CN112722324B - Vertical take-off and landing electric aircraft test platform - Google Patents
Vertical take-off and landing electric aircraft test platform Download PDFInfo
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- CN112722324B CN112722324B CN202110069118.XA CN202110069118A CN112722324B CN 112722324 B CN112722324 B CN 112722324B CN 202110069118 A CN202110069118 A CN 202110069118A CN 112722324 B CN112722324 B CN 112722324B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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Abstract
The invention belongs to the technical field of vertical take-off and landing airplanes, and particularly relates to a vertical take-off and landing electric airplane test platform. The test platform solves the technical problems that the existing vertical take-off and landing aircraft is high in test, research and development cost and the like in research and development. This VTOL electric aircraft test platform includes platform frame and a plurality of screw motor, its characterized in that, the installation room that is used for placing energy, equipment and balancing weight has on the platform frame, a plurality of screw motor is located the top of platform frame, and a plurality of screw motor sets up around the installation room, be equipped with the adjusting device that can adjust screw motor distance between relative installation room between screw motor and the platform frame, platform frame bottom is equipped with the bradyseism structure that can carry out the bradyseism to the platform frame of whereabouts. The invention reduces the test and development cost of the vertical take-off and landing aircraft in the research and development.
Description
Technical Field
The invention belongs to the technical field of vertical take-off and landing airplanes, and particularly relates to a vertical take-off and landing electric airplane test platform.
Background
The pure electric aircraft adopts the power battery system and the motor system to replace the power of the internal combustion engine, has unique quality different from the traditional aircraft, does not generate waste gas during the operation, does not discharge tail gas pollution, is very beneficial to environmental protection and air cleanness, and can be said to be almost zero pollution.
However, the airplane is a special transportation vehicle, and the requirement on safety performance is very high, which results in long development period of the airplane, many test items and large investment. Each new aircraft was subjected to flight tests from completion of manufacture to flying to the blue sky. In the process of flight test, some systems and equipment of the tested airplane need to be additionally modified to the tested airplane to carry out flight test, some performances of the tested airplane are detected in advance through real flight, the airplane is called an aerial test platform, and the aerial test platform can test a plurality of systems of electronic radar, an engine, communication, electromechanics and the like of the tested airplane.
Because the vertical take-off and landing electric aircraft is a relatively new product, the development process is different from the traditional aircraft, and a flight test testing technology and a solution thereof, which are key technologies for aircraft development and flight test, are still in the research and discussion stage. For an electric vertical take-off and landing aircraft with a relatively simple system, the verification of important system functions of a flight control system is completed on the basis of matching the actual production condition of a manufacturing system, and then the analysis, planning and design of a test mode and a test system structural framework of a project can be carried out.
In the development process, in order to guarantee the performance requirement of the system, the tests of the power system and the flight control system occupy a very long period, a proper model is required for testing, if an equal proportion prototype used by an aerial experiment platform similar to the traditional airplane is used, a mold is required to be developed, the cost investment is high, the cost is high, even if an retired airplane or a self-made equal proportion experiment prototype is used, the cost and the manufacturing period can be limited, and the research and development period of the airplane can be greatly limited. And after the equal proportion model machine completes the test task, the equal proportion model machine has no additional use, and belongs to waste.
Disclosure of Invention
Aiming at the problems in the prior art, the invention provides a vertical take-off and landing electric aircraft test platform, which aims to solve the technical problems that: how to reduce the test development cost in development.
The purpose of the invention can be realized by the following technical scheme:
the utility model provides a VTOL electric aircraft test platform, includes platform frame and a plurality of screw motor, its characterized in that, the last installation room that is used for placing energy, equipment and balancing weight that has of platform frame, a plurality of screw motor is located the top of platform frame, and a plurality of screw motor sets up around the installation room, be equipped with the adjusting device that can adjust screw motor distance between relative the installation room between screw motor and the platform frame, platform frame bottom is equipped with the bradyseism structure that can carry out the bradyseism to the platform frame.
