up decelerating wing system driven by initiating explosive device and provided with locking function |
| CN106813537A (en) * | 2016-12-13 | 2017-06-09 | 中国航天空气动力技术研究院 | A kind of four axle combines the helm gear of precision actuation |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103134394B (en) | 2014-10-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103134394B (en) | Rocket projectile control wing ejection control device | |
| EP3374723B1 (en) | Aerospike rocket motor assembly | |
| US9410503B2 (en) | Packaged propellant air-induced variable thrust rocket engine | |
| CN103803095A (en) | Pneumatic launcher for mini-type unmanned plane | |
| CN107063615A (en) | A kind of single gravel erosion combustion gas big gun experimental rig | |
| CN108177791A (en) | Launching tube | |
| CN203083451U (en) | Rocket projectile control wing ejection control device | |
| EP2947304B1 (en) | Gas turbine engine with selective flow path | |
| CN204346246U (en) | The Simple transmitting device of bulletfragment | |
| US8729443B2 (en) | Projectile and method that include speed adjusting guidance and propulsion systems | |
| CN110259602B (en) | A rechargeable multi-pulse solid rocket motor | |
| US7642491B2 (en) | Aircraft spiraling mechanism with jet assistance—D | |
| CN205561674U (en) | Rocket dummy round of laying mines | |
| CN103192988A (en) | Airship | |
| CN202315037U (en) | Portable ejection device | |
| CN106643294A (en) | Dual-mode launcher for airborne missile | |
| CN204404903U (en) | A kind of liquid carbon dioxide vaporization shooting throwing arm | |
| CN104567542B (en) | A kind of liquid carbon dioxide vaporization shooting throwing arm | |
| CN202442648U (en) | Air defense projectile launcher | |
| AU2012277568A1 (en) | A bomb for deployment from an air vehicle | |
| CN107270781A (en) | It is a kind of can be with the emitter of secondary acceleration | |
| CN112594089A (en) | Shuttle dart type vertical launching returnable hypersonic missile aircraft | |
| CN107144178B (en) | A kind of turn emitter | |
| CN101629517A (en) | Jet propulsion method and jet engine | |
| JP6505566B2 (en) | Rocket fireworks launcher |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20141029 Termination date: 20150304 |
|
| EXPY | Termination of patent right or utility model |