CN110608258B - Helicopter main-reduction and semi-driving hydraulic vibration isolator - Google Patents
Helicopter main-reduction and semi-driving hydraulic vibration isolator Download PDFInfo
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- CN110608258B CN110608258B CN201910897911.1A CN201910897911A CN110608258B CN 110608258 B CN110608258 B CN 110608258B CN 201910897911 A CN201910897911 A CN 201910897911A CN 110608258 B CN110608258 B CN 110608258B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F13/00—Units comprising springs of the non-fluid type as well as vibration-dampers, shock-absorbers, or fluid springs
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F9/00—Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium
- F16F9/32—Details
- F16F9/3207—Constructional features
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F9/00—Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium
- F16F9/32—Details
- F16F9/3207—Constructional features
- F16F9/3214—Constructional features of pistons
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Vibration Prevention Devices (AREA)
Abstract
The invention relates to a helicopter vibration control technology, in particular to a helicopter main halving active hydraulic vibration isolator. The invention solves the problems of slow response, complex structure, high manufacturing cost and high failure rate of the conventional electronic semi-active vibration isolator. A helicopter main-halving active hydraulic vibration isolator comprises a main body mechanism, a hydraulic amplification mechanism and a rigidity adjusting mechanism; the main body mechanism comprises a disc-shaped base, a circular cylinder barrel and an inclined stay bar; the hydraulic amplification mechanism comprises a damping spring, a small piston, a large piston, a vibration input shaft and a double-flange straight pipe; the rigidity adjusting mechanism comprises a connecting flange, a plate spring, a rectangular frame, a limiting sliding block, an auxiliary constraint sliding block, a rack, a transmission shaft and a connecting rod. The invention is suitable for helicopter vibration control.
Description
Technical Field
The invention relates to a helicopter vibration control technology, in particular to a helicopter main halving active hydraulic vibration isolator.
Background
During flight of the helicopter, rotor vibration loads are transmitted to the fuselage through the main reducing system, thereby affecting the riding comfort on one hand and the reliability of helicopter components and onboard equipment on the other hand. In order to reduce the rotor vibration load transmitted to the fuselage, a commonly adopted measure at present is to install an electronic semi-active vibration isolator between the main reducing system and the fuselage of the helicopter. However, practice shows that the electronic semi-active vibration isolator has the problems of slow response, complex structure, high manufacturing cost and high failure rate due to the limit of the structure of the electronic semi-active vibration isolator. Therefore, a new vibration isolator needs to be invented to solve the above problems of the existing electronic type semi-active vibration isolator.
Disclosure of Invention
The invention provides a helicopter main-reduction half-active hydraulic vibration isolator, which aims to solve the problems of slow response, complex structure, high manufacturing cost and high failure rate of the existing electronic half-active vibration isolator.
The invention is realized by adopting the following technical scheme:
a helicopter main-halving active hydraulic vibration isolator comprises a main body mechanism, a hydraulic amplification mechanism and a rigidity adjusting mechanism;
the main body mechanism comprises a disc-shaped base, a circular cylinder barrel and an inclined stay bar;
a vertically through central round hole is formed in the center of the end surface of the disc-shaped base; the upper end surface of the disc-shaped base is radially provided with two longitudinal strip-shaped grooves and two transverse strip-shaped grooves; the rear end of the first longitudinal strip-shaped groove is closed, and the front end of the first longitudinal strip-shaped groove penetrates through the outer side surface of the disc-shaped base; the front end of the second longitudinal strip-shaped groove is closed, and the rear end of the second longitudinal strip-shaped groove penetrates through the outer side surface of the disc-shaped base; the two ends of the first horizontal bar-shaped groove are sealed, and the first horizontal bar-shaped groove is positioned on the left side of the central circular hole of the disc-shaped base; the left end of the second horizontal strip-shaped groove is closed, and the right end of the second horizontal strip-shaped groove penetrates through the outer side surface of the disc-shaped base; the lower end of the round cylinder barrel is closed, and the upper end of the round cylinder barrel is provided with an opening; the inner side surface of the round cylinder barrel is a step surface with a thick upper part and a thin lower part; the upper end of the outer side surface of the circular cylinder barrel is fixedly matched with the lower end of the hole wall of the central circular hole of the disc-shaped base; a positioning convex ring extends from the middle of the outer side surface of the round cylinder barrel; the number of the diagonal braces is a plurality of; the upper end of each inclined stay bar is fixed with the lower end surface of the disc-shaped base; the lower end of each inclined strut is fixed with the upper end face of the positioning convex ring of the circular cylinder barrel; the inclined support rods are arranged around the central line of the disc-shaped base at equal intervals;
the hydraulic amplification mechanism comprises a damping spring, a small piston, a large piston, a vibration input shaft and a double-flange straight pipe;
the lower end of the damping spring is fixed with the lower inner end face of the round cylinder barrel; the small piston is assembled on the thin section of the inner side surface of the round cylinder in a sliding manner, and the lower end surface of the small piston is fixed with the upper end of the damping spring; the large piston is assembled on the thick section of the inner side surface of the circular cylinder barrel in a sliding mode, and hydraulic oil is filled between the large piston and the small piston; the vibration input shaft is vertically fixed in the center of the upper end face of the large piston; the inner side surface of the double-flange straight pipe is in clearance fit with the side surface of the vibration input shaft, and the lower end surface of the lower flange of the double-flange straight pipe is fixed with the upper end surface of the large piston;
the rigidity adjusting mechanism comprises a connecting flange, a plate spring, a rectangular frame, a limiting slide block, an auxiliary constraint slide block, a rack, a transmission shaft and a connecting rod;
the inner side surface of the connecting flange is in clearance fit with the side surface of the vibration input shaft, and the lower end surface of the connecting flange is fixed with the upper end surface of the upper flange of the double-flange straight pipe; a central circular hole which is communicated up and down is formed in the center of the surface of the plate spring, and the hole wall of the central circular hole is in clearance fit with the side surface of the vibration input shaft; the lower surface of the plate spring is fixed with the upper end surface of the connecting flange; the number of the rectangular frames is two; the two rectangular frames are respectively sleeved at the two ends of the plate spring in a sliding manner; the centers of the outer side surfaces of the upper frame edges of the two rectangular frames are respectively provided with an upper assembling convex column in an extending way; the centers of the outer side surfaces of the lower frame sides of the two rectangular frames are respectively provided with a lower assembling convex column in an extending way; the number of the limiting slide blocks is two; the two limiting slide blocks are respectively assembled in the two longitudinal strip-shaped grooves in a sliding manner; the centers of the surfaces of the two limiting sliding blocks are respectively provided with a central circular hole which is communicated up and down, and the upper ends of the hole walls of the two central circular holes are respectively fixedly matched with the lower ends of the side surfaces of the lower assembling convex columns of the two rectangular frames; the auxiliary restraint sliding block is assembled in the first horizontal strip-shaped groove in a sliding mode, and an assembly convex column extends from the center of the upper surface of the auxiliary restraint sliding block; the rack is assembled in the second horizontal strip-shaped groove in a sliding mode, and the tooth surface of the rack faces upwards; the transmission shaft is vertically fixed at the left end of the upper surface of the rack; the number of the connecting rods is four; both ends of each connecting rod are provided with an assembly round hole which is communicated up and down; the hole walls of the two assembling round holes of the first connecting rod are in clearance fit with the side surface of the lower assembling convex column of the first rectangular frame and the side surface of the assembling convex column of the auxiliary constraint sliding block respectively; the hole walls of two assembling circular holes of the second connecting rod are in clearance fit with the side surface of the lower assembling convex column of the second rectangular frame and the side surface of the assembling convex column of the auxiliary constraint sliding block respectively; the hole walls of the two assembling round holes of the third connecting rod are in clearance fit with the side surface of the upper assembling convex column of the first rectangular frame and the side surface of the transmission shaft respectively; the hole walls of two assembling round holes of the fourth connecting rod are in clearance fit with the side surface of the upper assembling convex column of the second rectangular frame and the side surface of the transmission shaft respectively.
When the vibration isolator works, the vibration isolator (namely the helicopter main reducing and semi-active hydraulic vibration isolator) is arranged between a main reducing system and a helicopter body of a helicopter, and a rack is connected with an external driving device (such as an electric motor, a hydraulic cylinder and the like). The specific working process is as follows: when the helicopter flies, the vibration load of the rotor wing is input into the vibration isolator through the vibration input shaft, and then the vibration load is transmitted to the helicopter body by two paths: the first path is transmitted to the machine body through the large piston, the hydraulic oil, the small piston, the damping spring, the circular cylinder barrel and the disc-shaped base in sequence, and the second path is transmitted to the machine body through the large piston, the double-flange straight pipe, the connecting flange, the plate spring, the rectangular frame and the limiting slide block in sequence. In the process, the large piston vibrates up and down under the action of the vibration load of the rotor wing, and the small piston is pushed by hydraulic oil to vibrate up and down. If the input frequency of the rotor wing vibration load is equal to the anti-resonance point frequency of the vibration isolator, the inertia force of the small piston vibration can just offset the pressure of hydraulic oil, so that the first rotor wing vibration load is prevented from being transmitted, and the rotor wing vibration load transmitted to the fuselage is reduced. If the input frequency of the vibration load of the rotor wing is not equal to the anti-resonance point frequency of the vibration isolator, the anti-resonance point frequency of the vibration isolator is adjusted through the rigidity adjusting mechanism until the anti-resonance point frequency of the vibration isolator is equal to the input frequency of the vibration load of the rotor wing. The specific adjustment process is as follows: the rack is driven by the external driving device to move transversely, the rack drives the two rectangular frames to move longitudinally through the transmission shaft and the connecting rod, and therefore the working length of the plate spring (namely the distance between the two rectangular frames) is changed, the rigidity of the vibration isolator is changed, and the anti-resonance point frequency of the vibration isolator is changed.
Based on the process, compared with the existing electronic semi-active vibration isolator, the helicopter main-reduction semi-active hydraulic vibration isolator provided by the invention adopts a brand new structure, reduces the rotor wing vibration load transmitted to the helicopter body, and has the advantages of quick response, simple structure, low manufacturing cost and low failure rate.
Further, the side upper end of the transmission shaft is fixedly provided with a shaft cap. When the connecting rod works, the shaft cap is used for preventing the connecting rod from falling off.
The electronic semi-active vibration isolator is reasonable in structure and ingenious in design, effectively solves the problems of slow response, complex structure, high manufacturing cost and high failure rate of the existing electronic semi-active vibration isolator, and is suitable for controlling the vibration of a helicopter.
Drawings
Fig. 1 is a schematic perspective view of the present invention.
Fig. 2 is a schematic plan view of the present invention.
Fig. 3 is a right side view of fig. 2.
Fig. 4 is a sectional view a-a of fig. 2.
Fig. 5 is a top view of fig. 2.
In the figure: 101-a disc-shaped base, 102-a circular cylinder, 103-a diagonal brace, 104-a longitudinal strip-shaped groove, 105-a transverse strip-shaped groove, 201-a damping spring, 202-a small piston, 203-a large piston, 204-a vibration input shaft, 205-a double-flange straight pipe, 301-a connecting flange, 302-a plate spring, 303-a rectangular frame, 304-a limiting slide block, 305-an auxiliary constraint slide block, 306-a rack, 307-a transmission shaft, 308-a connecting rod and 309-a shaft cap.
Detailed Description
A helicopter main-halving active hydraulic vibration isolator comprises a main body mechanism, a hydraulic amplification mechanism and a rigidity adjusting mechanism;
the main body mechanism comprises a disc-shaped base 101, a circular cylinder 102 and a diagonal brace 103;
a vertically through center round hole is formed in the center of the end face of the disc-shaped base 101; the upper end surface of the disc-shaped base 101 is radially provided with two longitudinal strip-shaped grooves 104 and two transverse strip-shaped grooves 105; the rear end of the first longitudinal strip-shaped groove 104 is closed, and the front end of the first longitudinal strip-shaped groove penetrates through the outer side surface of the disc-shaped base 101; the front end of the second longitudinal strip-shaped groove 104 is closed, and the rear end of the second longitudinal strip-shaped groove runs through the outer side surface of the disc-shaped base 101; both ends of the first horizontal bar-shaped groove 105 are closed, and the first horizontal bar-shaped groove 105 is positioned on the left side of the central circular hole of the disc-shaped base 101; the left end of the second horizontal strip-shaped groove 105 is closed, and the right end of the second horizontal strip-shaped groove runs through the outer side surface of the disc-shaped base 101; the lower end of the round cylinder barrel 102 is closed, and the upper end is provided with an opening; the inner side surface of the round cylinder barrel 102 is a step surface with a thick upper part and a thin lower part; the upper end of the outer side surface of the circular cylinder barrel 102 is fixedly matched with the lower end of the hole wall of the central circular hole of the disc-shaped base 101; a positioning convex ring extends from the middle of the outer side surface of the round cylinder barrel 102; the number of the diagonal braces 103 is a plurality; the upper end of each inclined strut 103 is fixed with the lower end face of the disc-shaped base 101; the lower end of each inclined strut 103 is fixed with the upper end face of the positioning convex ring of the round cylinder barrel 102; the inclined support rods 103 are arranged at equal intervals around the central line of the disc-shaped base 101;
the hydraulic amplification mechanism comprises a damping spring 201, a small piston 202, a large piston 203, a vibration input shaft 204 and a double-flange straight pipe 205;
the lower end of the damping spring 201 is fixed with the lower inner end face of the round cylinder 102; the small piston 202 is assembled on the thin section of the inner side surface of the circular cylinder barrel 102 in a sliding mode, and the lower end face of the small piston 202 is fixed with the upper end of the damping spring 201; the large piston 203 is assembled on the thick section of the inner side surface of the circular cylinder barrel 102 in a sliding mode, and hydraulic oil is filled between the large piston 203 and the small piston 202; the vibration input shaft 204 is vertically fixed at the center of the upper end face of the large piston 203; the inner side surface of the double-flange straight pipe 205 is in clearance fit with the side surface of the vibration input shaft 204, and the lower end surface of the lower flange of the double-flange straight pipe 205 is fixed with the upper end surface of the large piston 203;
the rigidity adjusting mechanism comprises a connecting flange 301, a plate spring 302, a rectangular frame 303, a limiting sliding block 304, an auxiliary restricting sliding block 305, a rack 306, a transmission shaft 307 and a connecting rod 308;
the inner side surface of the connecting flange 301 is in clearance fit with the side surface of the vibration input shaft 204, and the lower end surface of the connecting flange 301 is fixed with the upper end surface of the upper flange of the double-flange straight pipe 205; a vertically through center circular hole is formed in the center of the surface of the plate spring 302, and the hole wall of the center circular hole is in clearance fit with the side surface of the vibration input shaft 204; the lower surface of the plate spring 302 is fixed with the upper end surface of the connecting flange 301; the number of the rectangular frames 303 is two; the two rectangular frames 303 are respectively sleeved at two ends of the plate spring 302 in a sliding manner; the centers of the outer side surfaces of the upper frame edges of the two rectangular frames 303 are respectively provided with an upper assembling convex column in an extending way; the centers of the outer side surfaces of the lower frame edges of the two rectangular frames 303 are respectively provided with a lower assembling convex column in an extending way; the number of the limiting slide blocks 304 is two; the two limiting slide blocks 304 are respectively assembled in the two longitudinal strip-shaped grooves 104 in a sliding manner; the centers of the surfaces of the two limiting sliding blocks 304 are respectively provided with a vertically through central circular hole, and the upper ends of the hole walls of the two central circular holes are respectively fixedly matched with the lower ends of the side surfaces of the lower assembling convex columns of the two rectangular frames 303; the auxiliary restricting slide block 305 is slidably assembled in the first horizontal strip-shaped groove 105, and an assembling convex column extends from the center of the upper surface of the auxiliary restricting slide block 305; the rack 306 is slidably assembled in the second horizontal strip-shaped groove 105, and the tooth surface of the rack 306 faces upwards; the transmission shaft 307 is vertically fixed at the left end of the upper surface of the rack 306; the number of links 308 is four; both ends of each connecting rod 308 are provided with an assembly round hole which is communicated up and down; the hole walls of the two assembling round holes of the first connecting rod 308 are in clearance fit with the side surface of the lower assembling convex column of the first rectangular frame 303 and the side surface of the assembling convex column of the auxiliary constraint sliding block 305 respectively; the hole walls of the two assembling circular holes of the second connecting rod 308 are in clearance fit with the side surface of the lower assembling convex column of the second rectangular frame 303 and the side surface of the assembling convex column of the auxiliary constraint sliding block 305 respectively; the hole walls of the two assembling round holes of the third connecting rod 308 are in clearance fit with the side surface of the upper assembling convex column of the first rectangular frame 303 and the side surface of the transmission shaft 307 respectively; the hole walls of the two assembling round holes of the fourth connecting rod 308 are in clearance fit with the side surface of the upper assembling convex column of the second rectangular frame 303 and the side surface of the transmission shaft 307 respectively.
A shaft cap 309 is fixedly fitted to the upper end of the side surface of the drive shaft 307.
