CN103017746B - Horologe rotating pointer direction gyroscope for automatically controlling changing curve flight and resetting - Google Patents
Horologe rotating pointer direction gyroscope for automatically controlling changing curve flight and resetting Download PDFInfo
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- CN103017746B CN103017746B CN201210507440.7A CN201210507440A CN103017746B CN 103017746 B CN103017746 B CN 103017746B CN 201210507440 A CN201210507440 A CN 201210507440A CN 103017746 B CN103017746 B CN 103017746B
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Abstract
The invention relates to a horologe rotating pointer direction gyroscope for automatically controlling changing curve flight and resetting. The horologe rotating pointer direction gyroscope comprises a fixed horizontal ring, a horizontal rotating shaft, a hard connecting rod, a gyroscope and three heavy pointers, wherein the horizontal rotating shaft is arranged beyond the circle center point of the horizontal ring, the rotating shaft is fixed on the ring through two bearings so as to freely rotate around the axial line of the rotating shaft; the hard connecting rod is fixedly arranged below the center position of the rotating shaft; the gyroscope is fixedly connected with the lower end of the hard connecting rod; and the three heavy pointers which are different in weight as well as different in length and similar to horologe hour-minute-second pointers and can positively and negatively rotate on a same plane are arranged above the center position of the rotating shaft. The horologe rotating pointer direction gyroscope is characterized in that when one heavy pointer rotates, the rotating heavy pointer enables the rotating shaft to rotate due to the gravity action of the heavy pointer, and because the gyroscope fixedly connected with the hard hard connecting rod is arranged below the center of the rotating shaft, the rotation of the rotating shaft enables the gyroscope and the gyroscope hard connecting rod to rotate together.
Description
Technical field
The present invention relates to the clock and watch automatically controlling ten thousand varied curve flight resets and revolve pin gyroscopic compass, be applicable to comprise the curved flight of all aircraft and the automatic control of reset, belong to science and technology of aviation field.
Background technology
The epoch of guided missile 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 guided missile of anti-ballistic attack, nearest report Russia develops a kind of curved flight guided missile not having anti-missile system to attack, but their this controlling curve flight theory is mainly by navigation, and often there is unpredictable situation in modern war, such as once war starts, satellite system is destroyed by enemy and loses self-navigation function, or early can be found by enemy pole by Navigation Control always and be attacked by anti-missile system; Preferably have one can not need to navigate to control, and can automatically control its curved flight not by the device that enemy is followed the tracks of by electric wave, can be unlikely just being blocked at MISSILE LAUNCHING initial stage and mid-term; As everybody knows, from being transmitted into, to lock target of attack actual be exactly a para-curve to guided missile, that is be the line of two points of launching site and impact point, if there is no anti-missile interception, guided missile does not just need to do curvilinear motion, but in order to avoid anti-missile interception, guided missile must be made to do random curve, do such curve easy, while how making guided missile do curve, guided missile can also be made to reset get back on the originally predetermined some point line track struck target, this is only the most key; The present invention is exactly that what address this problem is again preferably the simplest way.
Summary of the invention
The object of this invention is to provide a kind of can not need to control by navigation can do complex curve flight and the clock and watch that automatic control ten thousand varied curve flown from launching site to the some point line track the struck target flight that makes guided missile get back to initial setting of automatically reseting again resets revolve pin gyroscopic compass by robot.
Structure of the present invention is on a fixing horizontal circular ring, cross the rotating shaft that annulus centre point installs a level, rotating shaft is fixed on annulus by two bearings, this root rotating shaft can freely be rotated by axial line around the shaft, at below, the center (i.e. the centre point of annulus) of a rotating shaft fixed installation hard connecting rod, the lower end of hard connecting rod is fixedly connected with a gyro, at the heavy pointer that can do positive and negative rotation in same plane that the Hour Minute Second pointer of top, the center (i.e. the centre point of annulus) of rotating shaft installation three samples different in size its weight certain also different similar to Clock and Watch is the same, when three heavy pointers are all with shaft parallel and on the upside of the rotating shaft being overlapped in the same side, the center of circle of annulus, now gyro and the hard connecting rod of gyro because of Action of Gravity Field in vertical position, the position of heavy pointer now and rotating shaft and the gyro be attached thereto and the hard connecting rod of gyro is set as the initial points of three heavy pointers and rotating shaft and gyro and the hard connecting rod of gyro.
