CN104192311B - A kind of finishing bevel gear cuter push-down Vehicle nose deflection driven device - Google Patents
A kind of finishing bevel gear cuter push-down Vehicle nose deflection driven device Download PDFInfo
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- CN104192311B CN104192311B CN201410431751.9A CN201410431751A CN104192311B CN 104192311 B CN104192311 B CN 104192311B CN 201410431751 A CN201410431751 A CN 201410431751A CN 104192311 B CN104192311 B CN 104192311B
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Abstract
The invention discloses a kind of finishing bevel gear cuter push-down Vehicle nose deflection driven device, comprise supporting mechanism, actuating unit, bevel-type reversing gear, jointed gear unit, head and be rotationally connected arm mechanism, aircraft Tou Ti bindiny mechanism; Actuating unit, bevel-type reversing gear and aircraft Tou Ti bindiny mechanism are fixed on the base of supporting mechanism, actuating unit arranges along body axis, and jointed gear unit promotes head and be rotationally connected arm mechanism to rotate around the bulb in the spherical sleeve of supporting mechanism; When Vehicle nose's shell deflects, aircraft computer sends signal, actuating unit receives control signal, actuating unit drives bevel-type reversing gear to rotate, convert rotational motion is the straight-line motion of jointed gear unit by bevel-type reversing gear, head and be rotationally connected arm mechanism and rotate round spherical sleeve, realizes Vehicle nose's deflection.Deflection driven apparatus structure is simple, compact, is specially adapted to small aircraft.
Description
Technical field
The present invention relates to a kind of Vehicle nose deflection driven device, specifically, relate to a kind of finishing bevel gear cuter push-down Vehicle nose deflection driven device.
Background technology
Vehicle nose's deflection control device, that Vehicle nose's relative flight device fuselage deflects certain angle to any direction, Vehicle nose produces corresponding aerodynamic force, the i.e. control effort of aircraft, thus produce the control torque of relative flight device barycenter, aircraft is made to produce corresponding attitude angle, the motor-driven overload of final generation.Vehicle nose's deflection control device can realize aircraft and move in driftage and pitch channel.
In technical literature disclosed at present, there is Four types in deflection driven mechanism of Vehicle nose: piezoelectric ceramic type, magnetostriction type, liquid (gas) pressure type and rotating sloping disk type.
Piezoelectric ceramic type: the development effort of Americana " pipe is penetrated Intelligent Compression deflection and adapted to ammunition " (BLAM) adopts piezoceramic deflection driven mechanism to realize the deflection of head.It is configured with many piezoceramic rods at aircraft interior, sets around body interval.Piezoceramic rod almost with aircraft fuselage axis being parallel, their length can change according to the change of suffered pressure, Vehicle nose is deflected, obtains good aerodynamic characteristic.
Magnetostriction type: Americana " magnetic deformation missile guidance systems " (MMGS) utilizes movable " droop-snoot " to design aircraft guidance system.A spherical hinge adapter and one group of magnetic telescopic driver composition deflection driven mechanism.Magnetostrictive rod that three performances are identical (or the magnetostrictive rod that four identical, be separated by 90 ° and place) in aircraft fuselage around the placement of 120 °, body interval, sensor can judge the angle of " droop-snoot " required deflection, thus produces the control effort of change of flight device flight path.
Liquid (gas) pressure type: three hydraulic telescopic machanisms are separated by 120 ° and are arranged (or four hydraulic telescopic machanisms be separated by 90 ° arrange), and with tripod turret and bottom support bracket hinged, tripod turret is connected with three-legged support by spherical linkage.When hydraulic telescopic machanism is all in non-retracted position, Vehicle nose is in undeflected state.When Vehicle nose needs to deflect, air craft carried computing machine is to hydraulic telescopic machanism transfer instruction, make three hydraulic telescopic machanisms by extending or shortening certain distance, drive tripod turret to rotate, make Vehicle nose deflect into the position of needs.Fluid pressure type mechanism is described in document " design of bullet deflection machanism and simulation analysis " (Northwestern Polytechnical University's 2012 Master degree candidate's thesis).
