CN103770952A - Gravity navigation system for controlling aircraft to fly in curve through exoatmosphere gravity ball - Google Patents
Gravity navigation system for controlling aircraft to fly in curve through exoatmosphere gravity ball Download PDFInfo
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- CN103770952A CN103770952A CN201410044400.2A CN201410044400A CN103770952A CN 103770952 A CN103770952 A CN 103770952A CN 201410044400 A CN201410044400 A CN 201410044400A CN 103770952 A CN103770952 A CN 103770952A
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Abstract
The invention discloses a gravity navigation system for controlling an aircraft to fly in a curve through an exoatmosphere gravity ball. The system comprises an elliptical support track, an elliptical moving track and a gravity ball fixed on the moving track, wherein a driven belt pulley, a set of motor and a belt are arranged on the lower side of the support track; the driven belt pulley and the set of motor are used for driving the moving track to move; the belt is used for connecting the motor with the driven belt pulley. The system is characterized in that the support track and the moving track are arranged in the head of the aircraft; the moving track and the support track are both of closed elliptical shapes; the moving track is arranged on the upper side of the support track and is overlapped with the support track; the elliptical surfaces of the moving track and the support track are parallel to a horizontal plane formed by a longitudinal symmetry axis of the aircraft and the transverse symmetry axis of the aircraft; an upper support track support rod is arranged between the support track and the moving track; an upper support track support gear is arranged at the upper part of the upper support track support rod; outer gear teeth are formed at the periphery of the upper support track support gear; the outer gear teeth of the upper support track support gear are meshed with chain teeth on the lower side surface of the moving track.
Description
Technical field
The present invention relates to exoatmosphere gravitation ball 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
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 patent of invention " the heavy pointer control in 201410044391.7 exoatmospheres Curve for Aerocraft center of flying gravity navigationsystem " of Wei Baiqing is the invention " 201310696350.1 for controlling many pointers controller of curved flight time and direction " that utilizes uncle minister in ancient times Wei, do many pointers controller of curved flight as setup control aircraft, make the aircraft curved flight of section awing also not there is any repeatability and do not there is any regularity, thereby enemy cannot be tackled this, and the present invention utilizes gravitation ball to move as elliptical path in the front end position of aircraft average rate, with the front end gravity center shift of change of flight device, thereby make aircraft run-off the straight, and then make aircraft form the flight of change rail.
Summary of the invention
The object of this invention is to provide a kind of do not need light current control, by forceful electric power and gravitation ball control make aircraft center of gravity be offset change of flight direction and do curved flight, and the exoatmosphere gravitation ball 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.
Exoatmosphere gravitation ball control Curve for Aerocraft center of flying gravity navigationsystem, comprise an oval-shaped supporting rail, an oval-shaped moving rail, with the gravitation ball being fixed on moving rail, supporting rail downside has a belt that drives the negative pulley wheel that moves of moving rail and a set of motor and connection motor and negative pulley wheel; It is characterized in that:
1, supporting rail and moving rail are arranged on Vehicle nose position, moving rail and supporting rail are the ellipse of composition closed, the ellipse of moving rail and the ellipse of supporting rail are in full accord, and moving rail is at the upside of supporting rail overlapping with supporting rail, the elliptical area of moving rail and supporting rail is parallel with the horizontal surface of aircraft lateral symmetry axle composition with the longitudinal axis of symmetry of aircraft, the transverse of moving rail and supporting rail is parallel with aircraft lateral symmetry axle, and the ellipse short shaft of moving rail and supporting rail is parallel with the longitudinal axis of symmetry of aircraft, between supporting rail and moving rail, have a supporting rail upper support bar, a supporting rail upper support wheel is arranged at the top of supporting rail upper support bar, and supporting rail upper support wheel periphery has the outer gear teeth, and the outer gear teeth of supporting rail upper support wheel are meshed with the sprocket of moving rail downside, under the leftmost side of oval supporting rail, there is a negative pulley wheel, negative pulley wheel is in occupation of the position of a supporting rail upper support wheel, one side of negative pulley wheel has an accessory whorl being fixedly connected with negative pulley wheel concentric and with negative pulley wheel, on accessory whorl, there is external gear, accessory whorl external gear is meshed with the sprocket of moving rail downside, negative pulley wheel is connected with the motor of negative pulley wheel downside by belt, electric machine rotation passes through belt-driving, drive negative pulley wheel and accessory whorl thereof to rotate, the accessory whorl gear teeth are meshed and drive moving rail to move with the sprocket of moving rail 2 downsides, the mobile gravitation ball being fixed on moving rail that drives of moving rail moves, thereby the overall center of gravity that makes Vehicle nose occurs to be offset and to make Vehicle nose that the low-angle of direction inclination to centre-of gravity shift occurs, and then make aircraft occur to become rail flight to the direction tilting.
