CN103910073A - Exosphere repetition pointer control aircraft curve flight gravity center navigation system - Google Patents
Exosphere repetition pointer control aircraft curve flight gravity center navigation system Download PDFInfo
- Publication number
- CN103910073A CN103910073A CN201410044391.7A CN201410044391A CN103910073A CN 103910073 A CN103910073 A CN 103910073A CN 201410044391 A CN201410044391 A CN 201410044391A CN 103910073 A CN103910073 A CN 103910073A
- Authority
- CN
- China
- Prior art keywords
- aircraft
- heavy
- pointer
- gravity
- heavy pointer
- 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.)
- Granted
Links
- 230000005484 gravity Effects 0.000 title claims abstract description 74
- 230000000694 effects Effects 0.000 claims abstract description 5
- 150000001875 compounds Chemical class 0.000 claims description 4
- 238000000034 method Methods 0.000 claims description 3
- 238000010586 diagram Methods 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 230000001788 irregular Effects 0.000 description 2
- 210000001015 abdomen Anatomy 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000002498 deadly effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000005303 weighing Methods 0.000 description 1
Abstract
An exosphere repetition pointer control aircraft curve flight gravity center navigation system comprises a multiple pointer controller with a plurality of horologe repetition pointer machinery controllers which are different in length, different in weight and different in rotation speed. The exosphere repetition pointer control aircraft curve flight gravity center navigation system is characterized in that the multiple pointer controller is horizontally installed on a head position of an aircraft, and parallel to the central axis of the aircraft and a horizontal plane across the central axis of the aircraft, all repetition pointers are located on positions parallel to the central axis of the aircraft before rotation, all the repetition pointers point in the direction of the tail of the aircraft, and simultaneously the whole weight of the aircraft is divided into two symmetrical halves through the center axis of the aircraft, and when the repetition pointers clockwise rotate, a gravity effect which is offset toward the center axis of the aircraft is generated, the aircraft inclines at a small angle towards the gravity side direction, and accordingly the aircraft can perform an orbital transfer flight towards the inclination direction.
Description
Technical field
The present invention relates to the heavy pointer control in exoatmosphere Curve for Aerocraft center of flying gravity navigationsystem, be applicable to comprise the curved flight of all aircraft and the automatic control of reset, belong to aerospace sciemtifec and technical sphere.
Background technology
In the U.S. and Russian epoch of dominating aerospace flight vehicle lead in the development of science and technology, what China failed to contend with it always can do curved flight avoids the aerospace flight vehicle of anti-ballistic attack, report Russia develops a kind of curved flight aerospace flight vehicle that does not have anti-missile system to attack recently, but their this control curved flight principle is the stage casing of flying in exoatmosphere utilizes jet application force to carry out the heading of change of flight device, certain jet fuel be should consume like this, navigation and the jet direction of light current control utilized again simultaneously; And modern war tends to occur unpredictable situation, such as once war starts, satellite system is destroyed by enemy and is lost automatic navigation function, or can early be found by enemy's utmost point and be attacked by anti-missile system by Navigation Control always, in addition another deadly defect of Navigation Control be exactly they be all by light current controlling run, this light current is very easily destroyed by enemy's strong electromagnetic and ineffective; Preferably there is one can not need navigation and light current to control, and can automatically control the device of not followed the tracks of by electric wave or not destroyed by enemy's strong electromagnetic by enemy of its curved flight, can be unlikely being just blocked at vehicle launch initial stage and mid-term; As everybody knows, from being transmitted into, to lock target of attack actual be exactly a parabola to aircraft, that is to say the line of two points that are launch point and object point, if there is no anti-missile interception, aircraft just does not need to have done curvilinear motion, but in order to avoid anti-missile interception, must make aircraft do random curve, do such curve easy, when how making aircraft do curve, can also make aircraft reset and get back on launch point and original predetermined some point line track striking target, this is only the most key; The invention " 201310230221.3 clock and watch revolve pin ten thousand varied curve flight self-return direction controllers " of Wei Baiqing has solved a difficult problem for curved flight reset, another invention " 201310458435.6 clock and watch revolve the rotational automatic return direction of pin forceful electric power power-assisted controller " of Wei Baiqing has solved a difficult problem for forceful electric power conversion power, difficult problem when " 201310696350.1 for the controlling many pointers controller of curved flight time and direction " of Wei Baiqing solved mechanical control speed control; But these seem the stage casing of can automatic vehicle flying in exoatmosphere and do curved flight and can automatically reply the control setup flying on the some point line track turning back between launch point and object point, because there is no atmosphere and cannot realize predetermined object in exoatmosphere.
