CN202013151U - GPS (global positioning system) and inertia combined guided cartridge of 120mm mortar - Google Patents
GPS (global positioning system) and inertia combined guided cartridge of 120mm mortar Download PDFInfo
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- CN202013151U CN202013151U CN201120139678XU CN201120139678U CN202013151U CN 202013151 U CN202013151 U CN 202013151U CN 201120139678X U CN201120139678X U CN 201120139678XU CN 201120139678 U CN201120139678 U CN 201120139678U CN 202013151 U CN202013151 U CN 202013151U
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- gps
- cartridge
- inertial
- mortar
- guidance
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Abstract
The utility model discloses a GPS (global positioning system) and inertia combined guided cartridge of a 120mm mortar. The guided cartridge comprises a warhead, a control cabin and an empennage, wherein the warhead is internally equipped with high explosives and a detonator device; the control cabin is internally equipped with a GPS guided device and an inertial guided device; the inertial guided device utilizes an inertial measurement unit to measure motion parameters of a missile and automatically guides the cartridge to a target area; and a GPS receiver receives signals broadcast by a navigation satellite to correct the flight path of the cartridge. After being launched, the cartridge obtains the initial attitude information through independent alignment in the air. After the starting control for a cartridge body, by utilizing the combined guidance of the inertia/the GPS, the cartridge is controlled in real time, and a trajectory is corrected to accurately hit the target, therefore, the precision ''surgical operation'' strike to the enemy target can be implemented.
Description
Technical field
The utility model relates to a kind of flying pig, relates in particular to a kind of GPS and inertial navigation combined guidance shell of 120mm mortar.
Background technology
Conventional ammunition guidanceization, long-range, precision are a great trend of present ground force weapons development at present, and hit the basis that precision formula ground force is based oneself upon in following IT-based warfare.
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.
Present flying pig all adopts the technical scheme of inertial guidance, so need to improve the attack precision of shell at present, 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 enemy's ground target is implemented the precision strike of " operation " formula, improve the fighting efficiency of ammunition.
The combined guidance shell 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.
Summary of the invention
In view of this, the utility model provides a kind of GPS and inertial navigation combined guidance shell of 120mm mortar, adopts GPS and inertial navigation combined guidance, and purpose is to utilize two kinds of guidance systems work characteristics separately, compensates mutually, further improves the attack precision of ammunition.
A kind of GPS of 120mm mortar and inertial navigation combined guidance shell, comprise warhead, control cabinet, empennage, high explosive and fuze mechanism are housed in the wherein said warhead, it is characterized in that: GPS guidance device and inertial unit are housed in the control cabinet, described inertial unit is measured the kinematic parameter of guided missile, and generation is guidanceed command, and shell is directed to the target area automatically, described GPS receiver receives the signal that aeronautical satellite is broadcast, and revises the flight path of shell.
Described explosive assembly casing material is steel, and the shell caliber is 120mm.
The flying pig of GPS and inertial navigation combined guidance adopts cutting edge technology, mainly solve the attack precision that improves ammunition, improve the problem of the fighting efficiency of ammunition, can adapt to various applied environments place, have the property of great convenience and flexibility in actual applications, be with a wide range of applications.
Description of drawings
In order to be illustrated more clearly in the utility model embodiment or technical scheme of the prior art, to do one to the accompanying drawing of required use in embodiment or the description of the Prior Art below introduces simply, apparently, accompanying drawing in describing below only is embodiment more of the present utility model, for those of ordinary skills, under the prerequisite of not paying creative work, can also obtain other accompanying drawing according to these accompanying drawings.
Fig. 1 is a mortar GPS+ inertial navigation combined guidance shell structural representation
The specific embodiment
For the purpose, technical scheme and the advantage that make the utility model embodiment clearer, below in conjunction with the accompanying drawing among the utility model embodiment, technical scheme among the utility model embodiment is clearly and completely described, obviously, described embodiment only is the utility model part embodiment, rather than whole embodiment.Based on the embodiment in the utility model, the ability those of ordinary skill is not being made the every other embodiment that is obtained under the creative work prerequisite, all belongs to the scope of the utility model protection.
GPS and inertial navigation combined guidance flying pig under the prerequisite that keeps former bullet profile as far as possible, have removed the fuse part of protocephalic region, and original cabin section has partly been carried out the adaptability correction, are transformed into to 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 stability.
As shown in Figure 1, full bullet comprise 1, the electromagnetic wave transparent material shell; 2, battery; 3, package module; 4, rudder control combination; 5, steering wheel; 6, warhead powder charge; 7, explosive assembly casing; 8, empennage; Full bullet is divided into control cabinet, warhead and three portion's sections of empennage in the past backward.A whole set of guidance control system instrument and equipment and executing agency are installed in the control cabinet.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.Empennage is partly continued to use original empennage, does not make an amendment, and material is an aluminium.In explosive assembly casing, navigate control combination and packed part carry out the assembling of widget again with dynamite charge in elder generation.Secondly the whole body of going up is partly carried out general assembly, at last empennage is combined with body.
Usefulness for maximum efficiency performance mortar launching guidance shell reduces launch preparation time, and under the normal condition, the mortar emission needs 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.Shell with 120mm is an example, and following table is the data of primary structure characteristics
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.
After the shell emission, 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.
Utilize the combined guidance system, can 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 enemy's ground target is implemented the precision strike of " operation " formula, improve the fighting efficiency of ammunition.Have total arrangement and pneumatic design technology under the multiple constraint.Miniaturization missile-borne power technology, 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); Airborne equipment anti high overload technology; Attitude stabilization and zero-miss guidance designing technique under the big attitude misalignment.
GPS+ inertial navigation combined guidance shell utilizes 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.
The above only is the specific embodiment of the present utility model; should be pointed out that for those skilled in the art, under the prerequisite that does not break away from the utility model principle; can also make some improvements and modifications, these improvements and modifications also should be considered as protection domain of the present utility model.
Claims (2)
1. the GPS of a 120mm mortar and inertial navigation combined guidance shell comprise warhead, control cabinet, empennage, and high explosive and fuze mechanism are housed in the wherein said warhead, it is characterized in that:
GPS guidance device and inertial unit are housed in the described control cabinet.
2. the GPS of 120mm mortar and inertial navigation combined guidance shell according to claim 1 is characterized in that described explosive assembly casing material is steel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201120139678XU CN202013151U (en) | 2011-05-05 | 2011-05-05 | GPS (global positioning system) and inertia combined guided cartridge of 120mm mortar |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201120139678XU CN202013151U (en) | 2011-05-05 | 2011-05-05 | GPS (global positioning system) and inertia combined guided cartridge of 120mm mortar |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202013151U true CN202013151U (en) | 2011-10-19 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201120139678XU Expired - Fee Related CN202013151U (en) | 2011-05-05 | 2011-05-05 | GPS (global positioning system) and inertia combined guided cartridge of 120mm mortar |
Country Status (1)
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| CN (1) | CN202013151U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104457446A (en) * | 2014-11-28 | 2015-03-25 | 北京航天控制仪器研究所 | Aerial self-alignment method of spinning guided cartridge |
| CN109708535A (en) * | 2019-01-28 | 2019-05-03 | 西安深瞳智控技术有限公司 | A kind of coaxial double-oar tail portion push type miniature missile |
| CN112817339A (en) * | 2019-11-15 | 2021-05-18 | 中国北方工业有限公司 | Instruction fusion algorithm for composite guided aircraft |
| CN114963888A (en) * | 2022-04-19 | 2022-08-30 | 湖北航天飞行器研究所 | Integrated missile controller and installation and use method thereof |
-
2011
- 2011-05-05 CN CN201120139678XU patent/CN202013151U/en not_active Expired - Fee Related
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104457446A (en) * | 2014-11-28 | 2015-03-25 | 北京航天控制仪器研究所 | Aerial self-alignment method of spinning guided cartridge |
| CN104457446B (en) * | 2014-11-28 | 2016-02-10 | 北京航天控制仪器研究所 | A kind of aerial Alignment Method of the guided cartridge that spins |
| CN109708535A (en) * | 2019-01-28 | 2019-05-03 | 西安深瞳智控技术有限公司 | A kind of coaxial double-oar tail portion push type miniature missile |
| CN112817339A (en) * | 2019-11-15 | 2021-05-18 | 中国北方工业有限公司 | Instruction fusion algorithm for composite guided aircraft |
| CN112817339B (en) * | 2019-11-15 | 2022-12-23 | 中国北方工业有限公司 | Instruction fusion algorithm for composite guided aircraft |
| CN114963888A (en) * | 2022-04-19 | 2022-08-30 | 湖北航天飞行器研究所 | Integrated missile controller and installation and use method thereof |
| CN114963888B (en) * | 2022-04-19 | 2023-11-03 | 湖北航天飞行器研究所 | Integrated missile controller and installation and use method thereof |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20111019 Termination date: 20140505 |