CN1515870A - Variable wing guidance bomb - Google Patents
Variable wing guidance bomb Download PDFInfo
- Publication number
- CN1515870A CN1515870A CNA031003028A CN03100302A CN1515870A CN 1515870 A CN1515870 A CN 1515870A CN A031003028 A CNA031003028 A CN A031003028A CN 03100302 A CN03100302 A CN 03100302A CN 1515870 A CN1515870 A CN 1515870A
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- bomb
- increment
- wing
- aircraft
- empennage
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Abstract
The present invention relates to a kind of variable wing mechanism and its automatic control system mounted on general bomb. A hemispherical hanging chamber is mounted on the lower portion of general bomb along the longitudinal overall length, in the chamber a folding wing and a folding wing equi-speed opening mechanism are mounted. At the same time, in the hanging chamber an inertial guidance piezoelectric fluidic gyro, an automatic control system and a GPS accurate location system are mounted so as to implement the goal of automatically and accurately hitting a target.
Description
Affiliated technical field
The present invention relates to Air Force weapon.The wing that the GP bomb of thrown with airplane adds with the present invention, empennage and the upright wing make it to increase the horizontal gliding distance of bomb.Use the remote auto control technology simultaneously, make bomb directly accurately hit the quick explosive in guidance increment end of set objective.
Background technology
At present, the bomb that known air force uses is freely thrown in from aircraft, is only determined the opportunity of deliver through the simple parameters such as distance of calculating air speed, ground velocity, the relative target of flying height by the navigator.Bomb only depends on acceleration of gravity and aircraft flight to give the inertia force flight hit of bomb, and the accuracy rate of dropping a bomb is very low, and it is many to consume bomb, but the bomb that hits the mark is few.Simultaneously, more non-military striking target caused undue harm, the earth mankind's ecological environment is also caused very big destruction.In a word, most of is that the GP bomb of feature is not good weapon in not with throwing.
In addition, because bomb is the energy flight by inertia and gravity freely falling body, flying distance is very short, and operational aircraft must be thrown in nearby in the target sky, and aircraft enters enemy's defensive fire net, not only is difficult to win victory, and makes fallen dangerous increasing on the contrary.
Summary of the invention
For overcome existing GP bomb hit rate low, need enter the enemy firepower net when throwing, very danger etc. the invention provides a kind of technology of increment guidance glomb as the deadly defect of weapon with adapt to the needs of modernized war.Install missile wing additional and produce lift, improve lift-drag ratio, to increase the gliding flight distance of bomb.Simultaneously, install piezoelectricity jet gyro, acceleration transducer, large torque steering wheel, GPS location receiving system, terminal guidance numerical control PS and the hemispherical parachute terminal guidance system etc. of automatic control usefulness in the extension cabin below additional bomb additional by step motor control, carry out the automatic operation of hit by hanging mechanisms such as single-chip microcomputer and electronic logic element in the cabin, revise the semi-ballistic trajectory of gliding flight.By above-mentioned setting of the present invention, original GP bomb has been become can be to the accurate last quick explosive that hits of target.
The present invention solves the technical scheme that its technical problem takes: a semicircular suspension cabin is set below the body of GP bomb, and longitudinally unanimous on the whole with the total length of body.Its volume, volume account for the 1/3-1/4 of bomb volume.In the extension cabin that this adds, the place ahead is equipped with the main wing of fly bomb and launches the main shaft of main wing, the stepper motor driven fan-shaped gear mechanism that launches usefulness.Near the rear portion empennage and the upright wing of fly bomb are housed, the volume similar to the main wing development mechanism, slightly little main shaft and sector gear development mechanism, and in the body both sides vertically disposed two upright wing depository dishes.When launching main wing, empennage, two upright wings can protrude upward in box synchronously simultaneously.So far, bomb has originally become a controllable flight device fully by above-mentioned layout of the present invention.
Owing to,, can be equipped with the lifting area of different big or small main wings, empennage according to the difference of payload (bomb itself) size with respect to the bomb body.When strengthening lift-drag ratio, can increase wing area and fin area, improve the distance of bearing capacity and gliding flight, realize the increment of GP bomb.The distance of air attack ground target being strengthened, effectively avoid enemy's defensive fire to attack, is a kind of glomb of obvious increase operational efficiency.
On main wing and empennage, all place common lifting rudder face and direction rudder face, control pitching and horizontal stability respectively, correct course-line deviation.