The present invention utilizes fly in the exoatmosphere heading in stage casing of Action of Gravity Field change of flight device, make aircraft fly in exoatmosphere stage casing by set track do curved flight, and being set in aircraft reentries before target of attack, can make aircraft return to and do curve flight track before, return on the some point line track between vehicle launch point and target of attack point and fly, this returning on predetermined flight track is automatic, need to be by navigating to make any adjustments direction, realized by many pointers controller setup control, and this setting with control the non-light current control that is machinery, so just can make the aircraft stage casing of flying in exoatmosphere not launch, also do not receive, more form without burner oil the result that heat is followed the tracks of and light current control causes strong electromagnetic to be destroyed, aircraft, in the exoatmosphere apart from earth's surface 1000km left and right, still has the gravity that exceedes 70% compared with earth's surface, and therefore, this scheme reaches predetermined object of the present invention surely, the present invention utilizes uncle minister in ancient times's Wei invention " 201310696350.1 for controlling many pointers controller of curved flight time and direction ", do many pointers controller of curved flight as setup control aircraft, this many pointers controller can make N aircraft have the curved flight of unduplicated N kind, and can make the aircraft curved flight of section awing also not there is any repeatability and not there is any regularity, thereby enemy cannot be tackled this.
Summary of the invention
The object of this invention is to provide a kind of do not need light current control, by the heavy pointer control of machinery make aircraft center of gravity be offset change of flight direction and do curved flight, and the exoatmosphere weight pointer control Curve for Aerocraft center of flying gravity navigationsystem that can aircraft be returned to fly on the some point line track between vehicle launch point and target of attack point by the time of setting and flight path.
The heavy pointer control in exoatmosphere Curve for Aerocraft center of flying gravity navigationsystem, comprises a set of many pointers controller of controlling with the branched heavy pointer machinery of clock and watch with different length, Different Weight and different rotation rates that is arranged on Vehicle nose; It is characterized in that:
1, many pointers controller level is arranged on Vehicle nose position, and to cross axis horizontal surface parallel with aircraft axis and aircraft, all heavy pointers rotation before all in the position parallel with aircraft axis, and all heavy pointers all point to same direction and point to aircraft caudal directions, now the overall weight of aircraft is taking aircraft axis as symmetrical; Many pointers controller is the rotative speed of being controlled the heavy pointer of each clock and watch by machinery, the longest No. 1 the heaviest heavy pointer rotative speed is the slowest, be that swing circle T1 value is maximum, it is slightly fast that vice-minister's time No. 2 heavy heavy pointer rotative speeds weigh pointer rotative speed than No. 1, its swing circle T2 value is less than T1, and T1=n2T2; The 3rd long the triple No. 3 heavy pointer rotative speeds are faster than the speed of No. 2 heavy pointer rotations, and its swing circle T3 is less than T2, and T1=n3T3; No. 4 heavy pointer rotative speeds of the 4th long quadruple are faster again than the speed of No. 3 heavy pointer rotations, and its swing circle T4 is less than T3, and T1=n 4T4; N2, n3, n4 are positive integer, n2< n3< n4, and in order to make aircraft not form repetition curved flight, general No. 1 heavy pointer, in whole curved flight process, only rotates a circle, or rotates two weeks; The gravity of the skew aircraft axis that the weight of each heavy pointer produces in the time of this heavy pointer rotation, enough make aircraft produce a low-angle inclination, thereby make aircraft can occur to become rail flight effect to a side, then can to the flight track of original setting, fly by automatic returning again, but aircraft at extraatmospheric flight curve without the need for too large curve radian, so that aircraft more easily revert to the continuation flight on the pre-flight flight track of curve of doing of original setting, thereby can not make aircraft because departing from flight track do curved flight.
