CN111044980A - Pitching device for simulating flight attitude - Google Patents
Pitching device for simulating flight attitude Download PDFInfo
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- CN111044980A CN111044980A CN201911278602.2A CN201911278602A CN111044980A CN 111044980 A CN111044980 A CN 111044980A CN 201911278602 A CN201911278602 A CN 201911278602A CN 111044980 A CN111044980 A CN 111044980A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S7/00—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00
- G01S7/02—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00 of systems according to group G01S13/00
- G01S7/40—Means for monitoring or calibrating
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- Computer Networks & Wireless Communication (AREA)
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- General Physics & Mathematics (AREA)
- Radar, Positioning & Navigation (AREA)
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Abstract
The invention provides a pitching device for simulating flight attitude, which comprises a base component, a power component, a transmission component and a pitching frame component, wherein the base component comprises a base, the base is provided with two mutually independent upper chambers, a lower chamber positioned below the upper chambers and a partition plate for partitioning the upper chambers and the lower chambers into an upper structure and a lower structure, and a power supply battery is arranged in the lower chamber; the transmission assembly is arranged in the upper cavity, and the power assembly is arranged on the base and positioned outside the upper cavity; the output end of the power assembly penetrates through the upper cavity and is in driving connection with the input end of the transmission assembly, the output end of the transmission assembly is in driving connection with the input end of the pitching frame assembly, and the pitching frame assembly is arranged on the outer side of the base; the power supply battery is electrically connected with the power assembly through a wire penetrating through a preset hole in the partition plate, and the battery and the pitching frame are arranged on the same equipment, so that flight attitude simulation of the flight equipment can be realized, and guidance, radar device testing, debugging and inspection in an indoor test field can be realized.
Description
Technical Field
The invention relates to the field of guidance and radar, in particular to a pitching device for simulating flight attitude.
Background
The radar guide device is an important component of the flight equipment, and in order to ensure the safe operation of the flight equipment, precise and rigorous testing and regulation and control are required in advance so as to be put into use.
In a real situation, there are no large obstacles in the air, and the signal transmission in the air is very different from the ground. Meanwhile, flying equipment (such as a projectile body and an unmanned aerial vehicle) cannot use a fixed power supply like ground equipment, but uses a battery and the like to supply power, and the voltage and the power which can be provided by the battery are far inferior to those of the fixed power supply.
In the prior art, when the radar guiding device simulates real working conditions, a fixed power supply mode is mostly adopted, or only a small load can be simulated, so that certain errors can exist in the radar guiding test precision. Therefore, in order to perform testing, experimenting, and debugging work of the radar guide device, a unique apparatus capable of simulating a flying posture while mounting the radar device and the battery is required.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides the pitching device which is widely applicable and can simulate the attitude change of a projectile body flying in the air.
The embodiment of the invention provides a pitching device for simulating a flight attitude, which comprises a base component, a power component, a transmission component and a pitching frame component, wherein the base component comprises a base, the base is provided with two mutually independent upper chambers, a lower chamber positioned below the upper chambers and a partition plate for separating the upper chambers from the lower chambers into an upper structure and a lower structure, and a power supply battery is arranged in the lower chamber; the transmission assembly is arranged in the upper cavity, and the power assembly is arranged on the base and positioned outside the upper cavity; the output end of the power assembly penetrates through the upper cavity and is in driving connection with the input end of the transmission assembly, the output end of the transmission assembly is in driving connection with the input end of the pitching frame assembly, and the pitching frame assembly is arranged on the outer side of the base; the power supply battery is electrically connected with the power assembly through a lead penetrating through a preset hole in the partition plate.
Preferably, the power assembly comprises a servo motor and a speed reducer, an output shaft of the servo motor is connected with an input shaft of the speed reducer, the servo motor is electrically connected with the power supply battery, and the speed reducer is arranged on the base through a speed reducer mounting seat;
preferably, the power assembly further comprises a motor cover, the motor cover is fixedly arranged on the base, and the servo motor and the speed reducer are hermetically arranged in the motor cover;
preferably, the transmission assembly comprises a worm connected with an output shaft of the speed reducer and a turbine connected with the worm in a transmission manner, a turbine shaft is arranged in the turbine, two ends of the turbine shaft are exposed outside the turbine, two ends of the turbine are respectively arranged in arc-shaped grooves formed in the base, one end of the turbine shaft is connected with the pitching frame assembly, and an upper cover plate is arranged at the top of the base.
Preferably, a first worm bearing and a second worm bearing are respectively arranged at two ends of the worm, the first worm bearing is arranged close to an output shaft of the speed reducer, the second worm bearing is arranged far away from the output shaft of the speed reducer, worm bearing seats are respectively arranged at the bottoms of the first worm bearing and the second worm bearing, the worm bearing seats are fixedly connected to the base through a Z-direction worm pressing plate, the Z-direction worm pressing plate is connected with the turbine bearing seat, and a lifting assembly for adjusting the height of the worm bearing seat is arranged on the base;
preferably, the lifting assembly comprises an adjusting screw rod arranged on the partition plate and a Z-direction worm small shaft connected to the worm bearing seat, one end of the adjusting screw rod is arranged in the lower chamber, the other end of the adjusting screw rod is positioned in the upper chamber and is abutted against the worm bearing seat, one end of the Z-direction worm small shaft is in threaded connection with a small shaft nut, a Z-direction worm small shaft adjusting pad is sleeved outside the other end of the Z-direction worm small shaft nut, and a cover plate is arranged at one end of the small shaft nut, which is far away from the adjusting screw rod;
preferably, two sides of the first worm bearing and the second worm bearing are respectively provided with an outer end cover of the worm bearing and an inner end cover of the worm bearing, and the inner end cover of the worm bearing is arranged close to the center of the worm compared with the outer end cover of the worm bearing.
Preferably, a turbine bearing sleeved outside the turbine is arranged in the arc-shaped groove, the turbine bearing is connected to the base through a turbine bearing lock catch, an inner turbine bearing retainer ring and an outer turbine bearing retainer ring are respectively arranged on two sides of the turbine bearing, and the outer turbine bearing retainer ring is connected with the inner turbine bearing retainer ring through a locking nut and used for limiting radial movement of the turbine bearing;
preferably, a first mounting seat and a second mounting seat for mounting a hall sensor are arranged on the side wall of the upper chamber close to the worm, the first mounting seat and the second mounting seat are symmetrically distributed on two sides of the turbine shaft, a magnetic sheet seat is arranged on the turbine at a position corresponding to the first mounting seat, an encoder is arranged on the turbine shaft, and the encoder, the magnetic sheet seat and the hall sensor are all electrically connected with the power supply battery;
preferably, every single move frame subassembly include with the pivot that the turbine shaft transmission is connected and connect the link of pivot, the both ends of link are equipped with every single move frame respectively and locate the piece that hits of every single move frame, be equipped with the frame pad on the every single move frame, the frame pad pass through locking screw with the turbine is connected.
Has the advantages that:
the battery and the pitching frame are arranged on the same device, so that flight attitude simulation can be provided for the guidance of the flight device and the radar device, guidance, test, debugging and inspection of the radar device can be performed in an indoor test field, the structure is reasonable in design and compact in structure, not only is stable and reliable in structure, but also can bear large load, is small in size and free of sharp appearance, can avoid signal interference in use, can simulate a real environment, can provide large torque under the condition of low power, can be accurately positioned according to requirements, and is convenient to install and transport among indoor fields.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
FIG. 1 is a schematic structural diagram of the present invention.
Fig. 2 is a front view of a sectional structure a-a of fig. 1.
Fig. 3 is a side view of the structure of fig. 1C-C in partial section.
Fig. 4 is a partial sectional structural view of B-B of fig. 2.
In the figure, 1, a motor cover; 2. bumping the block; 3. a reducer mounting base; 4. a base; 5. a turbine shaft; 6. an upper cover plate; 7. a worm gear; 8. a worm gear bearing lock catch; 9. a worm pressure plate adjusting block; 10. a pitch frame; 11. the outer end cover of the worm bearing; 12. a Z-direction worm pressing plate; 13. a worm lock nut; 14. a hand wheel cover plate; 15. an inner end cover of the worm bearing; 16. a worm bearing seat; 17. a Z-direction worm small-shaft cushion block; 18. a Z-direction worm small shaft; 19. a small-shaft nut; 20. a worm gear bearing outer retainer ring; 21. a turbine shaft side cover plate; 22. a worm gear bearing inner retainer ring; 23. a frame pad; 24. locking the nut; 25. an encoder mounting base; 26. a worm side cover plate; 27. a first mounting seat; 28. a worm; 29. a worm bearing lock catch; 30. a socket board; 31. a magnetic sheet mounting seat; 32. a worm bearing cushion; 33. a cover plate; 34. a second mounting seat; 35. a first worm bearing; 36. a servo motor; 37. a speed reducer; 38. a second worm bearing; 39. a turbine bearing; 40. an encoder; 41. an upper chamber; 42. a lower chamber; 43. a partition plate; 44. an arc-shaped slot; 51. adjusting the screw rod; 54. locking the screw; 60. a connecting frame; 101. a rotating shaft; 110. mounting a platform; 131. hand wheel connecting rod.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be obtained by a person skilled in the art without inventive effort based on the embodiments of the present invention, are within the scope of the present invention.
As shown in fig. 1, an embodiment of the present invention provides a pitching apparatus for simulating a flight attitude, including a base assembly, a power assembly, a transmission assembly, and a pitching frame assembly, where the base assembly includes a base 4, the base 4 is provided with two independent upper chambers 41, a lower chamber 42 located below the upper chamber 41, and a partition plate 43 separating the upper chamber 41 and the lower chamber 42 into an upper structure and a lower structure, and the lower chamber 42 is provided with a power supply battery inside; the transmission assembly is arranged in the upper chamber 41, and the power assembly is arranged on the base 4 and positioned outside the upper chamber 41; the output end of the power assembly penetrates through the upper chamber 41 to be in driving connection with the input end of the transmission assembly, the output end of the transmission assembly is in driving connection with the input end of the pitching frame assembly, and the pitching frame assembly is arranged on the outer side of the base 4; the power supply battery is electrically connected to the power assembly by wires passing through pre-set holes in the partition 43. Through installing battery and every single move frame on same equipment, can realize flight equipment's flight gesture analogue simulation, realize that the indoor test place guides, radar installation's experiment, debugging and inspection.
As shown in fig. 1, the power assembly includes a servo motor 36 and a speed reducer 37, an output shaft of the servo motor 36 is connected with an input shaft of the speed reducer 37, the servo motor 36 is electrically connected with a power supply battery, the speed reducer 37 is arranged on the base 4 through a speed reducer mounting base 3, the power assembly further includes a motor cover 1, the motor cover 1 is fixedly arranged on the base 4, the servo motor 36 and the speed reducer 37 are arranged in the motor cover 1 in a sealing manner, the motor cover is arranged on the base and used for protecting the speed reducer and the servo motor, dust is prevented from entering, a worm gear transmission mode is adopted, a self-locking function is provided, additional use of a bolt is not needed.
As shown in fig. 1 and 2, the transmission assembly includes a worm 28 connected to an output shaft of the speed reducer 37 and a turbine 7 connected to the worm 28 in a transmission manner, a turbine shaft 5 is disposed in the turbine 7, both ends of the turbine shaft 5 are exposed outside the turbine 7, both ends of the turbine 7 are disposed in arc-shaped grooves 44 formed in the base 4, respectively, one end of the turbine shaft 5 is connected with the pitching frame assembly, an upper cover plate 6 is disposed on the top of the base 4, the upper cover plate 6 is in a streamline design, so that interference on radar testing can be avoided, the upper cover plate is disposed on the top of the base, it is ensured that the turbine, the worm and the turbine shaft are in a dust-free state.
As shown in fig. 1 and 2, a first worm bearing 35 and a second worm bearing 38 are respectively disposed at two ends of the worm 28, the first worm bearing 35 is disposed near an output shaft of the speed reducer 37, the second worm bearing 38 is disposed away from the output shaft of the speed reducer 37, worm bearing blocks 16 are respectively disposed at bottoms of the first worm bearing 35 and the second worm bearing 38, the worm bearing blocks 16 are connected to the base 4 through worm bearing lock catches 29, the worm bearing blocks 16 are fixedly connected to the base 4 through Z-direction worm pressure plates 12, the Z-direction worm pressure plates 12 are connected to the worm bearing blocks 16 through worm lock nuts 13, and a lifting assembly for adjusting the height of the worm bearing blocks 16 is disposed on the base 4. The purpose of smooth rotation can be achieved by adjusting the clearance between the worm wheel and the worm.