2, gravitation ball was positioned at the position of the most close aircraft empennage of oval moving rail before movement, i.e. oval moving rail major axis position directly over the longitudinal axis of symmetry of aircraft, and now the overall weight of aircraft is take the longitudinal axis of symmetry of aircraft as symmetrical, in the time that the gravitation ball on driven by motor moving rail does clickwise along oval-shaped moving rail, because gravitation ball is the position of oval moving rail major axis and moving rail joint directly over moving apart the longitudinal axis of symmetry of aircraft, make the longitudinal axis of symmetry of deviation of gravity center aircraft of aircraft and be offset to the left side of the longitudinal axis of symmetry of aircraft, thereby make aircraft that a low-angle inclination occur to the left, and then make the direction that aircraft is tilted to the left become rail flight, along with the gravitation ball clws anglec of rotation increases, the distance of the longitudinal axis of symmetry of deviation of gravity center aircraft of aircraft also increases gradually, the angle that aircraft is tilted to the left also constantly increases, aircraft occurs to become rail flight degree to the direction tilting and also increases gradually, directly over gravitation ball clickwise arrival aircraft lateral symmetry axle time, be that gravitation ball clickwise is while arriving the position of oval moving rail minor axis and moving rail joint, it is maximum that the distance of the longitudinal axis of symmetry of deviation of gravity center aircraft of aircraft reaches, it is maximum that the angle that aircraft is tilted to the left also reaches, aircraft occurs to become rail flight degree to the direction tilting and also reaches maximum, along with gravitation ball continues to be rotated in a clockwise direction, the distance of the longitudinal axis of symmetry of deviation of gravity center aircraft of aircraft also reduces gradually, the angle that aircraft is tilted to the left also constantly reduces, aircraft occurs to become rail flight degree to the direction tilting and also reduces gradually, directly over the longitudinal axis of symmetry of gravitation ball clickwise arrival aircraft time, be that gravitation ball clickwise is while arriving the position of oval moving rail major axis and moving rail joint, the distance of the longitudinal axis of symmetry of deviation of gravity center aircraft of aircraft is zero, the angle of aircraft run-off the straight is also zero, it is also zero that aircraft occurs to become rail flight degree to the direction tilting, now, aircraft revert to gravitation ball and does the state of flight before clickwise, be that aircraft revert on the some point line track between vehicle launch point and target of attack point and flies, in the time that the gravitation ball on driven by motor moving rail continues to do clickwise along oval-shaped moving rail, the center of gravity of aircraft starts again to depart from the longitudinal axis of symmetry of aircraft and is offset to the right side of the longitudinal axis of symmetry of aircraft, thereby make aircraft that a low-angle inclination occur to the right, and then make the direction that aircraft is tilted to the right become rail flight, along with the gravitation ball clws anglec of rotation increases, the distance of the longitudinal axis of symmetry of deviation of gravity center aircraft of aircraft also increases gradually, the angle that aircraft is tilted to the right also constantly increases, aircraft occurs to become rail flight degree to the direction tilting and also increases gradually, directly over gravitation ball clickwise arrival aircraft lateral symmetry axle time, be that gravitation ball clickwise is while arriving the position of oval moving rail minor axis and moving rail joint, it is maximum that the distance of the longitudinal axis of symmetry of deviation of gravity center aircraft of aircraft reaches, it is maximum that the angle that aircraft is tilted to the right also reaches, aircraft occurs to become rail flight degree to the direction tilting and also reaches maximum, along with gravitation ball continues to be rotated in a clockwise direction, the distance of the longitudinal axis of symmetry of deviation of gravity center aircraft of aircraft also reduces gradually, the angle that aircraft is tilted to the right also constantly reduces, aircraft occurs to become rail flight degree to the direction tilting and also reduces gradually, directly over the longitudinal axis of symmetry of gravitation ball clickwise arrival aircraft time, be that gravitation ball clickwise is while reverting to the position of oval moving rail major axis and moving rail joint, the distance of the longitudinal axis of symmetry of deviation of gravity center aircraft of aircraft is zero, the angle of aircraft run-off the straight is also zero, it is also zero that aircraft occurs to become rail flight degree to the direction tilting, now, aircraft again revert to gravitation ball and does the state of flight before clickwise, be that aircraft revert on the some point line track between vehicle launch point and target of attack point and flies.
