CN102155882A - 120mm mortar GPS+ inertial navigation composite guided projectile - Google Patents
120mm mortar GPS+ inertial navigation composite guided projectile Download PDFInfo
- Publication number
- CN102155882A CN102155882A CN2010105944800A CN201010594480A CN102155882A CN 102155882 A CN102155882 A CN 102155882A CN 2010105944800 A CN2010105944800 A CN 2010105944800A CN 201010594480 A CN201010594480 A CN 201010594480A CN 102155882 A CN102155882 A CN 102155882A
- Authority
- CN
- China
- Prior art keywords
- projectile
- gps
- guidance
- mortar
- target
- 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.)
- Pending
Links
Images
Abstract
The invention discloses a 120mm mortar global positioning system (GPS+) inertial navigation composite guided projectile, which can be launched from a hidden or open-air fire position under the condition that the coordinate of a target is given to perform precise attack on a small-sized ground target within the range of 1 to 7 km away from a gun emplacement. A typical target comprises point and area targets such as a common fixed fortification, a force staging area, a technical position weapon, personnel, vehicle and the like. In the 120mm mortar GPS+ inertial navigation composite guided projectile, a 120mm rattling flare is used as a design prototype; on the premise of keeping the appearance of the original projectile as much as possible, the fuze part of the original head part is eliminated, and the molded line of the original cabin section part for placing a parachute is adaptively modified and is reformed into a control cabin which meets the requirement of controlling the installation of equipment; according to lethality requirements, the structural proportion of a warhead cabin to the control cabin is reasonably adjusted, and the powder charging weight of a warhead is ensured; and the original tail wing structure is completely remained, so that the stability of the projectile during flying is ensured. The guided projectile is still launched by the original 120mm caliber mortar to attach a fixed ground target; after the projectile is launched, the initial attitude information is acquired through aerial autonomous alignment; and after a projectile body is started to be controlled, the projectile is subjected to combined guidance by inertia/GPS, and the modified ballistic trajectory of the projectile is controlled in real time for precise hit, so that an enemy target can be precisely attacked in a surgical operation mode.
Description
Affiliated technical field
Conventional ammunition guidanceization, long-range, precision are a great trend of present ground force weapons development, and hit the basis that precision formula ground force is based oneself upon in following IT-based warfare.120 millimeters mortar GPS+ inertial navigation combined guidance shells can be under the situation of known target coordinate, from hidden or open-air shooting position emission, the small-scale terrestrial target of the emplacement 1-7km scope of adjusting the distance is implemented precision strike, typical target comprises: general fixing fortification, army assembles ground, points such as technical area weapons, personnel, vehicle, appearance mark.
Background technology
120 millimeters mortar GPS+ inertial navigation combined guidance shells are to be prototype with 120 millimeters bore flares, by it being carried out pneumatic remodeling and adding guidance control package and the dress high explosive, realize compeling the autonomous precision strike of bullet, and this kind is designed to leading domestic.Fill up the blank of domestic heavy caliber mortar precision guided munition, as equipped our troops, can improve my army's army operation usefulness greatly.
Summary of the invention
One, structure and effect
(1) structure
It is prototype that 120 millimeters mortar GPS+ inertial navigation combined guidance shells compel to hit flare with 120 millimeters, under the prerequisite that keeps former bullet profile as far as possible, removed the fuse part of protocephalic region, the cabin section molded lines partly of original placement parachute has been carried out the adaptability correction, be transformed into and satisfy the control cabinet that control appliance is installed; According to the demand of killing and wounding, rationally adjusted the structure proportion of warhead cabin and control cabinet, guarantee the warhead weight of charge.Keep former tail structure fully, guarantee to compel to play aloft stable (see figure 1).
Full bullet is divided into control cabinet, warhead and three portion's sections of empennage in the past backward
1, control cabinet: a whole set of guidance control system instrument and equipment and executing agency are installed in the control cabinet.
