CN107943075A - It is a kind of that the method that yawing breaks away from attack is penetrated using big gun - Google Patents
It is a kind of that the method that yawing breaks away from attack is penetrated using big gun Download PDFInfo
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- CN107943075A CN107943075A CN201711175812.XA CN201711175812A CN107943075A CN 107943075 A CN107943075 A CN 107943075A CN 201711175812 A CN201711175812 A CN 201711175812A CN 107943075 A CN107943075 A CN 107943075A
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- 238000000034 method Methods 0.000 title claims abstract description 20
- 230000001133 acceleration Effects 0.000 claims description 8
- 241000208340 Araliaceae Species 0.000 description 1
- 235000005035 Panax pseudoginseng ssp. pseudoginseng Nutrition 0.000 description 1
- 235000003140 Panax quinquefolius Nutrition 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000013467 fragmentation Methods 0.000 description 1
- 238000006062 fragmentation reaction Methods 0.000 description 1
- 235000008434 ginseng Nutrition 0.000 description 1
- 231100000518 lethal Toxicity 0.000 description 1
- 230000001665 lethal effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
- G05D1/10—Simultaneous control of position or course in three dimensions
- G05D1/107—Simultaneous control of position or course in three dimensions specially adapted for missiles
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Automation & Control Theory (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The method that yawing breaks away from attack is penetrated using big gun the present invention relates to a kind of, is included the following steps：By the onboard flight radar real time scan in aircraft and determine to attack the first flight parameter of flying object, and the first flight parameter is inputted into the on-board controller in aircraft；On-board controller is according to onboard data storehouse matching and identifies and attacks flying object model and confirm to attack flying object striking radius；Obtain the second flight parameter of aircraft in real time from inertial navigation system by on-board controller；Predicted by on-board controller according to the first flight parameter to attack the flight path of flying object, if it is equal to striking radius to attack the air line distance of flying object and aircraft, the transmitter then automatically controlled by on-board controller positioned at aircraft wing bottom fires shells rapidly, is attacked with hiding.In method provided by the invention, the quick change of flight device course of powerful torque of moment generation is penetrated using big gun by the control of on-board controller, the attack of flying object is attacked to hide.
Description
Technical field
The present invention relates to space flight and aviation technical field, more particularly to a kind of the side that yawing breaks away from attack is penetrated using big gun
Method.
Background technology
The fighter plane fought fiercely in the air, no matter how advanced how excellent performance is, run into attack flying object attack when
Time can only also make various limited maneuvers under the control stick of pilot, although above-mentioned maneuver can temporarily change
Become flight path, but since the yawing of generation is limited, and to still suffer from the regular hour poor for the form that directly operates of pilot,
So that yaw after aircraft still cannot effectively break away to attack the attack of flying object so that fighter plane when in face of missile attack still
Lose larger.
The content of the invention
For the above problem existing for the yaw of existing fighter plane, one kind is now provided and penetrates yawing using big gun and breaks away from attack
Method, with the control of on-board controller using big gun penetrate moment generation the quick change of flight device course of powerful torque, hide
Keep away to attack the attack of flying object.
Concrete technical scheme is as follows：
It is a kind of that the method that yawing breaks away from attack is penetrated using big gun, have the feature that, include the following steps：
Step 1：By the onboard flight radar real time scan in aircraft and determine the first flight ginseng to attack flying object
Number, and the first flight parameter is inputted into the on-board controller in aircraft；
Step 2：On-board controller attacks flying object model and confirms to fly to attack according to onboard data storehouse matching and identification
Thing striking radius；
Step 3：Obtain the second flight parameter of aircraft in real time from inertial navigation system by on-board controller；
Step 4：Predicted by on-board controller according to the first flight parameter to attack the flight path of flying object, and according to winged to attack
The flight path of row thing and the second flight parameter are calculated to attack the air line distance of flying object and aircraft, if to attack flying object and aircraft
Air line distance be less than or equal to striking radius, then the transmitter positioned at aircraft wing bottom is automatically controlled by on-board controller
Fire shells rapidly, quickly to produce yawing, the flight course angle of change of flight device, hides to attack the attack of flying object.
Above-mentioned method, also has the feature that, height that the first flight parameter includes attacking flying object, speed plus
Speed and flight course angle.
Above-mentioned method, also has the feature that, the second flight parameter includes the height, speed, acceleration of aircraft
With flight course angle.
Above-mentioned method, also has the feature that, inertial navigation system is obtained three-dimensional by gyroscope and accelerometer
Directional information and three-dimensional acceleration information, and calculated with this and obtain the second flight parameter.
Above-mentioned method, also has the feature that, is guided missile to attack flying object.
Above-mentioned method, also has the feature that, shell is blank cartridge.
The beneficial effect of such scheme is：
Provided by the invention to penetrate yawing using big gun and break away from the method for attack, the control for passing through on-board controller utilizes
Big gun penetrates the quick change of flight device course of powerful torque of moment generation, and the attack of flying object is attacked to hide.
Embodiment
The technical solution in the embodiment of the present invention is clearly and completely retouched below in conjunction with the embodiment of the present invention
State, it is clear that described embodiment is only part of the embodiment of the present invention, instead of all the embodiments.Based on the present invention
In embodiment, the every other implementation that those of ordinary skill in the art are obtained on the premise of creative work is not made
Example, belongs to the scope of protection of the invention.
It should be noted that in the case where there is no conflict, the feature in embodiment and embodiment in the present invention can phase
Mutually combination.
With reference to specific embodiment, the invention will be further described, but not as limiting to the invention.
It is a kind of that the method that yawing breaks away from attack is penetrated using big gun, include the following steps：
Step 1：By the onboard flight radar real time scan in aircraft and determine to attack the first flight parameter of guided missile,
It is main to include height, speed, acceleration and flight course angle, and the first flight parameter is inputted into the airborne control in aircraft
Device；
Step 2：On-board controller is according to internal database (by disclosing the appearance of guided missile now, performance data generates)
Match somebody with somebody and identify to attack guided missile model and confirm to attack flying object striking radius；
Step 3：Obtain the second flight parameter of aircraft in real time from inertial navigation system by on-board controller, main bag
Include height, speed, acceleration and flight course angle, external information is not depended in view of inertial navigation technology in the present embodiment, and
And electromagnetic interference is not easily susceptible to, thus selected from the second flight parameter is obtained in real time by inertial navigation system, in order to further improve
Precision, also may be selected by satellite navigation system, as GPS, Galileo system or dipper system obtain the in real time
Two flight parameters；
Step 4：By on-board controller according to the modeling of the first flight parameter and real-time estimate come attack flying object it is one section following when
Between flight path, and according to come attack the flight path of flying object and the second flight parameter calculate the straight line of attacking flying object and aircraft away from
From if being less than or equal to striking radius to attack the air line distance of flying object and aircraft, position is automatically controlled by on-board controller
Transmitter in aircraft wing bottom launches rapidly blank, quickly to produce yawing, the flight of change of flight device
Course angle, hides to attack the attack of flying object；
Specifically, inertial navigation system obtains three-dimensional information and three by gyroscope and accelerometer in the present embodiment
Acceleration information is tieed up, and is calculated with this and obtains the second flight parameter.
Caused huge recoil is penetrated using big gun in the present embodiment and produce yawing, to realize the quick of flight course
Change, the attack of guided missile is attacked to hide, can in the present embodiment for the ease of producing yawing in time in a desired direction
Rotary gun turret is respectively provided with the bottom of aircraft both sides wing, is quickly rotated to suitable angular with the control according to on-board controller
Spend and fire shells, to produce effective yawing rapidly, aircraft quickly rotated, rolled, and by aircraft rapidly
Tumbling motion departs to attack the striking radius of guided missile, can also be fled from by the rapidly tumbling motion of aircraft to attack guided missile fragmentation
Lethal radius.
It these are only preferred embodiments of the present invention, not thereby limit embodiments of the present invention and protection domain, it is right
For those skilled in the art, it should can appreciate that all equivalent substitutions with made by present specification and show
And the obtained scheme of change being clear to, it should be included in protection scope of the present invention.