This VTOL electric aircraft test platform mainly used tests the vertical lift of aircraft, the installation room on the platform frame is used for placing the required energy of aircraft flight, equipment and balancing weight, according to different models, its inside equipment quantity, position and weight all can change, the position size that sets up of screw motor all need verify through the flight test, a plurality of screw motors that platform frame top set up around the installation room, adjust the screw motor through adjusting device distance between relative the installation room, realize this VTOL electric aircraft test platform can carry out experimental certification to the prototype in different research and development processes, thereby reduce the testing cost in research and development, simultaneously because there are very many unstable factors in the flight test, consequently, the in-process of VTOL probably has the risk of falling, through the bradyseism structure that sets up in the bottom of platform frame, can cushion when VTOL electric aircraft test platform falls, reduce the testing research and development cost in research and development.
In the vertical take-off and landing electric aircraft test platform, the installation chamber is located in the middle of the platform frame, the adjusting device comprises an upper cross frame, the upper cross frame is transversely arranged at the top of the platform frame, the adjusting device further comprises an installation seat which is arranged on the upper cross frame in a sliding mode, and the propeller motor is installed on the installation seat. The mount pad slides along its length direction on last crossbearer to drive the screw motor and adjust lateral position on the platform frame, thereby adjust the screw motor and for the distance between the installation room, realize this VTOL electric aircraft test platform can test the authentication to the prototype of different research and development in-process, thereby reduce the test cost in research and development.
In the vertical take-off and landing electric aircraft test platform, the mounting base comprises two connecting plates arranged at intervals, the upper cross frame is positioned between the two connecting plates, and the upper cross frame is connected with the two connecting plates through fasteners. Go up the crossbearer and be located between two connecting plates, the crossbearer slides for the guide rail more than two connecting plates, and after the suitable position was adjusted to the mount pad, fixed two connecting plates and last crossbearer through the fastener to realize this VTOL electric aircraft test platform can test the authentication to the prototype of different research and development in-process, reduce the test cost in research and development.
In the vertical take-off and landing electric aircraft test platform, the platform frame comprises a longitudinal beam which is longitudinally arranged, a sliding sleeve which can slide along the length direction of the longitudinal beam is sleeved on the longitudinal beam, and the sliding sleeve is connected with the upper transverse frame. The sliding sleeve slides on the longitudinal beam to drive the upper cross beam to move longitudinally along the platform frame, so that the distance between the propeller motors relative to the installation chamber is adjusted, the test platform for the vertical take-off and landing electric aircraft can perform test certification on prototype machines in different research and development processes, and the test cost in research and development is reduced.
In foretell VTOL electric aircraft test platform, platform frame's bottom is equipped with two piece at least bottom end rails that set up along its longitudinal separation, the bradyseism structure is including vertical setting up the sleeve on every bottom end rail both ends respectively, and it is provided with the telescopic shaft to slide in the sleeve, the top of telescopic shaft is equipped with prevents that the telescopic shaft from deviating from the baffle I in the sleeve, and the bottom of telescopic shaft is equipped with baffle two, telescopic bottom is equipped with baffle three, be equipped with the bradyseism spring of cup jointing on the telescopic shaft between baffle three and the baffle two. When the aircraft falls, baffle two atresss and drives the telescopic shaft rebound in the sleeve, and baffle two exert pressure towards the bradyseism spring, compress the bradyseism spring, make the bradyseism spring absorb the impact, thereby avoid landing firmly when VTOL electric aircraft test platform falls, reduce the damage to VTOL electric aircraft test platform, thereby reduce the test cost in research and development, baffle one sets up and can prevent VTOL electric aircraft test platform from deviating from the sleeve after liftoff telescopic shaft, the bottom of platform frame is equipped with two at least lower crossbeams that set up along its longitudinal separation, and every lower crossbeam both ends all are provided with sleeve isotructure, can promote the effect of the holistic bradyseism energy-absorbing of VTOL electric aircraft test platform, reduce the damage to VTOL electric aircraft test platform, thereby reduce the test cost in research and development.
In the vertical take-off and landing electric aircraft test platform, the bottom of the baffle II is connected with a steering wheel support, and the bottom of the steering wheel support is connected with a steering wheel. The two bottoms of the baffle plates are connected with the steering wheel support and the steering wheels, so that the vertical take-off and landing electric aircraft test platform can move to the test position, and when the vertical take-off and landing electric aircraft test platform falls, the impact on the vertical take-off and landing electric aircraft test platform can be dispersed through the rolling of the steering wheels, the damage to the vertical take-off and landing electric aircraft test platform is reduced, and the test cost in research and development is reduced.
In the vertical take-off and landing electric aircraft test platform, the platform frame further comprises a support rod, and two ends of the support rod are respectively connected with the upper cross frame and the lower cross beam. The setting of bracing piece can promote VTOL electric aircraft test platform's structural stability, especially can promote the support to last frame.
In the vertical take-off and landing electric aircraft test platform, the two ends of the supporting rod are connected with universal joints, the universal joints at the two ends of the supporting rod are respectively connected with the upper cross frame and the lower cross beam, the vertical height distance between the upper cross frame and the lower cross beam is smaller than the length of the supporting rod, the supporting rod is arranged obliquely relative to the upper cross frame, and the supporting rod is also arranged obliquely relative to the lower cross beam. The bracing piece sets up for last crossbearer slope, and the bracing piece also inclines to set up for the bottom end rail, can disperse the vertical impact force when taking off and land the electric aircraft test platform perpendicularly and fall through the direction that sets up of bracing piece, reduce the impact to last crossbearer, because the regulation on the vertical position is carried out according to the test demand of difference to last crossbearer needs, the both ends of bracing piece are passed through the universal joint and are connected with last crossbearer and bottom end rail, and the vertical height distance between last crossbearer and the bottom end rail is less than the length of bracing piece, can keep being connected with last crossbearer and bottom end rail when not changing the bracing piece, thereby reduce the test cost in research and development.
Compared with the prior art, the invention has the following advantages:
1. the distance between the propeller motors relative to the installation chamber is adjusted through the adjusting device, and the test platform for the vertical take-off and landing electric aircraft can perform test certification on prototype machines in different research and development processes.
2. The both ends of bracing piece are passed through the universal joint and are connected with last crossbearer and bottom end rail, and go up the length that the vertical height apart from being less than the bracing piece between crossbearer and the bottom end rail, can keep being connected with last crossbearer and bottom end rail when not changing the bracing piece, reduce the test cost in research and development.
3. And the second baffle plate applies pressure to the cushioning spring to compress the cushioning spring, so that the cushioning spring absorbs impact, the vertical take-off and landing electric aircraft test platform is prevented from being hard landed when falling, and the damage to the vertical take-off and landing electric aircraft test platform is reduced.
Drawings
Fig. 1 is a schematic perspective view of the vertical take-off and landing electric aircraft test platform.
Fig. 2 is a schematic cross-sectional structure diagram of the test platform of the vertical take-off and landing electric aircraft.
Fig. 3 is a schematic perspective view of another view angle of the test platform for vertical take-off and landing electric aircraft.
Fig. 4 is a schematic perspective view of the vertical take-off and landing electric aircraft test platform from a bottom perspective.
In the figure, 1, a platform frame; 1a, an installation chamber; 1b, longitudinal beams; 1c, a sliding sleeve; 1d, a lower cross beam; 1e, a support rod; 1f, a universal joint; 2. a propeller motor; 3. an adjustment device; 3a, an upper cross frame; 3b, a mounting seat; 3b1, a connecting plate; 3c, fastening pieces; 4. a cushioning structure; 4a, a sleeve; 4b, a telescopic shaft; 4c, a first baffle; 4d, a second baffle plate; 4e, a baffle III; 4f, a cushioning spring; 5. a steering wheel support; 6. and a steering wheel.
Detailed Description
The following are specific embodiments of the present invention and are further described with reference to the accompanying drawings, but the present invention is not limited to these embodiments.
Example one
As shown in fig. 1 to 4, this VTOL electric aircraft test platform includes platform frame 1, platform frame 1 includes the major structure that a plurality of pipe fittings were built, through the building of pipe fitting, form the installation room 1a that is used for placing the energy, equipment and balancing weight at the middle part of platform frame 1, the top of platform frame 1 is equipped with a plurality of screw motor 2, a plurality of screw motor 2 sets up around installation room 1a, be equipped with between screw motor 2 and the platform frame 1 and adjust screw motor 2 for the adjusting device 3 of distance between the installation room 1 a.
This vertical take-off and landing electric aircraft test platform mainly used tests the vertical lift of aircraft, installation room 1a on the platform frame 1 is used for placing the required energy of aircraft flight, equipment and balancing weight, according to different models, its internal plant number, position and weight all can change, screw motor 2 set up the position size and all need verify through the flight test, a plurality of screw motors 2 that 1 top of platform frame set up center on installation room 1a sets up, adjust for the distance between the installation room 1a through adjusting device 3 to screw motor 2, realize that this vertical take-off and landing electric aircraft test platform can carry out experimental authentication to the prototype of different research and development in-process, thereby reduce the cost of software in research and development.
As shown in fig. 1 to 4, the top of the platform frame 1 is provided with longitudinal beams 1b longitudinally arranged along the vertical take-off and landing electric aircraft testing platform, the number of the longitudinal beams 1b is two, the two longitudinal beams 1b are arranged along the transverse interval, the longitudinal beams 1b are fixedly connected with the pipe fitting, the front end and the rear end of each longitudinal beam 1b are respectively provided with a sliding sleeve 1c in a sleeved mode, the sliding sleeves 1c can slide along the length direction of the longitudinal beams 1b, and a bolt or a pin shaft used for fixing the sliding sleeves 1c is arranged between the sliding sleeves 1c and the longitudinal beams 1 b. The adjusting device 3 includes two upper cross frames 3a connected to the top surface of the sliding sleeve 1c, and the two upper cross frames 3a are respectively disposed at the front and rear portions of the longitudinal beam 1 b. Every upper transverse frame 3a all spans on two longerons 1b, and adjusting device 3 still includes to slide and sets up mount pad 3b on upper transverse frame 3a, and the quantity of mount pad 3b is four, and every upper transverse frame 3 a's both ends all are equipped with a mount pad 3b, and screw motor 2 install in with mount pad 3b on.
As shown in fig. 1 to 4, the mounting seat 3b slides along the length direction of the upper cross frame 3a, so as to drive the propeller motor 2 to adjust the transverse position on the platform frame 1, the sliding sleeve 1c slides on the longitudinal beam 1b, and drives the upper cross beam to move longitudinally along the platform frame 1, so as to adjust the distance between the propeller motor 2 and the mounting chamber 1a, so that the test platform for the vertical take-off and landing electric aircraft can perform test certification on prototype machines in different research and development processes, and thus the test cost in research and development is reduced.
The mount pad 3b includes the connecting plate 3b1 that two intervals set up, goes up crossbearer 3a and is located between two connecting plates 3b1, has all seted up the pilot hole on going up crossbearer 3a and two connecting plates 3b1, is equipped with fastener 3c in the pilot hole and fixes two connecting plates 3b1 and last crossbearer 3 a. According to actual use requirements, a plurality of assembly holes are arranged on the upper cross frame 3a at intervals along the length direction of the upper cross frame.
As shown in fig. 1 to 3, the platform frame 1 further includes two lower beams 1d located at the bottom, the two lower beams 1d are arranged at intervals along the longitudinal direction of the platform frame 1, and the lower beams 1d and the upper beams 3a are parallel to each other. Platform frame 1's bottom still is equipped with bradyseism structure 4, bradyseism structure 4 is including the vertical sleeve 4a that sets up on every bottom end rail 1d both ends respectively, it is provided with telescopic shaft 4b to slide in the sleeve 4a, telescopic shaft 4 b's top is equipped with and prevents that telescopic shaft 4b from deviating from a baffle 4c in the sleeve 4a, telescopic shaft 4 b's bottom is equipped with baffle two 4d, sleeve 4 a's bottom is equipped with baffle three 4e, be equipped with the bradyseism spring 4f of cup jointing on telescopic shaft 4b between baffle three 4e and the baffle two 4 d.
Because of the large number of instability factors in flight testing, there may be a risk of falling during vertical ascent and descent. When the airplane falls, the baffle II 4d is stressed to drive the telescopic shaft 4b to move upwards in the sleeve 4a, the baffle II 4d applies pressure to the cushioning spring 4f to compress the cushioning spring 4f, so that the cushioning spring 4f absorbs impact, hard landing when the VTOL electric airplane test platform falls is avoided, damage to the VTOL electric airplane test platform is reduced, test cost in research and development is reduced, the baffle I4 c can prevent the VTOL electric airplane test platform from falling out of the sleeve 4a after being lifted off the ground, at least two lower cross beams 1d which are longitudinally arranged along the platform frame 1 are arranged at the bottom of the platform frame 1, structures such as the sleeve 4a are arranged at two ends of each lower cross beam 1d, the overall cushioning and energy absorption effects of the VTOL electric airplane test platform can be improved, damage to the VTOL electric airplane test platform is reduced, and test and research and development cost in research and development is reduced.
As shown in fig. 1 to 3, a steering wheel support 5 is connected to the bottom of the second baffle 4d, and a steering wheel 6 is connected to the bottom of the steering wheel support 5. When the vertical take-off and landing electric aircraft testing platform falls, the impact on the vertical take-off and landing electric aircraft testing platform can be dispersed through the rolling of the steering wheel 6, and the damage to the vertical take-off and landing electric aircraft testing platform is reduced.
As shown in fig. 1 to 4, the platform frame 1 further includes a support rod 1e, two ends of the support rod 1e are respectively connected to the upper cross frame 3a and the lower cross beam 1d, specifically, two ends of the support rod 1e are both connected to universal joints 1f, the universal joints 1f at two ends of the support rod 1e are respectively connected to the upper cross frame 3a and the lower cross beam 1d, a vertical height distance between the upper cross frame 3a and the lower cross beam 1d is smaller than a length of the support rod 1e, the support rod 1e is disposed in an inclined manner relative to the upper cross frame 3a, and the support rod 1e is also disposed in an inclined manner relative to the lower cross beam 1 d. Bracing piece 1e sets up for last crossbearer 3a slope, and bracing piece 1e also sets up for bottom end rail 1d slope, vertical impact force when can falling VTOL electric aircraft test platform disperses through the direction that sets up of bracing piece 1e, reduce the impact to last crossbearer 3a, because last crossbearer 3a needs to carry out the regulation on the longitudinal position according to the test demand of difference, the both ends of bracing piece 1e are passed through universal joint 1f and are connected with last crossbearer 3a and bottom end rail 1d, and the vertical height distance is less than the length of bracing piece 1e between last crossbearer 3a and the bottom end rail 1d, can keep being connected with last crossbearer 3a and bottom end rail 1d when not changing bracing piece 1e, thereby reduce the test cost in research and development.
Example two
The present embodiment is substantially the same as the above embodiments, and the difference is that in the present embodiment, a sliding slot is formed on the upper cross frame 3a along the length direction thereof, the mounting seat 3b is slidably disposed in the sliding slot, and the mounting seat 3b and the upper cross frame 3a are connected and fixed by the fastening member 3 c.
The bottom of platform frame 1 is equipped with three longerons 1b, and the both ends of every longeron 1b all are equipped with bradyseism structure 4, are equipped with the bradyseism gum cover of cup jointing on telescopic shaft 4b between baffle three 4e and the baffle two 4d in the bradyseism structure 4.
Be equipped with three upper cross frames 3a on longeron 1b, every upper cross frame 3a all spanes on two longerons 1b, and adjusting device 3 still includes to slide and sets up mount pad 3b on upper cross frame 3a, and the quantity of mount pad 3b is six, and every upper cross frame 3 a's both ends all are equipped with a mount pad 3b.
The specific embodiments described herein are merely illustrative of the spirit of the invention. Various modifications or additions may be made to the described embodiments, or alternatives may be employed, by those skilled in the art, without departing from the spirit or ambit of the invention as defined in the appended claims.
Although the terms platform frame, installation room and stringer are used more here, the possibility of using other terms is not excluded. These terms are used merely to more conveniently describe and explain the nature of the present invention; they are to be construed as being without limitation to any additional limitations that may be imposed by the spirit of the present invention.
Claims (7)
1. The utility model provides a VTOL electric aircraft test platform, includes platform frame (1) and a plurality of screw motor (2), its characterized in that, have installation room (1 a) that is used for placing energy, equipment and balancing weight on platform frame (1), a plurality of screw motor (2) are located the top of platform frame (1), and a plurality of screw motor (2) set up around installation room (1 a), be equipped with between screw motor (2) and platform frame (1) and adjust screw motor (2) for adjusting device (3) of distance between installation room (1 a), platform frame (1) bottom is equipped with bradyseism structure (4) that can carry out the bradyseism in platform frame (1), adjusting device (3) include crossbearer (3 a) and slide and set up mount pad (3 b) on last crossbearer (3 a), go up crossbearer (3 a) and transversely set up in the top of platform frame (1), screw motor (2) install on mount pad (3 b), platform frame (1) is including vertical setting up longeron (1 b) the length of longitudinal slide sleeve (1 c) and slide sleeve (1 c) can link to each other along its length.
