CN103910073B - The heavy pointer in exoatmosphere controls Curve for Aerocraft center of flying gravity navigationsystem - Google Patents
The heavy pointer in exoatmosphere controls Curve for Aerocraft center of flying gravity navigationsystem Download PDFInfo
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- CN103910073B CN103910073B CN201410044391.7A CN201410044391A CN103910073B CN 103910073 B CN103910073 B CN 103910073B CN 201410044391 A CN201410044391 A CN 201410044391A CN 103910073 B CN103910073 B CN 103910073B
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Abstract
The heavy pointer in exoatmosphere controls Curve for Aerocraft center of flying gravity navigationsystem, comprises a set of with branched many pointers controller with the heavy pointer Mechanical course of clock and watch of different length, Different Weight and different rotation rates; It is characterized in that: many pointers controller level is arranged on Vehicle nose position, and cross axis plane-parallel with aircraft axis and aircraft, all heavy pointers are all in the position with aircraft axis parallel before rotation, and all heavy pointers all point to aircraft caudal directions, now the overall weight of aircraft with aircraft axis for symmetry; When heavy pointer does clockwise direction rotation, an Action of Gravity Field to the skew of side, aircraft axis can be produced, and make aircraft occur one to gravity side to inclination low-angle, thus make aircraft produce the flight of adipping change rail.
Description
Technical field
The present invention relates to the heavy pointer in exoatmosphere and control 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
The epoch of aerospace flight vehicle lead in the development of science and technology are dominated in the U.S. and Russia, what China failed to contend with it always can do curved flight to avoid the aerospace flight vehicle of anti-ballistic attack, nearest report Russia develops a kind of curved flight aerospace flight vehicle not having anti-missile system to attack, but their this controlling curve flight theory is stage casing of namely flying in exoatmosphere utilizes jet application force to carry out the heading of change of flight device, certain jet fuel should be consumed like this, the direction that utilization is navigated and vulnerabilities scan is jet again simultaneously; And often there is unpredictable situation in modern war, such as once war starts, satellite system is destroyed by enemy and loses automatic navigation function, or early can be found by enemy pole by Navigation Control always and be attacked by anti-missile system, another deadly defect of Navigation Control is exactly them is in addition all run by vulnerabilities scan, and this light current is very easily ineffective by the strong electromagnetic of enemy destruction; Preferably there is one that navigation and light current can not be needed to control, and automatically can control not followed the tracks of by electric wave by enemy or not by the device that enemy's strong electromagnetic is destroyed, being unlikely just being blocked at vehicle launch initial stage and mid-term of its curved flight; As everybody knows, from being transmitted into, to lock target of attack actual be exactly a parabola to aircraft, that is be the line of two points of launch point and object point, if there is no anti-missile interception, aircraft does not just need to do curvilinear motion, but in order to avoid anti-missile interception, aircraft must be made to do random curve, do such curve easy, while how making aircraft do curve, aircraft can also be made to reset and get back to launch point with on the originally predetermined some point line track struck target, this is only the most key; The invention of Wei Baiqing " 201310230221.3 clock and watch revolve pin ten thousand varied curve flight self-return direction controlling instrument " solves a difficult problem that curved flight resets, another invention " 201310458435.6 clock and watch revolve pin forceful electric power power-assisted rotational automatic return direction controlling instrument " of Wei Baiqing solves a difficult problem for forceful electric power switching kinetics, and many pointers controller of controlling curve flight time and direction " 201310696350.1 for " of Wei Baiqing then solve difficult problem during machinery control speed control; But these seem and can do curved flight and can automatically reply the control setup that the some point line track that turns back between launch point and object point flies in automatic vehicle stage casing of namely flying in exoatmosphere, cannot realize predetermined object because of not having air in exoatmosphere.
