CN101984331B

CN101984331B - Dynamics comprehensive test bed for half-unfolding gas bomb with long tilting rotor wing

Info

Publication number: CN101984331B
Application number: CN201010502248XA
Authority: CN
Inventors: 董凌华; 侯鹏; 杨卫东
Original assignee: Nanjing University of Aeronautics and Astronautics
Current assignee: Nanjing University of Aeronautics and Astronautics
Priority date: 2010-09-30
Filing date: 2010-09-30
Publication date: 2012-11-28
Anticipated expiration: 2030-09-30
Also published as: CN101984331A

Abstract

The invention discloses a dynamics comprehensive test bed for a half-unfolding gas bomb with a long tilting rotor wing, comprising a wing, a tilting driving mechanism, a tilting rotor wing nacelle and a power-driven system, wherein the power-driven system is arranged at one end of the wing, the other end of the wing is connected with the tilting driving mechanism, and the tilting driving mechanism is also connected with the tilting rotor wing nacelle and drives the tilting rotor wing nacelle to rotate. By using the structure, the deficiency in test means in research filed of tilting rotor wing gas bomb dynamics problems in China is solved, and the invention provides the test bed capable of researching the stability, tilting transition state dynamic test and vibration control of the tilting rotor craft, which can be used for checking theoretical analysis results.

Description

The long tilting rotor gas springing mechanics integrated test platform of half exhibition

Technical field

The invention belongs to aviation field, relate to a kind of test platform, be meant a kind of test unit that is used for tilting rotor gas springing mechanics study especially.

Background technology

Tiltrotor aircraft is a kind of novel rotor craft, and its verted nacelle that will have rotor places the wing tip of wing, has the advantage that helicopter VTOL and aircraft fly before fast concurrently, demonstrates huge military value and civilian potentiality.Tiltrotor aircraft is when having helicopter VTOL and aircraft concurrently and flying advantage before fast; The whole dynamics problems that also have helicopter and propeller aeroplane; Compare the rotor body coupling of pure helicopter or the coupling between the wind stick wing, the various coupled relations of tiltrotor are more complicated, particularly in the transient process of tiltrotor between two kinds of state of flights; The inertia of system and coupled characteristic respective change, gas bullet Coupled Dynamics problem are particularly complicated.The long tiltrotor aircraft model of half exhibition can be simulated the dynamics problem of basic tiltrotor aircraft, and therefore the long tiltrotor aircraft model test of half exhibition becomes the basic means of tiltrotor aircraft dynamics research.

Domestic research to the tiltrotor aircraft gordian technique also is in the starting stage, and the necessary experimental study means of gas springing mechanics study shortage about tiltrotor aircraft are used to check the also result of proof theory analysis.For this reason, China needs to carry out the test platform of the Study on Vibration Control that tiltrotor aircraft gas bullet is stable, tiltrotor aircraft verts research of transition state dynamic test and tiltrotor aircraft.

This case inventor promptly is based on above consideration, develops the long tilting rotor gas springing mechanics integrated test platform of half exhibition that this case discloses.

Summary of the invention

Fundamental purpose of the present invention; Be to provide a kind of half exhibition long tilting rotor gas springing mechanics integrated test platform; It can solve the deficiency of domestic tilting rotor gas springing mechanics problem research field research technique aspect; Provide a cover can carry out the test platform of the Study on Vibration Control that tiltrotor aircraft gas bullet is stable, tiltrotor aircraft verts research of transition state dynamic test and tiltrotor aircraft, be used to check result of theoretic analysis.

In order to reach above-mentioned purpose, solution of the present invention is:

The long tilting rotor gas springing mechanics integrated test platform of a kind of half exhibition; Comprise wing, the driving mechanism that verts, tilting rotor nacelle and Power Drive Unit; Wherein, Power Drive Unit is located at an end of wing, and the other end of wing then connects the driving mechanism that verts; The said driving mechanism that verts also connects the tilting rotor nacelle, and drives the rotation of tilting rotor nacelle.