2. The vtol electric aircraft testing platform according to claim 1, characterized in that the installation room (1 a) is located in the middle of the platform frame (1).
3. The VTOL electric aircraft testing platform according to claim 2, characterized in that the mounting seat (3 b) comprises two connecting plates (3 b 1) arranged at intervals, the upper cross frame (3 a) is positioned between the two connecting plates (3 b 1), and the upper cross frame (3 a) is connected with the two connecting plates (3 b 1) through a fastener (3 c).
4. The vertical take-off and landing electric aircraft test platform as claimed in claim 2 or 3, wherein the bottom of the platform frame (1) is provided with at least two lower beams (1 d) arranged at intervals along the longitudinal direction of the platform frame, the shock absorption structure (4) comprises sleeves (4 a) vertically arranged at two ends of each lower beam (1 d), telescopic shafts (4 b) are arranged in the sleeves (4 a) in a sliding manner, the top ends of the telescopic shafts (4 b) are provided with first baffle plates (4 c) for preventing the telescopic shafts (4 b) from being separated from the sleeves (4 a), the bottom ends of the telescopic shafts (4 b) are provided with second baffle plates (4 d), the bottom ends of the sleeves (4 a) are provided with third baffle plates (4 e), and shock absorption springs (4 f) sleeved on the telescopic shafts (4 b) are arranged between the third baffle plates (4 e) and the second baffle plates (4 d).
5. The VTOL electric aircraft testing platform according to claim 4, wherein a steering wheel bracket (5) is connected to the bottom of the second baffle plate (4 d), and a steering wheel (6) is connected to the bottom of the steering wheel bracket (5).
6. The VTOL electric aircraft testing platform according to claim 4, characterized in that the platform frame (1) further comprises a support bar (1 e), and both ends of the support bar (1 e) are respectively connected with the upper cross frame (3 a) and the lower cross beam (1 d).
7. The VTOL electric aircraft testing platform according to claim 6, wherein the two ends of the supporting rod (1 e) are connected with universal joints (1 f), the universal joints (1 f) at the two ends of the supporting rod (1 e) are respectively connected with an upper cross frame (3 a) and a lower cross beam (1 d), the vertical height distance between the upper cross frame (3 a) and the lower cross beam (1 d) is less than the length of the supporting rod (1 e), the supporting rod (1 e) is arranged obliquely relative to the upper cross frame (3 a), and the supporting rod (1 e) is also arranged obliquely relative to the lower cross beam (1 d).
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110069118.XA CN112722324B (en) | 2021-01-19 | 2021-01-19 | Vertical take-off and landing electric aircraft test platform |
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| CN202110069118.XA CN112722324B (en) | 2021-01-19 | 2021-01-19 | Vertical take-off and landing electric aircraft test platform |
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| CN112722324B true CN112722324B (en) | 2022-12-20 |
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| CN113200152A (en) * | 2021-06-16 | 2021-08-03 | 青岛航空技术研究院 | Small-sized composite wing unmanned aerial vehicle power testing device and testing method thereof |
| CN116119024B (en) * | 2023-04-17 | 2023-07-18 | 成都沃飞天驭科技有限公司 | Aircraft test platform and design method thereof |
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| CN111959822A (en) * | 2020-09-02 | 2020-11-20 | 厦门市汉飞鹰航空科技有限公司 | Can demonstrate iron bird test bench of unmanned aerial vehicle take off and land power |
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| CN106061838A (en) * | 2014-01-20 | 2016-10-26 | 罗博杜伯公司 | Multicopters with variable flight characteristics |
| KR20170135579A (en) * | 2016-05-31 | 2017-12-08 | 김성남 | Multi-purpose drone with slide arm |
| US10183747B1 (en) * | 2016-08-26 | 2019-01-22 | Kitty Hawk Corporation | Multicopter with boom-mounted rotors |
| CN106628130A (en) * | 2016-12-26 | 2017-05-10 | 中国航空工业集团公司西安飞机设计研究所 | Unmanned aerial vehicle nose landing gear shock absorption and steering mechanism |
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