3, the present invention also has a kind of structure: oval supporting rail and moving rail are arranged on the inclined to one side Vehicle nose in the top position of whole aircraft, the oval long axis length that is supporting rail and moving rail reaches the more than 2/3rds of the longitudinal axis of symmetry length of aircraft, moving rail and supporting rail are the ellipse of composition closed, the ellipse of moving rail and the ellipse of supporting rail are in full accord, and moving rail is at the upside of supporting rail overlapping with supporting rail, the elliptical area of moving rail and supporting rail is parallel with the horizontal surface of aircraft lateral symmetry axle composition with the longitudinal axis of symmetry of aircraft, the ellipse short shaft of moving rail and supporting rail is parallel with aircraft lateral symmetry axle, the transverse of moving rail and supporting rail is parallel with the longitudinal axis of symmetry of aircraft, between supporting rail and moving rail, have a supporting rail upper support bar, a supporting rail upper support wheel is arranged at the top of supporting rail upper support bar, and supporting rail upper support wheel periphery has the outer gear teeth, and the outer gear teeth of supporting rail upper support wheel are meshed with the sprocket of moving rail downside, under the leftmost side of oval supporting rail, there is a negative pulley wheel, negative pulley wheel is in occupation of the position of a supporting rail upper support wheel, one side of negative pulley wheel has an accessory whorl being fixedly connected with negative pulley wheel concentric and with negative pulley wheel, on accessory whorl, there is external gear, accessory whorl external gear is meshed with the sprocket under supporting rail, negative pulley wheel is connected with the motor of negative pulley wheel downside by belt, electric machine rotation passes through belt-driving, drive negative pulley wheel and accessory whorl thereof to rotate, the accessory whorl gear teeth are meshed with the sprocket of supporting rail downside and drive supporting rail to move, the mobile gravitation ball being fixed on moving rail that drives of moving rail moves, thereby the overall center of gravity that makes aircraft occurs to be offset and to make aircraft that the low-angle of direction inclination to centre-of gravity shift occurs, and then make aircraft occur to become rail flight to the direction tilting.
4, the weight of gravitation ball does not need to weigh very much, because only need to make aircraft have certain small angle inclination and make aircraft have a low-angle can realize the curved flight of aircraft to the flight of aircraft direction of tilt change rail.
5, after gravitation ball rotates a circle along oval moving rail, aircraft energy automatic returning is to gravitation ball along oval moving rail rotation heading and state of flight before, and at every turn after gravitation ball rotates a circle along oval moving rail, adjust the rotative speed of the oval moving rail of driven by motor, flight curve that just can change of flight device, make the extra-atmospheric flight stage casing of aircraft between putting from launch point to target of attack without that repeat, irregular curved flight, thereby make enemy cannot tackle in extraatmospheric flight stage casing the attack aircraft of my army's transmitting.
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, by adjusting the rotative speed of the oval moving rail of driven by motor, flight curve that just can change of flight device, make the extra-atmospheric flight stage casing of aircraft between putting from launch point to target of attack without that repeat, irregular curved flight, thereby make enemy cannot tackle in extraatmospheric flight stage casing the attack aircraft of my army's transmitting.