Rotating sloping disk type: the Perenosniy Zenitniy Raketniy Kompleks (MANPADS) of Britain is a kind of small-sized, light Perenosniy Zenitniy Raketniy Kompleks pickaback.Aircraft afterbody has four orthogonal balancing planes, does not have traditional rudder face.The deflection driven mechanism of Vehicle nose is made up of two relatively turnable swash plates, and each swashplate angle is 2 degree, is connected by bearing.Swash plate rotates through two rare-earth permanent magnet motors and drives, and the angle of Vehicle nose's deflection is determined according to autopilot instruction.Rotating sloping disk type mechanism is described in document " simulation study of inclined disc type deflection machanism scheme " (" Computer Simulation ", the 2008,25th volume the 10th phase: 23-26).
Piezoelectric ceramic type and magnetostriction type material construction very expensive, and the deformation produced is smaller, needs comparatively complicated enlarger, also requires very strict usage condition.Liquid (gas), although pressure type deflection driven mechanism can provide larger moment, needs subsidiary gas, liquid structure, and larger by the impact of ambient temperature; Rotating sloping disk type, easily cause the coupling in Vehicle nose's deflection situation, and the lateral overload that can carry is smaller.
Summary of the invention
In order to avoid the deficiency that prior art exists, the present invention proposes a kind of finishing bevel gear cuter push-down Vehicle nose deflection driven device.
The technical solution adopted for the present invention to solve the technical problems is: comprise supporting mechanism, actuating unit, bevel-type reversing gear, jointed gear unit, head and be rotationally connected arm mechanism, aircraft Tou Ti bindiny mechanism, actuating unit, bevel-type reversing gear and aircraft Tou Ti bindiny mechanism are fixed on the base of supporting mechanism, two cover actuating units arrange along body axis, and jointed gear unit promotes head and be rotationally connected arm mechanism to rotate around the bulb in the spherical sleeve of supporting mechanism; When Vehicle nose's shell deflection, aircraft computer sends signal, actuating unit receives control signal, actuating unit drives bevel-type reversing gear to rotate, convert rotational motion is the straight-line motion of jointed gear unit by bevel-type reversing gear, head and be rotationally connected arm mechanism and rotate around spherical sleeve, realize the angle of inclination of positive and negative 15 degree of Vehicle nose, head is at deflection 0 ~ 360 degree, azimuth intrinsic deflection;
Described supporting mechanism comprises base, the first sleeve pedestal, the second sleeve pedestal, spherical sleeve, first sleeve pedestal, the second sleeve pedestal and spherical sleeve connection, wherein, first sleeve pedestal supports as the center of turn of the first lever, second sleeve pedestal supports as the center of turn of the second lever, and the bulb in spherical sleeve is as the ball pivot heart being rotationally connected arm;
Described bevel-type reversing gear comprises master bevel gear assembly, from bevel gear assembly, rack plate, base support, master bevel gear assembly comprises master bevel gear clutch shaft bearing, master bevel gear axle, master bevel gear gear, master bevel gear second bearing, comprises from finishing bevel gear cuter clutch shaft bearing from bevel gear assembly, from finishing bevel gear cuter second bearing, from bevel gear shaft, from finishing bevel gear cuter gear, master bevel gear assembly and be fixed on rack plate from bevel gear assembly, on base support, to partner bevel-type reversing gear from bevel gear assembly and master bevel gear assembly, convert rotational motion is the straight-line motion of jointed gear unit by bevel-type reversing gear, master bevel gear assembly is respectively the first bevel gear assembly and the second bevel gear assembly, is respectively first from bevel gear assembly from bevel gear assembly, second from bevel gear assembly, 3rd from bevel gear assembly and the 4th from bevel gear assembly, first actuating unit of actuating unit is connected with the first master bevel gear assembly, second actuating unit is connected with the second master bevel gear assembly, first bevel gear assembly engages from bevel gear assembly from bevel gear assembly and the 3rd with first, and the second bevel gear assembly engages from bevel gear assembly from bevel gear assembly and the 4th with second,