2, in the time that No. 1 heavy pointer does clockwise direction rotation, rotation is left behind the position parallel with aircraft axis, can produce an Action of Gravity Field to the skew of left side, aircraft axis, make aircraft under this Action of Gravity Field, occur a direction to gravity side direction to the left direction tilt a low-angle, along with the angle of No. 1 heavy pointer clickwise increases, the angle that aircraft is tilted to the left also increases gradually, in the time that No. 1 heavy pointer is rotated clockwise to the position vertical with aircraft axis, now heavy pointer produces skew gravity maximum left, the angle that aircraft is tilted to the left is also maximum, along with the continuation clickwise of No. 1 heavy pointer, the skew gravity that No. 1 heavily pointer produces left reduces again gradually, the angle that aircraft is tilted to the left is also reduced gradually, when No. 1 heavy pointer clickwise arrives with aircraft axis again when parallel position, while weighing pointed Vehicle nose No. 1, the skew gravity that heavy pointer produces is zero, the angle that makes aircraft run-off the straight is also zero, in the time that No. 1 heavy pointer continues to do clickwise, the skew gravity direction that the skew gravity direction that No. 1 heavy pointer produces and No. 1 heavy pointer produce when clickwise on the left of aircraft axis is contrary, now No. 1 heavy pointer is made clickwise and is produced skew gravity to the right on right side, aircraft axis, aircraft is tilted to right, along with No. 1 heavy pointer is made right handed angle and is increased gradually, the angle that aircraft is tilted to the right also increases gradually, when No. 1 heavy pointer rotates to aircraft axis for the second time when vertical position, now heavy pointer produces skew gravity maximum to the right, the angle that aircraft is tilted to the right is also maximum, along with the continuation clickwise of No. 1 heavy pointer, the skew gravity that No. 1 heavily pointer produces to the right reduces again gradually, the angle that aircraft is tilted to the right is also reduced gradually, when No. 1 heavy pointer rotation arrives with aircraft axis again when parallel position, when No. 1 heavy pointer comes back to start position, the skew gravity that heavy pointer produces is zero, the angle that makes aircraft run-off the straight is also zero, the time that now No. 1 heavy pointer dextrorotation is circled is the swing circle T1 of No. 1 heavy pointer, other heavy pointers are done simultaneously and are weighed the equidirectional clockwise direction rotation of pointer for No. 1, and the gravity of rotation generation is offset rule and the inclination rule of aircraft generation and the gravity of No. 1 heavy pointer rotation generation are offset to rule with the same to the inclination rule of aircraft generation.
3, in the time that all heavy pointers rotate by the rotative speed of each heavy pointer and swing circle simultaneously, the compound skew gravity producing makes the flight of aircraft skew occur and forming curves flight, there is certain rotation regulation because set each heavy pointer, when all heavy pointers are in setting-up time, rotate after the number of turns separately according to rotative speed and swing circle separately, while getting back to the state of starting point simultaneously, aircraft also just again revert on the flight track originally doing before curved flight and flies, be that aircraft revert on the some point line track between vehicle launch point and target of attack point and flies, and then enter atmospheric envelope target of attack.
The present invention compared with prior art has the following advantages:
1, the present invention can be by the gravity center shift of aircraft inside, make aircraft produce to lopsidedness and make aircraft become rail flight, and do not need the power by adjusting burner oil generation to make aircraft become rail flight, can alleviate aircraft and carry at extraatmospheric fuel.
2, different T1, T2, T3, the T4 parameters of the each heavy pointer of many pointers controller in the present invention, each heavy pointer is rotated with rotative speed separately simultaneously, the compound action power producing makes aircraft form random curvilinear motion, utilize mechanical power control aircraft to form multiple irregular curved flight, make aircraft can not send and accept any signal before entering atmospheric envelope again, thus be difficult for by enemy follow the tracks of interception, the strong electromagnetic that also exempts from enemy destroys.
3, the present invention is by the aircraft of many pointers controller control, increase cost is low, the symmetrical flight curve of controlling of energy, most critical be to make aircraft after the irregular curved flight of making some cycles, can automatic returning to the some point line track between vehicle launch point and the target of attack point of original setting, continue flight.
Brief description of the drawings
Fig. 1 is the schematic diagram of the embodiment of the present invention;
Fig. 2 is middle heavy pointer schematic diagram embodiment illustrated in fig. 1;
Fig. 3 is middle M enlarged diagram embodiment illustrated in fig. 1;
Fig. 4 be embodiment illustrated in fig. 1 in many pointers controller schematic diagram;
Fig. 5 is middle AA section drawing embodiment illustrated in fig. 1.