As shown in fig. 3, the lifting assembly includes an adjusting screw 51 disposed on the partition 43 and a Z-direction worm small shaft 18 connected to the worm bearing seat 16, one end of the adjusting screw 51 is disposed in the lower chamber 42, the other end of the adjusting screw is disposed in the upper chamber 41 and abuts against the worm bearing seat 16, one end of the Z-direction worm small shaft 18 is connected to a small shaft nut 19 in a threaded manner, a Z-direction worm small shaft adjusting pad 17 is sleeved outside the other end of the adjusting screw, and a cover plate 33 is disposed at one end of the small shaft nut 19 away from the adjusting screw 51. The small shaft nut 19 is screwed to drive the Z-direction worm small shaft 18 to rotate, so that the worm bearing seat 16 is driven to move to the position of the adjusting screw 51, the adjusting screw 51 is rotated to fix the height of the worm bearing seat 16 or put down the worm bearing seat, the distance between the worm 28 and the worm wheel 7 is adjusted, and the effect that the worm and the worm wheel rotate smoothly is achieved.
As shown in fig. 1 and 2, a hand wheel connecting rod 131 is disposed at one end of the worm 28 away from the speed reducer 37, and is used for manually rotating the worm 28 to drive the turbine 7 to rotate, but a motor or speed reducer failure needs to be maintained or a joint of the speed reducer and the turbine is jammed, the hand wheel connecting rod 131 can be manually rotated to drive the worm 28 to return an output shaft of the speed reducer 37, so as to facilitate maintenance, a hand wheel cover plate 14 for the hand wheel connecting rod 131 to pass through is disposed on the base 4, a through hole for the hand wheel connecting rod 131 to pass through is further disposed on the hand wheel cover plate 14, a hand wheel is disposed at the other end of the hand wheel connecting rod 131 away from the worm 28, so as to facilitate operation of rotating the hand wheel connecting rod 131, a worm side cover plate 26 is further disposed at one side of the upper chamber 41 of the base 4, and is detachable during maintenance, a socket plate 30 is disposed, the bottom of the base 4 is disposed on a mounting platform 110.
As shown in fig. 2, a flange is sleeved on one end of the turbine shaft 7 penetrating through the base 4, and a turbine shaft side cover plate 21 is arranged on the flange and used for enclosing the turbine shaft 7 in a sealed space, so as to prevent particles in dust or air from entering between the turbine shaft 7 and the turbine bearing 39 to affect increase of friction and affect service life of the turbine shaft.
As shown in fig. 2 and 4. The two sides of the first worm bearing 35 and the second worm bearing 38 are respectively a worm bearing outer end cover 11 and a worm bearing inner end cover 15, the worm bearing inner end cover 15 is arranged closer to the center of the worm 28 than the worm bearing outer end cover 11, a turbine bearing 39 sleeved outside the turbine 7 is arranged in the arc-shaped groove 44, the turbine bearing 39 is connected to the base 4 through a turbine bearing lock catch 8, two sides of the turbine bearing 39 are respectively provided with a turbine bearing inner retainer ring 22 and a turbine bearing outer retainer ring 20, and the turbine bearing outer retainer ring 20 is connected with the turbine bearing inner retainer ring 22 through a lock nut 24 and used for limiting the radial movement of the turbine bearing 39.
As shown in fig. 2, a first mounting seat 27 and a second mounting seat 34 for mounting a hall sensor are arranged on a side wall of the upper chamber 41 close to the worm 28, the first mounting seat 27 and the second mounting seat 34 are symmetrically distributed on two sides of the turbine shaft 5, a magnetic sheet seat 31 is arranged on the turbine 7 corresponding to the first mounting seat 27, an encoder 40 is arranged on the turbine shaft 5, and the encoder 40, the magnetic sheet seat 31 and the hall sensor are all electrically connected with a power supply battery.
As shown in fig. 4, the pitching frame assembly comprises a rotating shaft 101 in transmission connection with the other end of the turbine shaft 5 and a connecting frame 60 connected with the rotating shaft 101, a pitching frame 10 and a bump 2 arranged on the pitching frame 10 are respectively arranged at two ends of the connecting frame 60, a frame pad 23 is arranged on the pitching frame 10, the frame pad 23 is connected with the turbine 7 through a locking screw 54, and the base 4 and the pitching frame 10 are both made of cast aluminum. The lifting appliance has the advantages that the total weight is low under the condition of meeting the use performance, and the lifting appliance can be carried and installed manually under the condition that lifting equipment is not needed.
In the description of the present invention, numerous specific details are set forth. It is understood, however, that embodiments of the invention may be practiced without these specific details. In some instances, well-known methods, structures and techniques have not been shown in detail in order not to obscure an understanding of this description. Similarly, it should be appreciated that in the foregoing description of exemplary embodiments of the invention, various features of the invention are sometimes grouped together in a single embodiment, figure, or description thereof for the purpose of streamlining the disclosure and aiding in the understanding of one or more of the various inventive aspects. However, the disclosed method should not be interpreted as reflecting an intention that: that the invention as claimed requires more features than are expressly recited in each claim. Rather, as the following claims reflect, inventive aspects lie in less than all features of a single foregoing disclosed embodiment. Thus, the claims following the detailed description are hereby expressly incorporated into this detailed description, with each claim standing on its own as a separate embodiment of this invention.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; such modifications and substitutions do not depart from the spirit and scope of the present invention, and they should be construed as being included in the following claims and description.
Claims (10)
1. A pitching device for simulating flight attitude is characterized by comprising a base component, a power component, a transmission component and a pitching frame component,
the base assembly comprises a base (4), the base (4) is provided with two mutually independent upper chambers (41), a lower chamber (42) positioned below the upper chambers (41) and a partition plate (43) for separating the upper chambers (41) from the lower chambers (42) into an upper structure and a lower structure, and a power supply battery is arranged in the lower chamber (42);
the transmission assembly is arranged in the upper chamber (41), and the power assembly is arranged on the base (4) and positioned outside the upper chamber (41);
the output end of the power assembly penetrates through the upper chamber (41) to be in driving connection with the input end of the transmission assembly, the output end of the transmission assembly is in driving connection with the input end of the pitching frame assembly, and the pitching frame assembly is arranged on the outer side of the base (4);
the power supply battery is electrically connected with the power assembly through a lead wire passing through a preset hole on the partition plate (43).
2. Pitching device for simulating a flight attitude according to claim 1, wherein said power assembly comprises a servo motor (36) and a reducer (37), the output shaft of said servo motor (36) is connected to the input shaft of said reducer (37), said servo motor (36) is electrically connected to said power supply battery, and said reducer (37) is mounted on said base (4) through a reducer mounting (3).
3. Pitching apparatus for simulating a flight attitude according to claim 2, wherein said power assembly further comprises a motor cover (1), said motor cover (1) is fixed on said base (4), and said servo motor (36) and said reducer (37) are sealed in said motor cover (1).
4. The pitching device for simulating the flying attitude according to claim 2, wherein the transmission assembly comprises a worm (28) connected with the output shaft of the reducer (37) and a turbine (7) in transmission connection with the worm (28), a turbine shaft (5) is arranged in the turbine (7), both ends of the turbine shaft (5) are exposed to the outside of the turbine (7), both ends of the turbine (7) are respectively arranged in arc-shaped grooves (44) formed in the base (4), one end of the turbine shaft (5) is connected with the pitching frame assembly, and the top of the base (4) is provided with an upper cover plate (6).
5. Pitching apparatus for simulating a flight attitude according to claim 4, a first worm bearing (35) and a second worm bearing (38) are respectively arranged at two ends of the worm (28), the first worm bearing (35) is disposed near an output shaft of the speed reducer (37), the second worm bearing (38) is disposed away from the output shaft of the speed reducer (37), the bottoms of the first worm bearing (35) and the second worm bearing (38) are respectively provided with a worm bearing seat (16), the worm bearing seat (16) is fixedly connected to the base (4) through a Z-direction worm pressure plate (12), the Z-direction worm pressure plate (12) is connected with the turbine bearing seat (16), and a lifting component for adjusting the height of the worm bearing seat (16) is arranged on the base (4).
6. The pitching device for simulating the flying attitude according to claim 5, wherein the lifting assembly comprises an adjusting screw (51) arranged on the partition plate (43) and a Z-direction worm small shaft (18) connected to the worm bearing seat (16), one end of the adjusting screw (51) is arranged in the lower chamber (42), the other end of the adjusting screw is arranged in the upper chamber (41) and abutted against the worm bearing seat (16), one end of the Z-direction worm small shaft (18) is in threaded connection with a small shaft nut (19), a Z-direction worm small shaft adjusting pad (17) is sleeved outside the other end of the Z-direction worm small shaft adjusting screw, and a cover plate (33) is arranged at one end of the small shaft nut (19) far away from the adjusting screw (51).
7. The pitching apparatus for simulating flight attitude according to claim 5, wherein the first and second worm bearings (35, 38) have a worm bearing outer end cover (11) and a worm bearing inner end cover (15) on both sides, respectively, and the worm bearing inner end cover (15) is disposed closer to the center of the worm (28) than the worm bearing outer end cover (11).