The present invention utilizes Action of Gravity Field change of flight device namely to fly in exoatmosphere the heading in stage casing, make aircraft namely fly in exoatmosphere stage casing by setting track do curved flight, and being set in aircraft reentries before target of attack, aircraft can be made to return to the flight track before doing curve, namely 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, do not need to make any adjustments by navigating direction, realized by many pointers controller setup control, and this setting with control the non-vulnerabilities scan being machinery, aircraft stage casing of namely flying in exoatmosphere so just can be made not launch, also do not receive, more form without burner oil the result that heat is followed the tracks of and vulnerabilities scan causes strong electromagnetic to be destroyed, aircraft is in the exoatmosphere of distance earth's surface about 1000km, and still have the gravity more than 70% compared with earth's surface, therefore, this scheme reaches predetermined object of the present invention surely, the present invention utilizes the invention many pointers controller of controlling curve flight time and direction " 201310696350.1 for " of uncle minister in ancient times Wei, many pointers controller of curved flight is done as setup control aircraft, this many pointers controller can make N number of aircraft have the curved flight of unduplicated N kind, and the aircraft curved flight of section awing can be made also not have any repeatability namely do not have any regularity, thus enemy cannot be tackled to this.
Summary of the invention
The object of this invention is to provide a kind of do not need vulnerabilities scan, controlled to make aircraft center of gravity offset change of flight direction by the heavy pointer of machinery and do curved flight and the heavy pointer in exoatmosphere that the some point line track that aircraft can be made to return between vehicle launch point and target of attack point by the time of setting and flight path flies controls Curve for Aerocraft center of flying gravity navigationsystem.
The heavy pointer in exoatmosphere controls Curve for Aerocraft center of flying gravity navigationsystem, comprises a set of many pointers controller weighing pointer Mechanical course with the branched clock and watch with different length, Different Weight and different rotation rates being arranged on Vehicle nose; It is characterized in that:
1, many pointers controller level is arranged on Vehicle nose position, and cross axis plane-parallel with aircraft axis and aircraft, all heavy pointers are all in the position with aircraft axis parallel before rotation, and all heavy pointers all point to same direction namely points to aircraft caudal directions, now the overall weight of aircraft with aircraft axis for symmetry; Many pointers controller is by the rotative speed of the heavy pointer of each clock and watch of Mechanical course, the longest No. 1 the heaviest heavy pointer rotative speed is the slowest, namely swing circle T1 value is maximum, vice-minister's time No. 2 heavy heavy pointer rotative speeds weigh pointer rotative speed than No. 1 slightly fast, its swing circle T2 value is less than T1, and T1=n2*T2; 3rd long No. 3 triple heavy pointer rotative speeds weigh pointer rotation speed than No. 2 is faster, and its swing circle T3 is less than T2, and T1=n3*T3; No. 4 heavy pointer rotative speeds speed that heavy pointer rotates than No. 3 of the 4th long quadruple is faster again, and its swing circle T4 is less than T3, and T1=n4*T4; 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 weight skew aircraft axis of generation when this heavy pointer rotates of each heavy pointer, aircraft is enough made to produce a low-angle inclination, thus make aircraft can occur to become rail flight effect to side, then can fly to the flight track of original setting by automatic returning again, but aircraft at extraatmospheric flight curve without the need for too large curve radian, fly with the continuation on the pre-flight flight track of curve of doing making aircraft more easily revert to original setting, thus aircraft can not be made to depart from flight track because doing curved flight.
