CN104217622A - Simulation aircraft and system thereof - Google Patents
Simulation aircraft and system thereof Download PDFInfo
- Publication number
- CN104217622A CN104217622A CN201410437901.7A CN201410437901A CN104217622A CN 104217622 A CN104217622 A CN 104217622A CN 201410437901 A CN201410437901 A CN 201410437901A CN 104217622 A CN104217622 A CN 104217622A
- Authority
- CN
- China
- Prior art keywords
- rotation axis
- driving cabin
- support
- simulated flight
- flight device
- 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.)
- Granted
Links
Abstract
The invention discloses a simulation aircraft and a system thereof. The simulation aircraft comprises a support, a first rotation shaft is horizontally arranged on the support, a transmission case is fixedly connected at one end of the first rotation shaft extending out of the support, and one side of the transmission case is connected with a cockpit. The first rotation shaft is provided with a hollow cavity, a second rotation shat is arranged in the cavity, the second rotation shaft and the first rotation shaft are coaxially arranged, one end of the second rotation shaft extending into the transmission case is in linkage with a fourth rotation shaft through a linkage mechanism, the fourth rotation shaft is perpendicular to the first rotation shat in horizontal projection, and the cockpit is hinged to an end portion of the fourth rotation shaft extending out of the transmission case through a hinge pin. The second rotation shaft is creatively arranged in the first rotation shaft, so the whole simulation aircraft is simple in structure, small in space occupation, complete in functions, low in manufacturing cost and convenient to mount.
Description
Technical field
The present invention relates to simulated flight technical field, specifically design a kind of simulated flight device of experiencing for pilot's daily workout or airhog's simulated flight and system thereof.
Background technology
Along with the development of China's aeronautical technology, and Defence business in the urgent need to, the problem of pilot's critical shortage highlights day by day, and therefore, in very long one period, cultivating high-quality, high-quality pilot will be the most important thing of defense sector.Pilot trains in the early stage and obviously can not learn various flare maneuver and skill completely on prototype in technical ability enhancement training process, simulated flight device then with its training cost low, security good, convenient operation control, and flight experience effect true to nature and become pilot training optimum training equipment.
As Chinese patent literature CN102779438A discloses a kind of simulated aircraft full action emulation flight mechanical execution system, comprise basis, always configure group, girder, gas-holder and air-control device, the first telecontrol equipment, the second telecontrol equipment, the 3rd telecontrol equipment, power electric transmitting device and cabin analogue means; First telecontrol equipment one end is arranged in basis, and the other end runs through girder and holds up cabin analogue means, the first telecontrol equipment is provided with power electric transmitting device; Second telecontrol equipment one end is provided with the second motor and power electric transmitting device, and the other end is provided with the second cylinder; 3rd telecontrol equipment one end is provided with the 3rd motor and the 3rd cylinder, and the other end is connected with the driving cabin in the analogue means of cabin through the longitudinal axis axle sleeve be arranged on the second telecontrol equipment.Though this simulation system can in the state of flight of the axial simulated aircraft of X, Y, Z tri-, but the right-angled intersection adopted due to its transverse axis and the longitudinal axis coordinates, its vertical pivot is then arranged at immediately below its point of crossing, and therefore this simulation system need take larger spatial volume, is not easy to install; And these simulation system parts are more, complex structure, cost of manufacture is higher.
Summary of the invention
For this reason, technical matters to be solved by this invention be existing simulated flight device to take volume comparatively large, be not easy to install, and parts are more, complex structure, manufacturing cost is high, for this reason, it is simple that the present invention proposes a kind of structure, small volume and the lower simulated flight device of cost of manufacture.
For solving the problems of the technologies described above, simulated flight device of the present invention by the following technical solutions:
A kind of simulated flight device, it comprises support, and on described support, level is provided with the first rotation axis, and one end of extending described support of described first rotation axis is fixedly connected with transmission case, the side of described transmission case connects driving cabin, and described driving cabin is vertical with described first rotation axis to be arranged, the first drive unit being arranged on described first rotation axis side drives described driving cabin with the axis forward and reverse rotation of described first rotation axis around described first rotation axis, described first rotation axis has the die cavity of a hollow, the second rotation axis is provided with in described die cavity, described second rotation axis and described first rotation axis are coaxially arranged, one end away from described driving cabin of described second rotation axis is connected with the second drive unit, linked by link gear and the 4th rotation axis in one end extended in described transmission case of described second rotation axis, the horizontal projection of described 4th rotation axis is vertical with the horizontal projection of described first rotation axis, described driving cabin extends the end of described transmission case one end at described 4th rotation axis by hinge, described second drive unit drives described driving cabin around the forward and reverse rotation of axis of described 4th rotation axis, described driving cabin is connected with the 3rd drive unit, described 3rd drive unit drives described driving cabin to swing around described bearing pin.
Preferably, described second rotation axis is fixedly installed on inside described die cavity by several bearings.
Preferably, described first drive unit comprises the first drive motor be fixedly installed on the bracket, and the first transmission being located at described first drive motor output terminal is paid, the outer wall of described first rotation axis is arranged with and pays with described first transmission the second transmission coordinated and pay.
Preferably, it is the first worm gear or the first worm screw that described first transmission is paid, and it is the first worm screw or the first worm gear that described second transmission is paid.
Preferably, described first transmission is paid to pay with described second transmission and is two axes intersect and the bevel gear cooperatively interacted or spiral gear.
Preferably, described link gear comprises the second worm screw being set in described second rotation axis end and the second worm gear be set on described 4th rotation axis, and described second rotation axis drives described driving cabin around the positive and negative rotation of axis of described 4th rotation axis by described second worm screw and described second worm gear.
Preferably, described link gear comprises the 3rd rotation axis be fixed on by bearing on relative two sidewalls of described transmission case, the axis of described 3rd rotation axis and the axis being parallel of described second rotation axis, the end sleeve that described second rotation axis extends described first rotation axis is provided with the first gear, described first gear and the second gears meshing be set on described 3rd rotation axis; The position just right with described 4th rotation axis of described 3rd rotation axis is arranged with the second worm screw, described 4th rotation axis is arranged with the second worm gear coordinated with described second worm screw, described 3rd rotation axis coordinates the positive and negative rotation of axis driving described driving cabin around described 4th rotation axis by worm and gear.
Preferably, described 3rd drive unit is rudder pedals, and described rudder pedals is connected with described driving cabin by linkage assembly, and described rudder pedals drives described driving cabin to swing around described bearing pin.
Preferably, described 4th rotation axis extends to outside described transmission case away from one end of described driving cabin, and is connected with the counter weight device that can adjust position along the axis of described 4th rotation axis mated with described driving cabin and load-carrying thereof.
Preferably, described support comprises the first support being arranged on the axial medium position of described first rotation axis, and be arranged on second support away from described driving cabin one end of described first rotation axis, described first support and described second support is triangular in shape or trapezoidal shape.
Preferably, the side of the close described driving cabin of described first support is provided with some tilting support bars, and one end of described support bar is against on the sidewall of described first support, on the base that the other end of described support bar is against described support or ground.
Preferably, described first support is also provided with the second support bar, one end of described second support bar is against the middle and lower part of described support bar, on the base that its other end is against described support or described ground.
Preferably, be provided with the vault curtain of the image for showing projection arrangement projection outside described driving cabin, described driving cabin is trapped among inner side by described vault curtain.
Preferably, described vault curtain is spheroidal or the ellipsoid bodily form.
Preferably, described projection arrangement is arranged on the outside of described vault curtain.
Preferably, described projection arrangement comprises several projector, and described projector is disposed in an evenly spaced relation in the outside of described vault curtain.
A kind of simulated flight system, it comprises several simulated flight devices, and described in several, simulated flight device is all connected to master controller, and described simulated flight device is the simulated flight device described in above-mentioned any one.
Technique scheme of the present invention has the following advantages compared to existing technology:
1. its second rotation axis of simulated flight device of the present invention is arranged in the die cavity of described first rotation axis, and described first rotation axis is coaxial in described second rotation axis, its bearing of trend is consistent, described first rotation axis can drive described driving cabin to swing up and down around the axis of described first rotation axis under the effect of the first drive unit, and then completes rising, somersault or underriding action; Described second rotation axis is driven by the second drive unit, described driving cabin can be driven to rotate around described 4th rotation axis axis, and then complete roll action; 3rd drive unit is then by driving described driving cabin to swing around described bearing pin; 3rd drive unit of simulated flight device of the present invention is rudder pedals, and simulation personnel step on two pedals in left and right by pin can realize the left and right turn action of simulated flight device on surface level (being also (X, Y) face).Simulated flight device of the present invention can not only simulate every flare maneuver of aircraft (mainly referring to aircraft), and owing to creatively the second rotation axis being arranged in the first rotation axis, therefore can save a large amount of spaces and related components quantity, have that multiple functional, structure is simple, low cost of manufacture, advantage easy for installation; In addition, drive unit (motor) can also be made to be fixed on support, and electric wire rotates without the need to the rotation with driving cabin, and then improves Supply Security.
2. the second rotation axis of the present invention is fixedly installed on inside described die cavity by several bearings, also namely bearing inner race is tightly set on described second rotation axis, bearing outer ring then closely cooperates with the die cavity inwall of the first rotation axis, adopt this setup that the first rotation axis and the second rotation axis can be made to be connected as a single entity and to support each other, strengthen the safety and stability performance of whole simulated flight device; And two rotation axiss can not interfere each other, it (is also (X that driving cabin can be driven respectively to realize level, Y) face) or vertical direction (be also (X, Z) face or (Y, Z) face) Arbitrary Rotation, rotate more flexible, more convenient operation.
3. the 4th rotation axis of simulated flight device of the present invention extends to outside transmission case away from one end of driving cabin, and be connected with and mate with driving cabin weight and common people's body weight and can automatically along the counter weight device of the axial adjustment position of the 4th rotation axis, when simulation personnel sit after driving cabin, counter weight device can according to its body weight automatic adjusting position, this setup will can ensure that driving cabin has good balance stability energy on transmission case further, and then improves the security of training.
4. the side of the close described driving cabin of the first support of the present invention is provided with some tilting support bars, one end of this support bar is against on the sidewall of the first support, on the base that its other end is against support or ground, because driving cabin is the one end being hung on the first rotation axis, due to Action of Gravity Field, first support has the trend to driving cabin lopsidedness, two-way arranges and refers to they sup-port first support, then can effectively reduce driving cabin and the first support be produced to the acting force applied, and then strengthen security performance.
5. the driving cabin arranged outside of simulated flight device of the present invention has the vault curtain for showing projection, described ball curtain is spheroidal or the ellipsoid bodily form, contributes to the field range expanding trainee, improves simulation vivid effect, make trainee have sensation on the spot in person, and then greatly improve training effect.
6. the projection arrangement of simulated flight device of the present invention is arranged on the outside of vault curtain, and this setup can avoid the driving cabin problem that image is delayed when simulating roll, somersault action.
7. simulated flight system of the present invention comprises several simulated flight devices of the present invention, and make simulated flight device be connected to master controller, its connected mode realizes long-range connection by broadband, optical fiber etc., by the centralized control of master controller, and projection arrangement projects according to the view pre-set, remote collaboration simulated aircraft fistfight rehearsal between each training base can be realized, and then the airmanship of trainee can be improved, improve its combat capabilities.
Accompanying drawing explanation
In order to make content of the present invention be more likely to be clearly understood, below according to a particular embodiment of the invention and by reference to the accompanying drawings, the present invention is further detailed explanation, wherein
Fig. 1 is the schematic front view of simulated flight device of the present invention;
Fig. 2 is the schematic side view of simulated flight device of the present invention;
Fig. 3 is the schematic top plan view of simulated flight device of the present invention;
Fig. 4 is the first worm screw of simulated flight device of the present invention and the structural representation of the first worm gear;
Fig. 5 is the second worm screw of simulated flight device of the present invention and the structural representation of the second worm gear;
The structural representation that Fig. 6 simulated flight device of the present invention coordinates with projection arrangement;
The structural representation of Fig. 7 simulated flight system of the present invention;
The schematic front view of the third embodiment of Fig. 8 simulated flight device of the present invention;
The schematic side view of the third embodiment of Fig. 9 simulated flight device of the present invention;
The schematic top plan view of the third embodiment of Figure 10 simulated flight device of the present invention.
In figure, Reference numeral is expressed as:
10-first rotation axis; 11-first drive unit; 12-die cavity; 13-first drive motor; 14-second transmission is paid; 15-first transmission is paid; 20-second rotation axis; 21-second drive unit; 22-first gear; 30-the 3rd rotation axis; 32-second gear; 23,33-second worm screw; 40-the 4th rotation axis; 41-bearing pin; 42-second worm gear; 43-counter weight device; 50-support; 51-first support; 52-second support; 53-support bar; 54-second support bar; 6-vault curtain; 7-projector; 8-transmission case; 9-driving cabin.
Embodiment
Embodiment one
See Fig. 1-3, a kind of simulated flight device, it comprises support 50, on described support 50, level is provided with the first rotation axis 10, one end of extending described support 50 of described first rotation axis 10 is fixedly connected with transmission case 8, and described transmission case is fixed by modes such as welding or bolt connections, and the side of described transmission case 8 connects driving cabin 9, described driving cabin 9 is vertical with described first rotation axis 10 to be arranged, and also namely simulates the axis back to described first rotation axis 10 when trainee is sitting in driving cabin 9; The first drive unit 11 being arranged on described first rotation axis 10 side drives described driving cabin 9 with the axis forward and reverse rotation of described first rotation axis 10 around described first rotation axis 10, to realize in first plane ± N × 360 degree rotate at any angle, and complete the described simulator cockpit 9 seat fore-and-aft direction that flies and rotate the emulation of (somersault action).
Described first rotation axis 10 has the die cavity 12 of a hollow, the second rotation axis 20 is provided with in described die cavity 12, described second rotation axis 20 is coaxially arranged with described first rotation axis 10, one end away from described driving cabin 9 of described second rotation axis 20 is connected with the second drive unit 21, linked by link gear and the 4th rotation axis 40 in one end extended in described transmission case 8 of described second rotation axis 20, described second drive unit 21 is fixed on support 50, the horizontal projection of described 4th rotation axis 40 is vertical with the horizontal projection of described first rotation axis 10, described driving cabin 9 is hinged on by bearing pin 41 end that described 4th rotation axis 40 extends described transmission case 8 one end, described second drive unit 21 drives described driving cabin 9 to rotate forward or backwards around the axis of described 4th rotation axis 40, to realize in second plane ± N × 360 degree rotate at any angle, complete the described driving cabin 9 seat left and right directions that flies and rotate the emulation of (roll action).
Described driving cabin 9 is connected with the 3rd drive unit, described 3rd drive unit is rudder pedals, described rudder pedals is connected with driving cabin by bar linkage structure, simulation personnel step on left-hand tread plate or right-hand tread plate by pin, can realize driving cabin 9 and carry out swinging in certain limit around bearing pin 41; Driven by yaw rudder manpower in driving cabin 9, realize rotating arbitrarily in limited angular region in described bearing pin 41 horizontal radial plane, complete described driving cabin 9 and take off on land, land and the flat action emulation flown when turning.Certainly according to specific design requirement, described rudder pedals can also adopt alternate manner to drive, and as electronic mode etc., and then realizes automatically controlling.
Because the second rotation axis 20 is creatively arranged in the first rotation axis 10 by the present invention, therefore a large amount of spaces and related components quantity can be saved, in addition, by drive unit (drive motor) is fixed on support, and then make whole simulated flight device rotating member drive unit not do the rotation of any locus, evade and cause on the basis of emergency risk in electric power input, realize position impression emulation during flight operation, and then improve Supply Security, have that multiple functional, structure is simple, low cost of manufacture, advantage easy for installation.
In the present embodiment, described second rotation axis 20 is fixedly installed on inside described die cavity 12 by two bearings near its two ends, bearing inner race is tightly set on described second rotation axis 20, bearing outer ring then closely cooperates with the die cavity inwall of the first rotation axis 10, adopt this setup that the first rotation axis 10 and the second rotation axis 20 can be made to be connected as a single entity and to support each other, strengthen the safety and stability performance of whole simulated flight device
See Fig. 1, Fig. 4, described first drive unit 11 in the present embodiment comprises the first drive motor 13 be fixedly installed on described support 50, and the first transmission being located at described first drive motor 13 output terminal pays 15, the outer wall of described first rotation axis 10 is arranged with and pays 15 the second transmissions coordinated with described first transmission and pay 14, first drive motor 13 rotates, and then driven the first transmission of output terminal to pay 15 driving second transmissions to pay 14 rotations, second transmission drives the first rotation axis 10 to rotate while paying 14 rotations, first rotation axis 10 drives driving cabin 9 to rotate up or down further, rise with simulated implementation, somersault, underriding action.
In the present embodiment, because described second rotation axis 20 is arranged in the die cavity 12 of described first rotation axis 10, the second drive unit 21 for turning described second rotation axis 20 is arranged on the end of described second rotation axis 20, therefore the first drive unit 11 for driving described first rotation axis 10 to rotate is arranged on the lateral location of described first rotation axis 10, and is fixed on support 50; Described first transmission pay 15 pay 14 with described second transmission between adopt worm and gear to coordinate, to improve the stability of transmission, concrete, described first sheathed first worm screw of output terminal turning motor 13, the outside of described first rotation axis 10 is arranged with the first worm gear, and described first drive motor 13 drives described first rotation axis 10 to rotate by described first worm screw with coordinating of described first worm gear.
Certainly, the first worm screw and the first worm gear is adopted to be a kind of preferred version, in other embodiments, described first transmission pays 15, and to pay 14 can also be two bevel gears or spiral gear cooperatively interacted with described second transmission, and two bevel gears or helical gear axes intersect are crisscross arranged, or the kind of drive that other two rotating shaft axis intersects, described first rotation axis 10 is driven to rotate forward or backwards as long as described first drive unit 11 can be realized, the structure type that concrete transmission is paid is not limit, different transmissions can be chosen according to actual working ability and accuracy requirement to pay.
Certainly, if selected by the first drive unit 11 and the first drive unit 21 to turn motor speed too high, then can by arranging reduction gear or mechanism carries out reduction of speed, can meet the various actions index of simulated flight.
See Fig. 1, Fig. 5, the specific constructive form of the described link gear in the present embodiment is: one end end sleeve directly sheathed second worm screw 23 extended in described transmission case 8 of described second rotation axis 20, described second worm screw 23 realizes worm and gear with the second worm gear 42 on the 4th rotation axis 40 and coordinates, when described second drive unit 21 drives described second rotation axis 20 to rotate, second rotation axis 20 directly drives the 4th rotation axis 40 to rotate by the second worm screw 23 and the second worm gear 42, and then drive driving cabin 9 to realize in second plane ± N × 360 degree Arbitrary Rotation, complete the emulation that described simulator cockpit flight seat left and right directions rotates (roll action).
Because now the second rotation axis 20 directly drives driving cabin 9 to rotate by worm-and-wheel gear, and then avoid the drawback that the transmission caused because there is backlash in gear drive is unstable, the rigid impact of the gear teeth easily occurs, and this setup parts are less, structure is simpler, transmission is more stable, and simulated effect is better.
In addition, described second rotation axis 20 in the present embodiment also can adopt two kinds of drive such as bevel gear or spiral gear with the worm gear between the 4th rotation axis 40 with coordinating of worm screw, drives described 4th rotation axis 40 to rotate can the concrete transmission form of paying not limit as long as it can realize the second rotation axis 20 when rotating.
In the present embodiment, because driving cabin 9 is hung on the side of transmission case 8, the deadweight of trainee and driving cabin 9 can apply a larger torsion to transmission case 8, and then affect rotational stability and the security performance of driving cabin 9, therefore the 4th rotation axis 40 is extended to outside described transmission case 8 away from one end of described driving cabin 9, and the counter weight device 43 mated with described driving cabin 9 and load-carrying thereof is connected in its end, simulation personnel are seated in after in driving cabin 9, counter weight device 43 can according to simulation personnel body weight along the 4th rotation axis 40 axis direction near or away from driving cabin 9, and then keep transmission case 8, driving cabin 9 has good balance quality all the time at the axis direction of the 4th rotation axis 40 under work and off working state, and then raising security, increase the service life.
In the present embodiment, described support 50 comprises the first support 51 being arranged on the axial medium position of described first rotation axis 10, and be arranged on second support 52 away from described driving cabin 9 one end of described first rotation axis 10, described first support 51 and described second support 52 is triangular in shape or trapezoidal shape, described first support 51 be arranged in parallel with described second support 52; By arranging the first substantially parallel support 53 and the second support 54, greatly can alleviate the weight of whole analogue means, and triangle or trapezium structure are conducive to again improving stability of strutting system.
In the present embodiment, the side of the close described driving cabin 9 of described first support 51 is provided with some tilting support bars 53, one end of described support bar 53 is against on the sidewall of described first support 51, on the base that the other end of described support bar 53 is against described support 50 or ground.Described support bar 53 can prevent the first support 51 to the lopsidedness of driving cabin 9, and then strengthens the stability of strutting system of support.
In the present embodiment, described first support 51 is also provided with the second support bar 54, one end of described second support bar 54 is against the middle and lower part of described support bar 53, on the base that its other end is against described support 50 or described ground, described second support bar 54 is by supporting the conflict of support bar 53, the supporting role of support bar 53 to the first support 51 can be strengthened further, simultaneously, because the second support bar 54 ground is in the position on the lower side, middle part of support bar 53, it is highly lower, can not affect the simulated action of driving cabin 9.
See Fig. 6, the vault curtain 6 of the image for showing projection arrangement projection is provided with outside described driving cabin 9 in the present embodiment, described driving cabin 9 is trapped among inner side by described vault curtain 6, described vault curtain 6 is in spheroidal or the ellipsoid bodily form, described projection arrangement is arranged on the outside of described vault curtain 6, described projection arrangement comprises several projector 7, and described projector 7 uniform intervals arranges the outside of described vault curtain 6.By the arranged outside vault curtain 9 at driving cabin 9, and make vault curtain 9 substantially in spheroidal or the ellipsoid bodily form, and by the image projection made on vault curtain 9, the simulated environment that trainee sees in driving cabin 9 is really true to life, because vault curtain 6 is spheroid form, trainee can be made to have impression on the spot in person, and then strengthen training interest, improve training effect.And aircraft is when doing roll and somersault action, if use image servo-actuated (projector moves with driving cabin), computing machine is needed to carry out trigonometric function calculating, and in Computer Image Processing process, the arithmetic speed of trigonometric function is the path linearly calculating arithmetic speed, speed is comparatively slow, therefore by projector 7 being arranged on the outside of driving cabin 9, avoids this calculation procedure, thus shorten the image servo-actuated time, and then avoid the delayed problem of image.
Embodiment two
See Fig. 7, a kind of simulated flight system, it comprises several simulated flight devices, and described in several, simulated flight device is all connected to master controller, and described simulated flight device is the simulated flight device described in above-described embodiment.Connected mode in the present embodiment realizes long-range connection by broadband, optical fiber etc., by the centralized control of master controller, and projection arrangement projects according to the view pre-set, remote collaboration simulated aircraft fistfight rehearsal between each training base can be realized, and then the airmanship of trainee can be improved, improve its combat capabilities.
Embodiment three
See Fig. 8-10, on the basis of above-described embodiment one and embodiment two, the described link gear between described second rotation axis 20 and described 4th rotation axis 40 can also replace to following form:
Described link gear comprises the 3rd rotation axis 30 be fixed on by two bearings on relative two sidewalls of described transmission case 8 (described transmission case 8 is cube structure), the axis of described 3rd rotation axis 30 and the axis being parallel of described second rotation axis 20, the end sleeve that described second rotation axis 20 extends described first rotation axis 10 is provided with the first gear 22, and described first gear 22 engages with the second gear 32 be set on described 3rd rotation axis 30; The position just right with described 4th rotation axis 40 of described 3rd rotation axis 30 is arranged with the second worm screw 33, described 4th rotation axis 40 is arranged with the second worm gear 42 coordinated with described second worm screw 33, described 3rd rotation axis 30 is coordinated by worm and gear and drives described driving cabin 9 around the axis forward of described 4th rotation axis 40 or reverse turn.Also the second rotation axis 20 forward or reverse is first driven when namely described second drive unit 21 rotates, described second rotation axis 20 and then drive the 3rd rotation axis 30 to rotate with engaging of the second gear 32 by the first gear 22, the 4th rotation axis 40 is driven to rotate by the second worm screw 33 with coordinating of the second worm gear 42 when 3rd rotation axis 30 rotates, because the 4th rotation axis 40 is fixed on two relative sidewalls of transmission case 8 by bearing, and the axis direction of the 4th rotation axis 40 is vertical with the axis direction of the first rotation axis 10, now the 4th rotation axis 40 can drive driving cabin 9 to rotate forward or backwards around its axle center, also namely roll action simulated by driving cabin 9.
Obviously, above-described embodiment is only for clearly example being described, and the restriction not to embodiment.For those of ordinary skill in the field, can also make other changes in different forms on the basis of the above description.Here exhaustive without the need to also giving all embodiments.And thus the apparent change of extending out or variation be still among the protection domain of the invention.
Claims (17)
1. a simulated flight device, it is characterized in that: comprise support (50), the upper level of described support (50) is provided with the first rotation axis (10), one end of extending described support (50) of described first rotation axis (10) is fixedly connected with transmission case (8), the side of described transmission case (8) connects driving cabin (9), and described driving cabin (9) is vertical with described first rotation axis (10) to be arranged; The first drive unit (11) being arranged on described first rotation axis (10) side drives described driving cabin (9) with the axis forward and reverse rotation of described first rotation axis (10) around described first rotation axis (10);
Described first rotation axis (10) has the die cavity (12) of a hollow, the second rotation axis (20) is provided with in described die cavity (12), described second rotation axis (20) and described first rotation axis (10) are coaxially arranged, one end away from described driving cabin (9) of described second rotation axis (20) is connected with the second drive unit (21), linked by link gear and the 4th rotation axis (40) in one end extended in described transmission case (8) of described second rotation axis (20), the horizontal projection of described 4th rotation axis (40) is vertical with the horizontal projection of described second rotation axis (20), described driving cabin (9) is hinged on by bearing pin (41) end that described 4th rotation axis (40) extends described transmission case (8) one end, described second drive unit (21) drives described driving cabin (9) around the forward and reverse rotation of axis of described 4th rotation axis (40),
Described driving cabin (9) connects the 3rd drive unit, and described 3rd drive unit drives described driving cabin (9) to swing around described bearing pin (41).
2. a kind of simulated flight device according to claim 1, is characterized in that: described second rotation axis (20) is fixedly installed on described die cavity (12) inner side by several bearings.
3. a kind of simulated flight device according to claim 1 and 2, it is characterized in that: described first drive unit (11) comprises the first drive motor (13) be fixedly installed on described support (50), and the first transmission being located at described first drive motor (13) output terminal is paid (15), the outer wall of described first rotation axis (10) is arranged with and pays the second transmission that (15) coordinate with described first transmission and pay (14).
4. a kind of simulated flight device according to claim 3, is characterized in that: (15) are paid in described first transmission is the first worm gear or the first worm screw, and (14) are paid in described second transmission is the first worm screw or the first worm gear.
5. a kind of simulated flight device according to claim 3, is characterized in that: described first transmission is paid (15) and described second transmission and paid (14) and be two axes intersect and the bevel gear cooperatively interacted or spiral gear.
6. according to the arbitrary described a kind of simulated flight device of claim 1-5, it is characterized in that: described link gear comprises the second worm screw (23) being set in described second rotation axis (20) end and the second worm gear (42) be set on described 4th rotation axis (40), described second rotation axis (20) coordinates the positive and negative rotation of axis driving described driving cabin (9) around described 4th rotation axis (40) with described second worm gear (42) by described second worm screw (23).
7. according to the arbitrary described a kind of simulated flight device of claim 1-5, it is characterized in that: described link gear comprises the 3rd rotation axis (30) be fixed on by bearing on relative two sidewalls of described transmission case (8), the described axis of the 3rd rotation axis (30) and the axis being parallel of described second rotation axis (20), the end sleeve that described second rotation axis (20) extends described first rotation axis (10) is provided with the first gear (22), described first gear (22) is engaged with the second gear (32) be set on described 3rd rotation axis (30), the just right position of described 3rd rotation axis (30) and described 4th rotation axis (40) is arranged with the second worm screw (33), described 4th rotation axis (40) is arranged with the second worm gear (42) coordinated with described second worm screw (33), described 3rd rotation axis (30) coordinates the positive and negative rotation of axis driving described driving cabin (9) around described 4th rotation axis (40) by worm and gear.
8. according to the arbitrary described a kind of simulated flight device of claim 1-7, it is characterized in that: described 3rd drive unit is rudder pedals, described rudder pedals is connected with described driving cabin (9) by linkage assembly, and described rudder pedals drives described driving cabin (9) to swing around described bearing pin (41).
9. according to the arbitrary described a kind of simulated flight device of claim 1-8, it is characterized in that: described 4th rotation axis (40) extends to described transmission case (8) outside away from one end of described driving cabin (9), and is connected with the counter weight device (43) that can adjust position along the axis of described 4th rotation axis (40) mated with described driving cabin (9) and load-carrying thereof.
10. according to the arbitrary described a kind of simulated flight device of claim 1-9, it is characterized in that: described support (50) comprises the first support (51) being arranged on the axial medium position of described first rotation axis (10), and be arranged on second support (52) away from described driving cabin (9) one end of described first rotation axis (10), described first support (51) and described second support (52) is triangular in shape or trapezoidal shape.
11. a kind of simulated flight devices according to claim 10, it is characterized in that: the side of the close described driving cabin (9) of described first support (51) is provided with some tilting support bars (53), one end of described support bar (53) is against on the sidewall of described first support (51), on the base that the other end of described support bar (53) is against described support (50) or ground.
12. a kind of simulated flight devices according to claim 11, it is characterized in that: described first support (51) is also provided with the second support bar (54), one end of described second support bar (54) is against the middle and lower part of described support bar (53), on the base that its other end is against described support (50) or described ground.
13. according to the arbitrary described a kind of simulated flight device of claim 1-12, it is characterized in that: described driving cabin (9) outside is provided with the vault curtain (6) of the image for showing projection arrangement projection, and described driving cabin (9) is trapped among inner side by described vault curtain (6).
14. a kind of simulated flight device systems according to claim 13, is characterized in that: described vault curtain (6) is in spheroidal or elliposoidal.
15. a kind of simulated flight device systems according to claim 13 or 14, is characterized in that: described projection arrangement is arranged on the outside of described vault curtain (6).
16. a kind of simulated flight device systems according to claim 15, it is characterized in that: described projection arrangement comprises several projector (7), described projector (7) is disposed in an evenly spaced relation in the outside of described vault curtain (6).
17. 1 kinds of simulated flight systems, it comprises several simulated flight devices, and described in several, simulated flight device is all connected to master controller, it is characterized in that: described simulated flight device is the arbitrary described simulated flight device of claim 13-16.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410437901.7A CN104217622B (en) | 2014-08-29 | 2014-08-29 | Simulation aircraft and system thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410437901.7A CN104217622B (en) | 2014-08-29 | 2014-08-29 | Simulation aircraft and system thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104217622A true CN104217622A (en) | 2014-12-17 |
| CN104217622B CN104217622B (en) | 2017-01-18 |
Family
ID=52099052
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410437901.7A Expired - Fee Related CN104217622B (en) | 2014-08-29 | 2014-08-29 | Simulation aircraft and system thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104217622B (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104464441A (en) * | 2014-12-24 | 2015-03-25 | 喻明 | Flight simulation training device |
| CN104616562A (en) * | 2015-02-16 | 2015-05-13 | 清华大学 | Rail type flight simulator having continuous overload simulation capability |
