CN209000276U - Four-degree-of-freedom helicopter Dynamic Flight Simulator - Google Patents
Four-degree-of-freedom helicopter Dynamic Flight Simulator Download PDFInfo
- Publication number
- CN209000276U CN209000276U CN201821463335.7U CN201821463335U CN209000276U CN 209000276 U CN209000276 U CN 209000276U CN 201821463335 U CN201821463335 U CN 201821463335U CN 209000276 U CN209000276 U CN 209000276U
- Authority
- CN
- China
- Prior art keywords
- rolling
- pivoted arm
- cockpit
- drive system
- yaw
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Landscapes
- Toys (AREA)
Abstract
The utility model discloses four-degree-of-freedom helicopter Dynamic Flight Simulator, space yaw, the simulation of three postures of rolling and pitching can be realized simultaneously under centrifugal field, while realizing overload simulation；Installing component on pivoted arm is by the way of centralized arrangement, balanced design method is wherein used, counterweight element is designed according to trim principle, and be mounted on pivoted arm, it is located at turn around the mass center of Dynamic Flight Simulator on axis, reduces simulator because vibrating caused by imbalance；The rotary inertia that Dynamic Flight Simulator is reduced using asymmetric pivoted arm structure, reduces the energy consumption of Dynamic Flight Simulator；The use of gear unit, avoiding the vibration of main decelerating motor from being transferred directly to pivoted arm causes entire Dynamic Flight Simulator vibration excessive, and the out-of-balance force of pivoted arm and pivoted arm installing component passes to civil engineering part by gear unit, enhances main decelerating motor operation stability.
Description
Technical field
The utility model belongs to helicopter dynamic flying analogue technique field, and in particular to four-degree-of-freedom helicopter dynamic flies
Row simulator.
Background technique
Four-degree-of-freedom helicopter Dynamic Flight Simulator is a kind of analog motion platform based on centrifuge, certainly by difference
It is synthesized by the movement spent with the variation of simulated flight person's spatial attitude, in ground environment Imitating helicopter free air anomaly flight appearance
State realizes the impression of the vision, vestibular and ontology of pilot's spatial disorientation, pilot is enable to have good spatial orientation
Power.
For in terms of simulator structure, centrifuge modelling device pivoted arm is connected with main motor at present, and pivoted arm is directly installed on master
On motor shaft, since main motor is connected with pivoted arm, main motor vibration is transferred directly in pivoted arm and cockpit structure, and cockpit is caused to shake
Move excessive, and the unbalanced load that pivoted arm and cockpit are formed reacts on main motor shaft, reduces the stability of motor.
In terms of realizing function for simulator, presently disclosed flight simulator is three free simulators, can be centrifuged
Rolling and pitching movement are provided for test specimen or trainer under the environment of field, but such device cannot provide yawing rotation；For can
The simulator of rolling, pitching and yawing rotation is provided for test specimen or trainer, which cannot provide realization centrifugal movement
Freedom degree, can only be moved under non-centrifugal field.
We has developed a kind of four-degree-of-freedom helicopter Dynamic Flight Simulator in order to solve problem above.
Summary of the invention
The purpose of this utility model is that solve the above-mentioned problems and provides a kind of four-degree-of-freedom helicopter dynamic and fly
Row simulator.
The utility model achieves the above object through the following technical schemes:
Four-degree-of-freedom helicopter Dynamic Flight Simulator, comprising:
For manned cockpit；
The pitching drive system of pitching motion is done for cockpit；
The rolling unit of rolling maneuver is done for cockpit；Rolling unit includes rolling drive system and rolling frame, and cockpit is logical
Pitching movement is done in rolling frame after crossing the connection of pitching drive system；
The yawing unit of yaw maneuver is done for cockpit；Yawing unit includes yaw drive system and yaw frame, rolling list
Member does yawing rotation in yaw frame after connecting by yaw drive system；
For providing centrifugal force for cockpit and cockpit being made to do the centrifugal unit of centrifugal action；Yawing unit and centrifugal unit
Act on end connection；The rotational plane of cockpit is vertical with the rotational plane of rolling frame, yaw the rotational plane of frame respectively with cockpit
The rotational plane of rotational plane and rolling frame is vertical.
Four-degree-of-freedom helicopter Dynamic Flight Simulator is driven by cockpit, centrifugal unit, rolling unit, yawing unit and pitching
Dynamic system composition, wherein centrifugal unit drives cockpit, rolling unit, yawing unit and the pitching drive system installed thereon, makes
Cockpit, rolling unit, yawing unit and pitching drive system rotate in its rotational plane, this is the first freedom degree；Yaw is single
In member, in cockpit, rolling unit and the pitching drive system that its yaw drive system drives yaw frame and is mounted on yaw frame
Rotation, this be the second freedom degree；In rolling unit, rolling frame is driven in its rolling drive system and is mounted on rolling frame
The rotation of cockpit and pitching drive system, this is third freedom degree；Pitching drive system driving cockpit is done in rolling frame turns shop
Which spreads, this is four-degree-of-freedom；Four-degree-of-freedom helicopter Dynamic Flight Simulator is moved with four-degree-of-freedom, can be in centrifugal field
It down while realizing space yaw, the simulation of three postures of rolling and pitching, while realizing overload simulation.
Specifically, centrifugal unit includes:
Main decelerating motor；
Gear unit；
Pivoted arm；The power output end of main decelerating motor and the power intake of gear unit connect, the power of gear unit
Output end is fixedly connected with the first end of pivoted arm；
Counterweight element；
Instrument room；Counterweight element and instrument room are installed in the first end top of pivoted arm, and yaw frame is mounted on the of pivoted arm
Two ends top.
Wherein main decelerating motor drives pivoted arm to make rotating motion by gear unit, and centrifugal movement is transferred to pivoted arm and pivoted arm
Installing component；Yawing unit is connect by yawing frame with centrifuge pivoted arm, realizes that centrifugal movement is transferred to yawing unit；On pivoted arm
Installing component by the way of centralized arrangement, wherein use balanced design method, according to trim principle design counterweight element, and
It is mounted on pivoted arm, is located at turn around the mass center of Dynamic Flight Simulator on axis, reduce simulator because shaking caused by imbalance
It is dynamic；The energy consumption of Dynamic Flight Simulator, drops in the rotary inertia that Dynamic Flight Simulator is reduced using asymmetric pivoted arm structure
It is low.
Further, gear unit includes:
Main shaft；The connection of one end of main geared motor output shaft and main shaft；
Bearing system；
Base；Base fixes on the ground, and the both ends side wall of main shaft is connect with the rotating part of bearing system, bearing system it is non-
Rotating part is fixed on base；The other end of main shaft is fixedly connected with the first end of pivoted arm.
The use of gear unit avoids the vibration of main decelerating motor from being transferred directly to pivoted arm and entire dynamic flying is caused to simulate
Device vibration is excessive, and the out-of-balance force of pivoted arm and pivoted arm installing component passes to civil engineering part by gear unit, enhances
Main decelerating motor operation stability.
Specifically, a bearing is installed, yaw drive system is mounted on the second end of pivoted arm, partially inside the second end of pivoted arm
The power output shaft of boat drive system is fixedly connected after the inner ring of bearing with the bottom of yaw frame.
Rotational power is provided by the component of yaw drive system for yaw frame and thereon, cockpit is allowed to carry out yawing rotation.
Specifically, it yaws and mounting platform and interface that promising rolling drive system provides is set on frame, rolling drive system
It is mounted on mounting platform, and is rotated by interface driver rolling frame.
Rotational power is provided by the component of rolling drive system for rolling frame and thereon, cockpit is allowed to carry out rolling movement.
Specifically, mounting platform and interface that promising pitching drive system provides, pitching drive system are set on rolling frame
It is mounted on mounting platform, and is rotated by interface driver cockpit.
Rotational power is provided for cockpit by pitching drive system, cockpit is allowed to carry out pitching movement.
The utility model has the beneficial effects that:
The four-degree-of-freedom helicopter Dynamic Flight Simulator of the utility model:
1, four-degree-of-freedom helicopter Dynamic Flight Simulator is by cockpit, centrifugal unit, rolling unit, yawing unit and pitching
Drive system composition, wherein centrifugal unit drives cockpit, rolling unit, yawing unit and the pitching drive system installed thereon,
Rotate cockpit, rolling unit, yawing unit and pitching drive system in its rotational plane, this is the first freedom degree；Yaw
In unit, it is in the cockpit, rolling unit and pitching driving that its yaw drive system drives yaw frame and is mounted on yaw frame
The rotation of system, this is the second freedom degree；In rolling unit, rolling frame is driven in its rolling drive system and is mounted on rolling frame
Cockpit and pitching drive system rotation, this be third freedom degree；Pitching drive system driving cockpit turns in rolling frame
Shop which, this be four-degree-of-freedom；Four-degree-of-freedom helicopter Dynamic Flight Simulator is moved with four-degree-of-freedom, can be centrifuged
It realizes space yaw, the simulation of three postures of rolling and pitching simultaneously off field, while realizing overload simulation.
2, wherein main decelerating motor is made rotating motion by gear unit driving pivoted arm, and centrifugal movement is transferred to pivoted arm and turns
Arm installing component；Yawing unit is connect by yawing frame with centrifuge pivoted arm, realizes that centrifugal movement is transferred to yawing unit；Pivoted arm
On installing component by the way of centralized arrangement, wherein use balanced design method, according to trim principle design counterweight element,
And be mounted on pivoted arm, it is located at turn around the mass center of Dynamic Flight Simulator on axis, caused by reducing simulator because of imbalance
Vibration；The rotary inertia that Dynamic Flight Simulator is reduced using asymmetric pivoted arm structure, makes the energy consumption of Dynamic Flight Simulator
It reduces.
3, the use of gear unit avoids the vibration of main decelerating motor from being transferred directly to pivoted arm and causes entire dynamic flying mould
Quasi- device vibration is excessive, and the out-of-balance force of pivoted arm and pivoted arm installing component passes to civil engineering part by gear unit, enhancing
Main decelerating motor operation stability.
Detailed description of the invention
Fig. 1 is the schematic perspective view of the utility model；
Fig. 2 is the detail of construction of yawing unit in the utility model；
Fig. 3 is the attachment structure schematic diagram of pivoted arm and yawing unit in the utility model；
Fig. 4 is the schematic diagram of the section structure of gear unit in the utility model.
In figure: 1, main decelerating motor；2, gear unit；21, main shaft；22, base；23, bearing system；3, pivoted arm；4, counterweight
Unit；5, instrument room；6, yawing unit；61, yaw drive system；62, frame is yawed；7, rolling unit；71, rolling driving system
System；72, rolling frame；8, cockpit.
Specific embodiment
The utility model is described in further detail with reference to the accompanying drawing:
Embodiment 1, as shown in Figure 1, Figure 2 and Figure 3:
Four-degree-of-freedom helicopter Dynamic Flight Simulator, comprising:
For manned cockpit 8；Component of the cockpit 8 as carrying pilot；
The pitching drive system of pitching motion is done for cockpit 8；
The rolling unit 7 of rolling maneuver is done for cockpit 8；Rolling unit 7 includes rolling drive system 71 and rolling frame 72,
Cockpit 8 does pitching movement in rolling frame 72 after connecting by pitching drive system；
The yawing unit 6 of yaw maneuver is done for cockpit 8；Yawing unit 6 includes yaw drive system 61 and yaw frame 62,
Rolling unit 7 does yawing rotation in yaw frame 62 after connecting by yaw drive system 61；
For providing centrifugal force for cockpit 8 and cockpit 8 being made to do the centrifugal unit of centrifugal action；Yawing unit 6 and centrifugation are single
The effect end connection of member；The rotational plane of cockpit 8 is vertical with the rotational plane of rolling frame 72, the rotational plane difference of yaw frame 62
It is vertical with the rotational plane of the rotational plane of cockpit 8 and rolling frame 72.
Four-degree-of-freedom helicopter Dynamic Flight Simulator is by cockpit 8, centrifugal unit, rolling unit 7, yawing unit 6 and bows
Drive system composition is faced upward, cockpit 8, rolling unit 7, yawing unit 6 and the pitching that wherein centrifugal unit driving is installed thereon drive
System rotates cockpit 8, rolling unit 7, yawing unit 6 in its rotational plane with pitching drive system, this is free for first
Degree；In yawing unit 6, in cockpit 8, the rolling list that its yaw drive system 61 drives yaw frame 62 and is mounted on yaw frame 62
The rotation of member 7 and pitching drive system, this is the second freedom degree；In rolling unit 7, rolling is driven in its rolling drive system 71
The rotation of frame 72 and the cockpit 8 being mounted on rolling frame 72 and pitching drive system, this is third freedom degree；Pitching drive system
Driving cockpit 8 done in rolling frame 72 turn shop which, this be four-degree-of-freedom；Four-degree-of-freedom helicopter Dynamic Flight Simulator
It is moved with four-degree-of-freedom, space yaw, the simulation of three postures of rolling and pitching can be realized simultaneously under centrifugal field, while real
Now overload simulation.
Four-degree-of-freedom helicopter Dynamic Flight Simulator can arbitrarily synthesize under centrifugal field environment for pilot's three-dimensional space
Posture improves pilot's spatial orientation ability；
Embodiment 2, as shown in Figure 1:
The present embodiment the difference from embodiment 1 is that: centrifugal unit includes:
Main decelerating motor 1；
Gear unit 2；
Pivoted arm 3；The power output end of main decelerating motor 1 is connect with the power intake of gear unit 2, gear unit 2
Power output end is fixedly connected with the first end of pivoted arm 3；
Counterweight element 4；
Instrument room 5；Counterweight element 4 and instrument room 5 are installed in the first end top of pivoted arm 3, and yaw frame 62, which is mounted on, to be turned
The second end top of arm 3.
Wherein main decelerating motor 1 by gear unit 2 drive pivoted arm 3 make rotating motion, centrifugal movement be transferred to pivoted arm 3 and
3 installing component of pivoted arm；Yawing unit 6 is connect by yawing frame 62 with centrifuge pivoted arm 3, and it is single to realize that centrifugal movement is transferred to yaw
Member 6；Installing component on pivoted arm 3 is by the way of centralized arrangement, wherein using balanced design method, is designed according to trim principle
Counterweight element 4, and be mounted on pivoted arm 3, it is located at turn around the mass center of Dynamic Flight Simulator on axis, reduces simulator because not
It is vibrated caused by balance；The rotary inertia that Dynamic Flight Simulator is reduced using 3 structure of asymmetric pivoted arm, makes dynamic flying mould
The energy consumption of quasi- device reduces.
Embodiment 3, as shown in Figure 1 and Figure 4:
The present embodiment the difference from example 2 is that: gear unit 2 includes:
Main shaft 21；Main 1 output shaft of decelerating motor is connect with one end of main shaft 21, to transmit torque；
Bearing system 23；
Base 22；Base 22 fixes on the ground, and the both ends side wall of main shaft 21 is connect with the rotating part of bearing system 23, axis
Hold is that 23 non-rotating part is fixed on base 22；The other end of main shaft 21 is fixedly connected with the first end of pivoted arm 3.
The use of gear unit 2 avoids the vibration of main decelerating motor 1 from being transferred directly to pivoted arm 3 and causes entire dynamic flying
Simulator vibration is excessive, and the out-of-balance force of 3 installing component of pivoted arm 3 and pivoted arm passes to civil engineering part by gear unit 2,
Enhance main 1 operation stability of decelerating motor.
Main shaft 21 and main decelerating motor 1 output axis connection realize the transmitting of Motor torque, and main shaft 21 is made to make rotating motion；Machine
Seat 22 fixes on the ground, and is connect by bearing system 23 with main shaft 21, then fixing bearing is 23 non-rotating part, base 22
The gravity for supporting pivoted arm 3 and 3 upper mounting component of pivoted arm, plays carrying；Bearing system 23 is installed between base 22 and main shaft 21,
It realizes that pivoted arm 3 positions, guarantees the even running under the unbalanced moments effect that centrifugal force generates of pivoted arm 3, and make main decelerating motor 1
The torque of generation is transferred to pivoted arm 3, guarantees that pivoted arm 3 does centrifugal rotation movement, Dynamic Flight Simulator is made integrally to realize centrifugal field
Environment.
Embodiment 4, as shown in Figure 1:
The present embodiment the difference from example 2 is that:
One bearing is installed, yaw drive system 61 is mounted on the second end of pivoted arm 3, yaw inside the second end of pivoted arm 3
The power output shaft of drive system 61 is fixedly connected after the inner ring of bearing with the bottom of yaw frame 62.
Rotational power is provided by the component of yaw drive system 61 for yaw frame 62 and thereon, cockpit 8 is allowed to be yawed
Movement.
Embodiment 5, as depicted in figs. 1 and 2:
The present embodiment the difference from embodiment 1 is that: the peace that promising rolling drive system 71 provides is set on yaw frame 62
Assembling platform and interface, rolling drive system 71 are mounted on mounting platform, and are rotated by interface driver rolling frame 72.
Rotational power is provided by the component of rolling drive system 71 for rolling frame 72 and thereon, cockpit 8 is allowed to carry out rolling
Movement.
Embodiment 6, as depicted in figs. 1 and 2:
The present embodiment the difference from embodiment 1 is that: the installation that promising pitching drive system provides is set on rolling frame 72
Platform and interface, pitching drive system are mounted on mounting platform, and are rotated by interface driver cockpit 8.