3, the present invention simple in structure, with low cost, can symmetrical control flight curve, 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.
Accompanying drawing explanation
Fig. 1 is the generalized section of the embodiment of the present invention one;
Fig. 2 is schematic top plan view embodiment illustrated in fig. 1;
Fig. 3 is middle M enlarged diagram embodiment illustrated in fig. 1;
Fig. 4 is the schematic side view in embodiment illustrated in fig. 1;
Fig. 5 is middle N enlarged diagram embodiment illustrated in fig. 4;
Fig. 6 is middle P enlarged diagram embodiment illustrated in fig. 5;
Fig. 7 is middle Q enlarged diagram embodiment illustrated in fig. 5;
Fig. 8 is middle centre-of gravity shift schematic diagram embodiment illustrated in fig. 1;
Fig. 9 is the generalized section of the embodiment of the present invention two.
In Fig. 1-9: 1, supporting rail 2, moving rail 3, inclined bearing bar 4, gravitation ball 5, negative pulley wheel 6, belt 7, aircraft vertical axis of symmetry 8, motor 9, the longitudinal axis of symmetry 10 of aircraft, centre bearing bar 11, aircraft abdomen shell 12, aircraft lateral symmetry axle 13, the longitudinal pipe link 14 of supporting rail, Vehicle nose 15, aircraft body portion 16, aircraft empennage 17, supporting rail upper support bar 18, supporting rail upper support wheel 19, supporting rail upper support wheel shaft 20, heeling device lateral symmetry axle 21, heeling device vertical axis of symmetry 22, aircraft leaning angle 23, motor center of gravity is to the vertical distance L2 24 of aircraft vertical axis of symmetry, gravitation ball center of gravity is to the vertical distance L1 25 of heeling device vertical axis of symmetry, aircraft center of gravity 26, cross aircraft center of gravity vertical axis.
The specific embodiment
In the embodiment shown in Fig. 1-9: exoatmosphere gravitation ball control Curve for Aerocraft center of flying gravity navigationsystem, comprise an oval-shaped supporting rail 1, an oval-shaped moving rail 2, with the gravitation ball 4 being fixed on moving rail 2, supporting rail 1 downside has a belt 6 that drives the negative pulley wheel 5 that moves of moving rail 2 and a set of motor 8 and connection motor 8 and negative pulley wheel 5, it is characterized in that: supporting rail 1 and moving rail 2 are arranged on Vehicle nose 14 positions, moving rail 2 is with supporting rail 1 ellipse that forms closed, the ellipse of the ellipse of moving rail 2 and supporting rail 1 is in full accord, and moving rail 2 is at the upside of supporting rail 1 overlapping with supporting rail 1, the elliptical area of moving rail 2 and supporting rail 1 is parallel with the horizontal surface that aircraft lateral symmetry axle 12 forms with the longitudinal axis of symmetry 9 of aircraft, the transverse of moving rail 2 and supporting rail 1 is parallel with aircraft lateral symmetry axle 12, the ellipse short shaft of moving rail 2 and supporting rail 1 is parallel with the longitudinal axis of symmetry 9 of aircraft, between supporting rail 1 and moving rail 2, there is a supporting rail upper support bar 17, a supporting rail upper support wheel 18 is arranged at the top of supporting rail upper support bar 17, supporting rail upper support is taken turns 18 peripheries the outer gear teeth, and the outer gear teeth of supporting rail upper support wheel 18 are meshed with the sprocket of moving rail 2 downsides, under the leftmost side of oval supporting rail 1, there is a negative pulley wheel 5, negative pulley wheel 8 is in occupation of the position of a supporting rail upper support wheel 18, one side of negative pulley wheel 5 have one with negative pulley wheel 5 concentrics and the accessory whorl that is fixedly connected with negative pulley wheel 5, on accessory whorl, there is external gear, accessory whorl external gear is meshed with the sprocket of moving rail 2 downsides, negative pulley wheel 5 is connected with the motor 8 of negative pulley wheel 5 downsides by belt 6, motor 8 rotates by belt 6 transmissions, drive negative pulley wheel 5 and accessory whorl thereof to rotate, the accessory whorl gear teeth are meshed with the sprocket of moving rail 2 downsides and drive moving rail 2 to move, the mobile gravitation ball 4 being fixed on moving rail 2 that drives of moving rail 2 moves, thereby the overall center of gravity that makes Vehicle nose 14 occurs to be offset and to make Vehicle nose 14 that the low-angle of direction inclination to centre-of gravity shift occurs, and then make aircraft occur to become rail flight to the direction tilting.