8. The pitching device for simulating the flight attitude according to claim 4, wherein a turbine bearing (39) sleeved outside the turbine (7) is arranged in the arc-shaped groove (44), the turbine bearing (39) is connected to the base (4) through a turbine bearing lock catch (8), an inner turbine bearing retainer ring (22) and an outer turbine bearing retainer ring (20) are respectively arranged on two sides of the turbine bearing (39), and the outer turbine bearing retainer ring (20) is connected with the inner turbine bearing retainer ring (22) through a lock nut (24) and used for limiting the radial movement of the turbine bearing (39).
9. The pitching device for simulating the flying attitude according to claim 8, wherein the upper chamber (41) has a first mounting seat (27) and a second mounting seat (34) for mounting a hall sensor on the side wall near the worm (28), the first mounting seat (27) and the second mounting seat (34) are symmetrically distributed on both sides of the turbine shaft (5), a magnetic sheet seat (31) is arranged on the turbine (7) corresponding to the first mounting seat (27), an encoder (40) is arranged on the turbine shaft (5), and the encoder (40), the magnetic sheet seat (31) and the hall sensor are electrically connected to the power supply battery.
10. The pitching device for simulating the flying attitude according to claim 4, wherein the pitching frame assembly comprises a rotating shaft (101) in transmission connection with the turbine shaft (5) and a connecting frame (60) connected with the rotating shaft (101), a pitching frame (10) and a bump (2) arranged on the pitching frame (10) are respectively arranged at two ends of the connecting frame (60), a frame pad (23) is arranged on the pitching frame (10), and the frame pad (23) is connected with the turbine (7) through a locking screw (54).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911278602.2A CN111044980B (en) | 2019-12-13 | 2019-12-13 | Pitching device for simulating flight attitude |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911278602.2A CN111044980B (en) | 2019-12-13 | 2019-12-13 | Pitching device for simulating flight attitude |
Publications (2)
| Publication Number | Publication Date |
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| CN111044980A true CN111044980A (en) | 2020-04-21 |
| CN111044980B CN111044980B (en) | 2023-07-07 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201911278602.2A Active CN111044980B (en) | 2019-12-13 | 2019-12-13 | Pitching device for simulating flight attitude |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117588527A (en) * | 2024-01-16 | 2024-02-23 | 东北大学 | Speed reducer with double input modes |
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| CN201875378U (en) * | 2010-12-02 | 2011-06-22 | 中国科学院沈阳自动化研究所 | Underwater electric feedback cloud deck without bulk motion |
| CN203300802U (en) * | 2013-05-10 | 2013-11-20 | 北京航天光华电子技术有限公司 | Satellite antenna elevation transmission device |
| CN105652684A (en) * | 2014-11-13 | 2016-06-08 | 北京航天计量测试技术研究所 | Novel large-size four-freedom attitude simulation structure |
| KR101850647B1 (en) * | 2017-04-25 | 2018-04-19 | 국방과학연구소 | Apparatus being possible to apply flight load and control attitude for testing wing of flight vehicle |
| CN109592083A (en) * | 2018-10-16 | 2019-04-09 | 天津中精微仪器设备有限公司 | A kind of spacecraft simulator with automatic weighing |
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2019
- 2019-12-13 CN CN201911278602.2A patent/CN111044980B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201875378U (en) * | 2010-12-02 | 2011-06-22 | 中国科学院沈阳自动化研究所 | Underwater electric feedback cloud deck without bulk motion |
| CN203300802U (en) * | 2013-05-10 | 2013-11-20 | 北京航天光华电子技术有限公司 | Satellite antenna elevation transmission device |
| CN105652684A (en) * | 2014-11-13 | 2016-06-08 | 北京航天计量测试技术研究所 | Novel large-size four-freedom attitude simulation structure |
| KR101850647B1 (en) * | 2017-04-25 | 2018-04-19 | 국방과학연구소 | Apparatus being possible to apply flight load and control attitude for testing wing of flight vehicle |
| CN109592083A (en) * | 2018-10-16 | 2019-04-09 | 天津中精微仪器设备有限公司 | A kind of spacecraft simulator with automatic weighing |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117588527A (en) * | 2024-01-16 | 2024-02-23 | 东北大学 | Speed reducer with double input modes |
| CN117588527B (en) * | 2024-01-16 | 2024-03-19 | 东北大学 | Speed reducer with double input modes |
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| Publication number | Publication date |
|---|---|
| CN111044980B (en) | 2023-07-07 |
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