CN104192311A - Drive device for head deflection of bevel gear push-rod type aircraft - Google Patents
Drive device for head deflection of bevel gear push-rod type aircraft Download PDFInfo
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- CN104192311A CN104192311A CN201410431751.9A CN201410431751A CN104192311A CN 104192311 A CN104192311 A CN 104192311A CN 201410431751 A CN201410431751 A CN 201410431751A CN 104192311 A CN104192311 A CN 104192311A
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Abstract
The invention discloses a drive device for head deflection of a bevel gear push-rod type aircraft. The drive device for head deflection of the bevel gear push-rod type aircraft comprises a supporting mechanism, power mechanisms, a bevel gear steering mechanism, a connection rod transmission mechanism, a head and rotation connection arm mechanism and an aircraft head body connection mechanism. The power mechanism, the bevel gear steering mechanism and the aircraft head body connection mechanism are fixed to a base of the supporting mechanism. The power mechanisms are arranged along the axis of a machine body. The connection rod transmission mechanism pushes the head and rotation connection arm mechanism to rotate around a ball head in a spherical sleeve of the supporting mechanism. When the head shell of the aircraft begins to conduct deflection, an aircraft computer sends out a signal, and the power mechanisms receive control signals and drive the bevel gear steering mechanism to rotate. The bevel gear steering mechanism converts the rotation movement to linear movement of the connection rod transmission mechanism. The head and rotation connection arm mechanism rotates around the spherical sleeve so as to achieve head deflection of the aircraft. The deflection drive device is simple and compact in structure, and is especially suitable for small aircrafts.
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 the relative aircraft fuselage of Vehicle nose is to the certain angle of any direction deflection, in Vehicle nose, produce corresponding aerodynamic force, it is the control effort of aircraft, thereby produce the control torque of relative aircraft barycenter, make aircraft produce corresponding attitude angle, finally produce motor-driven overload.Vehicle nose's deflection control device can be realized aircraft and move on driftage and pitch channel.
In current disclosed technical literature, 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: Americana " pipe is penetrated Intelligent Compression deflection and adapted to ammunition " development effort (BLAM) adopts the deflection of piezoceramic deflection driven winding machine head.Its in aircraft internal configurations many piezoceramic rods, around body interval, set.Piezoceramic rod is almost parallel with aircraft fuselage axis, and their length can change according to the variation of suffered pressure, makes Vehicle nose carry out deflection, obtains good aerodynamic characteristic.
Magnetostriction type: Americana " magnetic deformation missile-operation control system " is (MMGS) to utilize movable " droop-snoot " to design aircraft guidance system.A spherical hinge adapter and one group of magnetic telescopic driver form deflection driven mechanism.Three magnetostrictive rod (or four identical magnetostrictive rods that performance is identical, be separated by 90 ° and place) in aircraft fuselage around the placement of 120 °, body interval, sensor can be judged the angle of " droop-snoot " required deflection, thereby 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 hinged with tripod turret and bottom support bracket, and tripod turret is connected with three-legged support by spherical linkage.When hydraulic telescopic machanism is during all in not flexible state, Vehicle nose is in undeflected state.When Vehicle nose need to carry out deflection, 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 needing.In document " design of bullet deflection machanism and simulation analysis " (2012 Master degree candidate's thesis of Northwestern Polytechnical University), fluid pressure type mechanism has been described.
Rotating sloping disk type: the Perenosniy Zenitniy Raketniy Kompleks of Britain (MANPADS) is a kind of small-sized, light Perenosniy Zenitniy Raketniy Kompleks pickaback.Aircraft afterbody has four orthogonal balancing planes, there is no traditional rudder face.The deflection driven mechanism of Vehicle nose is comprised of two relatively turnable swash plates, and each swashplate angle is 2 degree, by bearing, connects.Swash plate rotates and drives by two rare-earth permanent magnet motors, and the angle of Vehicle nose's deflection is determined according to autopilot instruction.At document " simulation study of inclined disc type deflection machanism scheme " (< < Computer Simulation > >, 2008, the 25 the 10th phases of volume: described rotating sloping disk type mechanism 23-26).
Piezoelectric ceramic type and magnetostriction type material cost are very expensive, and the deformation producing is smaller, need comparatively complicated enlarger, also require very strict usage condition.Liquid (gas), although pressure type deflection driven mechanism can provide larger moment, need to attach gas, liquid structure, and is subject to the impact of ambient temperature larger; 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
The deficiency existing for fear of prior art, 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 are arranged 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 is received control signal, actuating unit drives bevel-type reversing gear rotation, bevel-type reversing gear is converted into the straight-line motion of jointed gear unit by rotatablely moving, head and be rotationally connected arm mechanism and rotate around spherical sleeve, realizes the angle of inclination of positive and negative 15 degree of Vehicle nose, and head is at deflection azimuth 0-360 degree intrinsic deflection.
Beneficial effect
The finishing bevel gear cuter push-down Vehicle nose deflection driven device that the present invention proposes, can realize the angle of inclination that Vehicle nose's maximum can reach positive and negative 15 degree, and head is 0-360 ° of intrinsic deflection at deflection azimuth.According to the simulation analysis of static system characteristic and dynamic characteristics is learnt, deflection driven device can be realized given Vehicle nose's angle of inclination exactly, and meets the requirement of aircraft control to its rapidity.
Structure and the principle of work of finishing bevel gear cuter push-down of the present invention Vehicle nose deflection driven device are simple, and the components and parts of use are conventional components and parts, are conducive to reduce the expense of aircraft control program; By appropriate design deflection machanism, can obtain larger Vehicle nose's angle of inclination; Structure can be born larger axial force, and carrying side force is functional; Device adopts motor-driven mode, easy for installation, compact, simple in structure, is applicable to small aircraft, does not need subsidiary gas, liquid structure; Device connects structure and adopts motor drive mode in less space, to install, and to compare speed of response very fast with fluid pressure type structure; Motor diameter and aircraft diameter approach, and 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. erection unit 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. reduction 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 bevel gear clutch shaft bearing 32. from bevel gear second bearing 33. from bevel gear shaft 34. from bevel gear gear 35. linear bearing bracing frame 36. linear bearing
The specific embodiment
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, the first sleeve pedestal 13, the second sleeve pedestal 12 and spherical sleeve 3; Between the first sleeve pedestal 13, the second sleeve pedestal 12 and spherical sleeve 3, be connected by screw, wherein the first sleeve pedestal 13 supports as the heart that turns of the first lever 15, the 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 that is 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 every cover comprises servomotor 22 and drop-gear box 23, and servomotor 22 output shafts are 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 are arranged along aircraft body axis.Bevel-type reversing gear comprises 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 the second bearing 30, from finishing bevel gear cuter clutch shaft bearing 31, from finishing bevel gear cuter the 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 the second bearing 30, from bevel gear assembly, comprise from finishing bevel gear cuter clutch shaft bearing 31, from finishing bevel gear cuter the second bearing 32, from bevel gear shaft 33, from finishing bevel gear cuter gear 34, from bevel gear assembly and the master bevel gear assembly bevel-type reversing gear that partners, bevel-type reversing gear is converted into the straight-line motion of jointed gear unit by rotatablely moving, from bevel gear shaft 33, directly process a cylindrical wheel, the first side wall push rod 18 in cylindrical wheel drivening rod transmission device from bevel gear shaft 33, the second sidewall push rod 19, the 3rd sidewall push rod 20, the 4th sidewall push rod 21, form rack-and-gear revolute pair, the rotation of vertical flight device body axis is converted into the straight-line motion that is 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, from bevel gear assembly, has four, 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.The 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.The first bevel gear assembly and first forms engagement from bevel gear assembly and the 3rd from bevel gear assembly, and the second bevel gear assembly and second forms engagement from bevel gear assembly and the 4th from bevel gear assembly.Jointed gear unit in the 7, first push rod under the 6, second push rod on the second push rod under the 8, first push rod 9, ball pivot cap 10, the second lever 14, the first lever 15, rotating shaft 16, nut 17, the first side wall push rod 18, the second sidewall push rod 19, the 3rd sidewall push rod 20 and the 4th sidewall push rod 21 form, wherein on the second push rod, in the 6, first push rod, under the 8, first push rod, 9 form the first push rod and the 3rd push rods, on the second push rod, under the 6, second push rod, form the second push rod and the 4th push rod.The first push rod, the 3rd push rod, ball pivot cap 10, the 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, the second sidewall push rod 19 and the 4th sidewall push rod 21 form second group of jointed gear unit.In bevel-type reversing gear, the first cylindrical wheel from bevel gear assembly and the first side wall push rod 18 form engagement, the 3rd cylindrical wheel from bevel gear assembly and the 3rd sidewall push rod 20 form engagement, 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 is driving the first push rod and the 3rd push rod to be parallel to the straight-line motion of aircraft body axis, between the first lever 15 and the first push rod, the 3rd push rod, by ball pivot cap 10, is connected.In bevel-type reversing gear, the second cylindrical wheel from bevel gear assembly and the second sidewall push rod 19 form engagement, the 4th cylindrical wheel from bevel gear assembly and the 4th sidewall push rod 21 form engagement, the 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 is driving the second push rod and the 4th push rod to be parallel to the straight-line motion of aircraft body axis, between the second lever 14 and the first push rod, the 3rd push rod, by ball pivot cap 10, is connected.Jointed gear unit by bevel-type reversing gear from bevel gear assembly the rotation of cylindrical wheel transform into the straight-line motion that is 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 arm 4, two and are rotationally connected arm fixture block 5 and by bolt, are fixed into as a whole, head and be rotationally connected arm mechanism and rotate around the bulb in the spherical sleeve 3 in supporting mechanism, be rotationally connected arm 4 and be rotationally connected and between arm fixture block 5, 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 around the bulb of the spherical sleeve 3 in supporting mechanism promoting head and being rotationally connected arm mechanism, promote the deflection of head shell 1.Aircraft head body connecting device comprises corrugated shell 11, corrugated shell 11 is connected by screw with base 24He Vehicle nose shell 1, it guarantees relative base 24 deflections of head shell 1, and guaranteeing there is a relatively smooth surface 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 while being 0 °, servomotor 19 is in initial condition, in head shell 1 angle of inclination of aircraft or deflection azimuth one while being not 0 °, claims motor in deflection state.
Take the head shell 1 of aircraft from angle of inclination as 0 ° and deflection azimuth as 0 ° deflects into angle of inclination as 15 ° and deflection azimuth as 120 ° is example, servomotor 19 is when initial condition, head shell 1 deflection angle is that 0 ° and deflection azimuth are 0 °, when the head shell 1 of aircraft need to carry out deflection, aircraft computer sends signal, actuating unit is received control signal, actuating unit drives 28 rotations of master bevel gear axle, bevel-type reversing gear is converted into the straight-line motion of jointed gear unit by rotatablely moving, 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 are arranged 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 is received control signal, actuating unit drives bevel-type reversing gear rotation, bevel-type reversing gear is converted into the straight-line motion of jointed gear unit by rotatablely moving, head and be rotationally connected arm mechanism and rotate around spherical sleeve, realizes the angle of inclination of positive and negative 15 degree of Vehicle nose, and head is at deflection azimuth 0-360 degree intrinsic deflection.
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 |
Applications Claiming Priority (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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| Publication Number | Publication Date |
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| CN104192311A true CN104192311A (en) | 2014-12-10 |
| CN104192311B 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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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105932903A (en) * | 2016-06-14 | 2016-09-07 | 南京理工大学 | Spherical multi-degree-of-freedom piezoelectric actuator-based warhead deflection device |
| CN111846192A (en) * | 2020-06-04 | 2020-10-30 | 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 | 航天科工微电子系统研究院有限公司 | Kinetic energy interceptor based on head deflection |
| CN114987742A (en) * | 2022-08-08 | 2022-09-02 | 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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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105932903A (en) * | 2016-06-14 | 2016-09-07 | 南京理工大学 | Spherical multi-degree-of-freedom piezoelectric actuator-based warhead deflection device |
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| CN111846192A (en) * | 2020-06-04 | 2020-10-30 | 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 | 航天科工微电子系统研究院有限公司 | Kinetic energy interceptor based on head deflection |
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| 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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| CN104192311B (en) | 2016-04-13 |
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