Flight test attitude limiting device for eVTOL
By designing flight test attitude restriction devices for eVTOL, including test benches, anti-fall ropes and attitude restriction mechanisms, the problem of the inability to effectively protect eVTOL aircraft in the prior art is solved, especially in high altitude and large attitude angle scenarios, the safety of the aircraft and the accuracy and effectiveness of the test are improved.
Patent Information
- Application Number
- CN202421772835.4
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Priority Date
- 2024-06-26
- Filing Date
- 2024-07-25
- Publication Date
- 2025-05-27
- Estimated Expiration
- 2034-07-25
AI Technical Summary
The prior art cannot effectively protect the aircraft in eVTOL flight tests, especially in high altitude and large attitude angle scenarios, and the adjustability and accuracy of the protection device are insufficient.
A flight test attitude restriction device for eVTOL is designed, including a test bench, an aircraft anti-fall rope and an attitude restriction mechanism. The attitude restriction mechanism consists of an attitude restriction frame, an attitude restriction column, a support column and a fixed base. Through the combination and adjustment of these components, the allowable attitude of the aircraft is accurately controlled.
Through the combination of the attitude restriction frame and the attitude limit column, the precise control of the attitude of the aircraft is solved, and the problem of the inability to effectively protect the aircraft at high altitude and large attitude angle scenarios in the prior art is solved, and the safety of the aircraft during the test process and the accuracy and effectiveness of the test are improved.
Smart Images
Figure CN222905875U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of aviation, in particular to a flight test attitude limiting device for eVTOL. Background Technique
[0002] During the flight control test of an electric vertical takeoff and landing aircraft (eVTOL), due to the maturity and reliability of systems such as the flight control system, navigation system, three-electric system (power supply, electronic speed controller, motor), ground control system, and aircraft structure, as well as errors and other unpredictable factors that may occur during the test, irreversible damage may be caused to the aircraft structure and systems. Therefore, necessary protection for the aircraft is required during the flight test of eVTOL.
[0003] Currently, most drone and eVTOL companies mainly use the method of adding restraint poles and restraint ropes to provide additional protection for the aircraft. However, the defects of these protection measures are mainly as follows:
[0004] (1) It is unable to provide effective protection for the aircraft in some specific dangerous scenarios, such as power failure, motor failure, and flight control system failure at relatively high altitudes;
[0005] (2) The protection means is single and redundant protection cannot be provided;
[0006] (3) The adjustability and accuracy of the entire protection device are poor. Content of the Utility Model
[0007] The main technical problem to be solved by the utility model is to provide a flight test attitude limiting device for eVTOL, which has the advantages of high reliability, accurate positioning, high safety, etc., and has a broad market prospect in the application and popularization of flight test protection devices.
[0008] To solve the above technical problem, a technical solution adopted by the utility model is:
[0009] Provide a flight test attitude limiting device for eVTOL, which includes: a test bench, an aircraft anti-fall pull rope, and an attitude limiting mechanism. The aircraft anti-fall pull rope is arranged on the test bench and connected to the aircraft to be used for pulling the aircraft.
[0010] The attitude limiting mechanism includes an attitude limiting frame, a fixed base, attitude limiting columns, and support columns. One or more groups of the attitude limiting columns are oppositely arranged on both sides below the test bench. One fixed base is provided with one of the attitude limiting columns and two of the support columns. The bottoms of the attitude limiting column and the support columns are rotatably connected to the fixed base, and the top of the attitude limiting column is movably connected to the tops of the two support columns, so as to adjust the installation inclination angle of the attitude limiting column by connecting support columns of different lengths. The attitude limiting frame is connected to the aircraft, and the outer side of the attitude limiting frame is sleeved on the attitude limiting column to cooperate with the attitude limiting column to limit the attitude of the aircraft during flight.
[0011] In a preferred embodiment of the present invention, the test bench is a gantry.
[0012] In a preferred embodiment of the present invention, the anti-falling pull rope of the aircraft is made of a steel cable.