Claims (6)
1. a kind of penetrate the method that yawing breaks away from attack using big gun, it is characterised in that includes the following steps：
Step 1：By the onboard flight radar real time scan in aircraft and determine to attack the first flight parameter of flying object, and
First flight parameter is inputted into the on-board controller in aircraft；
Step 2：On-board controller attacks flying object model and confirms to attack to attack flying object according to onboard data storehouse matching and identification
Hit radius；
Step 3：Obtain the second flight parameter of aircraft in real time from inertial navigation system by on-board controller；
Step 4：Predicted by on-board controller according to the first flight parameter to attack the flight path of flying object, and according to attacking flying object
Flight path and the second flight parameter calculate to attack the air line distance of flying object and aircraft, if to attack the straight of flying object and aircraft
Linear distance is less than or equal to striking radius, then it is rapid to automatically control transmitter positioned at aircraft wing bottom by on-board controller
Fire shells, quickly to produce yawing, the flight course angle of change of flight device, hides to attack the attack of flying object.
2. according to the method described in claim 1, it is characterized in that, first flight parameter is included to attack the height of flying object
Degree, speed, acceleration and flight course angle.
3. according to the method described in claim 1, it is characterized in that, second flight parameter includes height, the speed of aircraft
Degree, acceleration and flight course angle.
4. according to the method described in claim 3, it is characterized in that, the inertial navigation system passes through gyroscope and accelerometer
Three-dimensional information and three-dimensional acceleration information are obtained, and is calculated with this and obtains the second flight parameter.
5. according to claim 1-4 any one of them methods, it is characterised in that described come to attack flying object be guided missile.
6. according to claim 1-4 any one of them methods, it is characterised in that the shell is blank cartridge.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711175812.XA CN107943075A (en) | 2017-11-22 | 2017-11-22 | It is a kind of that the method that yawing breaks away from attack is penetrated using big gun |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201711175812.XA CN107943075A (en) | 2017-11-22 | 2017-11-22 | It is a kind of that the method that yawing breaks away from attack is penetrated using big gun |
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| CN107943075A true CN107943075A (en) | 2018-04-20 |
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| CN201711175812.XA Pending CN107943075A (en) | 2017-11-22 | 2017-11-22 | It is a kind of that the method that yawing breaks away from attack is penetrated using big gun |
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4421007A (en) * | 1981-12-10 | 1983-12-20 | Hanes Jr Norris H | Air bomb system |
| CN1430720A (en) * | 2000-05-25 | 2003-07-16 | 斯托姆金属有限公司 | Directional control of missiles |
| CN101554923A (en) * | 2008-12-04 | 2009-10-14 | 寿国伟 | Airplane missile defense system |
| CN101575000A (en) * | 2008-05-08 | 2009-11-11 | 李晓亮 | Battleship with missile-attack prevention device |
| CN102167161A (en) * | 2010-11-26 | 2011-08-31 | 重庆兆迈机械技术研发有限公司 | Three-dimensional flying aircraft |
| CN103673785A (en) * | 2012-09-20 | 2014-03-26 | 王正铉 | Antimissile preventing missile having stealth function and flying in moth-type deflecting mode |
| CN104850129A (en) * | 2014-12-19 | 2015-08-19 | 北京控制工程研究所 | Salutatory reentry pre-bias direction lateral guide method |
-
2017
- 2017-11-22 CN CN201711175812.XA patent/CN107943075A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4421007A (en) * | 1981-12-10 | 1983-12-20 | Hanes Jr Norris H | Air bomb system |
| CN1430720A (en) * | 2000-05-25 | 2003-07-16 | 斯托姆金属有限公司 | Directional control of missiles |
| CN101575000A (en) * | 2008-05-08 | 2009-11-11 | 李晓亮 | Battleship with missile-attack prevention device |
| CN101554923A (en) * | 2008-12-04 | 2009-10-14 | 寿国伟 | Airplane missile defense system |
| CN102167161A (en) * | 2010-11-26 | 2011-08-31 | 重庆兆迈机械技术研发有限公司 | Three-dimensional flying aircraft |
| CN103673785A (en) * | 2012-09-20 | 2014-03-26 | 王正铉 | Antimissile preventing missile having stealth function and flying in moth-type deflecting mode |
| CN104850129A (en) * | 2014-12-19 | 2015-08-19 | 北京控制工程研究所 | Salutatory reentry pre-bias direction lateral guide method |
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Application publication date: 20180420 |