When a heavy pointer rotates, rotate heavy pointer due to weight pointer Action of Gravity Field rotating shaft is rotated, but because be fixedly connected with a gyro by hard connecting rod below spindle central, so the rotation of rotating shaft also makes to rotate together with the hard connecting rod of gyro of gyro and connection gyro, its detailed process is: when a heavy pointer rotates, the heavy pointer rotated makes rotating shaft rotate, and the angle to rotate along with this heavy pointer increases, the angle that rotating shaft rotates also increases thereupon, when this heavy pointer rotates to vertical with rotating shaft first time from initial point, rotating shaft rotates and reaches maximum angle, with pointer continuation rotation emphatically, the anglec of rotation of rotating shaft diminishes again gradually, when heavy pointer rotate to first time overlapping with rotating shaft time, the vanishing i.e. rotating shaft but also get back to initial point again of the anglec of rotation of its rotating shaft, then with pointer continuation rotation emphatically, rotating shaft rotates to direction contrary before this, and angle also becomes large gradually, when heavy pointer rotates to again with rotating shaft second time plumbness, rotating shaft also reaches maximum in the reciprocal anglec of rotation, and with positive dirction, to rotate the maximum angle reached completely the same, after heavy pointer continues rotation again, the anglec of rotation of rotating shaft diminishes again gradually, until when heavy pointer gets back to initial point, also vanishing and rotating shaft also get back to initial point to the anglec of rotation of rotating shaft, heavy pointer from initial point rotate to rotating shaft first time the overlapping rotating shaft anglec of rotation that rotating shaft is rotated with the relation curve of this heavy pointer anglec of rotation, from continuing rotation with rotating shaft first time lap position, to get back to the relation curve of initial point (namely this heavy pointer is overlapping with rotating shaft for the second time) rotating shaft the is occurred rotating shaft anglec of rotation that opposite direction rotates and this heavy pointer anglec of rotation identical with heavy pointer, that is, heavy pointer is in the process of rotating a circle, and in the overall process that rotating shaft one sideway swivel makes rotating shaft rotate, to rotate at rotating shaft opposite side the overall process that rotating shaft is rotated just the same with this heavy pointer, but the anglec of rotation is contrary, in like manner, when three heavy pointers rotate with different rotational speeies simultaneously, rotating shaft can be made equally to do the rotation of certain angle, certainly, this rotates is three coefficient results of heavy pointer, the sense of rotation of three heavy pointers can be identical, also can be different, the rule of three heavy pointer rotational speeies should meet: in the time that the longest No. 1 the heaviest heavy pointer rotates a circle, No. 2 heavy pointers of vice-minister rotate m week, the shortest No. 3 heavy pointers rotate n week, wherein m, n are integer, three heavy pointers rotate under such rotational speed condition simultaneously just can accomplish that three heavy pointers can get back to initial point after rotating simultaneously, and makes rotating shaft get back to initial point.
Aircraft is when awing there is certain inclination angle in wing, aircraft will be made to turn to the direction of wing dropping, that is, when the wing of aircraft is tilted to the left, aircraft is just turned left, when the wing of aircraft is tilted to the right, aircraft just bends to right, and when aircraft is flying at a constant speed period, when the angle that its wing is tilted to the left is identical with the time with time and the angle be tilted to the right, it is the same that aircraft is turned with the camber line bent to right left, in other words, after the wing of aircraft is tilted to the left the flight regular hour with certain angle, be tilted to the right with same angle again and fly the identical time, aircraft will after a camber line flight, get back to original heading.Equally, the wing of aircraft also can be made when aircraft is turned to the left or to the right to occur and consistent angular slope to the left or to the right of turning.
Utilize above principle, when three of gyroscopic compass of the present invention heavy pointers rotate by we, make the signal transmission of the rotation of rotating shaft and gyro and gyro hard connecting rod generation certain angle to the flank of aircraft or controlling party to empennage to control the turning of aircraft, that is, if utilize gyroscopic compass of the present invention heavy pointer to rotate the heading controlling aircraft, when a heavy pointer starts to rotate, drive the rotation of rotating shaft, this signal transmission to control aircraft turning empennage and make aircraft start turn, when this heavy pointer rotate to first time vertical with rotating shaft time, the angle that aircraft is turned reaches maximum, when this heavy pointer continues rotate and drive rotating shaft to rotate, the anglec of rotation of rotating shaft diminishes gradually, namely the angle of turn of aircraft also diminishes gradually, until this heavy pointer rotates to overlapping with rotating shaft for the first time, the anglec of rotation vanishing of rotating shaft, the now angle of turn of aircraft also vanishing, namely the heading before the heading of aircraft makes it turn with this heavy pointer is consistent, but flight track is not now on original flight track, when this heavy pointer continues rotate and drive rotating shaft to rotate in the opposite direction, aircraft is also rotated by the opposite direction of rotating shaft and makes it turn in the opposite direction, and its angle of turn also becomes large gradually along with the continuation of this heavy pointer rotates the angle making rotating shaft rotate in the opposite direction, thus make aircraft also gradually become large to the angle of turning in the other direction, this heavy pointer rotate to second time vertical with rotating shaft time, the anglec of rotation second time of rotating shaft reaches maximum, it transmits and makes aircraft reach maximum to the angle of turning also second time in the other direction, when this heavy pointer rotate get back to initial point and the anglec of rotation of rotating shaft diminished gradually also get back to initial point time, the angle of turn of aircraft also diminishes gradually, the heading of last aircraft when initial point is got back in rotating shaft and this heavy pointer rotate make aircraft turn before heading consistent, and the rotation that the flight track of aircraft has also been got back to because of this heavy pointer makes on the flight track before aircraft turning.
The clock and watch that automatic control ten thousand varied curve flight resets revolve pin gyroscopic compass, comprise a fixing horizontal circular ring and cross the rotating shaft that annulus centre point installs a level, rotating shaft is fixed on annulus by two bearings, this root rotating shaft can freely be rotated by axial line around the shaft, at below, the center (i.e. the centre point of annulus) of a rotating shaft fixed installation hard connecting rod, the lower end of hard connecting rod is fixedly connected with a gyro, at the heavy pointer that can do positive and negative rotation in same plane that the Hour Minute Second pointer of top, the center (i.e. the centre point of annulus) of rotating shaft installation three samples different in size its weight certain also different similar to Clock and Watch is the same, it is characterized in that:
1, when a heavy pointer rotates, rotate heavy pointer due to weight pointer Action of Gravity Field rotating shaft is rotated, but because be fixedly connected with a gyro by hard connecting rod below spindle central, so the rotation of rotating shaft also makes to rotate together with the hard connecting rod of gyro of gyro and connection gyro, its detailed process is: when a heavy pointer rotates, the heavy pointer rotated makes rotating shaft rotate, and the angle to rotate along with this heavy pointer increases, the angle that rotating shaft rotates also increases thereupon, when this heavy pointer rotates to vertical with rotating shaft first time from initial point, rotating shaft rotates and reaches maximum angle, with pointer continuation rotation emphatically, the anglec of rotation of rotating shaft diminishes again gradually, when heavy pointer rotate to first time overlapping with rotating shaft time, the vanishing i.e. rotating shaft but also get back to initial point again of the anglec of rotation of its rotating shaft, then with pointer continuation rotation emphatically, rotating shaft rotates to direction contrary before this, and angle also becomes large gradually, when heavy pointer rotates to again with rotating shaft second time plumbness, rotating shaft also reaches maximum in the reciprocal anglec of rotation, and with positive dirction, to rotate the maximum angle reached completely the same, after heavy pointer continues rotation again, the anglec of rotation of rotating shaft diminishes again gradually, until when heavy pointer gets back to initial point, also vanishing and rotating shaft also get back to initial point to the anglec of rotation of rotating shaft, heavy pointer from initial point rotate to rotating shaft first time the overlapping rotating shaft anglec of rotation that rotating shaft is rotated with the relation curve of this heavy pointer