[0013] In a preferred embodiment of the present invention, one or more limiting openings movably connected to the attitude limiting column are provided on the outer side of the attitude limiting frame.
[0014] In a preferred embodiment of the present invention, the support column is a telescopic structure.
[0015] In a preferred embodiment of the present invention, the aircraft is connected to the ground and the test bench through a ground restraint rope.
[0016] In a preferred embodiment of the present invention, the upper part of the support column is movably connected to the attitude limiting column through a spherical plain bearing and a lug bolt.
[0017] In a preferred embodiment of the present invention, the support column and the attitude limiting column are connected to the fixed base through a pillow block bearing.
[0018] In a preferred embodiment of the present invention, the attitude limiting frame is connected to the fuselage and / or landing gear of the aircraft and rises and falls together with the aircraft.
[0019] The beneficial effects of the present invention are as follows: By combining the attitude limiting frame and the attitude limiting column to precisely control the allowed flight attitude, the problem that the aircraft cannot be protected at high altitude and large attitude angles in the test bench in the prior art is solved, and the safety of the aircraft during the test process, as well as the accuracy and effectiveness of the flight test, are improved. Description of the Drawings
[0020] To more clearly illustrate the technical solutions in the embodiments of the present utility model, the following will briefly introduce the drawings required for description in the embodiments. Obviously, the drawings in the following description are only some embodiments of the present utility model. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings, where:
[0021] Figure 1 is a schematic structural diagram of a preferred embodiment of a flight test attitude limiting device for eVTOL of the present utility model;
[0022] Figure 2 is a partial structural diagram of the attitude limiting mechanism of a preferred embodiment of a flight test attitude limiting device for eVTOL of the present utility model;
[0023] Figure 3 is another partial structural diagram of the attitude limiting mechanism of a preferred embodiment of a flight test attitude limiting device for eVTOL of the present utility model. Detailed implementation manners
[0024] The following will clearly and completely describe the technical solutions in the embodiments of the present utility model. Obviously, the described embodiments are only some of the embodiments of the present utility model, rather than all of them. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative efforts belong to the scope of protection of the present utility model.
[0025] Please refer to Figures 1-3 , the embodiments of the present utility model include:
[0026] A flight test attitude limiting device for eVTOL, whose structure includes: a test bench 1, an aircraft tow rope 2, and an attitude limiting mechanism 3. The attitude limiting mechanism is arranged below the test bench and is connected to the aircraft 4 to limit the attitude of the aircraft during flight.
[0027] Further preferably, the test bench can adopt a gantry.
[0028] Structure: The attitude limiting mechanism includes an attitude limiting frame 31 and attitude limiting columns 32. The attitude limiting frame is connected to the aircraft, and one or more groups of the attitude limiting columns are oppositely arranged on both sides of the aircraft, and the outside of the attitude limiting frame is sleeved on the attitude limiting columns.
[0029] Further preferably, the attitude limiting frame is fixed to the aircraft and / or the landing gear through a cross chuck and rises and falls together with the aircraft.
[0030] Further preferably, the attitude limiting column is fixed to the ground with expansion bolts through the fixed base 33.
[0031] Further preferably, a support column 34 is connected to the attitude limiting column to increase the stiffness and stability of the column.
[0032] Further preferably, the bottoms of the attitude limiting column and the support column are rotatably arranged on the fixed base, and the upper part of the support column is movably connected to the attitude limiting column through a spherical plain bearing 35 and lug bolts, so as to adjust the angle of the attitude limiting column by adjusting the lengths of the two support columns. Among them, the support column can directly adopt a telescopic rod, or support columns of different lengths can be directly installed.
[0033] In this embodiment, when the length of the support column is shortened, the upper part of the attitude limiting column inclines outward away from the aircraft, so that the included angle between the column and the aircraft becomes larger; when the length of the support column is extended, the upper part of the attitude limiting column inclines inward close to the aircraft, so that the included angle between the column and the aircraft becomes smaller.