It is that cockpit 8 provides rotational power by pitching drive system, cockpit 8 is allowed to carry out pitching movement.
The basic principles and main features and advantage of the utility model have been shown and described above.The technical staff of the industry
It should be appreciated that the present utility model is not limited to the above embodiments, the above embodiments and description only describe this
The principle of utility model, on the premise of not departing from the spirit and scope of the utility model, the utility model also has various change
And improvement, these various changes and improvements fall within the scope of the claimed invention.The utility model requires protection scope
It is defined by appending claims and equivalents.
Claims (6)
1. four-degree-of-freedom helicopter Dynamic Flight Simulator characterized by comprising
For manned cockpit；
The pitching drive system of pitching motion is done for cockpit；
The rolling unit of rolling maneuver is done for cockpit；Rolling unit includes rolling drive system and rolling frame, and cockpit is by bowing
Pitching movement is done in rolling frame after facing upward drive system connection；
The yawing unit of yaw maneuver is done for cockpit；Yawing unit includes yaw drive system and yaw frame, and rolling unit is logical
Yawing rotation is done in yaw frame after crossing yaw drive system connection；
For providing centrifugal force for cockpit and cockpit being made to do the centrifugal unit of centrifugal action；The effect of yawing unit and centrifugal unit
End connection；The rotational plane of cockpit is vertical with the rotational plane of rolling frame, yaw the rotational plane of frame respectively with the rotation of cockpit
The rotational plane of plane and rolling frame is vertical.
2. four-degree-of-freedom helicopter Dynamic Flight Simulator according to claim 1, which is characterized in that centrifugal unit packet
It includes:
Main decelerating motor；
Gear unit；
Pivoted arm；The power output end of main decelerating motor and the power intake of gear unit connect, the power output of gear unit
End is fixedly connected with the first end of pivoted arm；
Counterweight element；
Instrument room；Counterweight element and instrument room are installed in the first end top of pivoted arm, and yaw frame is mounted on the second end of pivoted arm
Top.
3. four-degree-of-freedom helicopter Dynamic Flight Simulator according to claim 2, which is characterized in that gear unit packet
It includes:
Main shaft；The connection of one end of main geared motor output shaft and main shaft；
Bearing system；
Base；Base fixes on the ground, and the both ends side wall of main shaft is connect with the rotating part of bearing system, bearing system it is nonrotational
Part is fixed on base；The other end of main shaft is fixedly connected with the first end of pivoted arm.
4. four-degree-of-freedom helicopter Dynamic Flight Simulator according to claim 2, it is characterised in that: the second end of pivoted arm
Inside is equipped with a bearing, and yaw drive system is mounted on the second end of pivoted arm, and the power output shaft of yaw drive system passes through
It is fixedly connected after the inner ring of bearing with the bottom of yaw frame.
5. four-degree-of-freedom helicopter Dynamic Flight Simulator according to claim 1, it is characterised in that: be arranged on yaw frame
The mounting platform and interface that promising rolling drive system provides, rolling drive system is mounted on mounting platform, and passes through interface
Drive the rotation of rolling frame.