2, when No. 1 heavy pointer does clockwise direction rotation, rotate leave with the position of aircraft axis parallel after, namely an Action of Gravity Field offset on the left of aircraft axis can be produced, make aircraft under this Action of Gravity Field, occur a direction to gravity side direction namely to the left direction to 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, when No. 1 heavy pointer is rotated clockwise to the position vertical with aircraft axis, now heavy pointer generation skew gravity is left maximum, the angle that aircraft is tilted to the left is also maximum, along with the continuation clickwise of No. 1 heavy pointer, No. 1 heavy pointer generation skew gravity left reduces again gradually, the angle that aircraft is tilted to the left also reduces gradually, when No. 1 heavy pointer clickwise arrives the position again parallel with aircraft axis, namely during No. 1 heavy pointed Vehicle nose, the skew gravity that heavy pointer produces is zero, the angle of aircraft run-off the straight is made also to be zero, when No. 1 heavy pointer continues to do clickwise, the skew gravity direction of No. 1 heavy pointer generation is contrary with the skew gravity direction that No. 1 heavy pointer produces during clickwise on the left of aircraft axis, namely now No. 1 heavy pointer is made clickwise and produces skew gravity to the right on the right side of aircraft axis, aircraft right direction is tilted, increase gradually along with No. 1 heavy pointer makes right handed angle, the angle that aircraft is tilted to the right also increases gradually, when No. 1 heavy pointer rotates to the position vertical with aircraft axis second time, now heavy pointer generation skew gravity is to the right maximum, the angle that aircraft is tilted to the right is also maximum, along with the continuation clickwise of No. 1 heavy pointer, No. 1 heavy pointer generation skew gravity to the right reduces again gradually, the angle that aircraft is tilted to the right also reduces gradually, when No. 1 heavy pointer rotation arrives the position again parallel with aircraft axis, namely when No. 1 heavy pointer comes back to start position, the skew gravity that heavy pointer produces is zero, the angle of aircraft run-off the straight is made also to be 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 made the equidirectional clockwise direction of heavy pointer with No. 1 simultaneously and are rotated, and rotate the gravity skew rule that produces and the inclination rule produced aircraft and weigh pointer and rotate the gravity produced with No. 1 to offset rule the same with the inclination rule that produces aircraft.
3, when all heavy pointers press the rotative speed of each heavy pointer and swing circle rotates simultaneously, the skew gravity of the compound produced makes the flight of aircraft occur to offset and forming curves flight, because set each heavy pointer have certain rotation regulation, when all heavy pointers are in setting-up time, after rotating the respective number of turns according to respective rotative speed and swing circle, when getting back to the state of starting point simultaneously, aircraft also just again revert on the flight track before originally doing curved flight and flies, namely the some point line track that aircraft revert between vehicle launch point and target of attack point 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 by the gravity center shift of aircraft interior, aircraft is produced to lopsidedness and makes aircraft become rail flight, and do not need the power produced by adjustment burner oil to make aircraft become rail flight, aircraft can be alleviated and carry at extraatmospheric fuel.
2, T1, T2, T3, T4 parameter that in the present invention, each heavy pointer of many pointers controller is different, each heavy pointer is rotated with respective rotative speed simultaneously, the compound action power produced makes aircraft form random curvilinear motion, namely utilize mechanical power to control aircraft and form multiple irregular curved flight, make aircraft can not send and accept any signal before entering atmospheric envelope again, thus not easily destroyed by the strong electromagnetic that enemy follows the tracks of interception, also exempt from enemy.
3, the aircraft that controlled by many pointers controller of the present invention, increase cost is low, energy is symmetrical controls flight curve, it is crucial that can make aircraft after the irregular curved flight making some cycles, can continue to fly by automatic returning to the some point line track between the vehicle launch point originally set and target of attack point.
Accompanying drawing explanation
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's 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.