[0034] Function: Through the attitude limiting frame, it is avoided that the attitude of the aircraft is too large during flight tests, resulting in the wings or fuselage touching the ground and the attitude getting out of control.
[0035] Method: Install an attitude limiting column at each of the four corners far away from the aircraft and fix it to the ground with expansion bolts; use 7-series aviation aluminum alloy pipes to connect with the landing gear of the aircraft to form an attitude limiting frame, which extends the lateral and longitudinal lengths of the aircraft. The outer side of the attitude limiting frame is sleeved on the attitude limiting column; when conducting flight tests, once the aircraft has excessive pitching, rolling or yawing, the limiting frame will contact the four columns, thus limiting the maximum attitude angle of the aircraft, so that the attitudes such as pitching, rolling and yawing can be accurately controlled within the range of the attitude limiting frame. In addition, the size and position distance of the attitude limiting frame and the attitude limiting column can be adjusted according to actual usage requirements to adjust the maximum allowable attitude angle of flight.
[0036] The beneficial effect of a flight test attitude limiting device for eVTOL of the present utility model is that: by combining the attitude limiting frame and the attitude limiting column to accurately control the allowable flight attitude, it solves the problem that the aircraft cannot be protected at high altitudes and large attitude angles in the test bench in the prior art, and improves the safety of the aircraft during the test process as well as the accuracy and effectiveness of the flight test.
[0037] The above are only the embodiments of the present utility model, and thus do not limit the patent scope of the present utility model. Any equivalent structure or equivalent process transformation made by using the content of the specification of the present utility model, or directly or indirectly applied in other related technical fields, shall be similarly included in the patent protection scope of the present utility model.
Claims
1. A flight test attitude limiting device for eVTOL, characterized in that: include: A test bench, an aircraft anti-fall pull rope, and an attitude limiting mechanism. The aircraft anti-fall pull rope is arranged on the test bench and connected to the aircraft to pull the aircraft. The attitude limiting mechanism includes an attitude limiting frame, a fixed base, an attitude limiting column, and a support column. One or more groups of the attitude limiting columns are relatively arranged on both sides below the test bench. One attitude limiting column and two support columns are arranged on a fixed base. The bottoms of the attitude limiting column and the support columns are rotatably connected to the fixed base. The top of the attitude limiting column is movably connected to the tops of the two support columns to adjust the installation inclination angle of the attitude limiting column by connecting support columns of different lengths. The attitude limiting frame is connected to the aircraft, and the outer side of the attitude limiting frame is sleeved on the attitude limiting column to cooperate with the attitude limiting column to limit the attitude of the aircraft during flight.
2. The flight test attitude limiting device for eVTOL according to claim 1, characterized in that: The test bench is a gantry.
3. The flight test attitude limiting device for eVTOL according to claim 1, characterized in that: The aircraft anti-fall pull rope adopts a steel cable.
4. The flight test attitude limiting device for eVTOL according to claim 1, characterized in that: The outer side of the posture limiting frame is provided with one or more limiting openings movably connected to the posture limiting columns.
5. The flight test attitude limiting device for eVTOL according to claim 1, characterized in that: The support column is a retractable structure.
6. The flight test attitude limiting device for eVTOL according to claim 1, characterized in that: The aircraft is connected to the ground test bench through ground restraint ropes.
7. The flight test attitude limiting device for eVTOL according to claim 1, characterized in that: The upper part of the support column is movably connected to the attitude limiting column through a joint bearing and a lug bolt.
8. The flight test attitude limiting device for eVTOL according to claim 1, characterized in that: The support column and the attitude limiting column bronze drum seat bearing are connected with the fixed base.
9. The flight test attitude limiting device for eVTOL according to claim 1, characterized in that: The attitude limiting frame is connected to the aircraft fuselage and / or the landing gear, and rises and falls together with the rise and fall of the aircraft.