The present invention also has a kind of structure: oval supporting rail 1 and moving rail 2 are arranged on the inclined to one side Vehicle nose in top 14 positions of whole aircraft, the oval long axis length that is supporting rail 1 and moving rail 2 reaches the more than 2/3rds of longitudinal axis of symmetry 9 length of aircraft, moving rail 2 is with supporting rail 1 ellipse that forms closed, the ellipse of the ellipse of moving rail 2 and supporting rail 1 is in full accord, and moving rail 2 is at the upside of supporting rail 1 overlapping with supporting rail 1, the elliptical area of moving rail 2 and supporting rail 1 is parallel with the horizontal surface that aircraft lateral symmetry axle 12 forms with the longitudinal axis of symmetry 9 of aircraft, the ellipse short shaft of moving rail 2 and supporting rail 1 is parallel with aircraft lateral symmetry axle 12, the transverse of moving rail 2 and supporting rail 1 is parallel with the longitudinal axis of symmetry 9 of aircraft, between supporting rail 1 and moving rail 2, there is a supporting rail upper support bar 17, a supporting rail upper support wheel 18 is arranged at the top of supporting rail upper support bar 17, supporting rail upper support is taken turns 18 peripheries the outer gear teeth, and the outer gear teeth of supporting rail upper support wheel 18 are meshed with the sprocket of moving rail 2 downsides, under the leftmost side of oval supporting rail 1, there is a negative pulley wheel 5, negative pulley wheel 5 is in occupation of the position of a supporting rail upper support wheel 18, one side of negative pulley wheel 5 have one with negative pulley wheel 5 concentrics and the accessory whorl that is fixedly connected with negative pulley wheel 5, on accessory whorl, there is external gear, accessory whorl external gear is meshed with the sprocket under supporting rail 1, negative pulley wheel 5 is connected with the motor 8 of negative pulley wheel 5 downsides by belt 6, motor 8 rotates by belt 6 transmissions, drive negative pulley wheel 5 and accessory whorl thereof to rotate, the accessory whorl gear teeth are meshed with the sprocket of moving rail 2 downsides and drive moving rail 2 to move, the mobile gravitation ball 4 being fixed on moving rail 2 that drives of moving rail 2 moves, thereby the overall center of gravity that makes aircraft occurs to be offset and to make aircraft that the low-angle of direction inclination to centre-of gravity shift occurs, and then make aircraft occur to become rail flight to the direction tilting.
The weight of gravitation ball 4 does not need to weigh very much, because only need to make aircraft have certain small angle inclination and make aircraft have a low-angle can realize the curved flight of aircraft to the flight of aircraft direction of tilt change rail.
After gravitation ball 4 rotates a circle along oval moving rail 2, aircraft energy automatic returning is to gravitation ball 4 along oval moving rail 2 rotations heading and state of flight before, and at every turn after gravitation ball 4 rotates a circle along oval moving rail 2, adjust the rotative speed that motor 8 drives oval moving rail 2, the just flight curve of energy change of flight device, make aircraft from launch point to target of attack point between extra-atmospheric flight stage casing without repeat, irregular curved flight, thereby make enemy cannot tackle in extraatmospheric flight stage casing the attack aircraft of my army's transmitting.
Claims (3)
1. exoatmosphere gravitation ball control Curve for Aerocraft center of flying gravity navigationsystem, comprise an oval-shaped supporting rail (1), an oval-shaped moving rail (2), with the gravitation ball (4) being fixed on moving rail (2), supporting rail (1) downside has one to drive the mobile negative pulley wheel (5) of moving rail (2) and the belt (6) of a set of motor (8) and a connection motor (8) and negative pulley wheel (5), it is characterized in that: supporting rail (1) and moving rail (2) are arranged on Vehicle nose (14) position, moving rail (2) is with supporting rail (1) ellipse that forms closed, the ellipse of the ellipse of moving rail (2) and supporting rail (1) is in full accord, and moving rail (2) is at the upside of supporting rail (1) overlapping with supporting rail (1), the elliptical area of moving rail (2) and supporting rail (1) is parallel with the horizontal surface of aircraft lateral symmetry axle (12) composition with the longitudinal axis of symmetry of aircraft (9), the transverse of moving rail (2) and supporting rail (1) is parallel with aircraft lateral symmetry axle (12), the ellipse short shaft of moving rail (2) and supporting rail (1) is parallel with the longitudinal axis of symmetry of aircraft (9), between supporting rail (1) and moving rail (2), there is a supporting rail upper support bar (17), a supporting rail upper support wheel (18) is arranged at the top of supporting rail upper support bar (17), supporting rail upper support wheel (18) periphery has the outer gear teeth, and the outer gear teeth of supporting rail upper support wheel (18) are meshed with the sprocket of moving rail (2) downside, under the leftmost side of oval supporting rail (1), there is a negative pulley wheel (5), negative pulley wheel (8) is taken turns the position of (18) in occupation of a supporting rail upper support, one side of negative pulley wheel (5) has an accessory whorl being fixedly connected with negative pulley wheel (5) concentric and with negative pulley wheel (5), on accessory whorl, there is external gear, accessory whorl external gear is meshed with the sprocket of moving rail (2) downside, negative pulley wheel (5) is connected with the motor (8) of negative pulley wheel (5) downside by belt (6), motor (8) rotates by belt (6) transmission, drive negative pulley wheel (5) and accessory whorl thereof to rotate, the accessory whorl gear teeth are meshed with the sprocket of moving rail (2) downside and drive moving rail (2) mobile, the mobile gravitation ball (4) being fixed on moving rail (2) that drives of moving rail (2) is mobile, thereby the overall center of gravity that makes Vehicle nose (14) occurs to be offset and to make Vehicle nose (14) that the low-angle of direction inclination to centre-of gravity shift occurs, and then make aircraft occur to become rail flight to the direction tilting, after gravitation ball (4) rotates a circle along oval moving rail (2), heading and state of flight before aircraft energy automatic returning rotates to gravitation ball (4) along oval moving rail (2), and at every turn after gravitation ball (4) rotates a circle along oval moving rail (2), adjust the rotative speed that motor (8) drives oval moving rail (2), the just flight curve of energy change of flight device, make aircraft from launch point to target of attack point between extra-atmospheric flight stage casing without repeat, irregular curved flight, thereby make enemy cannot tackle in extraatmospheric flight stage casing the attack aircraft of my army's transmitting, the weight of gravitation ball (4) does not need to weigh very much, because only need to make aircraft have certain small angle inclination and make aircraft have a low-angle can realize the curved flight of aircraft to the flight of aircraft direction of tilt change rail.