In specific implementation, the upper end of each inclined strut 103 is fixed with the lower end face of the disc-shaped base 101 through a bolt; the lower end of each inclined strut 103 is fixed with the upper end face of the positioning convex ring of the round cylinder barrel 102 through a bolt.
Claims (3)
1. The utility model provides a helicopter owner subtracts half initiative hydraulic pressure isolator which characterized in that: comprises a main body mechanism, a hydraulic amplifying mechanism and a rigidity adjusting mechanism;
the main body mechanism comprises a disc-shaped base (101), a circular cylinder (102) and a diagonal brace (103);
a vertically through center round hole is formed in the center of the end face of the disc-shaped base (101); the upper end surface of the disc-shaped base (101) is radially provided with two longitudinal strip-shaped grooves (104) and two transverse strip-shaped grooves (105); the rear end of the first longitudinal strip-shaped groove (104) is closed, and the front end of the first longitudinal strip-shaped groove penetrates through the outer side surface of the disc-shaped base (101); the front end of the second longitudinal strip-shaped groove (104) is closed, and the rear end of the second longitudinal strip-shaped groove penetrates through the outer side surface of the disc-shaped base (101); both ends of the first horizontal bar-shaped groove (105) are closed, and the first horizontal bar-shaped groove (105) is positioned on the left side of a central circular hole of the disc-shaped base (101); the left end of the second horizontal strip-shaped groove (105) is closed, and the right end of the second horizontal strip-shaped groove penetrates through the outer side surface of the disc-shaped base (101); the lower end of the round cylinder barrel (102) is closed, and the upper end is provided with an opening; the inner side surface of the round cylinder barrel (102) is a step surface with a thick upper part and a thin lower part; the upper end of the outer side surface of the circular cylinder barrel (102) is fixedly matched with the lower end of the hole wall of the central circular hole of the disc-shaped base (101); a positioning convex ring extends from the middle of the outer side surface of the round cylinder barrel (102); the number of the diagonal braces (103) is a plurality; the upper end of each inclined strut (103) is fixed with the lower end face of the disc-shaped base (101); the lower end of each inclined strut (103) is fixed with the upper end face of the positioning convex ring of the round cylinder barrel (102); the inclined supporting rods (103) are arranged around the central line of the disc-shaped base (101) at equal intervals;
the hydraulic amplification mechanism comprises a damping spring (201), a small piston (202), a large piston (203), a vibration input shaft (204) and a double-flange straight pipe (205);
the lower end of the damping spring (201) is fixed with the lower inner end face of the round cylinder barrel (102); the small piston (202) is assembled on the thin section of the inner side surface of the circular cylinder barrel (102) in a sliding mode, and the lower end face of the small piston (202) is fixed with the upper end of the damping spring (201); the large piston (203) is assembled on the thick section of the inner side surface of the circular cylinder barrel (102) in a sliding mode, and hydraulic oil is filled between the large piston (203) and the small piston (202); the vibration input shaft (204) is vertically fixed at the center of the upper end surface of the large piston (203); the inner side surface of the double-flange straight pipe (205) is in clearance fit with the side surface of the vibration input shaft (204), and the lower end surface of the lower flange of the double-flange straight pipe (205) is fixed with the upper end surface of the large piston (203);
the rigidity adjusting mechanism comprises a connecting flange (301), a plate spring (302), a rectangular frame (303), a limiting sliding block (304), an auxiliary constraint sliding block (305), a rack (306), a transmission shaft (307) and a connecting rod (308);
the inner side surface of the connecting flange (301) is in clearance fit with the side surface of the vibration input shaft (204), and the lower end surface of the connecting flange (301) is fixed with the upper end surface of the upper flange of the double-flange straight pipe (205); a vertically through central circular hole is formed in the center of the surface of the plate spring (302), and the hole wall of the central circular hole is in clearance fit with the side surface of the vibration input shaft (204); the lower surface of the plate spring (302) is fixed with the upper end surface of the connecting flange (301); the number of the rectangular frames (303) is two; the two rectangular frames (303) are respectively sleeved at two ends of the plate spring (302) in a sliding manner; the centers of the outer side surfaces of the upper frame edges of the two rectangular frames (303) are respectively provided with an upper assembling convex column in an extending way; the centers of the outer side surfaces of the lower