2, warhead: warhead inside is equipped with high explosive and fuze mechanism, and the explosive assembly casing material is steel, has guaranteed the fragmentation effect of bullet.
3, empennage: empennage is partly continued to use original empennage, does not make an amendment, and material is an aluminium.
(2) mechanism
Inertial guidance is to utilize principle of inertia control and guiding ammunition to fly to the technology of target.The principle of inertial guidance is to utilize inertial measuring unit to measure the kinematic parameter of guided missile, and formation is guidanceed command, and direction, size and action time by the control motor power, guided missile is directed to the target area automatically.Inertial guidance is not got in touch with the external world with from master mode work, so strong interference immunity and good concealment.
The operation principle of GPS (global positioning system) guidance is to utilize the GPS receiver of installing on the bullet to receive 4 signals that above aeronautical satellite is broadcast, and revises the flight path of ammunition, improves guidance precision.
Usefulness for 120 millimeters mortar launching guidance shells of maximum efficiency performance reduces launch preparation time, and under the normal condition, 120 millimeters mortar emissions need trumpeter 3 people.After getting into position, No. 1 the trumpeter is responsible for launching the landform arrangement in emplacement, expansion, the emission angle of site and azimuthal adjustment of mortar; No. 2 trumpeters be responsible for mortar projectile outlet, launch, power up, position wind field ordinary surveying and shell go into the tube emission, No. 3 trumpeters are responsible for the expansion of ground checkout equipment, power on; The measurement of coordinates of position of readiness, the measurement of coordinates of target.
Two, primary structure characteristics
Major technique
(1) adopts inertial guidance and GPS guidance combined guidance system
Inertial guidance is to utilize principle of inertia control and guiding ammunition to fly to the technology of target.The principle of inertial guidance is to utilize inertial measuring unit to measure the kinematic parameter of guided missile, and formation is guidanceed command, and direction, size and action time by the control motor power, guided missile is directed to the target area automatically.Inertial guidance is not got in touch with the external world with from master mode work, so strong interference immunity and good concealment.
The operation principle of GPS (global positioning system) guidance is to utilize the GPS receiver of installing on the bullet to receive 4 signals that above aeronautical satellite is broadcast, and revises the flight path of ammunition, improves guidance precision.
Utilize the combined guidance system, can be in the battlefield surroundings of complexity, utilize two kinds of guidance systems work characteristics separately, compensation mutually, further improve the attack precision of ammunition, and then realize improving the fighting efficiency (see figure 2) of ammunition to opposing the precision strike that ground target is implemented " operation " formula.
(2) total arrangement under the multiple constraint and pneumatic design technology.
(3) miniaturization missile-borne power technology.
(4) the multi-functional Navigation Control Unit designing technique of small integrated (containing parts such as missile-borne computer, GPS receiver, wireless telecommunications transceiver, the combination of MEMS inertia measurement).
(5) airborne equipment anti high overload technology.
(6) attitude stabilization and the zero-miss guidance designing technique under the big attitude misalignment.
120 millimeters mortar GPS+ inertial navigation combined guidance shell beneficial effects are:
120 millimeters mortar GPS+ inertial navigation combined guidance shells utilize the combined guidance system, can be in the battlefield surroundings of complexity, utilize two kinds of guidance systems work characteristics separately, compensation mutually, further improve the attack precision of ammunition, and then realize improving the fighting efficiency of ammunition to opposing the precision strike that ground target is implemented " operation " formula.
Description of drawings
Fig. 1 is 120 millimeters mortar GPS+ inertial navigation combined guidance shell structural representations
Full bullet is made up of empennage, explosive assembly casing, warhead ammunition, steering wheel, gps receiver, battery, electromagnetic wave transparent material shell.
Fig. 2 is 120 millimeters mortar GPS+ inertial navigation combined guidance shell working state schematic representations
After 120 millimeters mortar GPS+ inertial navigation combined guidance shell emissions, utilize inertial measuring unit to measure the kinematic parameter of guided missile, formation is guidanceed command, and direction, size and action time by the control motor power, guided missile is directed to the target area automatically.Utilize the GPS receiver of installing on the bullet to receive 4 signals that above aeronautical satellite is broadcast simultaneously, revise the flight path of ammunition, improve guidance precision.
The specific embodiment
As can be seen from Figure 1, earlier with dynamite charge in explosive assembly casing, navigate control combination and packed part carry out the assembling of widget again.Secondly the whole body of going up is partly carried out general assembly, at last empennage is combined with body.
As can be seen from Figure 2, utilize the combined guidance system, can be in the battlefield surroundings of complexity, utilize two kinds of guidance systems work characteristics separately, compensation mutually further improves the attack precision of ammunition, and then realizes enemy's ground target is implemented the precision strike of " operation " formula.
Claims (2)
1.120 millimeter mortar GPS+ inertial navigation combined guidance shell is the GPS receiver of installing on the bullet and utilizes principle of inertia control and guide the technology that ammunition flies to target.The principle of inertial guidance is to utilize inertial measuring unit to measure the kinematic parameter of guided missile, and formation is guidanceed command, and direction, size and action time by the control motor power, guided missile is directed to the target area automatically.Inertial guidance is not got in touch with the external world with from master mode work, so strong interference immunity and good concealment.
2.GPS the operation principle of (global positioning system) guidance is to utilize the GPS receiver of installing on the bullet to receive 4 signals that above aeronautical satellite is broadcast, and revises the flight path of ammunition, improves guidance precision.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010105944800A CN102155882A (en) | 2010-12-20 | 2010-12-20 | 120mm mortar GPS+ inertial navigation composite guided projectile |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010105944800A CN102155882A (en) | 2010-12-20 | 2010-12-20 | 120mm mortar GPS+ inertial navigation composite guided projectile |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102155882A true CN102155882A (en) | 2011-08-17 |
Family
ID=44437466
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010105944800A Pending CN102155882A (en) | 2010-12-20 | 2010-12-20 | 120mm mortar GPS+ inertial navigation composite guided projectile |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102155882A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105180728A (en) * | 2015-08-27 | 2015-12-23 | 北京航天控制仪器研究所 | Front data based rapid air alignment method of rotary guided projectiles |
| CN106708778A (en) * | 2016-12-13 | 2017-05-24 | 中国电子科技集团公司第二十研究所 | Command processing chip applied to command guidance system |
| CN107084645A (en) * | 2017-06-16 | 2017-08-22 | 北京理工大学 | Sniper rifle laser guidance bullet |
| CN110186481A (en) * | 2019-06-10 | 2019-08-30 | 西安航天三沃机电设备有限责任公司 | Calibration system and calibration method suitable for inertia component on small-sized seeker bullet |
| CN110220414A (en) * | 2019-04-28 | 2019-09-10 | 中国人民解放军63863部队 | A kind of terminal guidance shell firing table prepare in meet method |
| CN114442654A (en) * | 2020-11-03 | 2022-05-06 | 北京理工大学 | Satellite image composite guidance method |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5773751A (en) * | 1994-05-10 | 1998-06-30 | Bofors Liab Ab | Shell for gun with smooth-bore barrel |
| US20040107857A1 (en) * | 2002-06-27 | 2004-06-10 | Patria Vammas Oy | Arrangement for supporting mortar shell into barrel of weapon |
-
2010