2. exoatmosphere gravitation ball control Curve for Aerocraft center of flying gravity navigationsystem as claimed in claim 1, it is characterized in that: gravitation ball (4) was positioned at the position of the most close aircraft empennage (16) of oval moving rail (2) before movement, i.e. oval moving rail (2) major axis position directly over the longitudinal axis of symmetry of aircraft (9), now the overall weight of aircraft is take the longitudinal axis of symmetry of aircraft (9) as symmetrical, in the time that the gravitation ball (4) on motor (8) drive moving rail (2) does clickwise along oval-shaped moving rail (2), because gravitation ball (4) is the position of oval moving rail (2) major axis and moving rail (2) joint directly over moving apart the longitudinal axis of symmetry of aircraft (9), make the longitudinal axis of symmetry of deviation of gravity center aircraft (9) of aircraft and be offset to the left side of the longitudinal axis of symmetry of aircraft (9), thereby make aircraft that a low-angle inclination occur to the left, and then make the direction that aircraft is tilted to the left become rail flight, along with gravitation ball (4) the clws anglec of rotation increases, the distance of the longitudinal axis of symmetry of deviation of gravity center aircraft (9) of aircraft also increases gradually, the angle that aircraft is tilted to the left also constantly increases, aircraft occurs to become rail flight degree to the direction tilting and also increases gradually, directly over gravitation ball (4) clickwise arrival aircraft lateral symmetry axle (12) time, be that gravitation ball (4) clickwise is while arriving the position of oval moving rail (2) minor axis and moving rail (2) joint, it is maximum that the distance of the longitudinal axis of symmetry of deviation of gravity center aircraft (9) of aircraft reaches, it is maximum that the angle that aircraft is tilted to the left also reaches, aircraft occurs to become rail flight degree to the direction tilting and also reaches maximum, along with gravitation ball (4) continues to be rotated in a clockwise direction, the distance of the longitudinal axis of symmetry of deviation of gravity center aircraft (9) of aircraft also reduces gradually, the angle that aircraft is tilted to the left also constantly reduces, aircraft occurs to become rail flight degree to the direction tilting and also reduces gradually, directly over gravitation ball (4) the clickwise arrival longitudinal axis of symmetry of aircraft (9) time, be that gravitation ball (4) clickwise is while arriving the position of oval moving rail (2) major axis and moving rail (2) joint, the distance of the longitudinal axis of symmetry of deviation of gravity center aircraft (9) of aircraft is zero, the angle of aircraft run-off the straight is also zero, it is also zero that aircraft occurs to become rail flight degree to the direction tilting, now, aircraft revert to gravitation ball (4) and does the state of flight before clickwise, be that aircraft revert on the some point line track between vehicle launch point and target of attack point and flies, in the time that the gravitation ball (4) on motor (8) drive moving rail (2) continues to do clickwise along oval-shaped moving rail (2), the center of gravity of aircraft starts again to depart from the longitudinal axis of symmetry of aircraft (9) and is offset to the right side of the longitudinal axis of symmetry of aircraft (9), thereby make aircraft that a low-angle inclination occur to the right, and then make the direction that aircraft is tilted to the right become rail flight, along with gravitation ball (4) the clws anglec of rotation increases, the distance of the longitudinal axis of symmetry of deviation of gravity center aircraft (9) of aircraft also increases gradually, the angle that aircraft is tilted to the right also constantly increases, aircraft occurs to become rail flight degree to the direction tilting and also increases gradually, directly over gravitation ball (4) clickwise arrival aircraft lateral symmetry axle (12) time, be that gravitation ball (4) clickwise is while arriving the position of oval moving rail (2) minor axis and moving rail (2) joint, it is maximum that the distance of the longitudinal axis of symmetry of deviation of gravity center aircraft (9) of aircraft reaches, it is maximum that the angle that aircraft is tilted to the right also reaches, aircraft occurs to become rail flight degree to the direction tilting and also reaches maximum, along with gravitation ball (4) continues to be rotated in a clockwise direction, the distance of the longitudinal axis of symmetry of deviation of gravity center aircraft (9) of aircraft also reduces gradually, the angle that aircraft is tilted to the right also constantly reduces, aircraft occurs to become rail flight degree to the direction tilting and also reduces gradually, directly over gravitation ball (4) the clickwise arrival longitudinal axis of symmetry of aircraft (9) time, be that gravitation ball (4) clickwise is while reverting to the position of oval moving rail (2) major axis and moving rail (2) joint, the distance of the longitudinal axis of symmetry of deviation of gravity center aircraft (9) of aircraft is zero, the angle of aircraft run-off the straight is also zero, it is also zero that aircraft occurs to become rail flight degree to the direction tilting, now, aircraft again revert to gravitation ball (4) and does the state of flight before clickwise, be that aircraft revert on the some point line track between vehicle launch point and target of attack point and flies.