6. four-degree-of-freedom helicopter Dynamic Flight Simulator according to claim 1, it is characterised in that: be arranged on rolling frame
The mounting platform and interface that promising pitching drive system provides, pitching drive system is mounted on mounting platform, and passes through interface
Drive cockpit rotation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821463335.7U CN209000276U (en) | 2018-09-07 | 2018-09-07 | Four-degree-of-freedom helicopter Dynamic Flight Simulator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821463335.7U CN209000276U (en) | 2018-09-07 | 2018-09-07 | Four-degree-of-freedom helicopter Dynamic Flight Simulator |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209000276U true CN209000276U (en) | 2019-06-18 |
Family
ID=66798536
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821463335.7U Active CN209000276U (en) | 2018-09-07 | 2018-09-07 | Four-degree-of-freedom helicopter Dynamic Flight Simulator |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209000276U (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108961916A (en) * | 2018-09-07 | 2018-12-07 | 中国工程物理研究院总体工程研究所 | four-degree-of-freedom helicopter dynamic flight simulator |
| CN111681492A (en) * | 2020-07-23 | 2020-09-18 | 中国工程物理研究院总体工程研究所 | Centrifugal flight load and illusion simulator |
| CN111710210A (en) * | 2020-06-12 | 2020-09-25 | 中国人民解放军海军航空大学岸防兵学院 | Aircraft attitude control simulation training device |
| CN111816023A (en) * | 2020-07-27 | 2020-10-23 | 中国工程物理研究院总体工程研究所 | Kinematics method of novel four-axis manned centrifugal machine |
| CN111830847A (en) * | 2020-07-27 | 2020-10-27 | 中国工程物理研究院总体工程研究所 | Overload and attitude simulation method for classifying attitude motion errors of manned centrifuge |
| CN112331020A (en) * | 2020-11-11 | 2021-02-05 | 南京全控航空科技有限公司 | Multi-degree-of-freedom motion simulation platform |
-
2018
- 2018-09-07 CN CN201821463335.7U patent/CN209000276U/en active Active
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108961916A (en) * | 2018-09-07 | 2018-12-07 | 中国工程物理研究院总体工程研究所 | four-degree-of-freedom helicopter dynamic flight simulator |
| CN111710210A (en) * | 2020-06-12 | 2020-09-25 | 中国人民解放军海军航空大学岸防兵学院 | Aircraft attitude control simulation training device |
| CN111681492A (en) * | 2020-07-23 | 2020-09-18 | 中国工程物理研究院总体工程研究所 | Centrifugal flight load and illusion simulator |
| CN111681492B (en) * | 2020-07-23 | 2024-05-14 | 中国工程物理研究院总体工程研究所 | Centrifugal flight load and illusion analogue means |
| CN111816023A (en) * | 2020-07-27 | 2020-10-23 | 中国工程物理研究院总体工程研究所 | Kinematics method of novel four-axis manned centrifugal machine |
| CN111830847A (en) * | 2020-07-27 | 2020-10-27 | 中国工程物理研究院总体工程研究所 | Overload and attitude simulation method for classifying attitude motion errors of manned centrifuge |
| CN111830847B (en) * | 2020-07-27 | 2022-10-21 | 中国工程物理研究院总体工程研究所 | Overload and attitude simulation method for classifying attitude motion errors of manned centrifuge |
| CN112331020A (en) * | 2020-11-11 | 2021-02-05 | 南京全控航空科技有限公司 | Multi-degree-of-freedom motion simulation platform |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN209000276U (en) | Four-degree-of-freedom helicopter Dynamic Flight Simulator | |
| CN108961916A (en) | four-degree-of-freedom helicopter dynamic flight simulator | |
| KR101749996B1 (en) | Dual-axis platform for use in an unmanned aerial vehicle, triple-axis platform for use in unmanned aerial vehicle, and multi-rotor aerial vehicle | |
| WO2017070982A1 (en) | Motor, pan-tilt, and aircraft | |
| CN102390530B (en) | Micromechanical controllable flapping rotary wing aircraft and manufacturing method as well as control method thereof | |
| CN105547676A (en) | Multifunctional swing-arm type rotor wing test stand | |
| CN108766101A (en) | Three Degree Of Freedom for helicopter Dynamic Flight Simulator turns frame system | |
| CN200951831Y (en) | Multi-rotor wing craft | |
| CN204895843U (en) | Multiaxis aircraft | |
| CN110683074A (en) | High-dynamic centrifugal overload simulation test device | |
| CN105857597A (en) | Bionic dragonfly wing-flapping robot | |
| CN108583182A (en) | A kind of amphibious ball shape robot in sky land | |
| CN109147452A (en) | A kind of delay parachuting training analog platform | |
| CN111086634B (en) | Dragonfly-like double-flapping-wing micro aircraft | |
| Pan et al. | A kind of large-sized flapping wing robotic bird: Design and experiments | |
| CN109823566A (en) | A kind of vertically taking off and landing flyer flight control system test platform | |
| CN210555640U (en) | High-dynamic centrifugal overload simulation test device | |
| CN209028882U (en) | Three Degree Of Freedom for helicopter Dynamic Flight Simulator turns frame system | |
| CN104477383B (en) | Three-dimensional flapping flapping-wing drive mechanism | |
| Davis | Aerodynamic force interactions and measurements for micro quadrotors | |
| CN109410692B (en) | Omnidirectional rotary motion device for simulating flight | |
| CN208400337U (en) | Simulator and analog machine | |
| CN209388519U (en) | Rocking bar manipulates load device and rocking bar simulator | |
| CN107187593A (en) | A kind of multiple degrees of freedom unmanned plane with twin rotor system | |
| CN202802770U (en) | Multi-shaft aircraft toy |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |