CN202853875U - Reusable aircraft model experimental device capable of changing shape and parameters - Google Patents
Reusable aircraft model experimental device capable of changing shape and parameters Download PDFInfo
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- CN202853875U CN202853875U CN 201220490504 CN201220490504U CN202853875U CN 202853875 U CN202853875 U CN 202853875U CN 201220490504 CN201220490504 CN 201220490504 CN 201220490504 U CN201220490504 U CN 201220490504U CN 202853875 U CN202853875 U CN 202853875U
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Abstract
The utility model discloses a reusable aircraft model experimental device capable of changing shape and parameters. The reusable aircraft model experimental device comprises a bracket structure for supporting an aircraft model, a fuselage structure with a variable length, a body shell fairing and a control box. The bracket structure for supporting the aircraft model comprises a lower bracket, a motor, a hydraulic actuating cylinder and an upper bracket. The fuselage structure with the variable length comprises a middle grid trough girder, a front grid trough girder, a back grid trough girder, a fuselage balance and a tail balance. By employing the aircraft model experiment device, a front fuselage length can be changed through adjusting a card installation position between the front grid trough girder and the middle grid trough girder, a back fuselage length can be changed through adjusting an installation position of the back grid trough girder on the tail balance, and the change of an aircraft model fuselage length is realized. Through installing fuselage fairing with different shaped and layouts externally, the construction of different aircraft experimental models is realized.
Description
Technical field
The utility model relates to a kind of bath scaled model experimental device, is specially a kind of reused model aircraft experimental provision that changes profile and parameter.
Background technology
In the Design and manufacture process, often need to do wind tunnel experiment and ground experiment at fixed wing aircraft and rotary wing aircraft, be to save cost, and wind tunnel experiment and ground experiment often adopt model aircraft to come the Reality simulation aircraft.The new ideas aircraft usually needs its gordian technique is verified that the process of checking usually is to take the model aircraft with this new ideas aircraft key feature to test.
The model aircraft that adopts at present mostly is greatly wooden or the disposable model aircraft of metal-made, not reproducible utilization, and profile and parameter can not change fast.When aircraft carries out great many of experiments, and need to change design parameter according to experimental result the time, need to again process new model aircraft, cause with high costsly, experimental period is long, the resource significant wastage.
Summary of the invention
The technical matters that solves
In order to solve existing model aircraft profile and parameter change difficulty, the problem that can not reuse, the utility model proposes a kind of reused model aircraft experimental provision that changes profile and parameter, can change fast aerodynamic arrangement's form of aircraft, various parameters and profile, and can obtain respectively the experimental data of each parts.
Technical scheme
The technical solution of the utility model is:
Described a kind of reused model aircraft experimental provision that changes profile and parameter is characterized in that: comprise for the supporting structure that supports model aircraft, the airframe structure of variable-length, fuselage cover radome fairing and control enclosure; The fuselage cover radome fairing is enclosed within the airframe structure outside of variable-length; Control enclosure control gathers the support angle of balance data and supporting structure;
Described supporting structure for supporting model aircraft comprises lower carriage, motor, hydraulic actuator and upper bracket, the lower carriage lower end is fixed on the stationary plane, the airframe structure of variable-length is supported in the upper bracket upper end, the lower carriage upper end is connected by rotating shaft with the upper bracket lower end, the driven by motor hydraulic actuator drives upper bracket and rotates around the axis, thereby changes the support angle of supporting structure;
The airframe structure of described variable-length comprises middle part grid beam channel, anterior grid beam channel, rear portion grid beam channel, the gentle empennage balance in fuselage sky; The gentle empennage balance in described fuselage sky is the six degree of freedom balance, and the fuselage balance is fixedly mounted on the fuselage balance web joint, and described fuselage balance web joint is fixed in the upper bracket upper end; Fuselage balance top is fixed with empennage balance web joint, and the empennage balance is fixedly mounted on the empennage balance web joint; Middle part grid beam channel, anterior grid beam channel and rear portion grid beam channel are vertical symmetrical structure, and vertical plane of symmetry of middle part grid beam channel, anterior grid beam channel and rear portion grid beam channel overlaps; Middle part grid beam channel is connected by card is installed in grid with anterior grid beam channel; The tail end of middle part grid beam channel is useful on the hollow structure of placing the empennage balance; The empennage sky is flat in the described hollow structure, does not contact with middle part grid beam channel; The front end of rear portion grid beam channel is fixedly connected on empennage balance top.
Described a kind of reused model aircraft experimental provision that changes profile and parameter, it is characterized in that: the tail end of rear portion grid beam channel is fixed with the empennage installing plate; Be installed with symmetrical variable empennage system on the empennage installing plate.
Described a kind of reused model aircraft experimental provision that changes profile and parameter is characterized in that: described variable empennage system includes tailplane, vertical tail and angle controller, and vertical tail and tailplane form T-shaped tail structure; The vertical tail lower end is fixed on the empennage installing plate, and angle controller is installed on the vertical tail, the deflection angle of control tailplane; The angle controller front portion is fixed with the anterior radome fairing of empennage, and the angle controller rear portion is equipped with empennage rear portion radome fairing.
Described a kind of reused model aircraft experimental provision that changes profile and parameter, it is characterized in that: the front end of anterior grid beam channel is fixed with the canard installing plate; Be installed with symmetrical variable canard system on the canard installing plate; Described variable canard system includes two canards and two angle controllers, and angle controller is positioned at two canard centre positions, and is fixed on the canard installing plate; Each angle controller is controlled respectively the deflection angle of a slice canard.
Described a kind of reused model aircraft experimental provision that changes profile and parameter, it is characterized in that: described angle controller comprises angular adjustment handle, worm-and-wheel gear and angle turning axle, the angular adjustment handle is fixedly connected with worm screw is coaxial, worm gear is fixedly connected with the angle rotating shaft coaxle, the affixed deflection aerofoil of angle turning axle.
Described a kind of reused model aircraft experimental provision that changes profile and parameter is characterized in that: also include rotorjet system and rotor balances; Rotor balances are the six degree of freedom balance; Rotor balances are fixedly mounted on the fuselage balance web joint; The rotorjet system passes middle part grid beam channel and is fixedly connected with rotor balances top, and rotor balances all do not contact with middle part grid beam channel with the rotorjet system.
Beneficial effect
The model aircraft experimental provision that employing the utility model proposes, by adjusting the card installation site between anterior grid beam channel and the middle part grid beam channel, can adjust forward fuselage length, by adjusting rear portion grid beam channel in the installation site on empennage balance top, can adjust the rear portion fuselage length, realize the variation of model aircraft fuselage length, and by forwardly the fuselage radome fairing of different profiles and layout is installed, the aircraft empirical model that the realization structure is different in grid beam channel, middle part grid beam channel and rear portion grid beam channel outside.
The utility model adopts variable empennage system, can realize the different empennage distribution forms such as conventional empennage layout, lower vertical fin empennage layout, vee tail layout, H type tail layout, T-shaped empennage layout, and realize the deflection of movable aerofoil in the empennage system by angle controller.
The utility model has also adopted rotorjet system and rotor balances, can realize the model aircraft of structural belt rotor: in the situation that rotor does not rotate, can be assembled into normal configuration: namely without canard, only have main wing and empennage, also can be assembled into the Three-wing-surface layout: namely canard, main wing and empennage have; In the situation that rotor rotates, can be assembled into the helicopter type layout: namely without canard and empennage, only have rotor to rotate, also can be assembled into compound lifting body formula layout: existing rotor rotates, have again canard or empennage or both.
Adopt the utility model, the parameter of canard, empennage and rotor, profile can both change, and the relative installation of fuselage length and canard, empennage, rotor is all variable, can be suitable for the model experiment of all kinds aircraft, and critical piece need not be changed, and saves cost and experimental period.
Adopt the utility model, the power that rotor produces can be measured separately, and the power that empennage produces can be measured separately, and the long-living power of canard can calculate out by the power that the fuselage balance is measured, and can be used for studying the characteristic of different parts power, and influencing each other between each parts.
Description of drawings
Fig. 1: the structural representation that is used for the supporting structure of support model aircraft;
Fig. 2: the structural representation of the airframe structure of variable-length;
Fig. 3: the structural representation of the airframe structure of variable-length;
Fig. 4: the structural representation of rotorjet system;
Fig. 5: the structural representation of variable canard system;
Fig. 6: the structural representation of angle control enclosure;
Fig. 7: the structural representation of the anterior radome fairing of variable empennage system's removal empennage;
Fig. 8: the structural representation of variable empennage system;
Fig. 9: the structural representation of six degree of freedom balance;
Figure 10: the model structure synoptic diagram of T-shaped tail structure;
Figure 11: the model structure synoptic diagram of vee tail structure;
Figure 12: the model structure synoptic diagram of conventional tail wing structure;
Figure 13: the model structure synoptic diagram of H type tail structure;
Figure 14: the model structure synoptic diagram of lower vertical fin tail structure;
Wherein: 1, box-like lower carriage; 2, box-like upper bracket; 3, hydraulic actuator; 4, direct current generator; 5, rotor balances; 6, fuselage balance; 7, middle part grid beam channel; 8, control enclosure; 9, rear portion grid beam channel; 10, anterior grid beam channel; 11, empennage balance; 12, fuselage balance web joint; 13, anterior web joint; 14, control enclosure installing plate; 15, empennage balance web joint; 16, canard installing plate; 17, empennage installing plate; 18, blade tip jet blade; 19, speed probe; 20, wing drop dish; 21, pressurized strut; 22, rotor mounting bracket; 23, main shaft; 24, gas pipe line; 25, canard; 26, angle controller; 27, bearing (ball) cover; 28, the outer box of angle controller; 29, angular adjustment handle; 30, deep groove ball bearing; 31, worm screw; 32, angle turning axle; 33, worm gear; 34, tailplane; 35, vertical tail; 36, yaw rudder; 37, yaw rudder turning axle; 38, vertical tail stationary shaft; 39, empennage rear portion radome fairing; 40, the anterior radome fairing of empennage.
Embodiment
Below in conjunction with specific embodiment the utility model is described:
Present embodiment is a kind of reused model aircraft experimental provision that can change fast profile and parameter, comprise for the supporting structure that supports model aircraft, the airframe structure of variable-length, fuselage cover radome fairing and control enclosure 8, the fuselage cover radome fairing is enclosed within the airframe structure outside of variable-length, and control enclosure control gathers the support angle of balance data and supporting structure; In addition, this model aircraft experimental provision also includes variable empennage system, variable canard system, rotorjet system and rotor balances 5.
With reference to accompanying drawing 1, described supporting structure for supporting model aircraft comprises box-like lower carriage 1, direct current generator 4, hydraulic actuator 3 and box-like upper bracket 2, ground is fixed in by 4 foot bolt in box-like lower carriage 1 lower end, the side has the installation of 250mm * 250mm dull and stereotyped, direct current generator 4 and hydraulic actuator 3 are bolted to by 4 and install on the flat board, and hydraulic actuator top links to each other with bearing by axle with box-like upper bracket; Box-like upper bracket top links to each other with the fuselage balance web joint 12 of model aircraft airframe structure by 6 bolts, supports the airframe structure of variable-length, and box-like upper bracket bottom links to each other with box-like lower carriage 1 with deep groove ball bearing by axle; When needs change the model aircraft luffing angle, direct current generator drive hydraulic actuator drives box-like upper bracket and rotates around the connection rotating shaft with box-like lower carriage, thereby change the support angle of supporting structure, namely change the luffing angle of model aircraft, thereby can measure the get off the plane characteristic of model of different luffing angles.
With reference to accompanying drawing 2 and accompanying drawing 3, the airframe structure of described variable-length comprises middle part grid beam channel 7, anterior grid beam channel 10, rear portion grid beam channel 9, fuselage balance 6 and empennage balance 11.
Described fuselage balance, the gentle rotor balances in empennage sky are general six degree of freedom balance: in mutually perpendicular three directions strong sensor and torque sensor are installed, can measure the force and moment of these three direction six degree of freedoms, the balance upper and lower is flat board, have the series installation hole, be convenient to install.
Rotor balances 5 and fuselage balance 6 are fixedly connected on the fuselage balance web joint 12 by 4 bolts, and fuselage balance web joint 12 is fixedly connected on the box-like upper bracket 1 of model aircraft supporting structure by 6 bolts.Empennage balance web joint 15 is fixedly connected on fuselage balance 6 tops by 4 bolts, and the empennage balance is fixedly mounted on the empennage balance web joint by 4 bolts.
Middle part grid beam channel, anterior grid beam channel and rear portion grid beam channel are vertical symmetrical structure, and vertical plane of symmetry of middle part grid beam channel, anterior grid beam channel and rear portion grid beam channel overlaps, and this vertical plane of symmetry is vertical plane of symmetry of model aircraft.Middle part grid beam channel is connected by card is installed in grid with anterior grid beam channel, changes the installation site of card in different grids, i.e. capable of regulating forward fuselage length.The tail end of middle part grid beam channel is useful on the hollow structure of placing the empennage balance, and the empennage sky is flat in the described hollow structure, and does not contact with middle part grid beam channel, and what guaranteed the empennage balance measurement is the power that empennage produces.The front end of rear portion grid beam channel is fixedly connected on the bolt hole on empennage balance top by 4 bolts, by regulating rear portion grid beam channel front end in different set bolt hole site, empennage balance top, can adjust the rear portion fuselage length.Control enclosure installing plate 14 is welded on the middle upper rear end of middle part grid beam channel, and control enclosure 8 is installed on the control enclosure installing plate 14 by 4 bolts, the control of rotation, 3 balance measurement data acquisitions and each variable-angle of control enclosure control rotor.
The tail end of rear portion grid beam channel is welded with the empennage installing plate, is installed with symmetrical variable empennage system on the empennage installing plate.Described variable empennage system is different according to distribution form; its parts that comprise are also different; for example T-shaped empennage layout comprises tailplane 34; vertical tail 35; yaw rudder 36; yaw rudder turning axle 37; vertical tail stationary shaft 38; empennage rear portion radome fairing 39; the anterior radome fairing 40 of empennage and angle controller 26; tailplane links to each other with angle controller; can adjust the angle of attack of tailplane; tailplane is replaceable; can measure the characteristic of not stopping the profile tailplane; angle controller is fixed on the vertical tail; empennage rear portion radome fairing and the anterior radome fairing of empennage are installed in the outside of angle control enclosure; it is inner at radome fairing with the angle controller protection; and the rectified action that can play; vertical tail and vertical tail stationary shaft weld together; by bolt the vertical tail stationary shaft is fixed on the empennage installing plate; yaw rudder and yaw rudder turning axle weld together; yaw rudder links to each other by hinge with vertical tail; regulate the yaw rudder turning axle and then can regulate the drift angle of yaw rudder; characteristic under the different drift angles of energy direction of measurement rudder, other applicable distribution forms also have conventional empennage layout; lower vertical fin empennage layout; the vee tail layout; H type tail layout etc.
The front end of anterior grid beam channel is fixed with the canard installing plate, is installed with symmetrical variable canard system on the canard installing plate.Described variable canard system includes two canards and two angle controllers, and angle controller is positioned at two canard centre positions, and is weldingly fixed on the canard installing plate; Each angle controller is controlled respectively the deflection angle of a slice canard.Canard can be changed, and can measure the characteristic of different profile canards.
With reference to accompanying drawing 6, angle controller in the present embodiment comprises angular adjustment handle, worm-and-wheel gear and angle turning axle, angular adjustment handle 29 and worm screw 31 coaxial fixedly welding, and with deep groove ball bearing 30 supporting, worm gear 33 and the 32 coaxial fixedly welding of angle turning axle, and with deep groove ball bearing 30 supporting.In inside, the deep groove ball bearing 30 that porose mounting support is used it on outsidely adds top bearing cover 27 by 6 screws deep groove ball bearing 30 is fixed the outer box 28 of angle controller with the turbine and worm device protection of inside.The affixed deflection aerofoil of angle turning axle, by the rotational angle adjusting handle, drive the worm screw rotation, worm screw drives the worm gear rotation, the rotation of worm gear drives angle turning axle, angle turning axle and deflection aerofoil are affixed, and then the deflection aerofoil is driven rotation, regulate the angle of attack of deflection aerofoil (such as canard or tailplane).
With reference to accompanying drawing 4, described rotorjet system comprises blade tip jet blade 18, speed probe 19, wing drop dish 20, pressurized strut 21, rotor mounting bracket 22, main shaft 23, gas pipe line 21.Gas pipe line 21 is placed in the supporting structure of model aircraft, it links to each other by the flange that 6 screw holes are arranged with main shaft 23, main shaft 23 is tubular shaft, link to each other by screw with the blade tip jet blade 18 on top, the air that gas pipe line is carried enters the blade tip jet blade by hollow spindle, drive the rotation of blade tip jet blade, the rotor mounting bracket is installed at the main shaft middle part, flange arrangement is arranged at rotor mounting bracket bottom, be fixed on the rotor balances with flange arrangement by screw, main shaft top is equipped with the blade tip jet blade from top to bottom successively, speed probe and auto-bank unit, the replaceable characteristic of measuring different profile blades of blade tip jet blade, its inner passage links to each other with the inner gas pipe line of main shaft, and speed probe is fixed on main shaft top, blade tip jet blade below, be used for measuring gyroplane rotate speed, auto-bank unit is used for total distance of blade tip jet blade, feathering control, hydraulic actuator links to each other with auto-bank unit, is used for the control auto-bank unit.
Rotor balances top links to each other with the rotorjet system, and does not link to each other with airframe structure, guarantees the power of only having rotor to produce that rotor balances are measured, the fuselage balance measurement be the power that whole model aircraft produces except rotor.
This device canard 25, tailplane 34 and blade tip jet blade 18 can be replaced by the parts of different profiles, can be by the characteristic of the different outer appearance part of 6DOF balance measurement, the angle of attack of canard 25 and tailplane 34 changes by angle controller 26, rotational angle adjusting handle 21, then worm screw 31 is rotated.Worm screw 31 drives worm gear 33 by turbine and worm mechanism and rotates, and then angle turning axle 32 corresponding rotations can be regulated the angle of attack of canard 25 and tailplane 34.
The fuselage length of this device is variable, by changing the length of forward fuselage, can change the relative position of canard 25 and remaining part, be installed in the different bolt hole of empennage balance 11 by changing rear portion grid beam channel 9, can change the length of rear portion fuselage, the relative position of empennage system and remaining part can be changed, the characteristic of different each parts of relative position can be measured.
The top of the rotor balances 5 of this device only links to each other with the rotorjet system, do not link to each other with variable fuselage length structure, then can measure separately the power of rotorjet system, empennage balance 11 tops only link to each other with rear portion grid beam channel 9, then can measure separately the power that the empennage system produces, the power on the whole model aircraft except the rotorjet system that fuselage balance 6 is measured then can calculate the power that produces on the canard 25.
Claims (6)
1. the reused model aircraft experimental provision that can change profile and parameter is characterized in that: comprise for the supporting structure that supports model aircraft, the airframe structure of variable-length, fuselage cover radome fairing and control enclosure; The fuselage cover radome fairing is enclosed within the airframe structure outside of variable-length; Control enclosure control gathers the support angle of balance data and supporting structure;
Described supporting structure for supporting model aircraft comprises lower carriage, motor, hydraulic actuator and upper bracket, the lower carriage lower end is fixed on the stationary plane, the airframe structure of variable-length is supported in the upper bracket upper end, the lower carriage upper end is connected by rotating shaft with the upper bracket lower end, the driven by motor hydraulic actuator drives upper bracket and rotates around the axis, thereby changes the support angle of supporting structure;
The airframe structure of described variable-length comprises middle part grid beam channel, anterior grid beam channel, rear portion grid beam channel, the gentle empennage balance in fuselage sky; The gentle empennage balance in described fuselage sky is the six degree of freedom balance, and the fuselage balance is fixedly mounted on the fuselage balance web joint, and described fuselage balance web joint is fixed in the upper bracket upper end; Fuselage balance top is fixed with empennage balance web joint, and the empennage balance is fixedly mounted on the empennage balance web joint; Middle part grid beam channel, anterior grid beam channel and rear portion grid beam channel are vertical symmetrical structure, and vertical plane of symmetry of middle part grid beam channel, anterior grid beam channel and rear portion grid beam channel overlaps; Middle part grid beam channel is connected by card is installed in grid with anterior grid beam channel; The tail end of middle part grid beam channel is useful on the hollow structure of placing the empennage balance; The empennage sky is flat in the described hollow structure, does not contact with middle part grid beam channel; The front end of rear portion grid beam channel is fixedly connected on empennage balance top.
2. a kind of reused model aircraft experimental provision that changes profile and parameter according to claim 1, it is characterized in that: the tail end of rear portion grid beam channel is fixed with the empennage installing plate; Be installed with symmetrical variable empennage system on the empennage installing plate.
3. a kind of reused model aircraft experimental provision that changes profile and parameter according to claim 2, it is characterized in that: described variable empennage system includes tailplane, vertical tail and angle controller, and vertical tail and tailplane form T-shaped tail structure; The vertical tail lower end is fixed on the empennage installing plate, and angle controller is installed on the vertical tail, the deflection angle of control tailplane; The angle controller front portion is fixed with the anterior radome fairing of empennage, and the angle controller rear portion is equipped with empennage rear portion radome fairing.
4. according to claim 1 or 3 described a kind of reused model aircraft experimental provisions that change profile and parameter, it is characterized in that: the front end of anterior grid beam channel is fixed with the canard installing plate; Be installed with symmetrical variable canard system on the canard installing plate; Described variable canard system includes two canards and two angle controllers, and angle controller is positioned at two canard centre positions, and is fixed on the canard installing plate; Each angle controller is controlled respectively the deflection angle of a slice canard.
5. a kind of reused model aircraft experimental provision that changes profile and parameter according to claim 3, it is characterized in that: described angle controller comprises angular adjustment handle, worm-and-wheel gear and angle turning axle, the angular adjustment handle is fixedly connected with worm screw is coaxial, worm gear is fixedly connected with the angle rotating shaft coaxle, the affixed deflection aerofoil of angle turning axle.
6. according to claim 1,2,3,5 arbitrary described a kind of reused model aircraft experimental provisions that change profile and parameter, it is characterized in that: also include rotorjet system and rotor balances; Rotor balances are the six degree of freedom balance; Rotor balances are fixedly mounted on the fuselage balance web joint; The rotorjet system passes middle part grid beam channel and is fixedly connected with rotor balances top, and rotor balances all do not contact with middle part grid beam channel with the rotorjet system.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220490504 CN202853875U (en) | 2012-09-24 | 2012-09-24 | Reusable aircraft model experimental device capable of changing shape and parameters |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220490504 CN202853875U (en) | 2012-09-24 | 2012-09-24 | Reusable aircraft model experimental device capable of changing shape and parameters |
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| CN202853875U true CN202853875U (en) | 2013-04-03 |
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| CN 201220490504 Withdrawn - After Issue CN202853875U (en) | 2012-09-24 | 2012-09-24 | Reusable aircraft model experimental device capable of changing shape and parameters |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102865993A (en) * | 2012-09-24 | 2013-01-09 | 西北工业大学 | Recyclable airplane model experimental facility capable of changing appearance and parameter |
| CN105181289A (en) * | 2015-09-14 | 2015-12-23 | 江西洪都航空工业集团有限责任公司 | Fairing for empennage wind tunnel testing |
| CN109932123A (en) * | 2019-03-22 | 2019-06-25 | 中国船舶科学研究中心（中国船舶重工集团公司第七0二研究所） | Propeller single-blade leaf determination of six components of foree device |
| CN110514386A (en) * | 2019-08-05 | 2019-11-29 | 中国航空工业集团公司哈尔滨空气动力研究所 | One kind being based on motor-driven ducted tail rotor experiment supporting device |
-
2012
- 2012-09-24 CN CN 201220490504 patent/CN202853875U/en not_active Withdrawn - After Issue
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102865993A (en) * | 2012-09-24 | 2013-01-09 | 西北工业大学 | Recyclable airplane model experimental facility capable of changing appearance and parameter |
| CN102865993B (en) * | 2012-09-24 | 2014-10-15 | 西北工业大学 | Recyclable airplane model experimental facility capable of changing appearance and parameter |
| CN105181289A (en) * | 2015-09-14 | 2015-12-23 | 江西洪都航空工业集团有限责任公司 | Fairing for empennage wind tunnel testing |
| CN109932123A (en) * | 2019-03-22 | 2019-06-25 | 中国船舶科学研究中心（中国船舶重工集团公司第七0二研究所） | Propeller single-blade leaf determination of six components of foree device |
| CN109932123B (en) * | 2019-03-22 | 2020-10-16 | 中国船舶科学研究中心（中国船舶重工集团公司第七0二研究所） | Propeller single-blade six-component measuring device |
| CN110514386A (en) * | 2019-08-05 | 2019-11-29 | 中国航空工业集团公司哈尔滨空气动力研究所 | One kind being based on motor-driven ducted tail rotor experiment supporting device |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20130403 Effective date of abandoning: 20141015 |
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| RGAV | Abandon patent right to avoid regrant |