Above-mentioned Power Drive Unit comprises pedestal, motor, location-plate and flange, and wherein, motor and location-plate are fixed, and location-plate is connected with pedestal, and flange also is installed on the output shaft of motor.

Above-mentioned wing comprises dimension shape shell, main load-bearing part, crossbeam, transmission shaft and two flanges; Wherein, main load-bearing part is installed on through cushion block on the pedestal of Power Drive Unit, and an end and the described main load-bearing part of crossbeam are fixed; Transmission shaft is fixed with crossbeam, main load-bearing part rotationally; And two flanges are located at the two ends of transmission shaft successively, and wherein a flange is connected with the flange of Power Drive Unit, and another flange is connected with power input shaft in the driving mechanism that verts; Dimension shape outer casing frame is located on the crossbeam.

Above-mentioned wing comprises that also one strengthens rib and a plurality of panel beating rib, strengthen rib and be located on the main load-bearing part, and the panel beating rib is arranged successively and is installed on the crossbeam, and flange is also formed on the top of this panel beating rib, and dimension shape outer casing frame is located on this flange.

Above-mentioned transmission shaft comprises at least two interconnective rotating shafts, connects by the elasticity shaft joint between the adjacent shafts; Be respectively equipped with the bearing cup that has self-aligning bearing on said reinforcement rib and at least one panel beating rib, transmission shaft pass described bearing cup successively and with crossbeam, main load-bearing part installing and locating.

The above-mentioned driving mechanism that verts comprises fixed frame, the casing that verts, power input shaft, worm-and-wheel gear, control motor, gear shaft and the fluted disc that verts vert; On fixed frame and the wing crossbeam relatively an end of main load-bearing part is connected, the casing that verts is a cylindrical structural, be installed in rotation on the fixed frame, and the outer end of this casing that verts connects the tilting rotor nacelle respectively and the fluted disc that verts; Power input shaft runs through the casing that verts, and the one of which end is by the flange of flange connection wing, and the other end then penetrates the tilting rotor nacelle; Worm-and-wheel gear is installed on the fixed frame, and the control motor that verts is located on the worm-and-wheel gear, and gear shaft is connected worm-and-wheel gear and vert between the fluted disc, the drive fluted disc rotation of verting under the motion of worm-and-wheel gear.

Also be provided with a pair of brake block that can embrace the casing that verts by arch section on the said fixing frame.

Above-mentioned tilting rotor nacelle comprises nacelle casing, communtation deceleration device, rotor, sliding plate mechanism and rotor shaft, and wherein, the communtation deceleration device is located at the inside of nacelle casing, and the one of which end connects the power input shaft of the driving mechanism that verts, and the other end connects the rotor shaft of rotor; The outside of said nacelle casing also is provided with the shell that compound substance is processed; Sliding plate mechanism is installed on the nacelle casing, connects rotor through pitch-change-link; Rotor comprises propeller hub head and blade, and the propeller hub head is connected with blade through pitch hinge, and this pitch hinge also connects pitch-change-link through distance-variable rocker arm.

The collector ring mounting bracket that is used for fixing collector ring also is installed on the above-mentioned nacelle casing.

Above-mentioned sliding plate mechanism comprises installing sleeve, not rotating ring, clamping plate, connecting rod, rotating ring and spherical plain bearing rod end, and wherein, installing sleeve is fixed on the nacelle casing, and rotor shaft is passed this installing sleeve, and is positioned in the installing sleeve by deep groove ball bearing; Motionless being located on the installing sleeve, and can on installing sleeve, slide or locate; Rotating ring is set in not on the rotating ring rotationally, and this rotating ring is also through the connecting rod connecting cleat, and these clamping plate clamp rotor shaft after by bolted; On the overhanging pawl of said rotating ring spherical plain bearing rod end is installed also, this spherical plain bearing rod end connects pitch-change-link.

After adopting such scheme, the present invention has the following advantages:

(1) the long tiltrotor aircraft model of half exhibition can be simulated the dynamics problem of basic tiltrotor aircraft, can carry out many-sided tilting rotor dynamics researchs such as tilting rotor gas bullet stability, load and vibration;

(2) the present invention can effectively simulate the duty of helicopter flight pattern, transition flight pattern and aircraft flight pattern lower wing/rotor system, and is therefore applied widely;

(3) each the parts convenient disassembly among the present invention is easy to Maintenance and Repair; Particularly be directed against the gas bullet test of the tiltrotor of more topology layouts, can change parts according to actual needs;

(4) take fuselage that the design of propulsion system is installed, reduce the quality of rotor nacelle, the influence of line shaft for wing crossbeam rigidity also obviously lowered in the designing requirement that can alleviate the wing crossbeam, the use of elasticity shaft joint;

(5) can artificially set gyroplane rotate speed Changing Pattern and the nacelle rule of verting through servomotor, simple to operation, and safe, can be good at carrying out wing/rotor gas bullet test and analyze.

Description of drawings

Fig. 1 is a three-dimensional combination synoptic diagram of the present invention;

Fig. 2 is the structural representation of medium power drive unit of the present invention;

Fig. 3 is the external structure of wing among the present invention;

Fig. 4 is the cut-away view of wing among the present invention;

Fig. 5 is the synoptic diagram that is connected of driving mechanism and tilting rotor nacelle of verting among the present invention;

Fig. 6 is the inner structure synoptic diagram of tilting rotor nacelle among the present invention;

Fig. 7 is the partial sectional view that driving mechanism is connected with the tilting rotor nacelle that verts among the present invention;

Fig. 8 is the assembled sectional view of sliding plate mechanism among the present invention;

Fig. 9 is the vertical view of sliding plate mechanism among the present invention;

Figure 10 is the synoptic diagram of rotor among the present invention.

Embodiment

Below with conjunction with figs., syndeton of the present invention and principle of work are elaborated.

At first with reference to shown in Figure 1; The present invention provides a kind of half exhibition long tilting rotor gas springing mechanics integrated test platform, comprises wing 1, the driving mechanism 2 that verts, tilting rotor nacelle 3 and Power Drive Unit 4, wherein; Power Drive Unit 4 is located at an end of wing 1; The other end of wing 1 then connects the driving mechanism 2 that verts, and the said driving mechanism 2 that verts also connects tilting rotor nacelle 3, and drives 3 rotations of tilting rotor nacelle.

As shown in Figure 2; Power Drive Unit 4 comprises pedestal 41, motor 42, location-plate 43 and flange 44, and wherein, pedestal 41 is immobilizing foundations of whole test platform; Motor 42 adopts the AC servo motor of 5kW; And fixing with location-plate 43, and location-plate 43 is connected with pedestal 41, thus motor 42 is fixed on the pedestal 41; Flange 44 also is installed on the output shaft of motor 42, is used for outputting power.

Fig. 3 and Fig. 4 show the structure of wing 1 among the present invention; Described wing 1 mainly comprises dimension shape shell 11, main load-bearing part 12, crossbeam 13, transmission shaft, two

flanges

15,16, reinforcement rib 17 and panel beating ribs 18; Main load-bearing part 12 is installed on the pedestal 41 of Power Drive Unit 4 through cushion block 121; Also be located on the main load-bearing part 12 and strengthen rib 17, be used to carry the oscillating load that transmission shaft produces; One end of crossbeam 13 and described main load-bearing part 12 is fixing, sees Fig. 3, and arranges successively on this crossbeam 13 a plurality of (showing 7 among Fig. 4) panel beating rib 18 is installed, and flange is all formed on the top of this panel beating rib 18, is used for supporting dimension shape shell 11; Transmission shaft passes described panel beating rib 18 successively and strengthens rib 17; Particularly; In the present embodiment, described transmission shaft is to be formed by connecting 3 rotating shafts 141, connects by elasticity shaft joint 142 between the adjacent shafts 141; Transmission shaft is designed to the structure that segmentation connects; Help under wing 1 stressed diastrophic situation transmitting the rotation output of motor 42, and strengthening being respectively equipped with the bearing cup 143 that has self-aligning bearing on rib 17 and the suitable panel beating rib 18, described transmission shaft passes this bearing cup 143 successively; Two

flanges

15,16 are located at the two ends of transmission shaft respectively, and wherein, flange 15 is connected with the flange 44 of Power Drive Unit 4, and another flange 16 is connected with power input shaft 23 in the driving mechanism 2 that verts; Dimension shape shell 11 is erected on the flange of panel beating rib 18, is used to keep the aerodynamic configuration of wing 1.

Please refer to shown in Figure 5 again; It is the synoptic diagram that is connected of driving mechanism 2 and tilting rotor nacelle 3 of verting among the present invention; Wherein, The driving mechanism 2 that verts comprises fixed frame, the casing 22 that verts, power input shaft 23, worm-and-wheel gear 24, vert control motor 25, gear shaft 26 and the fluted disc 27 that verts, and wherein, cooperates shown in Figure 7; Fixed frame comprises fixture 211 and is divided into the reinforcement rib 212 at fixture 211 both ends, and on the crossbeam 13 of fixture 211 and wing 1 relatively an end of main load-bearing part 12 be connected; The casing 22 that verts is cylindrical structural, is installed on the fixed frame, and can in fixed frame, rotates, and its inner is passed two successively through deep groove ball bearing 221 and strengthened rib 212, and the outer end connects tilting rotor nacelle 3 respectively and verts fluted disc 27 through bolt; In addition; Also be provided with a pair of brake block 213 on the fixed frame, the arch section of this brake block 213 can be embraced the casing 22 that verts, like this when verting the test of nacelle fixed angle; Compress brake block 213 through bolt, can improve tilting rotor nacelle 3 security at the trial.

Power input shaft 23 runs through the casing 22 that verts, and stretches out in two reinforcement ribs 212, and the one of which end is by the flange 16 of flange connection wing 1, and the other end then penetrates tilting rotor nacelle 3, thereby power is imported the communtation deceleration device in the tilting rotor nacelle 3; Can in the casing 22 that verts, freely rotate in order to ensure power input shaft 23; Also between the two, be provided with a pair of single-row tapered roller bearing 222; And this single-row tapered roller bearing 222 also but the string of restricted power input shaft 23 is moving; And between the end of single-row tapered roller bearing 222 and power input shaft 23, be provided with thrust bearing 223, like this, single-row tapered roller bearing 222 can be with transverse vibration loading transfer to the thrust bearing 223 of power input shaft 23; And finally affact on the reinforcement rib 212, carry by fixed frame.

Worm-and-wheel gear 24 is installed on the fixture 211; The control motor 25 that verts is located on the worm-and-wheel gear 24; Be used to drive worm-and-wheel gear 24; And gear shaft 26 is connected worm-and-wheel gear 24 and vert between the fluted disc 27, under the motion of worm-and-wheel gear 24, drives the fluted disc 27 that verts and rotates.

As shown in Figure 6, tilting rotor nacelle 3 comprises nacelle casing 31, communtation deceleration device, rotor 33, sliding plate mechanism 34 and rotor shaft 35, wherein; The communtation deceleration device is located at the inside of nacelle casing 31; Described communtation deceleration device is made up of a pair of arc umbrella tooth 321, and the one of which end connects the power input shaft 23 of the driving mechanism 2 that verts, and the other end connects the rotor shaft 35 of rotor 33; The moment of torsion switching-over of power input shaft 23 is passed to rotor shaft 35, rotates to drive rotor 33; The outside of said nacelle casing 31 also is provided with the shell 311 that compound substance is processed, and sees shown in Figure 5.

Sliding plate mechanism 34 is used to regulate pitch, is installed on the nacelle casing 31, connects rotor 33 through pitch-change-link 335; Total distance in order to blade 332 on the control rotor 33; Cooperate Fig. 8 and shown in Figure 9, described sliding plate mechanism 34 comprises installing sleeve 341, not rotating ring 342, clamping plate 343, connecting rod 344, rotating ring 345 and spherical plain bearing rod end 346, wherein; Installing sleeve 341 is fixed on the nacelle casing 31; Rotor shaft 35 is passed this installing sleeve 341, and is positioned in the installing sleeve 341 by deep groove ball bearing, makes rotor shaft 35 in installing sleeve 341, to rotate; Rotating ring 342 is not located on the installing sleeve 341, and can on installing sleeve 341, slide or locate; Rotating ring 345 is set in not on the rotating ring 342 rotationally, and this rotating ring 345 is also through connecting rod 344 connecting cleats 343, and these clamping plate 343 can be by clamping rotor shaft 35 after the bolted; On the overhanging pawl of said rotating ring 345 spherical plain bearing rod end 346 is installed also, this spherical plain bearing rod end 346 connects pitch-change-links 335, like this, through sliding up and down of rotating ring 342 not, total distance of regulating blade 332 on the rotor 33.

In addition, collector ring mounting bracket 312 is installed also on the nacelle casing 31, this collector ring mounting bracket 312 is used for fixing the collector ring 313 of image data.

Please refer to shown in Figure 10 again; Rotor 33 mainly comprises propeller hub head 331 and blade 332, and wherein, propeller hub head 331 is connected with blade 332 through pitch hinge 333; And this pitch hinge 333 also connects pitch-change-link 335 through distance-variable rocker arm 334; According to the difference of test demand, can change different propeller hub heads, carry out the experimental study of different rotor forms.

Above embodiment is merely explanation technological thought of the present invention, can not limit protection scope of the present invention with this, every technological thought that proposes according to the present invention, and any change of on the technical scheme basis, being done all falls within the protection domain of the present invention.

Claims

1. one and half open up long tilting rotor gas springing mechanics integrated test platform; It is characterized in that: comprise wing (1), the driving mechanism that verts (2), tilting rotor nacelle (3) and Power Drive Unit (4); Wherein, Power Drive Unit (4) is located at an end of wing (1), and the other end of wing (1) then connects the driving mechanism that verts (2); The said driving mechanism that verts (2) also connects tilting rotor nacelle (3), and drives tilting rotor nacelle (3) rotation.

2. the long tilting rotor gas springing mechanics integrated test platform of half exhibition as claimed in claim 1; It is characterized in that: said Power Drive Unit (4) comprises pedestal (41), motor (42), location-plate (43) and first flange (44); Wherein, Motor (42) is fixing with location-plate (43), and location-plate (43) is connected with pedestal (41), and first flange (44) also is installed on the output shaft of motor (42).

3. the long tilting rotor gas springing mechanics integrated test platform of half exhibition as claimed in claim 2; It is characterized in that: said wing (1) comprises air-foil hull shape section (11), main load-bearing part (12), crossbeam (13), transmission shaft and second and third flange (15), (16); Wherein, Main load-bearing part (12) is installed on the pedestal (41) of Power Drive Unit (4) through cushion block (121); One end of crossbeam (13) and described main load-bearing part (12) are fixing, and transmission shaft is fixing with crossbeam (13), main load-bearing part (12) rotationally, and second and third flange (15), (16) are located at the two ends of transmission shaft successively; And second flange (15) is connected with first flange (44) of Power Drive Unit (4), and the 3rd flange (16) is connected with power input shaft (23) in the driving mechanism that verts (2); Air-foil hull shape section (11) is erected on the crossbeam (13).

4. the long tilting rotor gas springing mechanics integrated test platform of half exhibition as claimed in claim 3; It is characterized in that: said wing (1) comprises that also one strengthens rib (17) and a plurality of panel beating rib (18); Strengthening rib (17) is located on the main load-bearing part (12); And panel beating rib (18) is arranged successively and is installed on the crossbeam (13), and flange is formed on the top of this panel beating rib (18), and air-foil hull shape section (11) is erected on this flange.