| CN105810040A (en) * | 2016-05-18 | 2016-07-27 | 袁芫 | Airplane flying ground sliding trainer |
| CN105938667A (en) * | 2016-06-01 | 2016-09-14 | 广东思泓国际贸易有限公司 | Simulation platform |
| CN106110660A (en) * | 2016-08-15 | 2016-11-16 | 西安翔辉仿真科技有限公司 | Three 360 degree of axles comprehensive high speed sensation simulation emulator |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4713007A (en) * | 1985-10-11 | 1987-12-15 | Alban Eugene P | Aircraft controls simulator |
| US20030219701A1 (en) * | 2000-05-12 | 2003-11-27 | Zeier Bruce E. | Simulator for aircraft flight training |
| US20070218427A1 (en) * | 2005-11-14 | 2007-09-20 | Norman Lefton | Vehicle simulator environment |
| WO2011098093A9 (en) * | 2009-12-02 | 2012-01-05 | Kvitt- Construction | Modular triaxially movable flight and driving simulator for commercial production and marketing |
| CN102779438A (en) * | 2012-07-10 | 2012-11-14 | 黄力红 | Flight simulated mechanical execution system simulating full-motion of airplane |
| CN202632581U (en) * | 2012-05-28 | 2012-12-26 | 戴震宇 | Flight simulation control and experience device based on real air environment |
| WO2013113520A1 (en) * | 2012-02-03 | 2013-08-08 | Infocopter Gmbh | Aircraft simulating apparatus for helicopter hover simulation |
| CN204102366U (en) * | 2014-08-29 | 2015-01-14 | 喻明 | A kind of simulated flight device and system thereof |
-
2014
- 2014-08-29 CN CN201410437901.7A patent/CN104217622B/en not_active Expired - Fee Related
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4713007A (en) * | 1985-10-11 | 1987-12-15 | Alban Eugene P | Aircraft controls simulator |
| US20030219701A1 (en) * | 2000-05-12 | 2003-11-27 | Zeier Bruce E. | Simulator for aircraft flight training |
| US20070218427A1 (en) * | 2005-11-14 | 2007-09-20 | Norman Lefton | Vehicle simulator environment |
| WO2011098093A9 (en) * | 2009-12-02 | 2012-01-05 | Kvitt- Construction | Modular triaxially movable flight and driving simulator for commercial production and marketing |
| WO2013113520A1 (en) * | 2012-02-03 | 2013-08-08 | Infocopter Gmbh | Aircraft simulating apparatus for helicopter hover simulation |
| CN202632581U (en) * | 2012-05-28 | 2012-12-26 | 戴震宇 | Flight simulation control and experience device based on real air environment |
| CN102779438A (en) * | 2012-07-10 | 2012-11-14 | 黄力红 | Flight simulated mechanical execution system simulating full-motion of airplane |
| CN204102366U (en) * | 2014-08-29 | 2015-01-14 | 喻明 | A kind of simulated flight device and system thereof |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104464441A (en) * | 2014-12-24 | 2015-03-25 | 喻明 | Flight simulation training device |
| CN104616562A (en) * | 2015-02-16 | 2015-05-13 | 清华大学 | Rail type flight simulator having continuous overload simulation capability |
| CN105810040A (en) * | 2016-05-18 | 2016-07-27 | 袁芫 | Airplane flying ground sliding trainer |
| CN105938667A (en) * | 2016-06-01 | 2016-09-14 | 广东思泓国际贸易有限公司 | Simulation platform |
| CN106110660A (en) * | 2016-08-15 | 2016-11-16 | 西安翔辉仿真科技有限公司 | Three 360 degree of axles comprehensive high speed sensation simulation emulator |
| CN106110660B (en) * | 2016-08-15 | 2018-06-26 | 西安翔辉仿真科技有限公司 | Three axis 360 degrees omnidirection high speed sensation simulation emulators |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104217622B (en) | 2017-01-18 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104217622A (en) | Simulation aircraft and system thereof | |
| EP2508236A1 (en) | Aerobat toy | |
| CN103718226A (en) | Device for spatially moving persons | |
| CN105788393A (en) | Spatial movement simulating experience apparatus | |
| CN104637364A (en) | Rotating flight simulator | |
| CN103886782B (en) | A kind of 360 degree of omnidirectionals overload type of flight simulator | |
| CN204102366U (en) | A kind of simulated flight device and system thereof | |
| CN206672418U (en) | A kind of rotary simulation system of Three Degree Of Freedom | |
| CN104616563A (en) | Rocker arm type flight simulator having continuous overload simulation capability | |
| CN209056108U (en) | Flight training simulation system based on mixed reality and multi-degree-of-freedom motion platform | |
| CN202105445U (en) | Three-dimensional dynamic simulator | |
| CN207571968U (en) | A kind of single-driving type day the moon celestial body simulation motion demonstrating instrument | |
| CN106017851B (en) | A kind of active face manipulation gap simulator | |
| CN206021647U (en) | A kind of centrifugal rotation 6 DOF platform | |
| CN207571969U (en) | A kind of double drive formula day the moon celestial body simulation motion demonstrating instrument | |
| CN104971485A (en) | Sled simulating device of three-shaft electric type simulator through sliding mode | |
| CN203870839U (en) | Rotating device for aircraft simulation training | |
| CN105629639A (en) | Spherical display system based on super-wide field angle fish-eye lens | |
| CN212208630U (en) | Flight training simulation system | |
| CN211124496U (en) | Flight simulator | |
| CN219006117U (en) | Mechanical arm capable of encircling Mars model | |
| CN202728395U (en) | Mechanical joint and neck and tail structures of bionic mechanical dinosaur | |
| CN208400337U (en) | Simulator and analog machine | |
| CN215526981U (en) | Aircraft simulator | |
| CN207114883U (en) | Virtual reality experience device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170118 Termination date: 20210829 |