It is stamping forming by the normal carbon sheet metal that bullet is carried additionally the cabin outward, all around on the steel plate plane respectively punching press the thin groove of semicircle is arranged as reinforcement, to increase the integral rigidity of hanging the cabin.Obviously alleviate the weight of hanging the cabin by such layout, simplified the structure, reduced the manufacturing cost of increment aircraft, strengthened the operational efficiency of weapon.Lifting force of wings and resistance ratio are set at 3.According to aerodynamics and flight dynamics, learn that as calculated the flight of guided bomb and gliding distance equal the product of height (long measure: rice) and lift-drag ratio, that is: L=H*K
The height of the lift-drag ratio H-aircraft of L-gliding distance K-aircraft in the formula
The technology of the present invention is characterised in that and is provided with the larger area wing that the aerofoil profile of wing is subsonic plano-convex aerofoil profile.Adopt frp process to make the hollow wing of plano-convex aerofoil profile.Laterally be provided with in the hollow wing along the I-shaped girder of the magnesium alloy of span total length installation,, offset the bending moment that makes progress of lift generation in-flight to increase the bending strength of whole wing empennage.Be coated with alkyd resin layer with polishing at the skin of fiberglass covering, reduce friction resistance and mix the invisible coating of anti-radar wave prevents that radar from seeking, to improve the fight survival ability of guidance fly bomb.
Another one of the present invention is to the effect that:
In external pod, also be provided with the automatic control system of control flight attitude.The terminal guidance system that parachute is housed by piezoelectricity jet gyro velocity sensor, GPS accurate positioning device, terminal guidance digital imagery control system and afterbody has formed a control system that can fly to set objective fully automatically.Above-mentioned components and parts by the technology of the present invention is arranged make the aircraft of the bomb that wing is housed become a glide increment guided bomb.
The feature of the present invention program's aircraft is usual formula, is that the horizontal left and right sides of longitudinal axis is a symmetric arrangement with the bomb body center.The left and right sides upon deployment, by obtaining left and right horizontal symmetry and about about 10 ° upper counterangle that is inclined upwardly at arc guide groove that launches to be provided with on the axis and arc toothed gear mechanism and the linkage of covering of the fan double step, increase horizontal stability, the linearity of aircraft is good, and the accuracy rate of hit is guaranteed.
The inertia gyroscope guidance system of technical solution of the present invention is characterised in that: the main control semi-ballistic trajectory that adopts, the degree of accuracy of hitting that improves bomb.
Automatically the sensitive components of the control system of hit is to adopt solid state piezoelectric jet gyro, angular-rate sensor, the two to the control accuracy of lift-over driftage and reliability all greater than 0.999, volume and cigarette case are suitable, zero drift is ((°)/s)/min less than 0.1, electric current 15V, 240mA, the response time is less than 80ms.Can be by the isoparametric parts of the free degree, angular speed, angular acceleration and angular displacement of in good time locating tab assembly and control.Have A/D converter, microcontroller and electrically erasable controller in the control system, adapt to the requirement of complicated operational environment.
Embodiments of the invention are that the bomb of conventional 500kg level that one piece of present air force is equipped with has installed the various technical measures that described the present invention adopts as specification additional, design has also been made an adjustable wing guided bomb shown in accompanying drawing 1 upward view, left wing's wing 2, the right flank wing 3 of collapsible placement are housed in body 1 bottom, left and right development mechanism 4, port tailplane 5, starboard tailplane 6, about two empennage development mechanisms 7, total electric controller and 5W power pack 8, pack and terminal guidance device 9 are with the body 1 afterbody rigidly connected afterbody taper fairing 10 of bolt.Simultaneously, on accompanying drawing 2 front views, arranged the right upright wing 12, right upright wing box and rise wildhaber-novikov gear device 13, the upright wing 14 in a left side, upright wing box in a left side and rise wildhaber-novikov gear device 15, and hang cabin suspension ring 16, the suspension ring 17 of body 1, the extension cabin 18 that development mechanism is housed.The embodiment of the invention is to finish according to the described technical scheme of specification of the present invention fully, can hit the bull's-eye in firing practice, or participate under battle conditions.
Claims (6)
1, a kind of adjustable wing guided bomb is installed collapsible, main wing that can instantaneous synchronous expansion, empennage below body, and two upright wings is a kind of simple usual type aircraft of fuselage with the body, it is characterized in that: all the wing settings lift that can increase bomb increases gliding distance.
2, increment bomb aircraft according to claim 1 is characterized in that: aloft the semi-ballistic trajectory of the increment behind the drop bomb is to be controlled by the electronic installations such as inertial piezoelectric jet gyro of the automatic control of installing on the aircraft to make the automatic hit of aircraft.
3, increment bomb aircraft according to claim 1 is opened pack above target, target is implemented the device of final guidance.
4, the folding main wing of increment bomb aircraft according to claim 1, empennage development mechanism are made up of double step wildhaber-novikov gear mechanism.
5, power supply, total electric controller box are housed in the tail cone radome fairing of increment bomb aircraft according to claim 1.It is characterized in that: make body become the ichthyoid of standard.
6, the feature of two upright wings of increment bomb according to claim 1 is by the wildhaber-novikov gear device that steadily stretches out in the box that is contained in the aft body left and right sides.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA031003028A CN1515870A (en) | 2003-01-10 | 2003-01-10 | Variable wing guidance bomb |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA031003028A CN1515870A (en) | 2003-01-10 | 2003-01-10 | Variable wing guidance bomb |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN1515870A true CN1515870A (en) | 2004-07-28 |
Family
ID=34238972
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNA031003028A Pending CN1515870A (en) | 2003-01-10 | 2003-01-10 | Variable wing guidance bomb |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN1515870A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102121512A (en) * | 2010-12-23 | 2011-07-13 | 江西洪都航空工业集团有限责任公司 | Crossing and folding wing transmission device |
| RU2447397C2 (en) * | 2010-11-10 | 2012-04-10 | Александр Иванович Голодяев | Bomb |
| CN106403730A (en) * | 2016-11-24 | 2017-02-15 | 江西洪都航空工业集团有限责任公司 | Double-wing non-parachute terminal sensing ammunition |
| CN109489499A (en) * | 2018-12-26 | 2019-03-19 | 湖南省军合科技有限公司 | A kind of 3D printing folding wing scout missile |
| CN113282099A (en) * | 2020-12-16 | 2021-08-20 | 彩虹无人机科技有限公司 | Graphical representation method for bomb launching sector angle condition satisfaction condition of low-speed unmanned aerial vehicle |
| CN115342691A (en) * | 2022-08-05 | 2022-11-15 | 南京理工大学 | Bionic single-wing distributing and scattering device for clustered top-attacking ammunition |
| CN115356935A (en) * | 2022-10-18 | 2022-11-18 | 北京理工大学 | Large airspace conversion flight strategy optimization method based on multi-stage variable shape |
-
2003
- 2003-01-10 CN CNA031003028A patent/CN1515870A/en active Pending
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2447397C2 (en) * | 2010-11-10 | 2012-04-10 | Александр Иванович Голодяев | Bomb |
| CN102121512A (en) * | 2010-12-23 | 2011-07-13 | 江西洪都航空工业集团有限责任公司 | Crossing and folding wing transmission device |
| CN102121512B (en) * | 2010-12-23 | 2013-03-27 | 江西洪都航空工业集团有限责任公司 | Crossing and folding wing transmission device |
| CN106403730A (en) * | 2016-11-24 | 2017-02-15 | 江西洪都航空工业集团有限责任公司 | Double-wing non-parachute terminal sensing ammunition |
| CN109489499A (en) * | 2018-12-26 | 2019-03-19 | 湖南省军合科技有限公司 | A kind of 3D printing folding wing scout missile |
| CN109489499B (en) * | 2018-12-26 | 2024-02-06 | 湖南省军合科技有限公司 | 3D prints foldable wing and patrols flying saucer |
| CN113282099A (en) * | 2020-12-16 | 2021-08-20 | 彩虹无人机科技有限公司 | Graphical representation method for bomb launching sector angle condition satisfaction condition of low-speed unmanned aerial vehicle |
| CN113282099B (en) * | 2020-12-16 | 2023-03-10 | 彩虹无人机科技有限公司 | Graphical representation method for bomb launching sector angle condition satisfaction condition of low-speed unmanned aerial vehicle |
| CN115342691A (en) * | 2022-08-05 | 2022-11-15 | 南京理工大学 | Bionic single-wing distributing and scattering device for clustered top-attacking ammunition |
| CN115342691B (en) * | 2022-08-05 | 2023-08-18 | 南京理工大学 | Bionic single-wing scattering device for cluster top-attacking ammunition |
| CN115356935A (en) * | 2022-10-18 | 2022-11-18 | 北京理工大学 | Large airspace conversion flight strategy optimization method based on multi-stage variable shape |
| CN115356935B (en) * | 2022-10-18 | 2023-01-10 | 北京理工大学 | Large airspace conversion flight strategy optimization method based on multi-stage variable shape |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |