CN107478106A - Orbit launching ground effect wing is to extra large guided missile - Google Patents
Orbit launching ground effect wing is to extra large guided missile Download PDFInfo
- Publication number
- CN107478106A CN107478106A CN201710699495.5A CN201710699495A CN107478106A CN 107478106 A CN107478106 A CN 107478106A CN 201710699495 A CN201710699495 A CN 201710699495A CN 107478106 A CN107478106 A CN 107478106A
- Authority
- CN
- China
- Prior art keywords
- guided missile
- wing
- ground effect
- extra large
- guide rail
- 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
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Classifications
-
- 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
The present invention discloses a kind of orbit launching ground effect wing to extra large guided missile, belongs to naval's offensive weapon.Including bullet, body, jet, all-wing aircraft, empennage, the rudder wing, sliding block, guide rail and guiding gutter.It is characterized in that the ground effect that guided missile by naval vessel orbit launching or thrown with airplane, relies on all-wing aircraft acts on 14 meters of height and plunders sea level height flight, completes strike mission.The present invention is compared with prior art, flying height of the guided missile on sea is lower, more balances, be disguised stronger, it is found smaller with interception probability, make missile load ability bigger simultaneously because ground effect makees land used bounce-back, more multi fuel can be filled or carry bigger bullet, extend attack distance or increase attack power.
Description
First, technical field：
The present invention relates to naval to warship offensive weapon, specifically a kind of orbit launching ground effect wing is to extra large guided missile.
2nd, background technology：
Since missilery is used for military offensive purpose, the attacking and defending research and practice to guided missile are just constantly in and risen by turns
Among level, hide detecting numerous, among the method and measure for improving penetration ability, hedgehopping is bent using earth surface
Rate is hidden to keep away the means closed with the enemy, particularly flat horizontal, provides an accessible suitable space for hedgehopping, exists at present
Sea uses the extreme low-altitude aircraft closed with the enemy, 10 meters of many places space above.
3rd, the content of the invention：
The purpose of the present invention is to be directed to above present situation and demand, there is provided a kind of flying height is lower, more stable, penetration ability
Stronger orbit launching ground effect wing is to extra large guided missile.
The purpose of the present invention is achieved through the following technical solutions：
A kind of orbit launching ground effect wing is to extra large guided missile, including bullet, body, jet, all-wing aircraft, empennage, the rudder wing, slides
Block, guide rail and guiding gutter, it is characterized in that the ground effect that guided missile relies on all-wing aircraft acts on high-speed flight on the sea of 1-4 rice height, its
Body is the cylinder of big end down different radii arc combination, and front end is punctured into streamlined bullet, tail end installation engine and
Jet, the all-wing aircraft of big width small span is set in body middle front part both sides close to bottom surface, two sides of tail sets empennage, and afterbody is just
Top sets the rudder wing, and the sliding block run along guide rail is set in size arc joining place；Sea is led in equipment orbit launching ground effect wing
The horizontal guide rail launched a guided missile is installed, guide rail end docks the guiding gutter entrance of 90 degree of steerings on the carrier naval vessel of bullet.
The orbit launching ground effect wing is to extra large guided missile, it is characterized in that setting what more sets were launched a guided missile on identical carrier naval vessel
Guide rail and guiding gutter.
Described orbit launching ground effect wing is to extra large guided missile, it is characterized in that the guide rail and guiding gutter launched a guided missile are installed in variable
To rotating disk on.
Described orbit launching ground effect wing is to extra large guided missile, it is characterized in that the guided missile after transmitting, passes through engine and jet
Control, realize cruise phase low speed, close with the enemy advance section high speed speed change flight.
Described orbit launching ground effect wing is to extra large guided missile, it is characterized in that suspension arrangement is set in body top, with the machine of attacking and annihilating
Imitate effect flight or bomber is the plug-in release of carrier, after sliding to sea with relying on attack.
The orbit launching ground effect wing of the present invention compared with prior art, has with low content of technology to extra large guided missile, and it is easy to make,
It is easy to manipulate, the features such as application technology is ripe, reliability is high, additionally with following heavy more advantages：
1st, the standby more heavy load ability of flying instrument can be made using the effect of ground effect, more flight fuel can be filled in guided missile or take
The bigger oncoming warhead of band, extend attack distance or increase attack power.
2nd, more than half diameter and arc surface and all-wing aircraft, the setting of empennage and architectural feature are used below body, during making missile flight,
There is the flat consistent plane of more large area below, effect effect in ground is more prominent superior, makes flying height lower, more steady.
3rd, identical carrier naval vessel sets more set emitters, can more pieces of guided missile salvos or increase emission density, increase prominent anti-
The probability of success.
4th, emitter is arranged at rotating disk, be conveniently adjusted MISSILE LAUNCHING sensing, and need not or minor modification carrier naval vessel
Direction, it is easy to attack immediately after finding target.
5th, the speed changing function setting during missile flight, can make guided missile use economic pace in cruise section, nearly enemy's attack
Duan Caiyong high speed impact speed, while can also increase the interception difficulty being ascertained after finding, improve success attack probability.
6th, guide rail end docks 90 degree of steering diversion groove, can be oriented to guided missile igniting rear molding spray aerial, reduce high temp fire
Influence and infringement of the flame to carrier.
7th, using opportunity of combat as carrier, plug-in ground effect wing is launched to extra large guided missile, make to close with the enemy speed faster, flexibility ratio it is higher, more
It is adapted to battlefield demand in the range of opportunity of combat radius of action, more for attacking ability.
4th, illustrate：
Fig. 1 is orbit launching ground effect wing to schematic diagram above extra large guided missile.
Fig. 2 is front schematic view of the orbit launching ground effect wing to extra large guided missile.
Fig. 3 is in-orbit pending side schematic view of the orbit launching ground effect wing to extra large guided missile.
In figure：1 bullet, 2 bodies, 3 jets, 4 all-wing aircrafts, 5 empennages, the 6 rudder wings, 7 sliding blocks, 8 guide rails, 9 guiding gutters.
5th, embodiment：
The present invention is illustrated in further detail below with reference to Figure of description：
As depicted in figs. 1 and 2, orbit launching ground effect wing of the invention to extra large guided missile by bullet 1, body 2, jet 3, fly
The wing 4, empennage 5, the rudder wing 6 and sliding block 7 form, and its body 2 is combined as irregular cylinder, front end by the arc of 1: 2 radius
Streamlined bullet 1, rear end installation jet engine and controllable spray mouth 3 are punctured into, is set at the nearly bottom surface in middle front part both sides of body 2
The all-wing aircraft 4 of big width small span is put, two sides of tail sets empennage 5, and afterbody is arranged above the rudder wing 6, in nearly bottom surface size arc knot
The sliding block 7 run along track 8 is set at conjunction.Transmitting is installed on carrier naval vessel of the equipment orbit launching ground effect wing to extra large guided missile
The horizontal guide rail 8 of guided missile, the end of guide rail 8 to 90 degree turn to the entrances of guiding gutter 9.
It is the known technology of those skilled in the art in addition to the technical characteristic described in specification.
Claims (5)
1. a kind of orbit launching ground effect wing is to extra large guided missile, including bullet, body, jet, all-wing aircraft, empennage, the rudder wing, sliding block,
Guide rail and guiding gutter, it is characterized in that the ground effect that guided missile relies on all-wing aircraft acts on high-speed flight on the sea of 1-4 rice height, its body
For the cylinder of big end down different radii arc combination, front end is punctured into streamlined bullet, tail end installation engine and injection
Mouthful, the all-wing aircraft in body middle front part both sides close to the big width small span of bottom surface setting, two sides of tail sets empennage, afterbody surface
The rudder wing is set, the sliding block run along guide rail is set in size arc joining place；In equipment orbit launching ground effect wing to extra large guided missile
The horizontal guide rail launched a guided missile is installed, guide rail end docks the guiding gutter entrance of 90 degree of steerings on carrier naval vessel.
2. orbit launching ground effect wing is to extra large guided missile according to claim 1, it is characterized in that being set on identical carrier naval vessel more
Cover the guide rail and guiding gutter launched a guided missile.
3. orbit launching ground effect wing according to claim 1 is to extra large guided missile, it is characterized in that the guide rail and water conservancy diversion launched a guided missile
Groove is arranged on reversible rotating disk.
4. orbit launching ground effect wing according to claim 1 is to extra large guided missile, it is characterized in that the guided missile after launching, by starting
The control of machine and jet, cruise phase low speed is realized, close with the enemy and advance the speed change flight of section high speed.
5. orbit launching ground effect wing according to claim 1 is to extra large guided missile, it is characterized in that setting suspension dress in body top
Put, effect flight is imitated using the machine of attacking and annihilating or bomber as the plug-in release of carrier, after sliding to sea with relying on is attacked.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710699495.5A CN107478106A (en) | 2017-08-16 | 2017-08-16 | Orbit launching ground effect wing is to extra large guided missile |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710699495.5A CN107478106A (en) | 2017-08-16 | 2017-08-16 | Orbit launching ground effect wing is to extra large guided missile |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107478106A true CN107478106A (en) | 2017-12-15 |
Family
ID=60600715
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710699495.5A Pending CN107478106A (en) | 2017-08-16 | 2017-08-16 | Orbit launching ground effect wing is to extra large guided missile |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107478106A (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2606725A (en) * | 1946-09-24 | 1952-08-12 | Kellogg M W Co | Launching device |
| US2985072A (en) * | 1953-10-07 | 1961-05-23 | Robert E Carlberg | Missile launching system |
| US3215040A (en) * | 1963-03-26 | 1965-11-02 | Robert L Kossan | Adapter rail |
| GB2121149B (en) * | 1982-05-27 | 1985-07-24 | British Aerospace | Missile housing and launch arrangement |
| JPH04260797A (en) * | 1991-02-15 | 1992-09-16 | Mitsubishi Heavy Ind Ltd | Jet gas deflecting reaction cancelling device for missile |
| US5845875A (en) * | 1994-05-02 | 1998-12-08 | Lockheed Martin Corporation | Modular launch pad system |
| WO2010001051A2 (en) * | 2008-07-03 | 2010-01-07 | Dcns | Principle for the integration of missile-based weapon systems on a fixed ramp for stealth surface vessels in order to counter asymmetric threats |
| WO2015053859A1 (en) * | 2013-08-20 | 2015-04-16 | Lockheed Martin Corporation | Multiple missile carriage and launch guidance module |
-
2017
- 2017-08-16 CN CN201710699495.5A patent/CN107478106A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2606725A (en) * | 1946-09-24 | 1952-08-12 | Kellogg M W Co | Launching device |
| US2985072A (en) * | 1953-10-07 | 1961-05-23 | Robert E Carlberg | Missile launching system |
| US3215040A (en) * | 1963-03-26 | 1965-11-02 | Robert L Kossan | Adapter rail |
| GB2121149B (en) * | 1982-05-27 | 1985-07-24 | British Aerospace | Missile housing and launch arrangement |
| JPH04260797A (en) * | 1991-02-15 | 1992-09-16 | Mitsubishi Heavy Ind Ltd | Jet gas deflecting reaction cancelling device for missile |
| US5845875A (en) * | 1994-05-02 | 1998-12-08 | Lockheed Martin Corporation | Modular launch pad system |
| WO2010001051A2 (en) * | 2008-07-03 | 2010-01-07 | Dcns | Principle for the integration of missile-based weapon systems on a fixed ramp for stealth surface vessels in order to counter asymmetric threats |
| WO2015053859A1 (en) * | 2013-08-20 | 2015-04-16 | Lockheed Martin Corporation | Multiple missile carriage and launch guidance module |
Non-Patent Citations (3)
| Title |
|---|
| 卜亚军 等: "地效掠海巡航导弹气动布局研究与前景展望", 《飞航导弹》 * |
| 吕国鑫 等: "海效导弹外形设计及气动布局研究", 《全国低跨超声速空气动力学文集第一卷(2001年)》 * |
| 吕国鑫 等: "海效导弹气动外形设计方法研究", 《2003空气动力学前沿研究论文集》 * |
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Legal Events
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|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20171215 |