anglec of rotation, from continuing rotation with rotating shaft first time lap position, to get back to the relation curve of initial point (namely this heavy pointer is overlapping with rotating shaft for the second time) rotating shaft the is occurred rotating shaft anglec of rotation that opposite direction rotates and this heavy pointer anglec of rotation identical with heavy pointer, that is, heavy pointer is in the process of rotating a circle, and in the overall process that rotating shaft one sideway swivel makes rotating shaft rotate, to rotate at rotating shaft opposite side the overall process that rotating shaft is rotated just the same with this heavy pointer, but the anglec of rotation is contrary, in like manner, when three heavy pointers rotate with different rotational speeies simultaneously, rotating shaft can be made equally to do the rotation of certain angle, certainly, this rotates is three coefficient results of heavy pointer, the sense of rotation of three heavy pointers can be identical, also can be different, the rule of three heavy pointer rotational speeies should meet: in the time that the longest No. 1 the heaviest heavy pointer rotates a circle, No. 2 heavy pointers of vice-minister rotate m week, the shortest No. 3 heavy pointers rotate n week, wherein m, n are integer, three heavy pointers rotate under such rotational speed condition simultaneously just can accomplish that three heavy pointers can get back to initial point after rotating simultaneously, and makes rotating shaft get back to initial point.
2, when three heavy pointers are rotated, make the signal transmission of the rotation of rotating shaft and gyro and gyro hard connecting rod generation certain angle to the flank of aircraft or controlling party to empennage to control the turning of aircraft, rotate by a heavy pointer simply and rotating shaft is rotated and its rotating signal is controlled aircraft turning to describe in detail: when a heavy pointer starts to rotate, drive the rotation of rotating shaft, this signal transmission to control aircraft turning empennage and make aircraft start turn, when this heavy pointer rotate to first time vertical with rotating shaft time, the angle that aircraft is turned reaches maximum, when this heavy pointer continues rotate and drive rotating shaft to rotate, the anglec of rotation of rotating shaft diminishes gradually, namely the angle of turn of aircraft also diminishes gradually, until this heavy pointer rotates to overlapping with rotating shaft for the first time, the anglec of rotation vanishing of rotating shaft, the now angle of turn of aircraft also vanishing, namely the heading before the heading of aircraft makes it turn with this heavy pointer is consistent, but flight track is not now on original flight track, when this heavy pointer continues rotate and drive rotating shaft to rotate in the opposite direction, aircraft is also rotated by the opposite direction of rotating shaft and makes it turn in the opposite direction, and its angle of turn also becomes large gradually along with the continuation of this heavy pointer rotates the angle making rotating shaft rotate in the opposite direction, thus make aircraft also gradually become large to the angle of turning in the other direction, this heavy pointer rotate to second time vertical with rotating shaft time, the anglec of rotation second time of rotating shaft reaches maximum, it transmits and makes aircraft reach maximum to the angle of turning also second time in the other direction, when this heavy pointer rotate get back to initial point and the anglec of rotation of rotating shaft diminished gradually also get back to initial point time, the angle of turn of aircraft also diminishes gradually, and the last heading of aircraft when initial point is got back in rotating shaft, with this heavy pointer rotate make aircraft turn before heading consistent, and the rotation that the flight track of aircraft has also been got back to because of this heavy pointer makes on the flight track before aircraft turning, three heavy pointers rotate with different rotational speeies, they make a concerted effort rotating shaft is rotated, its rotation will become more complicated, the curve of the aircraft making it control becomes more irregular, but we are easy to the rotational speed designing, control three heavy pointers, thus make enemy cannot find out the flight rule of our aircraft and carry out anti-missile interception.
3, in practical operation, can according to device of the present invention, design a set of model, and related law, parameter and mathematical formulae are imported wherein, just compiled program can insert flight control, and the rotational speed of pre-designed three heavy pointers after aircraft takeoff and rule, thus the function the same with actual device of the present invention can be realized, automatically can do changeable irregular curve by the parameter of setting to control aircraft, but finally its multiple regression can be struck target to the flight track of setting by the condition of setting again.
4, heavy pointer can use two, also can be added to multiple, and heavy pointer uses more, and the flight curve of its aircraft just becomes more complicated does not more have rule, the more difficult tracking of enemy, interception.
The present invention compared with prior art has the following advantages:
1, the present invention can by presetting the parameters such as the rotational speed of three heavy pointers and period of change, makes aircraft can by the irregular polytropic curve flight of one, thus enemy cannot be got clear and tackle our aircraft.
2, volume of the present invention is little, purposes is wide, cost is low, symmetrically can control flight curve.
Accompanying drawing explanation
Fig. 1 is the structural representation of the embodiment of the present invention;
Fig. 2 is schematic top plan view embodiment illustrated in fig. 1;
Fig. 3 is middle A-A diagrammatic cross-section embodiment illustrated in fig. 1;
Fig. 4 is middle B-B diagrammatic cross-section embodiment illustrated in fig. 1.
In Fig. 1-4: 1, the heavy pointer of No. 2,1, rotating shaft 3, No. 3 heavy pointers 4, semi-disc 5, gyro 6, gyro connecting link 7, semi-disc connecting link 8, pointer shaft 9, No. 2 heavy pointers 10, annulus 11, bearing 12, headings.
Embodiment
In the embodiment shown in Fig. 1-4: the clock and watch automatically controlling ten thousand varied curve flight resets revolve pin gyroscopic compass, comprise a fixing horizontal circular ring 10 and cross the rotating shaft 1 that annulus 10 centre point installs a level, rotating shaft 1 is fixed on annulus 10 by two bearings 11, make this root rotating shaft 1 can around the shaft 1 axial line freely rotate, at below, the center (i.e. the centre point of annulus 10) of a rotating shaft 1 fixed installation hard connecting rod 6, the lower end of hard connecting rod 6 is fixedly connected with a gyro 5, at the heavy pointer that can do positive and negative rotation in same plane that the Hour Minute Second pointer of top, the center (i.e. the centre point of annulus 10) of rotating shaft 1 installation three samples different in size its weight certain also different similar to Clock and Watch is the same, it is characterized in that:
1, when a heavy pointer rotates, the heavy pointer rotated makes rotating shaft 1 rotate due to the Action of Gravity Field of heavy pointer, but because rotating shaft 1 central lower is fixedly connected with a gyro 5 by hard connecting rod, so the rotation of rotating shaft 1 also makes to rotate together with the hard connecting rod 6 of gyro of gyro 5 and connection gyro 5, its detailed process is: when a heavy pointer rotates, the heavy pointer rotated makes rotating shaft 1 rotate, and the angle to rotate along with this heavy pointer increases, the angle that rotating shaft 1 rotates also increases thereupon, when this heavy pointer rotates to vertical with rotating shaft 1 first time from initial point, rotating shaft 1 rotates and reaches maximum angle, with pointer continuation rotation emphatically, the anglec of rotation of rotating shaft 1 diminishes again gradually, when heavy pointer rotate to first time overlapping with rotating shaft 1 time, the vanishing i.e. rotating shaft 1 but also get back to initial point again of the anglec of rotation of its rotating shaft 1, then with pointer continuation rotation emphatically, rotating shaft 1 rotates to direction contrary before this, and angle also becomes large gradually, when heavy pointer rotates to again with rotating shaft 1 second time plumbness, rotating shaft 1 also reaches maximum in the reciprocal anglec of rotation, and with positive dirction, to rotate the maximum angle reached completely the same, after heavy pointer continues rotation again, the anglec of rotation of rotating shaft 1 diminishes again gradually, until when heavy pointer gets back to initial point, also vanishing and rotating shaft 1 also get back to initial point to the anglec of rotation of rotating shaft 1, heavy pointer rotates to the relation curve with rotating shaft 1 first time overlapping rotating shaft 1 anglec of rotation and this heavy pointer anglec of rotation that make rotating shaft 1 rotate from initial point, and from continuing rotation with rotating shaft 1 first time lap position, to get back to the relation curve of initial point (namely this heavy pointer is overlapping with rotating shaft for the second time) rotating shaft 1 is occurred rotating shaft 1 anglec of rotation that opposite direction rotates and this heavy pointer anglec of rotation identical with heavy pointer, that is, heavy pointer is in the process of rotating a circle, and in the overall process that rotating shaft 1 one sideway swivel makes rotating shaft 1 rotate, to rotate at rotating shaft 1 opposite side the overall process that rotating shaft 1 is rotated just the same with this heavy pointer, but the anglec of rotation is contrary, in like manner, when three heavy pointers rotate with different rotational speeies simultaneously, three heavy pointers rotating shaft 1 can be made equally to do the rotation of certain angle with joint efforts, certainly, this rotation is three coefficient results of weight pointer, the sense of rotation of three heavy pointers can be identical, also can be different, the rule of three heavy pointer rotational speeies should meet: in the time that the longest No. 1 the heaviest heavy pointer 2 rotates a circle, No. 2 heavy pointers 9 of vice-minister rotate m week, the shortest No. 3 heavy pointers 3 rotate n week, wherein m, n are positive integer, three heavy pointers rotate under such rotational speed condition simultaneously just can accomplish that three heavy pointers can get back to initial point after rotating simultaneously, and makes rotating shaft 1 get back to initial point.
2, when three heavy pointers are rotated, the signal transmission making rotating shaft 1 and gyro 5 and gyro hard connecting rod 6 that the rotation of certain angle occur to the flank of aircraft or controlling party to empennage to control the turning of aircraft, rotate by a heavy pointer simply and rotating shaft 1 is rotated and its rotating signal is controlled aircraft turning to describe in detail: when a heavy pointer starts to rotate, drive the rotation of rotating shaft 1, this signal transmission to control aircraft turning empennage and make aircraft start turn, when this heavy pointer rotate to first time vertical with rotating shaft 1 time, the angle that aircraft is turned reaches maximum, when this heavy pointer continues rotate and drive rotating shaft 1 to rotate, the anglec of rotation of rotating shaft 1 diminishes gradually, namely the angle of turn of aircraft also diminishes gradually, until this heavy pointer rotates to overlapping with rotating shaft 1 for the first time, the anglec of rotation vanishing of rotating shaft 1, the now angle of turn of aircraft also vanishing, namely the heading before the heading of aircraft makes it turn with this heavy pointer is consistent, but flight track is not now on original flight track, when this heavy pointer continues rotate and drive rotating shaft 1 to rotate in the opposite direction, aircraft is also rotated by the opposite direction of rotating shaft 1 and makes it turn in the opposite direction, and its angle of turn also becomes large gradually along with the continuation of this heavy pointer rotates the angle making rotating shaft 1 rotate in the opposite direction, thus make aircraft also gradually become large to the angle of turning in the other direction, this heavy pointer rotate to second time vertical with rotating shaft 1 time, the anglec of rotation second time of rotating shaft 1 reaches maximum, it transmits and makes aircraft reach maximum to the angle of turning also second time in the other direction, when this heavy pointer rotate get back to initial point and the anglec of rotation of rotating shaft 1 diminished gradually also get back to initial point time, the angle of turn of aircraft also diminishes gradually, and the last heading of aircraft when initial point is got back in rotating shaft 1, with this heavy pointer rotate make aircraft turn before heading consistent, and the rotation that the flight track of aircraft has also been got back to because of this heavy pointer makes on the flight track before aircraft turning, three heavy pointers rotate with different rotational speeies, they make a concerted effort rotating shaft 1 is rotated, its rotation will become more complicated, the curve of the aircraft making it control becomes more irregular, but we are easy to the rotational speed designing, control three heavy pointers, thus make enemy cannot find out the flight rule of our aircraft and carry out anti-missile interception.
3, in practical operation, can according to device of the present invention, design a set of model, and related law, parameter and mathematical formulae are imported wherein, just compiled program can insert flight control, and the rotational speed of pre-designed three heavy pointers after aircraft takeoff and rule, thus the function the same with actual device of the present invention can be realized, automatically can do changeable irregular curve by the parameter of setting to control aircraft, but finally its multiple regression can be struck target to the flight track of setting by the condition of setting again.
Claims (3)
1. the clock and watch automatically controlling ten thousand varied curve flight resets revolve pin gyroscopic compass, comprise a fixing horizontal circular ring (10) and cross the rotating shaft (1) that annulus (10) centre point installs a level, rotating shaft (1) is fixed on annulus (10) by two bearings (11), this root rotating shaft (1) can the axial line of (1) around the shaft freely be rotated, below, center (i.e. the centre point of an annulus) fixed installation hard connecting rod (6) of rotating shaft (1), the lower end of hard connecting rod (6) is fixedly connected with a gyro (5), the heavy pointer that can do positive and negative rotation in same plane that the Hour Minute Second pointer of three samples different in size its weight also different similar to Clock and Watch is certainly the same is installed in the top, center (i.e. the centre point of annulus 10) of rotating shaft (1), it is characterized in that: when a heavy pointer rotates, rotate heavy pointer due to weight pointer Action of Gravity Field rotating shaft (1) is rotated, but because rotating shaft (1) central lower is fixedly connected with a gyro (5) by hard connecting rod (6), so the rotation of rotating shaft (1) also makes to rotate together with the hard connecting rod of gyro (6) of gyro (5) and connection gyro (5), its detailed process is: when a heavy pointer rotates, the heavy pointer rotated makes rotating shaft (1) rotate, and the angle to rotate along with this heavy pointer increases, the angle that rotating shaft (1) rotates also increases thereupon, when this heavy pointer rotates to vertical with rotating shaft (1) first time from initial point, rotating shaft (1) rotates and reaches maximum angle, with pointer continuation rotation emphatically, the anglec of rotation of rotating shaft (1) diminishes again gradually, when heavy pointer rotate to first time overlapping with rotating shaft (1) time, the vanishing i.e. rotating shaft (1) but also get back to initial point again of the anglec of rotation of its rotating shaft (1), then with pointer continuation rotation emphatically, rotating shaft (1) rotates to direction contrary before this, and angle also becomes large gradually, when heavy pointer rotates to again with rotating shaft (1) second time plumbness, rotating shaft (1) also reaches maximum in the reciprocal anglec of rotation, and with positive dirction, to rotate the maximum angle reached completely the same, after heavy pointer continues rotation again, the anglec of rotation of rotating shaft (1) diminishes again gradually, until when heavy pointer gets back to initial point, also vanishing and rotating shaft (1) also get back to initial point to the anglec of rotation of rotating shaft (1), heavy pointer rotates to the relation curve of rotating shaft (1) anglec of rotation that rotating shaft (1) rotated overlapping with rotating shaft (1) first time and this heavy pointer anglec of rotation from initial point, and from continuing rotation with rotating shaft (1) first time lap position, to get back to the relation curve of initial point (namely this heavy pointer is overlapping with rotating shaft for the second time) rotating shaft (1) is occurred rotating shaft (1) anglec of rotation that opposite direction rotates and this heavy pointer anglec of rotation identical with heavy pointer, that is, heavy pointer is in the process of rotating a circle, in the overall process that rotating shaft (1) sideway swivel makes rotating shaft (1) rotate, to rotate at rotating shaft (1) opposite side the overall process that rotating shaft (1) is rotated just the same with this heavy pointer, but the anglec of rotation is contrary, in like manner, when three heavy pointers rotate with different rotational speeies simultaneously, three heavy pointers rotating shaft (1) can be made equally to do the rotation of certain angle with joint efforts, certainly, this rotation is three and weighs the coefficient results of pointer, the sense of rotation of three heavy pointers can be identical, also can be different, the rule of three heavy pointer rotational speeies should meet: in the time that the longest No. 1 the heaviest heavy pointer (2) rotates a circle, No. 2 heavy pointers (9) of vice-minister rotate m week, the shortest No. 3 heavy pointers (3) rotate n week, wherein m, n are positive integer, three heavy pointers rotate under such rotational speed condition simultaneously just can accomplish that three heavy pointers can get back to initial point after rotating simultaneously, and makes rotating shaft (1) get back to initial point.