Described jointed gear unit comprises first group of jointed gear unit, second group of jointed gear unit, the first push rod, the 3rd push rod, the second push rod, the 4th push rod, first push rod and the 3rd push rod form by the second push rod, in the first push rod, under the first push rod, and the second push rod and the 4th push rod form by the second push rod, under the second push rod; First group of jointed gear unit is made up of the first push rod, the 3rd push rod, ball pivot cap, the first lever, rotating shaft, nut, the first side wall push rod and the 3rd sidewall push rod, and second group of jointed gear unit is made up of the second push rod, the 4th push rod, the second lever, rotating shaft, nut, the second sidewall push rod and the 4th sidewall push rod; In bevel-type reversing gear, first engages from the cylindrical wheel bevel gear assembly with the first side wall push rod, 3rd engages from the cylindrical wheel bevel gear assembly with the 3rd sidewall push rod, the first side wall push rod and the 3rd sidewall push rod promote the first lever rotation by rotating shaft and nut, are connected between the first lever and the first push rod, the 3rd push rod by ball pivot cap; In bevel-type reversing gear, second engages from the cylindrical wheel bevel gear assembly with the second sidewall push rod, 4th engages from the cylindrical wheel bevel gear assembly with the 4th sidewall push rod, second sidewall push rod and the 4th sidewall push rod promote the second lever rotation by rotating shaft and nut, are connected between the second lever and the first push rod, the 3rd push rod by ball pivot cap;
Be rotationally connected arm mechanism to comprise head shell, erecting equipment plate, be rotationally connected arm, be rotationally connected arm fixture block, two be rotationally connected arm, two be rotationally connected arm fixture block and be connected, the bulb be rotationally connected in the spherical sleeve of arm mechanism in supporting mechanism rotates, be rotationally connected arm and be rotationally connected between arm fixture block and form ball pivot groove, head shell be rotationally connected arm and be connected, erecting equipment plate be rotationally connected arm and be connected.
Beneficial effect
The finishing bevel gear cuter push-down Vehicle nose deflection driven device that the present invention proposes, can realize the maximum angle of inclination reaching positive and negative 15 degree of Vehicle nose, and head is at deflection azimuth 0-360 ° intrinsic deflection.Learn according to the simulation analysis of static system characteristic and dynamic characteristics, deflection driven device can realize given Vehicle nose's angle of inclination exactly, and meets the requirement of flying vehicles control to its rapidity.
Simply, the components and parts of use are conventional components and parts for the structure of finishing bevel gear cuter push-down Vehicle nose of the present invention deflection driven device and principle of work, are conducive to the expense reducing flying vehicles control scheme; By appropriate design deflection machanism, larger Vehicle nose's angle of inclination can be obtained; Structure can bear larger axial force, and carrying side force is functional; Device adopts motor-driven mode, easy for installation, compact, and structure is simple, is applicable to small aircraft, does not need subsidiary gas, liquid structure; Device connects structure and adopts motor drive mode can install in less space, and speed of response is very fast compared with fluid pressure type structure; Motor diameter and aircraft diameter close, can make full use of aircraft exhibition to space.
Accompanying drawing explanation
Below in conjunction with drawings and embodiments, a kind of finishing bevel gear cuter push-down of the present invention Vehicle nose deflection driven device is described in further detail.
Fig. 1 is birds-eye view and the cutaway view hatching position view of deflection driven device of the present invention.
Fig. 2 a, Fig. 2 b, Fig. 2 c are deflection driven device schematic diagram of the present invention.
Fig. 3 a, Fig. 3 b are the bevel-type reversing gear schematic diagram of deflection driven device of the present invention.
Fig. 4 is the jointed gear unit schematic diagram of deflection driven device of the present invention.
Fig. 5 is the head of deflection driven device of the present invention and is rotationally connected arm mechanism schematic diagram.
In figure:
1. the spherical sleeve 4. of head shell 2. erecting equipment plate 3. is rotationally connected arm 5. and is rotationally connected on arm fixture block 6. second push rod under 7. second push rods in 8. first push rods under 9. first push rods 10. ball pivot cap 11. corrugated shell 12. second sleeve pedestal 13. first sleeve pedestal 14. second lever 15. first lever 16. rotating shaft 17. nut 18. the first side wall push rod 19. second sidewall push rod 20. the 3rd sidewall push rod 21. the 4th sidewall push rod 22. servomotor 23. drop-gear box 24. base 25. rack plate 26. base support 27. master bevel gear clutch shaft bearing 28. master bevel gear axle 29. master bevel gear gear 30. master bevel gear second bearings 31. from finishing bevel gear cuter clutch shaft bearing 32. from finishing bevel gear cuter second bearing 33. from bevel gear shaft 34. from finishing bevel gear cuter gear 35. linear bearing bracing frame 36. linear bearing
Detailed description of the invention
The present embodiment is a kind of finishing bevel gear cuter push-down Vehicle nose deflection driven device.
Consult Fig. 1 ~ Fig. 5, the present embodiment finishing bevel gear cuter push-down Vehicle nose deflection driven device, by supporting mechanism, actuating unit, bevel-type reversing gear, jointed gear unit, head and be rotationally connected arm mechanism and aircraft Tou Ti bindiny mechanism forms; Supporting mechanism comprises base 24, first sleeve pedestal 13, second sleeve pedestal 12 and spherical sleeve 3; Be connected by screw between first sleeve pedestal 13, second sleeve pedestal 12 and spherical sleeve 3, wherein the first sleeve pedestal 13 supports as the heart that turns of the first lever 15, second sleeve pedestal 12 supports as the heart that turns of the second lever 14, and the bulb in spherical sleeve 3 is as the ball pivot heart being rotationally connected arm 4.Actuating unit, bevel-type reversing gear and aircraft Tou Ti bindiny mechanism are arranged on the base 24 in supporting mechanism.Actuating unit has two covers, and often cover comprises servomotor 22 and drop-gear box 23, and servomotor 22 output shaft is connected by screw with drop-gear box 23, and drop-gear box 23 is arranged on the base 24 of supporting mechanism; Be respectively the first actuating unit and the second actuating unit, two cover actuating units arrange along aircraft body axis.Bevel-type reversing gear comprise rack plate 25, base support 26, master bevel gear clutch shaft bearing 27, master bevel gear axle 28, master bevel gear gear 29, master bevel gear second bearing 30, from finishing bevel gear cuter clutch shaft bearing 31, from finishing bevel gear cuter second bearing 32, from bevel gear shaft 33, from finishing bevel gear cuter gear 34, master bevel gear assembly comprises master bevel gear clutch shaft bearing 27, master bevel gear axle 28, master bevel gear gear 29, master bevel gear second bearing 30, comprise from finishing bevel gear cuter clutch shaft bearing 31, from finishing bevel gear cuter second bearing 32, from bevel gear shaft 33, from finishing bevel gear cuter gear 34 from bevel gear assembly, to partner bevel-type reversing gear from bevel gear assembly and master bevel gear assembly, convert rotational motion is the straight-line motion of jointed gear unit by bevel-type reversing gear, directly a cylindrical wheel is processed from bevel gear shaft 33, the first side wall push rod 18 from the cylindrical wheel drivening rod transmission device bevel gear shaft 33, second sidewall push rod 19, 3rd sidewall push rod 20, 4th sidewall push rod 21, composition rack-and-gear revolute pair, the rotation of vertical flight device body axis is converted into the straight-line motion being parallel to aircraft body axis, master bevel gear assembly and be fixed on rack plate 25 from bevel gear assembly, on base support 26.Wherein master bevel gear assembly has two, is respectively the first bevel gear assembly and the second bevel gear assembly, has four from bevel gear assembly, is respectively first from bevel gear assembly, second from bevel gear assembly, the 3rd from bevel gear assembly and the 4th from bevel gear assembly.First actuating unit of actuating unit is connected with the first master bevel gear assembly, and the second actuating unit is connected with the second master bevel gear assembly.First bevel gear assembly and first to be formed from bevel gear assembly and the 3rd from bevel gear assembly and engages, and the second bevel gear assembly and second to be formed from bevel gear assembly and the 4th from bevel gear assembly and engages.Jointed gear unit by under the 8, first push rod in the 7, first push rod under the 6, second push rod on the second push rod 9, ball pivot cap 10, second lever 14, first lever 15, rotating shaft 16, nut 17, the first side wall push rod 18, second sidewall push rod 19, the 3rd sidewall push rod 20 and the 4th sidewall push rod 21 form, wherein 9 composition the first push rods and the 3rd push rods under the 8, first push rod in the 6, first push rod on the second push rod, the second push rod forms the second push rod and the 4th push rod under the 6, second push rod.First push rod, the 3rd push rod, ball pivot cap 10, first lever 15, rotating shaft 16, nut 17, the first side wall push rod 18 and the 3rd sidewall push rod 20 form first group of jointed gear unit, and the second push rod, the 4th push rod, the second lever 14, rotating shaft 16, nut 17, second sidewall push rod 19 and the 4th sidewall push rod 21 form second group of jointed gear unit.In bevel-type reversing gear, first to be formed with the first side wall push rod 18 from the cylindrical wheel bevel gear assembly and engages, 3rd to be formed with the 3rd sidewall push rod 20 from the cylindrical wheel bevel gear assembly and engages, the first side wall push rod 18 and the 3rd sidewall push rod 20 promote the first lever 15 by rotating shaft 16 and nut 17 and rotate round turning the heart, the rotation of the first lever 15 drives the first push rod and the 3rd push rod to be parallel to the straight-line motion of aircraft body axis, is connected between the first lever 15 and the first push rod, the 3rd push rod by ball pivot cap 10.In bevel-type reversing gear, second to be formed with the second sidewall push rod 19 from the cylindrical wheel bevel gear assembly and engages, 4th to be formed with the 4th sidewall push rod 21 from the cylindrical wheel bevel gear assembly and engages, second sidewall push rod 19 and the 4th sidewall push rod 21 promote the second lever 14 by rotating shaft 16 and nut 17 and rotate round turning the heart, the rotation of the second lever 14 drives the second push rod and the 4th push rod to be parallel to the straight-line motion of aircraft body axis, is connected between the second lever 14 and the first push rod, the 3rd push rod by ball pivot cap 10.Jointed gear unit by bevel-type reversing gear from bevel gear assembly the rotation of cylindrical wheel transform into the straight-line motion being parallel to aircraft head axis of four push rods.Head and be rotationally connected arm mechanism and comprise head shell 1, erecting equipment plate 2, be rotationally connected arm 4 and be rotationally connected arm fixture block 5 and form, two are rotationally connected 4, two, arm and are rotationally connected arm fixture block 5 and are fixed into by bolt as a whole, head and be rotationally connected arm mechanism around in the spherical sleeve 3 in supporting mechanism bulb rotate, be rotationally connected arm 4 and be rotationally connected between arm fixture block 5 and form ball pivot groove, head shell 1 be rotationally connected arm 4 and be connected by screw, erecting equipment plate 2 by bolt be rotationally connected arm 4 and be connected.The first push rod in jointed gear unit, the second push rod, the 3rd push rod, the 4th push rod rotate promoting head and being rotationally connected arm mechanism around the bulb of the spherical sleeve 3 in supporting mechanism, the deflection of promotion head shell 1.Aircraft Tou Ti bindiny mechanism comprises corrugated shell 11, corrugated shell 11 is connected by screw with base 24 and Vehicle nose's shell 1, it ensures that head shell 1 respect thereto 24 deflects, and ensureing the surface having a relative smooth between head shell 1 and base 24, corrugated shell 11 plays the effect that restriction head shell 1 reverses simultaneously.
When head shell 1 angle of inclination of aircraft are 0 ° and deflection azimuth is 0 °, servomotor 19 is in initial condition, when in head shell 1 angle of inclination or deflection azimuth of aircraft one be not 0 ° time, then claim motor to be in deflection state.
For the head shell 1 of aircraft from angle of inclination be 0 ° and deflection azimuth be 0 ° deflect into angle of inclination be 15 ° and deflection azimuth be 120 °, when servomotor 19 is in initial condition, head shell 1 deflection angle is 0 ° and deflection azimuth is 0 °, when the head shell 1 of aircraft needs to deflect, aircraft computer sends signal, actuating unit receives control signal, actuating unit drives master bevel gear axle 28 to rotate, convert rotational motion is the straight-line motion of jointed gear unit by bevel-type reversing gear, push rod Vehicle nose and be rotationally connected arm mechanism and rotate round spherical sleeve 3, realizing Vehicle nose 19, to reach angle of inclination be 15 °, and deflection azimuth is 120 ° of states.
Claims (1)
1. a finishing bevel gear cuter push-down Vehicle nose deflection driven device, it is characterized in that: comprise supporting mechanism, actuating unit, bevel-type reversing gear, jointed gear unit, head and be rotationally connected arm mechanism, aircraft Tou Ti bindiny mechanism, actuating unit, bevel-type reversing gear and aircraft Tou Ti bindiny mechanism are fixed on the base of supporting mechanism, two cover actuating units arrange along body axis, and jointed gear unit promotes head and be rotationally connected arm mechanism to rotate around the bulb in the spherical sleeve of supporting mechanism; When Vehicle nose's shell deflection, aircraft computer sends signal, actuating unit receives control signal, actuating unit drives bevel-type reversing gear to rotate, convert rotational motion is the straight-line motion of jointed gear unit by bevel-type reversing gear, head and be rotationally connected arm mechanism and rotate around spherical sleeve, realize the angle of inclination of positive and negative 15 degree of Vehicle nose, head is at deflection 0 ~ 360 degree, azimuth intrinsic deflection;
Described supporting mechanism comprises base, the first sleeve pedestal, the second sleeve pedestal, spherical sleeve, first sleeve pedestal, the second sleeve pedestal and spherical sleeve connection, wherein, first sleeve pedestal supports as the center of turn of the first lever, second sleeve pedestal supports as the center of turn of the second lever, and the bulb in spherical sleeve is as the ball pivot heart being rotationally connected arm;
Described bevel-type reversing gear comprises master bevel gear assembly, from bevel gear assembly, rack plate, base support, master bevel gear assembly comprises master bevel gear clutch shaft bearing, master bevel gear axle, master bevel gear gear, master bevel gear second bearing, comprises from finishing bevel gear cuter clutch shaft bearing from bevel gear assembly, from finishing bevel gear cuter second bearing, from bevel gear shaft, from finishing bevel gear cuter gear, master bevel gear assembly and be fixed on rack plate from bevel gear assembly, on base support, to partner bevel-type reversing gear from bevel gear assembly and master bevel gear assembly, convert rotational motion is the straight-line motion of jointed gear unit by bevel-type reversing gear, master bevel gear assembly is respectively the first bevel gear assembly and the second bevel gear assembly, is respectively first from bevel gear assembly from bevel gear assembly, second from bevel gear assembly, 3rd from bevel gear assembly and the 4th from bevel gear assembly, first actuating unit of actuating unit is connected with the first master bevel gear assembly, second actuating unit is connected with the second master bevel gear assembly, first bevel gear assembly engages from bevel gear assembly from bevel gear assembly and the 3rd with first, and the second bevel gear assembly engages from bevel gear assembly from bevel gear assembly and the 4th with second,
Described jointed gear unit comprises first group of jointed gear unit, second group of jointed gear unit, the first push rod, the 3rd push rod, the second push rod, the 4th push rod, first push rod and the 3rd push rod form by the second push rod, in the first push rod, under the first push rod, and the second push rod and the 4th push rod form by the second push rod, under the second push rod; First group of jointed gear unit is made up of the first push rod, the 3rd push rod, ball pivot cap, the first lever, rotating shaft, nut, the first side wall push rod and the 3rd sidewall push rod, and second group of jointed gear unit is made up of the second push rod, the 4th push rod, the second lever, rotating shaft, nut, the second sidewall push rod and the 4th sidewall push rod; In bevel-type reversing gear, first engages from the cylindrical wheel bevel gear assembly with the first side wall push rod, 3rd engages from the cylindrical wheel bevel gear assembly with the 3rd sidewall push rod, the first side wall push rod and the 3rd sidewall push rod promote the first lever rotation by rotating shaft and nut, are connected between the first lever and the first push rod, the 3rd push rod by ball pivot cap; In bevel-type reversing gear, second engages from the cylindrical wheel bevel gear assembly with the second sidewall push rod, 4th engages from the cylindrical wheel bevel gear assembly with the 4th sidewall push rod, second sidewall push rod and the 4th sidewall push rod promote the second lever rotation by rotating shaft and nut, are connected between the second lever and the first push rod, the 3rd push rod by ball pivot cap;
Be rotationally connected arm mechanism to comprise head shell, erecting equipment plate, be rotationally connected arm, be rotationally connected arm fixture block, two be rotationally connected arm, two be rotationally connected arm fixture block and be connected, the bulb be rotationally connected in the spherical sleeve of arm mechanism in supporting mechanism rotates, be rotationally connected arm and be rotationally connected between arm fixture block and form ball pivot groove, head shell be rotationally connected arm and be connected, erecting equipment plate be rotationally connected arm and be connected.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410431751.9A CN104192311B (en) | 2014-08-28 | 2014-08-28 | A kind of finishing bevel gear cuter push-down Vehicle nose deflection driven device |
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| CN201410431751.9A CN104192311B (en) | 2014-08-28 | 2014-08-28 | A kind of finishing bevel gear cuter push-down Vehicle nose deflection driven device |
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| CN104192311A CN104192311A (en) | 2014-12-10 |
| CN104192311B true CN104192311B (en) | 2016-04-13 |
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| CN201410431751.9A Expired - Fee Related CN104192311B (en) | 2014-08-28 | 2014-08-28 | A kind of finishing bevel gear cuter push-down Vehicle nose deflection driven device |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105932903B (en) * | 2016-06-14 | 2018-01-05 | 南京理工大学 | A kind of bullet arrangement for deflecting based on spherical multi-freedom piezoelectric actuator |
| CN111846192B (en) * | 2020-06-04 | 2022-06-17 | 中国人民解放军国防科技大学 | Flight verification simulation cabin section for online identification of aircraft parameters |
| CN114279268A (en) * | 2021-11-17 | 2022-04-05 | 航天科工微电子***研究院有限公司 | Kinetic energy interceptor based on head deflection |
| CN114987742B (en) * | 2022-08-08 | 2022-11-04 | 陕西科技大学 | Aircraft head deflection control method and structure |
| CN117944875A (en) * | 2024-03-27 | 2024-04-30 | 陕西科技大学 | Aircraft head deflection control structure and control method |
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| US2911167A (en) * | 1952-04-08 | 1959-11-03 | Fay E Null | Heat seeker |
| US3067681A (en) * | 1960-01-04 | 1962-12-11 | Telecomputing Corp | Guided missile |
| US3111088A (en) * | 1962-02-27 | 1963-11-19 | Martin Marietta Corp | Target seeking missile |
| US4193567A (en) * | 1962-07-17 | 1980-03-18 | Novatronics, Inc. | Guidance devices |
| US5564651A (en) * | 1988-08-05 | 1996-10-15 | Rheinmetall Gmbh | Yaw angle free projectile |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2911167A (en) * | 1952-04-08 | 1959-11-03 | Fay E Null | Heat seeker |
| US3067681A (en) * | 1960-01-04 | 1962-12-11 | Telecomputing Corp | Guided missile |
| US3111088A (en) * | 1962-02-27 | 1963-11-19 | Martin Marietta Corp | Target seeking missile |
| US4193567A (en) * | 1962-07-17 | 1980-03-18 | Novatronics, Inc. | Guidance devices |
| US5564651A (en) * | 1988-08-05 | 1996-10-15 | Rheinmetall Gmbh | Yaw angle free projectile |
| CN103803069A (en) * | 2012-11-15 | 2014-05-21 | 西安韦德沃德航空科技有限公司 | Bevel-gear-transmission four-rotor-wing aircraft |
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