3. exoatmosphere gravitation ball control Curve for Aerocraft center of flying gravity navigationsystem as claimed in claim 1, it is characterized in that: the present invention also has a kind of structure: oval supporting rail (1) and moving rail (2) are arranged on the inclined to one side Vehicle nose in top (14) position of whole aircraft, the oval long axis length that is supporting rail (1) and moving rail (2) reaches the more than 2/3rds of the longitudinal axis of symmetry of aircraft (9) length, moving rail (2) is with supporting rail (1) ellipse that forms closed, the ellipse of the ellipse of moving rail (2) and supporting rail (1) is in full accord, and moving rail (2) is at the upside of supporting rail (1) overlapping with supporting rail (1), the elliptical area of moving rail (2) and supporting rail (1) is parallel with the horizontal surface of aircraft lateral symmetry axle (12) composition with the longitudinal axis of symmetry of aircraft (9), the ellipse short shaft of moving rail (2) and supporting rail (1) is parallel with aircraft lateral symmetry axle (12), the transverse of moving rail (2) and supporting rail (1) is parallel with the longitudinal axis of symmetry of aircraft (9), between supporting rail (1) and moving rail (2), there is a supporting rail upper support bar (17), a supporting rail upper support wheel (18) is arranged at the top of supporting rail upper support bar (17), supporting rail upper support wheel (18) periphery has the outer gear teeth, and the outer gear teeth of supporting rail upper support wheel (18) are meshed with the sprocket of moving rail (2) downside, under the leftmost side of oval supporting rail (1), there is a negative pulley wheel (5), negative pulley wheel (5) is taken turns the position of (18) in occupation of a supporting rail upper support, one side of negative pulley wheel (5) has an accessory whorl being fixedly connected with negative pulley wheel (5) concentric and with negative pulley wheel (5), on accessory whorl, there is external gear, accessory whorl external gear is meshed with the sprocket under supporting rail (1), negative pulley wheel (5) is connected with the motor (8) of negative pulley wheel (5) downside by belt (6), motor (8) rotates by belt (6) transmission, drive negative pulley wheel (5) and accessory whorl thereof to rotate, the accessory whorl gear teeth are meshed with the sprocket of moving rail (2) downside and drive moving rail (2) mobile, the mobile gravitation ball (4) being fixed on moving rail (2) that drives of moving rail (2) is mobile, thereby the overall center of gravity that makes aircraft occurs to be offset and to make aircraft that the low-angle of direction inclination to centre-of gravity shift occurs, and then make aircraft occur to become rail flight to the direction tilting.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410044400.2A CN103770952B (en) | 2014-02-06 | 2014-02-06 | Exoatmosphere gravitation ball controls Curve for Aerocraft center of flying gravity navigationsystem |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410044400.2A CN103770952B (en) | 2014-02-06 | 2014-02-06 | Exoatmosphere gravitation ball controls Curve for Aerocraft center of flying gravity navigationsystem |
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| Publication Number | Publication Date |
|---|---|
| CN103770952A true CN103770952A (en) | 2014-05-07 |
| CN103770952B CN103770952B (en) | 2015-09-09 |
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| CN201410044400.2A Expired - Fee Related CN103770952B (en) | 2014-02-06 | 2014-02-06 | Exoatmosphere gravitation ball controls Curve for Aerocraft center of flying gravity navigationsystem |
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1746025A1 (en) * | 2005-07-20 | 2007-01-24 | Japan Aerospace Exploration Agency | Method for designing an orbit of a spacecraft |
| US7685722B1 (en) * | 2008-08-22 | 2010-03-30 | Spire Jr Garold Dean | Compact celestial navigation device |
| 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
- 2014-02-06 CN CN201410044400.2A patent/CN103770952B/en not_active Expired - Fee Related
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1746025A1 (en) * | 2005-07-20 | 2007-01-24 | Japan Aerospace Exploration Agency | Method for designing an orbit of a spacecraft |
| US7685722B1 (en) * | 2008-08-22 | 2010-03-30 | Spire Jr Garold Dean | Compact celestial navigation device |
| 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 |
|---|---|
| CN103770952B (en) | 2015-09-09 |
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