2. the clock and watch automatically controlling ten thousand varied curve flight resets as claimed in claim 1 revolve pin gyroscopic compass, it is characterized in that: when three heavy pointers are rotated, the signal transmission making rotating shaft (1) and gyro (5) and the hard connecting rod of gyro (6) that the rotation of certain angle occur to the flank of aircraft or controlling party to empennage to control the turning of aircraft, rotate by a heavy pointer simply and rotating shaft (1) is rotated and its rotating signal is controlled aircraft turning to describe in detail: when a heavy pointer starts to rotate, drive the rotation of rotating shaft (1), this signal transmission to control aircraft turning empennage and make aircraft start turn, when this heavy pointer rotate to first time vertical with rotating shaft (1) time, the angle that aircraft is turned reaches maximum, when this heavy pointer continues rotate and drive rotating shaft (1) to rotate, the anglec of rotation of rotating shaft (1) diminishes gradually, namely the angle of turn of aircraft also diminishes gradually, until this heavy pointer rotates to overlapping with rotating shaft (1) for the first time, the anglec of rotation vanishing of rotating shaft (1), the now angle of turn of aircraft also vanishing, namely the heading before the heading of aircraft makes it turn with this heavy pointer is consistent, but flight track is not now on original flight track, when this heavy pointer continues rotate and drive rotating shaft (1) to rotate in the opposite direction, aircraft is also rotated by the opposite direction of rotating shaft (1) and makes it turn in the opposite direction, and its angle of turn also becomes large gradually along with the continuation of this heavy pointer rotates the angle making rotating shaft (1) rotate in the opposite direction, thus make aircraft also gradually become large to the angle of turning in the other direction, this heavy pointer rotate to second time vertical with rotating shaft (1) time, the anglec of rotation second time of rotating shaft (1) reaches maximum, it transmits and makes aircraft reach maximum to the angle of turning also second time in the other direction, when this heavy pointer rotate get back to initial point and the anglec of rotation of rotating shaft (1) diminished gradually also get back to initial point time, the angle of turn of aircraft also diminishes gradually, the heading of last aircraft when initial point is got back in rotating shaft (1) and this heavy pointer rotate make aircraft turn before heading consistent, and the rotation that the flight track of aircraft has also been got back to because of this heavy pointer makes on the flight track before aircraft turning, three heavy pointers rotate with different rotational speeies, they make a concerted effort rotating shaft (1) is rotated, its rotation will become more complicated, the curve of the aircraft making it control becomes more irregular, as long as but the rotational speed of design, the heavy pointers of control three, enemy just can be made cannot to find out the flight rule of our aircraft and carry out anti-missile interception.
3. the clock and watch automatically controlling ten thousand varied curve flight resets as claimed in claim 1 revolve pin gyroscopic compass, it is characterized in that: in practical operation, according to device of the present invention, design a set of model, and by related law, parameter and mathematical formulae import wherein, just compiled program can insert flight control, and the rotational speed of pre-designed three heavy pointers after aircraft takeoff and rule, thus the function the same with actual device of the present invention can be realized, automatically changeable irregular curve can be done by the parameter of setting to control aircraft, but finally its multiple regression can be struck target to the flight track of setting by the condition of setting again.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210507440.7A CN103017746B (en) | 2012-12-03 | 2012-12-03 | Horologe rotating pointer direction gyroscope for automatically controlling changing curve flight and resetting |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210507440.7A CN103017746B (en) | 2012-12-03 | 2012-12-03 | Horologe rotating pointer direction gyroscope for automatically controlling changing curve flight and resetting |
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| CN103017746A CN103017746A (en) | 2013-04-03 |
| CN103017746B true CN103017746B (en) | 2015-02-18 |
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| CN103383213B (en) * | 2013-06-11 | 2015-03-18 | 魏伯卿 | Self-return direction control instrument for changing curvilinear flight of timekeeper rotating pointer |
| CN103759589B (en) * | 2013-10-02 | 2015-04-22 | 魏伯卿 | Strong current boosting rotation automatic return direction controller for clock rotating needle |
| CN103759586B (en) * | 2013-12-18 | 2015-11-04 | 魏伯卿 | For many pointers controller in controlling curve flight time and direction |
| CN103910073B (en) * | 2014-02-05 | 2015-09-09 | 魏伯卿 | The heavy pointer in exoatmosphere controls Curve for Aerocraft center of flying gravity navigationsystem |
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| CN103017746A (en) | 2013-04-03 |
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