In Fig. 1-5: 1, Vehicle nose 2, No. 1 heavy pointer 3, annulus 4, No. 3 heavy pointers 5, heavy pointer shaft line 6, many pointers controller 7, No. 2 heavy pointers 8, aircraft body portion 9, aircraft axis 10, aircraft empennage 11, heading 12, annulus left and right axis left end and annulus point of connection B 13, annulus left and right axis 14, axis rear end and annulus point of connection C 15 before and after annulus, axis front end and annulus point of connection A 16 before and after annulus, axis 17 before and after annulus, annulus left and right axis right-hand member and annulus point of connection D 18, three pointer sleeves 19, B3 gear 20, B1 gear 21, B2 gear 22, B axle 23, C1 gear 24, C axle 25, C2 gear 26, D axle 27, D3 gear 28, D1 gear 29, D2 gear 30, F1 gear 31, F2 gear 32, F axle 33, many pointers center sleeve 34, No. 5 heavy pointer ring gears 35, No. 4 heavy pointer ring gears 36, No. 3 heavy pointer ring gears 37, No. 2 heavy pointer ring gears 38, No. 1 heavy pointer ring gear 39, E axle 40, C3 gear 41, E2 gear 42, E1 gear 43, aircraft abdomen 44, the aircraft back of the body 45, aircraft is crossed axis horizontal surface.
Detailed description of the invention
In the embodiment shown in Fig. 1-5: the heavy pointer control in exoatmosphere Curve for Aerocraft center of flying gravity navigationsystem, comprises a set of many pointers controller 6 of controlling with the branched heavy pointer machinery of clock and watch with different length, Different Weight and different rotation rates that is arranged on Vehicle nose 1; It is characterized in that: many pointers controller 6 levels are arranged on Vehicle nose 1 position, and to cross axis horizontal surface 45 parallel with aircraft axis 9 and aircraft, all heavy pointers rotation before all in the position parallel with aircraft axis 9, and all heavy pointers all point to same direction and point to aircraft caudal directions, now the overall weight of aircraft is taking aircraft axis 9 as symmetrical; Many pointers controller 6 is rotative speeds of being controlled the heavy pointer of each clock and watch by machinery, the longest No. 1 the heaviest heavy pointer 2 rotative speeds are the slowest, be that swing circle T1 value is maximum, inferior No. 2 heavy heavy pointer 7 rotative speeds of vice-minister are slightly faster than No. 1 heavy pointer 2 rotative speeds, its swing circle T2 value is less than T1, and T1=n2T2; The speed that the 3rd long the triple No. 3 heavy pointer 4 rotative speeds rotate than No. 2 heavy pointers 7 is faster, and its swing circle T3 is less than T2, and T1=n3T3; The speed that No. 4 heavy pointer rotative speeds of the 4th long quadruple rotate than No. 3 heavy pointers 4 is faster again, and its swing circle T4 is less than T3, and T1=n 4T4; N2, n3, n4 are positive integer, n2< n3< n4, and in order to make aircraft not form repetition curved flight, general No. 1 heavy pointer 2, in whole curved flight process, only rotates a circle, or rotates two weeks; The gravity of the skew aircraft axis 9 that the weight of each heavy pointer produces in the time of this heavy pointer rotation, enough make aircraft produce a low-angle inclination, thereby make aircraft can occur to become rail flight effect to a side, then can to the flight track of original setting, fly by automatic returning again, but aircraft at extraatmospheric flight curve without the need for too large curve radian, so that aircraft more easily revert to the continuation flight on the pre-flight flight track of curve of doing of original setting, thereby can not make aircraft because departing from flight track do curved flight.
In the time that No. 1 heavy pointer 2 does clockwise direction rotation, rotation is left behind the position parallel with aircraft axis 9, can produce an Action of Gravity Field to the 9 left side skews of aircraft axis, make aircraft under this Action of Gravity Field, occur a direction to gravity side direction to the left direction tilt a low-angle, along with the angle of No. 1 heavy pointer 2 clickwises increases, the angle that aircraft is tilted to the left also increases gradually, in the time that No. 1 heavy pointer 2 is rotated clockwise to the position vertical with aircraft axis 9, now heavy pointer produces skew gravity maximum left, the angle that aircraft is tilted to the left is also maximum, along with the continuation clickwise of No. 1 heavy pointer 2, the skew gravity that No. 1 heavy pointer 2 produces left reduces again gradually, the angle that aircraft is tilted to the left is also reduced gradually, when No. 1 heavy pointer 2 clickwise arrive with aircraft axis 9 again when parallel position, when No. 1 heavy pointer 2 points to Vehicle nose 1, the skew gravity that heavy pointer produces is zero, the angle that makes aircraft run-off the straight is also zero, in the time that No. 1 heavy pointer 2 continues to do clickwise, the skew gravity direction that the skew gravity direction that No. 1 heavy pointer 2 produces and No. 1 heavy pointer 2 produce in the time of the 9 left side clickwise of aircraft axis is contrary, now No. 1 heavy pointer 2 is made clickwise and is produced skew gravity to the right on 9 right sides, aircraft axis, aircraft is tilted to right, along with No. 1 heavy pointer 2 is made right handed angle and is increased gradually, the angle that aircraft is tilted to the right also increases gradually, when No. 1 heavy pointer 2 rotates to aircraft axis 9 for the second time when vertical position, now heavy pointer produces skew gravity maximum to the right, the angle that aircraft is tilted to the right is also maximum, along with the continuation clickwise of No. 1 heavy pointer 2, the skew gravity that No. 1 heavy pointer 2 produces to the right reduces again gradually, the angle that aircraft is tilted to the right is also reduced gradually, when No. 1 heavy pointer 2 rotations arrive with aircraft axis 9 again when parallel position, when No. 1 heavy pointer 2 comes back to start position, the skew gravity that heavy pointer produces is zero, the angle that makes aircraft run-off the straight is also zero, the time that now No. 1 heavy pointer 2 dextrorotations are circled is the swing circle T1 of No. 1 heavy pointer 2, other heavy pointers are done and No. 1 equidirectional clockwise direction rotation of heavy pointer 2 simultaneously, and the gravity of rotation generation is offset rule and the inclination rule of aircraft generation is offset to rule and the same to the inclination rule of aircraft generation with the gravity that No. 1 heavy pointer 2 rotations produce, in the time that all heavy pointers rotate by the rotative speed of each heavy pointer and swing circle simultaneously, the compound skew gravity producing makes the flight of aircraft skew occur and forming curves flight, there is certain rotation regulation because set each heavy pointer, when all heavy pointers are in setting-up time, rotate after the number of turns separately according to rotative speed and swing circle separately, while getting back to the state of starting point simultaneously, aircraft also just again revert on the flight track originally doing before curved flight and flies, be that aircraft revert on the some point line track between vehicle launch point and target of attack point and flies, and then enter atmospheric envelope target of attack.
No. 1 heavy pointer 2 makes the direction deflection of aircraft to gravity side direction and inclination because of the effect of the skew gravity that rotation produces, thereby form aircraft and do curve, in the time that No. 1 heavy pointer 2 starts to make clickwise from being parallel to the position of aircraft axis 9 and sensing aircraft afterbody, the rotation of No. 1 heavy pointer 2 produces the gravity that aircraft is offset to the left, this skew gravity makes the aircraft low-angle that is tilted to the left, thereby making aircraft generation become rail left advances, the angle of making clickwise along with No. 1 heavy pointer 2 in 9 left sides, aircraft axis increases, the gravity that aircraft is offset left is also continued to increase, the angle that aircraft tilts to the left also increases gradually, the angle that aircraft becomes rail flight left also increases gradually, in the time that No. 1 heavy pointer 2 rotates to perpendicular to aircraft axis 9 in 9 left sides, aircraft axis as clockwise direction, it is maximum that the angle that now aircraft is tilted to the left reaches, the angle that continues to do clickwise along with No. 1 heavy pointer 2 in 9 left sides, aircraft axis constantly increases, the skew gravity that No. 1 heavy pointer 2 produces left aircraft reduces again gradually, the angle that aircraft is tilted to the left also reduces gradually, when No. 1 heavy pointer 2 continues in 9 left sides, aircraft axis to go to aircraft axis 9 upsides and when parallel with aircraft axis 9 do dextrorotation, now No. 1 heavy pointer 2 points to Vehicle nose 1, and skew gravity is zero, it is also zero that aircraft produces the angle tilting, in the time that No. 1 heavy pointer 2 continues to make clickwise on 9 right sides, aircraft axis, No. 1 heavy pointer 2 produces a skew gravity to the right to aircraft, and make aircraft produce a low-angle tilting to the right, thereby making aircraft generation become rail to the right advances, the anglec of rotation that continues to do on 9 right sides, aircraft axis clickwise along with No. 1 heavy pointer 2 increases, the skew gravity producing to the right also increases gradually, the angle that aircraft is tilted to the right is also increased gradually, the angle that aircraft becomes rail flight to the right also increases gradually, in the time that No. 1 heavy pointer 2 continues to be rotated clockwise to perpendicular to aircraft axis 9 on 9 right sides, aircraft axis, it is maximum that the angle that now aircraft is tilted to the right reaches, the angle that continues to do clickwise along with No. 1 heavy pointer 2 on 9 right sides, aircraft axis constantly increases, the skew gravity that No. 1 heavy pointer 2 produces to the right aircraft reduces again gradually, the angle that aircraft is tilted to the right also reduces gradually, when No. 1 heavy pointer 2 continues on 9 right sides, aircraft axis to go to aircraft axis 9 upsides and when parallel with aircraft axis 9 do dextrorotation, and when No. 1 heavy pointer 2 points to aircraft tail position, this hour offset gravity is zero, it is also zero that aircraft produces the angle tilting, No. 1 heavy pointer 2 revert to rotation start position, be that aircraft revert to No. 1 heavy pointer 2 and does the state of flight before rotating, now the state of flight of aircraft also revert to No. 1 heavy pointer 2 and does to fly on the flight track before clickwise, on the some point line track between vehicle launch point and target of attack point, fly.