- 2010-12-20 CN CN2010105944800A patent/CN102155882A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5773751A (en) * | 1994-05-10 | 1998-06-30 | Bofors Liab Ab | Shell for gun with smooth-bore barrel |
| US20040107857A1 (en) * | 2002-06-27 | 2004-06-10 | Patria Vammas Oy | Arrangement for supporting mortar shell into barrel of weapon |
Non-Patent Citations (1)
| Title |
|---|
| 屈元宁: "二十一世纪的外军迫击炮", 《国防科技》 * |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105180728A (en) * | 2015-08-27 | 2015-12-23 | 北京航天控制仪器研究所 | Front data based rapid air alignment method of rotary guided projectiles |
| CN106708778A (en) * | 2016-12-13 | 2017-05-24 | 中国电子科技集团公司第二十研究所 | Command processing chip applied to command guidance system |
| CN106708778B (en) * | 2016-12-13 | 2020-04-28 | 中国电子科技集团公司第二十研究所 | Instruction processing chip applied to instruction guidance system |
| CN107084645A (en) * | 2017-06-16 | 2017-08-22 | 北京理工大学 | Sniper rifle laser guidance bullet |
| CN107084645B (en) * | 2017-06-16 | 2018-12-07 | 北京理工大学 | Sniper rifle laser guidance bullet |
| CN110220414A (en) * | 2019-04-28 | 2019-09-10 | 中国人民解放军63863部队 | A kind of terminal guidance shell firing table prepare in meet method |
| CN110186481A (en) * | 2019-06-10 | 2019-08-30 | 西安航天三沃机电设备有限责任公司 | Calibration system and calibration method suitable for inertia component on small-sized seeker bullet |
| CN114442654A (en) * | 2020-11-03 | 2022-05-06 | 北京理工大学 | Satellite image composite guidance method |
| CN114442654B (en) * | 2020-11-03 | 2023-10-27 | 北京理工大学 | Satellite image composite guidance method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US8314374B2 (en) | Remotely-guided vertical take-off system and method for delivering an ordnance to a target | |
| US8664575B2 (en) | Miniature missile | |
| CN105043171B (en) | A kind of longitudinal guidance method of the rocket projectile of constraint with angle | |
| RU2362962C1 (en) | "tverityanka" splinter-in-beam supercaliber grenade | |
| CN102155882A (en) | 120mm mortar GPS+ inertial navigation composite guided projectile | |
| CN213300979U (en) | Guidance projectile body that 40mm rocket tube sought with general strapdown | |
| CN112224412B (en) | Onboard anti-armor adsorbable warhead | |
| KR20170104812A (en) | Drone collecting and furnishing image data for bomb damage assessment and air-to-ground weaponry system including the same | |
| CN202013151U (en) | GPS (global positioning system) and inertia combined guided cartridge of 120mm mortar | |
| CN114432625B (en) | Remote accurate guidance fire extinguishing bomb | |
| CN214620888U (en) | Rocket projectile for 40 mm rocket tube based on straight nozzle extended-range engine | |
| CN214620889U (en) | Omnidirectional reverse inclined plane guided missile based on thrust direction change | |
| RU2709121C1 (en) | Jet projectile control unit | |
| CN211012682U (en) | Laser beam-steering guided missile emitted by 40mm rocket tube | |
| CN114136157A (en) | Guidance projectile body that 40mm rocket tube sought with general strapdown | |
| CN112129179A (en) | Laser beam-steering guided missile emitted by 40mm rocket tube | |
| CN211012681U (en) | Universal extended-range controlled projectile body platform for 40mm rocket tube | |
| CN217686889U (en) | Separable guided rocket projectile for 40mm rocket tube | |
| CN109357578A (en) | School shooting method is aimed at based on the calibration shell of Beidou navigation technology and artilleryman | |
| CN210952527U (en) | Wireless instruction guidance rocket projectile and controlled infrared beacon for 40mm rocket launcher | |
| Yeo | Guided weapons: Stand off munitions-essential for RAAF combat operations | |
| CN112050690A (en) | Universal extended-range controlled projectile body platform for 40mm rocket tube | |
| RU2368864C1 (en) | Fragmenting-beam projectile "posvizd" | |
| EP2342530B1 (en) | Artillery projectile with separately controlled booster actuation and fragment dispersion | |
| RU2293284C1 (en) | Arrangement for destruction of air targets |
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 |
Application publication date: 20110817 |