Detailed description of the invention
In the embodiment shown in Fig. 1-5: the heavy pointer in exoatmosphere controls Curve for Aerocraft center of flying gravity navigationsystem, comprise a set of be arranged on Vehicle nose 1 with branched many pointers controller 6 with the heavy pointer Mechanical course of clock and watch of different length, Different Weight and different rotation rates; It is characterized in that: many pointers controller 6 level is arranged on Vehicle nose 1 position, and cross axis plane-parallel with aircraft axis 9 and aircraft, all heavy pointers are all in the position parallel with aircraft axis 9 before rotation, and all heavy pointers all point to same direction namely points to aircraft caudal directions, now the overall weight of aircraft is symmetrical with aircraft axis 9; Many pointers controller 6 is by the rotative speed of the heavy pointer of each clock and watch of Mechanical course, the longest No. 1 the heaviest heavy pointer 2 rotative speed is the slowest, namely swing circle T1 value is maximum, secondary No. 2 heavy heavy pointer 7 rotative speeds of vice-minister are slightly faster than No. 1 heavy pointer 2 rotative speed, its swing circle T2 value is less than T1, and T1=n2*T2; The speed that 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=n3*T3; 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=n4*T4; 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 rotate two weeks; The gravity of weight skew aircraft axis 9 of generation when this heavy pointer rotates of each heavy pointer, aircraft is enough made to produce a low-angle inclination, thus make aircraft can occur to become rail flight effect to side, then can fly to the flight track of original setting by automatic returning again, but aircraft at extraatmospheric flight curve without the need for too large curve radian, fly with the continuation on the pre-flight flight track of curve of doing making aircraft more easily revert to original setting, thus aircraft can not be made to depart from flight track because doing curved flight.
When No. 1 heavy pointer 2 does clockwise direction rotation, rotate after leaving the position parallel with aircraft axis 9, namely the Action of Gravity Field of a skew on the left of aircraft axis 9 can be produced, make aircraft under this Action of Gravity Field, occur a direction to gravity side direction namely to the left direction to tilt a low-angle, along with the angle of No. 1 heavy pointer 2 clickwise increases, the angle that aircraft is tilted to the left also increases gradually, when No. 1 heavy pointer 2 is rotated clockwise to the position vertical with aircraft axis 9, now heavy pointer generation skew gravity is left maximum, 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 also reduces gradually, when No. 1 heavy pointer 2 clickwise arrives the position again parallel with aircraft axis 9, namely when No. 1 heavy pointer 2 points to Vehicle nose 1, the skew gravity that heavy pointer produces is zero, the angle of aircraft run-off the straight is made also to be zero, when No. 1 heavy pointer 2 continues to do clickwise, the skew gravity direction of No. 1 heavy pointer 2 generation is contrary with the skew gravity direction that No. 1 heavy pointer 2 produces during clickwise on the left of aircraft axis 9, namely now No. 1 heavy pointer 2 is made clickwise and produces skew gravity to the right on the right side of aircraft axis 9, aircraft right direction is tilted, increase gradually along with No. 1 heavy pointer 2 makes right handed angle, the angle that aircraft is tilted to the right also increases gradually, when No. 1 heavy pointer 2 rotates to the position vertical with aircraft axis 9 second time, now heavy pointer generation skew gravity is to the right maximum, 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 also reduces gradually, when No. 1 heavy pointer 2 rotation arrives the position again parallel with aircraft axis 9, namely when No. 1 heavy pointer 2 comes back to start position, the skew gravity that heavy pointer produces is zero, the angle of aircraft run-off the straight is made also to be 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 made the equidirectional clockwise direction of heavy pointer 2 with No. 1 simultaneously and are rotated, and rotate the gravity skew rule that produces and the inclination rule produced aircraft and No. 1 heavy pointer 2 and rotate the gravity produced to offset rule the same with the inclination rule that produces aircraft, when all heavy pointers press the rotative speed of each heavy pointer and swing circle rotates simultaneously, the skew gravity of the compound produced makes the flight of aircraft occur to offset and forming curves flight, because set each heavy pointer have certain rotation regulation, when all heavy pointers are in setting-up time, after rotating the respective number of turns according to respective rotative speed and swing circle, when getting back to the state of starting point simultaneously, aircraft also just again revert on the flight track before originally doing curved flight and flies, namely the some point line track that aircraft revert between vehicle launch point and target of attack point flies, and then enter atmospheric envelope target of attack.
No. 1 heavy pointer 2 makes aircraft to gravity side direction and the direction deflection of tilting because of the effect rotating the skew gravity produced, thus formation aircraft does curve, namely when No. 1 heavy pointer 2 makes clickwise from being parallel to aircraft axis 9 and point to the position of aircraft afterbody, the rotation of No. 1 heavy pointer 2 produces the gravity that aircraft is offset to the left, this skew gravity makes aircraft be tilted to the left a low-angle, thus make aircraft produce change rail advance left, the angle making clickwise along with No. 1 heavy pointer 2 on the left of aircraft axis 9 increases, the gravity that aircraft is offset left also continues to increase, the angle that aircraft tilts to the left also increases gradually, the angle that aircraft becomes rail flight left also increases gradually, when No. 1 heavy pointer 2 rotates to perpendicular to aircraft axis 9 as clockwise direction on the left of aircraft axis 9, the angle that now aircraft is tilted to the left reaches maximum, the angle continuing to do clickwise along with No. 1 heavy pointer 2 on the left of aircraft axis 9 constantly increases, No. 1 heavy pointer 2 makes aircraft generation skew gravity left reduce gradually again, the angle that aircraft is tilted to the left also reduces gradually, when No. 1 heavy pointer 2 to continue to go to do dextrorotation on the upside of aircraft axis 9 and is parallel with aircraft axis 9 on the left of aircraft axis 9, 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 tilted, when No. 1 heavy pointer 2 continues to make clickwise on the right side of aircraft axis 9, No. 1 heavy pointer 2 produces a skew gravity to the right to aircraft, and make aircraft produce a low-angle tilted to the right, thus make aircraft produce change rail advance to the right, the anglec of rotation continuing to do on the right side of aircraft axis 9 clickwise along with No. 1 heavy pointer 2 increases, the skew gravity produced to the right also increases 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 continues to be rotated clockwise to perpendicular to aircraft axis 9 on the right side of aircraft axis 9, the angle that now aircraft is tilted to the right reaches maximum, the angle continuing to do clickwise along with No. 1 heavy pointer 2 on the right side of aircraft axis 9 constantly increases, No. 1 heavy pointer 2 makes aircraft generation skew gravity to the right reduce gradually again, the angle that aircraft is tilted to the right also reduces gradually, when No. 1 heavy pointer 2 to continue to go to do dextrorotation on the upside of aircraft axis 9 and is parallel with aircraft axis 9 on the right side of aircraft axis 9, and No. 1 heavy pointer 2 is when pointing to aircraft tail position, this hour offset gravity is zero, it is also zero that aircraft produces the angle tilted, No. 1 heavy pointer 2 revert to rotation start position, namely aircraft revert to the heavy pointer 2 with No. 1 and does the state of flight before rotating, now the state of flight of aircraft also revert to No. 1 heavy pointer 2 make clickwise before flight track on fly, namely the some point line track between vehicle launch point and target of attack point flies.
Claims (1)
1. the heavy pointer in exoatmosphere controls Curve for Aerocraft center of flying gravity navigationsystem, comprises a set of many pointers controller (6) weighing pointer Mechanical course with the branched clock and watch with different length, Different Weight and different rotation rates being arranged on Vehicle nose (1), it is characterized in that: many pointers controller (6) level is arranged on Vehicle nose (1) position, and cross axis plane-parallel with aircraft axis (9) and aircraft, all heavy pointers are all in the position parallel with aircraft axis (9) before rotation, and all heavy pointers all point to same direction namely points to aircraft caudal directions, now the overall weight of aircraft is symmetrical with aircraft axis (9), many pointers controller (6) is by the rotative speed of the heavy pointer of each clock and watch of Mechanical course, the longest No. 1 the heaviest heavy pointer (2) rotative speed is the slowest, namely swing circle T1 value is maximum, vice-minister's time No. 2 heavy heavy pointer (7) rotative speeds weigh pointer (2) rotative speed than No. 1 slightly fast, its swing circle T2 value is less than T1, and T1=n2*T2, sooner, its swing circle T3 is less than T2 to 3rd long the triple No. 3 heavy pointer (4) rotative speeds speed that heavy pointer (7) rotates than No. 2, and T1=n3*T3, No. 4 heavy pointer rotative speeds speed that heavy pointer (4) rotates than No. 3 of the 4th long quadruple is faster again, and its swing circle T4 is less than T3, and T1=n4*T4, 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 rotate two weeks, the gravity of weight skew aircraft axis (9) of generation when this heavy pointer rotates of each heavy pointer, aircraft is enough made to produce a low-angle inclination, thus make aircraft can occur to become rail flight effect to side, then can fly to the flight track of original setting by automatic returning again, when No. 1 heavy pointer (2) does clockwise direction rotation, after the position parallel with aircraft axis (9) is left in rotation, namely an Action of Gravity Field to the skew of aircraft axis (9) left side can be produced, make aircraft under this Action of Gravity Field, occur a direction to gravity side direction namely to the left direction to tilt a low-angle, thus make aircraft produce change rail advance left, 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, when No. 1 heavy pointer (2) is rotated clockwise to the position vertical with aircraft axis (9), now heavy pointer generation skew gravity is left maximum, the angle that aircraft is tilted to the left is also maximum, along with the continuation clickwise of No. 1 heavy pointer (2), No. 1 heavy pointer (2) generation skew gravity left reduces again gradually, the angle that aircraft is tilted to the left also reduces gradually, when No. 1 heavy pointer (2) clickwise arrives the position again parallel with aircraft axis (9), namely when No. 1 heavy pointer (2) points to Vehicle nose (1), the skew gravity that heavy pointer produces is zero, the angle of aircraft run-off the straight is made also to be zero, when No. 1 heavy pointer (2) continues to do clickwise, the skew gravity direction that No. 1 heavy pointer (2) produces is contrary with the skew gravity direction that No. 1 heavy pointer (2) produces during clickwise on the left of aircraft axis (9), namely now No. 1 heavy pointer (2) is made clickwise on aircraft axis (9) right side and produces skew gravity to the right, aircraft right direction is tilted, thus make aircraft produce change rail advance to the right, increase gradually along with No. 1 heavy pointer (2) makes right handed angle, 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 the position vertical with aircraft axis (9) second time, now heavy pointer generation skew gravity is to the right maximum, the angle that aircraft is tilted to the right is also maximum, along with the continuation clickwise of No. 1 heavy pointer (2), No. 1 heavy pointer (2) generation skew gravity to the right reduces again gradually, the angle that aircraft is tilted to the right also reduces gradually, when No. 1 heavy pointer (2) rotation arrives the position again parallel with aircraft axis (9), namely when No. 1 heavy pointer (2) comes back to start position, the skew gravity that heavy pointer produces is zero, the angle of aircraft run-off the straight is made also to be zero, now No. 1 time that heavily pointer (2) dextrorotation is circled is No. 1 swing circle T1 weighing pointer (2), other heavy pointers are made heavy pointer (2) the equidirectional clockwise direction with No. 1 simultaneously and are rotated, and rotate the gravity skew rule that produces and the inclination rule produced aircraft and weigh pointer (2) and rotate the gravity produced with No. 1 to offset rule the same with the inclination rule that produces aircraft, when all heavy pointers press the rotative speed of each heavy pointer and swing circle rotates simultaneously, the skew gravity of the compound produced makes the flight of aircraft occur to offset and forming curves flight, namely the some point line track that aircraft revert between vehicle launch point and target of attack point flies, and then enters atmospheric envelope target of attack.
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| 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 |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410044391.7A CN103910073B (en) | 2014-02-05 | 2014-02-05 | The heavy pointer in exoatmosphere controls Curve for Aerocraft center of flying gravity navigationsystem |
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| Publication Number | Publication Date |
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| CN103910073A CN103910073A (en) | 2014-07-09 |
| CN103910073B true CN103910073B (en) | 2015-09-09 |
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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 |
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| Publication number | Publication date |
|---|---|
| CN103910073A (en) | 2014-07-09 |
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