5. the long tilting rotor gas springing mechanics integrated test platform of half exhibition as claimed in claim 4, it is characterized in that: said transmission shaft comprises at least two interconnective rotating shafts (141), connects by elasticity shaft joint (142) between the adjacent shafts (141); Be respectively equipped with the bearing cup (143) that has self-aligning bearing on said reinforcement rib (17) and at least one the panel beating rib (18), transmission shaft pass described bearing cup (143) successively and with crossbeam (13), main load-bearing part (12) installing and locating.

6. the long tilting rotor gas springing mechanics integrated test platform of half exhibition as claimed in claim 3 is characterized in that: the said driving mechanism that verts (2) comprises fixed frame, the casing that verts (22), power input shaft (23), worm-and-wheel gear (24), vert and control motor (25), gear shaft (26) and the fluted disc that verts (27); Fixed frame is connected with the end that wing (1) crossbeam (13) is gone up relative main load-bearing part (12); The casing (22) that verts is a cylindrical structural; Be installed in rotation on the fixed frame, and the outer end of this casing that verts (22) connects tilting rotor nacelle (3) and the fluted disc that verts (27) respectively; Power input shaft (23) runs through the casing that verts (22), and the one of which end is by the 3rd flange (16) of the 4th flange connection wing (1), and the other end then penetrates tilting rotor nacelle (3); Worm-and-wheel gear (24) is installed on the fixed frame; The control motor (25) that verts is installed on the worm-and-wheel gear (24); And gear shaft (26) is connected between worm-and-wheel gear (24) and the fluted disc that verts (27), under the motion of worm-and-wheel gear (24), drives the fluted disc (27) that verts and rotates.

7. the long tilting rotor gas springing mechanics integrated test platform of half exhibition as claimed in claim 6 is characterized in that: also be provided with a pair of brake block (213) that can embrace the casing that verts (22) by arch section on the said fixed frame.

8. the long tilting rotor gas springing mechanics integrated test platform of half exhibition as claimed in claim 6; It is characterized in that: said tilting rotor nacelle (3) comprises nacelle casing (31), communtation deceleration device, rotor (33), sliding plate mechanism (34) and rotor shaft (35); Wherein, The communtation deceleration device is located at the inside of nacelle casing (31), and the one of which end connects the power input shaft (23) of driving mechanism (2) of verting, and the other end connects the rotor shaft (35) of rotor (33); The outside of said nacelle casing (31) also is provided with the shell (311) that compound substance is processed; Sliding plate mechanism (34) is installed on the nacelle casing (31), connects rotor (33) through pitch-change-link (335); Rotor (33) comprises propeller hub head (331) and blade (332), and propeller hub head (331) is connected with blade (332) through pitch hinge (333), and this pitch hinge (333) also connects pitch-change-link (335) through distance-variable rocker arm (334).

9. the long tilting rotor gas springing mechanics integrated test platform of half exhibition as claimed in claim 8 is characterized in that: the collector ring mounting bracket (312) that is used for fixing collector ring (313) also is installed on the said nacelle casing (31).

10. the long tilting rotor gas springing mechanics integrated test platform of half exhibition as claimed in claim 8; It is characterized in that: said sliding plate mechanism (34) comprises installing sleeve (341), not rotating ring (342), clamping plate (343), connecting rod (344), rotating ring (345) and spherical plain bearing rod end (346); Wherein, Installing sleeve (341) is fixed on the nacelle casing (31), and rotor shaft (35) is passed this installing sleeve (341), and is positioned in the installing sleeve (341) by deep groove ball bearing; Rotating ring (342) is not located on the installing sleeve (341), and can go up at installing sleeve (341) and slide or the location; Rotating ring (345) is set in not on the rotating ring (342) rotationally, and also through connecting rod (344) connecting cleat (343), these clamping plate (343) are by clamping rotor shaft (35) after the bolted for this rotating ring (345); Spherical plain bearing rod end (346) also is installed on the overhanging pawl of said rotating ring (345), and this spherical plain bearing rod end (346) connects pitch-change-link (335).