frame edges of the two rectangular frames (303) are respectively provided with a lower assembling convex column in an extending way; the number of the limiting sliding blocks (304) is two; the two limiting sliding blocks (304) are respectively assembled in the two longitudinal strip-shaped grooves (104) in a sliding manner; the centers of the surfaces of the two limiting sliding blocks (304) are respectively provided with a vertically through central circular hole, and the upper ends of the hole walls of the two central circular holes are respectively fixedly matched with the lower ends of the side surfaces of the lower assembling convex columns of the two rectangular frames (303); the auxiliary restraint sliding block (305) is assembled in the first horizontal strip-shaped groove (105) in a sliding mode, and an assembly convex column extends from the center of the upper surface of the auxiliary restraint sliding block (305); the rack (306) is slidably assembled in the second transverse strip-shaped groove (105), and the tooth surface of the rack (306) faces upwards; the transmission shaft (307) is vertically fixed at the left end of the upper surface of the rack (306); the number of the connecting rods (308) is four; both ends of each connecting rod (308) are provided with an assembling round hole which is communicated up and down; the hole walls of two assembling round holes of the first connecting rod (308) are in clearance fit with the side surface of the lower assembling convex column of the first rectangular frame (303) and the side surface of the assembling convex column of the auxiliary constraint sliding block (305) respectively; the hole walls of two assembling round holes of the second connecting rod (308) are in clearance fit with the side surface of the lower assembling convex column of the second rectangular frame (303) and the side surface of the assembling convex column of the auxiliary constraint sliding block (305) respectively; the hole walls of two assembling round holes of the third connecting rod (308) are in clearance fit with the side surface of the upper assembling convex column of the first rectangular frame (303) and the side surface of the transmission shaft (307) respectively; the hole walls of two assembling round holes of the fourth connecting rod (308) are in clearance fit with the side surface of the upper assembling convex column of the second rectangular frame (303) and the side surface of the transmission shaft (307) respectively.
2. The helicopter main half active hydraulic vibration isolator according to claim 1, wherein: the upper end of the side surface of the transmission shaft (307) is fixedly provided with a shaft cap (309).
3. The helicopter main halving active hydraulic vibration isolator according to claim 1 or 2, characterized in that: the upper end of each inclined strut (103) is fixed with the lower end face of the disc-shaped base (101) through bolts; the lower end of each inclined strut (103) is fixed with the upper end face of the positioning convex ring of the round cylinder barrel (102) through a bolt.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910897911.1A CN110608258B (en) | 2019-09-23 | 2019-09-23 | Helicopter main-reduction and semi-driving hydraulic vibration isolator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910897911.1A CN110608258B (en) | 2019-09-23 | 2019-09-23 | Helicopter main-reduction and semi-driving hydraulic vibration isolator |
Publications (2)
| Publication Number | Publication Date |
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| CN110608258A CN110608258A (en) | 2019-12-24 |
| CN110608258B true CN110608258B (en) | 2020-10-30 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201910897911.1A Expired - Fee Related CN110608258B (en) | 2019-09-23 | 2019-09-23 | Helicopter main-reduction and semi-driving hydraulic vibration isolator |
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Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR1506385A (en) * | 1966-09-16 | 1967-12-22 | Sud Aviation | Method of attenuation and electro-hydraulic vibration attenuator for rotary wing aerodyne |
| CN101559833A (en) * | 2009-05-15 | 2009-10-21 | 江苏大学 | Passive vibration isolation device of main speed reduction box of helicopter |
| FR2959484B1 (en) * | 2010-04-30 | 2012-11-09 | Eurocopter France | DEVICE FOR REDUCING VIBRATIONS GENERATED BY A ROTOR OF SUSTENTATION OF A GIRAVION, AND HUB OF A ROTOR HAVING SUCH A DEVICE. |
| CN201891793U (en) * | 2010-10-19 | 2011-07-06 | 江苏大学 | Anti-resonance vibration isolation device for inertial mass energy storage type helicopter body |
| CN105644781A (en) * | 2015-03-02 | 2016-06-08 | 王泽民 | Method for balancing rotation torque of helicopter body |
| CN105299128B (en) * | 2015-11-27 | 2017-07-04 | 上海工程技术大学 | A kind of double acting platform-type parallel institution vibration reduction platform |
| CN109765022B (en) * | 2019-01-16 | 2024-04-16 | 南京航空航天大学 | Helicopter main reducer vibration isolation system test device |
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2019
- 2019-09-23 CN CN201910897911.1A patent/CN110608258B/en not_active Expired - Fee Related
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