Claims (1)
1. the heavy pointer control in exoatmosphere Curve for Aerocraft center of flying gravity navigationsystem, comprises a set of many pointers controller (6) of controlling with the branched heavy pointer machinery of clock and watch with different length, Different Weight and different rotation rates that is arranged on Vehicle nose (1), it is characterized in that: many pointers controller (6) level is arranged on Vehicle nose (1) position, and to cross axis horizontal surface (45) parallel with aircraft axis (9) and aircraft, all heavy pointers rotation before all in the position parallel with aircraft axis (9), and all heavy pointers all point to same direction and point to aircraft caudal directions, now the overall weight of aircraft is taking aircraft axis (9) as symmetrical, many pointers controller (6) is the rotative speed of being controlled the heavy pointer of each clock and watch by machinery, the longest No. 1 the heaviest heavy pointer (2) rotative speed is the slowest, be that swing circle T1 value is maximum, it is slightly fast that vice-minister's time No. 2 heavy heavy pointer (7) rotative speeds weigh pointer (2) rotative speed than No. 1, its swing circle T2 value is less than T1, and T1=n2T2, the speed that the 3rd long No. 3 triple heavy pointer (4) rotative speeds rotate than No. 2 heavy pointers (7) is faster, and its swing circle T3 is less than T2, and T1=n3T3, No. 4 heavy pointer rotative speeds of the 4th long quadruple are faster again than the speed of No. 3 heavy pointers (4) rotation, and its swing circle T4 is less than T3, and T1=n 4T4, n2, n3, n4 are positive integer, n2< n3< n4, and in order to make aircraft not form repetition curved flight, general No. 1 heavy pointer 2, in whole curved flight process, only rotates a circle, or rotates two weeks, the gravity of the skew aircraft axis (9) that the weight of each heavy pointer produces in the time of this heavy pointer rotation, enough make aircraft produce a low-angle inclination, thereby make aircraft can occur to become rail flight effect to a side, then can to the flight track of original setting, fly by automatic returning again, but aircraft at extraatmospheric flight curve without the need for too large curve radian, so that aircraft more easily revert to the continuation flight on the pre-flight flight track of curve of doing of original setting, thereby can not make aircraft because departing from flight track do curved flight, in the time that No. 1 heavy pointer (2) does clockwise direction rotation, rotation is left behind the position parallel with aircraft axis (9), can produce an Action of Gravity Field to the skew of aircraft axis (9) left side, make aircraft under this Action of Gravity Field, occur a direction to gravity side direction to the left direction tilt a low-angle, thereby making aircraft generation become rail left advances, along with the angle of No. 1 heavy pointer (2) clickwise increases, the angle that aircraft is tilted to the left also increases gradually, the angle that aircraft becomes rail flight left also increases gradually, in the time that No. 1 heavy pointer (2) is rotated clockwise to the position vertical with aircraft axis (9), now heavy pointer produces skew gravity maximum left, the angle that aircraft is tilted to the left is also maximum, along with the continuation clickwise of No. 1 heavy pointer (2), the skew gravity that No. 1 heavy pointer (2) produces left reduces again gradually, the angle that aircraft is tilted to the left is also reduced gradually, when No. 1 heavy pointer (2) clickwise arrives with aircraft axis (9) again when parallel position, when No. 1 heavy pointer (2) points to Vehicle nose (1), the skew gravity that heavy pointer produces is zero, the angle that makes aircraft run-off the straight is also zero, in the time that No. 1 heavy pointer (2) continues to do clickwise, the skew gravity direction that the skew gravity direction that No. 1 heavy pointer (2) produces and No. 1 heavy pointer (2) produce when clickwise on the left of aircraft axis (9) is contrary, now No. 1 heavy pointer (2) is made clickwise and is produced skew gravity to the right on right side, aircraft axis (9), aircraft is tilted to right, thereby making aircraft generation become rail to the right advances, along with No. 1 heavy pointer (2) is made right handed angle and is increased gradually, the angle that aircraft is tilted to the right also increases gradually, the angle that aircraft becomes rail flight to the right also increases gradually, when No. 1 heavy pointer (2) rotates to aircraft axis (9) for the second time when vertical position, now heavy pointer produces skew gravity maximum to the right, the angle that aircraft is tilted to the right is also maximum, along with the continuation clickwise of No. 1 heavy pointer (2), the skew gravity that No. 1 heavy pointer (2) produces to the right reduces again gradually, the angle that aircraft is tilted to the right is also reduced gradually, when No. 1 heavy pointer (2) rotation arrives with aircraft axis (9) again when parallel position, when No. 1 heavy pointer (2) comes back to start position, the skew gravity that heavy pointer produces is zero, the angle that makes aircraft run-off the straight is also zero, the time that now No. 1 heavy pointer (2) dextrorotation is circled is the swing circle T1 of No. 1 heavy pointer (2), other heavy pointers are done simultaneously and are weighed the equidirectional clockwise direction rotation of pointer (2) for No. 1, and the gravity of rotation generation is offset rule and the inclination rule of aircraft generation and the gravity of No. 1 heavy pointer (2) rotation generation are offset to rule with the same to the inclination rule of aircraft generation, in the time that all heavy pointers rotate by the rotative speed of each heavy pointer and swing circle simultaneously, the compound skew gravity producing makes the flight of aircraft skew occur and forming curves flight, there is certain rotation regulation because set each heavy pointer, when all heavy pointers are in setting-up time, rotate after the number of turns separately according to rotative speed and swing circle separately, while getting back to the state of starting point simultaneously, aircraft also just again revert on the flight track originally doing before curved flight and flies, be that aircraft revert on the some point line track between vehicle launch point and target of attack point and flies, and then enter atmospheric envelope target of attack.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410044391.7A CN103910073B (en) | 2014-02-05 | 2014-02-05 | The heavy pointer in exoatmosphere controls Curve for Aerocraft center of flying gravity navigationsystem |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410044391.7A CN103910073B (en) | 2014-02-05 | 2014-02-05 | The heavy pointer in exoatmosphere controls Curve for Aerocraft center of flying gravity navigationsystem |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103910073A true CN103910073A (en) | 2014-07-09 |
| CN103910073B CN103910073B (en) | 2015-09-09 |
Family
ID=51036144
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410044391.7A Expired - Fee Related CN103910073B (en) | 2014-02-05 | 2014-02-05 | The heavy pointer in exoatmosphere controls Curve for Aerocraft center of flying gravity navigationsystem |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103910073B (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3965582A (en) * | 1973-08-02 | 1976-06-29 | Krauss-Maffei Aktiengesellschaft | Gunnery practice method and apparatus |
| JPH03296804A (en) * | 1990-04-17 | 1991-12-27 | Kenichi Miya | Gravity direction holding device using balancing pendulum |
| US5228854A (en) * | 1992-07-21 | 1993-07-20 | Teledyne, Inc. | Combat training system and method |
| CN103017746A (en) * | 2012-12-03 | 2013-04-03 | 魏伯卿 | Horologe rotating pointer direction gyroscope for automatically controlling changing curve flight and resetting |
| CN103383213A (en) * | 2013-06-11 | 2013-11-06 | 魏伯卿 | Self-return direction control instrument for changing curvilinear flight of timekeeper rotating pointer |
-
2014
- 2014-02-05 CN CN201410044391.7A patent/CN103910073B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3965582A (en) * | 1973-08-02 | 1976-06-29 | Krauss-Maffei Aktiengesellschaft | Gunnery practice method and apparatus |
| JPH03296804A (en) * | 1990-04-17 | 1991-12-27 | Kenichi Miya | Gravity direction holding device using balancing pendulum |
| US5228854A (en) * | 1992-07-21 | 1993-07-20 | Teledyne, Inc. | Combat training system and method |
| CN103017746A (en) * | 2012-12-03 | 2013-04-03 | 魏伯卿 | Horologe rotating pointer direction gyroscope for automatically controlling changing curve flight and resetting |
| CN103383213A (en) * | 2013-06-11 | 2013-11-06 | 魏伯卿 | Self-return direction control instrument for changing curvilinear flight of timekeeper rotating pointer |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103910073B (en) | 2015-09-09 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103090728B (en) | Tail angle restraining guidance method based on sliding mode control | |
| EP3055641B1 (en) | Fin deployment mechanism for a projectile and method for fin deployment | |
| Wang et al. | Guidance and control design for a class of spin-stabilized projectiles with a two-dimensional trajectory correction fuze | |
| CN112648886B (en) | Combined guidance target intercepting method and system | |
| CN109506878B (en) | Multi-degree-of-freedom mechanism | |
| CN103383213B (en) | Self-return direction control instrument for changing curvilinear flight of timekeeper rotating pointer | |
| Elsaadany et al. | Accuracy improvement capability of advanced projectile based on course correction fuze concept | |
| Theodoulis et al. | Flight dynamics & control for smart munition: the ISL contribution | |
| CN103017746B (en) | Horologe rotating pointer direction gyroscope for automatically controlling changing curve flight and resetting | |
| CN103910073A (en) | Exosphere repetition pointer control aircraft curve flight gravity center navigation system | |
| US3135484A (en) | Control system for annular wing aircraft | |
| RU2272984C1 (en) | Rocket | |
| US9052171B2 (en) | Methods and devices for providing guidance and control of low and high-spin rounds | |
| CN103770952B (en) | Exoatmosphere gravitation ball controls Curve for Aerocraft center of flying gravity navigationsystem | |
| CN203605811U (en) | Electromagnetic-interference prevention clock rotation pointer self-return direction controller | |
| US3341152A (en) | Means for and method of controlling attitude of re-entry vehicle | |
| CN203780811U (en) | Device for controlling aircraft to do curved flight outside atmosphere through gravity ball | |
| Shi et al. | Lateral thrust and aerodynamics compound control system of missile based on adaptive fuzzy control | |
| CN103759589B (en) | Strong current boosting rotation automatic return direction controller for clock rotating needle | |
| Głębocki | Guidance impulse algorithms for air bomb control | |
| RU2199715C2 (en) | Guided missile | |
| Zhang et al. | Optimal guidance law of air to surface missile with terminal impact angle constraint | |
| De et al. | A Multiple Projectiles Weapon System Scheme and Hardware In-the-loop Simulation for Air-defense Rolling Missiles | |
| Li et al. | Virtual Target Based Terminal Guidance Law for Cruise Projectile Considering Impact Angle Constraint | |
| Qi et al. | Bounded differential game guidance law for interceptor with second-order maneuvering dynamics |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20181212 Address after: 225300 Pearl River Road, Yongan Town, Taizhou, Jiangsu Province, 108 Patentee after: Wang Yajun Address before: 314408 304, room 2, 30 shallow water bay, Kashi street, Haining, Jiaxing, Zhejiang. Patentee before: Wei Boqing |
|
| TR01 | Transfer of patent right | ||
| CP02 | Change in the address of a patent holder | ||
| CP02 | Change in the address of a patent holder |
Address after: 273500 University Student Science Park, No. 80 Xiwaihuan Road, Zoucheng City, Jining City, Shandong Province Patentee after: Wang Yajun Address before: 225300 Pearl River Road, Yongan Town, Taizhou, Jiangsu Province, 108 Patentee before: Wang Yajun |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20190723 Address after: 410205 High-tech Industrial Development Zone Bureau of Changsha Administration for Industry and Commerce, Hunan Province Patentee after: Hunan Wei Dao Mdt InfoTech Ltd Address before: 273500 University Student Science Park, No. 80 Xiwaihuan Road, Zoucheng City, Jining City, Shandong Province Patentee before: Wang Yajun |
|
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150909 Termination date: 20210205 |