A hover test flight test platform of an electric vertical take-off and landing aircraft

Abstract

The utility model discloses a kind of hoisting flight test platform of electric vertical take-off and landing aircraft, including guide rail assembly, support, hoisting assembly and hoisting assembly, guide rail assembly includes two mutually parallel tracks and the support of slidingly being arranged on track, support is made of crossbeam and two vertical rods, two vertical rods are respectively arranged on the support of two tracks.Hoisting assembly includes motor, lifting lug and connecting piece, motor is set on crossbeam by base, and can be moved along the length direction of crossbeam, motor is used to drive lifting lug to move up and down, connecting piece is set in the lower part of lifting lug.Hang flying tooling includes heading beam, two horizontal beams and two lifting ropes.The utility model's test platform is mainly applied to manned or unmanned composite wing electric vertical take-off and landing aircraft hoisting flight test scene, solve the problem that traditional flight test platform is poor in adaptability, installation and maintenance are complicated, difficult to flexibly adjust, realize safe controllable, modular assembly, multi-size aircraft adaptation flight test demand.

Description

Technical Field

[0001] This utility model relates to the field of aircraft flight test equipment technology, specifically to a lifting flight test platform for an electric vertical take-off and landing aircraft. Background Technology

[0002] Suspension-based flight testing refers to suspending (or partially restraining) an aircraft using a pylon, crane, or ground tethering device before it achieves full free flight, and conducting tests on the multirotor system's functionality, control laws, and attitude stability under safe and controllable conditions. In the research and testing of compound-wing electric aircraft (i.e., aircraft possessing both fixed-wing and multirotor capabilities), suspension-based flight testing (or "tethered hovering flight testing") in a multirotor configuration is a crucial and common testing method. Its main considerations are as follows:

[0003] 1. By hoisting the aircraft for test flights, it is securely fixed (e.g., by suspending it with ropes), and only the multi-rotor power system is activated for hovering or minor attitude adjustments. This ensures that even if a problem occurs, it will not lead to a free fall.

[0004] 2. In multi-rotor mode, the fixed wings of the aircraft generate almost no lift; all lift and attitude control come from the rotors. This is one of the most unique and complex flight phases for compound wing aircraft. The lift-up test flight is the first step in verifying the design goals for this phase.

[0005] The purpose of hoisting test flights is to verify the stability, controllability, and propulsion of the compound-wing electric aircraft under conditions that prevent it from crashing. Only after confirming safety and reliability through hoisting (or tethering) test flights will it proceed to free hovering flight, then transitional flight, and finally full-mode conversion flight. Therefore, the tooling for hoisting test flights is crucial.

[0006] Reference 1: Chinese patent document with publication number CN223132380U.

[0007] Reference 1 discloses a UAV hoisting test device, including two clamps for fixing the UAV, upper and lower clamps connected to a boom, the upper end of the boom connected to the front end of a safety rope with a safety length, the safety rope passing through a pulley installed on a crossbeam, the rear end of the safety rope connected to a take-up and release reel on a motor, the motor rotating to control the take-up and release of the safety rope, a linear displacement sensor connected to the upper end of the boom, the linear displacement sensor monitoring the distance and speed of the boom's movement, and controlling the motor to take up and release the safety rope, the length and speed of the safety rope taken up and released by the motor being the same as the distance and speed of the boom's movement monitored by the linear displacement sensor, the device is equipped with an emergency button, when the emergency button is pressed, the UAV ground control station receives a signal to control the UAV to stop propellers, the motor quickly retracts the safety rope to the safety length, and the safety rope slowly lifts the UAV to the initial test position. Utility Model Content

[0008] The purpose of this invention is to provide an electric vertical take-off and landing aircraft lifting test flight platform that differs from existing technical solutions.

[0009] The technical solution adopted in this utility model is: a lifting test flight platform for an electric vertical takeoff and landing aircraft, comprising:

[0010] A guide rail assembly comprising two parallel rails and supports slidably mounted on the rails; and

[0011] The support frame is a gantry structure, consisting of a crossbeam and two uprights, each mounted on a support for one of the two tracks; and

[0012] A lifting assembly, comprising a motor, lifting lugs, and connectors, wherein the motor is mounted on a crossbeam via a base and is movable along the length of the crossbeam; the motor drives the lifting lugs to move up and down; and connectors are located at the lower part of the lifting lugs; and

[0013] The hoisting fixture includes a heading beam, two transverse beams, and two hoisting ropes. The two transverse beams are distributed along the length of the heading beam, and the middle of the transverse beams is fixedly connected to the heading beam. The hoisting ropes are set between the two ends of the same transverse beam.

[0014] As a further optimization of the lifting test flight platform for an electric vertical take-off and landing aircraft of this utility model: the top of the base is provided with traveling wheels that can slide along the length of the crossbeam, the motor is fixedly installed on the base, and the output end of the motor is connected to the lifting lug through a transmission cable.

[0015] As a further optimization of the lifting test flight platform for an electric vertical take-off and landing aircraft of this utility model: the crossbeam includes several beams, which are connected in series along the length direction, and adjacent beams can be detachably fixed together.

[0016] As a further optimization of the lifting test flight platform for an electric vertical take-off and landing aircraft of this utility model: the track consists of an I-beam and a slide rail set on the top of the I-beam.

[0017] As a further optimization of the lifting test flight platform for an electric vertical take-off and landing aircraft of this utility model: the support includes a support body, a set of movable main wheels, an auxiliary wheel set, and a bracket mounting seat. The bracket mounting seat is set on the upper end face of the support body. The set of movable main wheels includes two movable main wheels set at the front and rear ends of the support body, and the movable main wheels are locked on the slide rail. The support body is provided with auxiliary wheel sets at the front, middle, and rear. Each auxiliary wheel set includes two auxiliary wheels located on both sides of the support body, and the auxiliary wheels travel along the lower surface of the upper flange of the I-beam.

[0018] As a further optimization of the lifting test flight platform for an electric vertical take-off and landing aircraft of this utility model: a heading beam mounting pipe is provided on the lower end face of the middle part of the transverse beam, and the heading beam passes through the heading beam mounting pipes of the two transverse beams in sequence.

[0019] As a further optimization of the lifting test flight platform for an electric vertical take-off and landing aircraft of this utility model: the side wall of the heading beam mounting tube is provided with a locking hole, and a locking bolt that can be screwed into the locking hole to fasten the heading beam and the heading beam mounting tube together.

[0020] As a further optimization of the lifting test flight platform for an electric vertical take-off and landing aircraft of this utility model: the transverse beam is connected to the lifting rope via lifting lugs.

[0021] As a further optimization of the lifting test platform for an electric vertical take-off and landing aircraft of this utility model: the lifting lug includes a transverse beam mounting tube, a pin, a locking pin, and two vertical rods. The vertical rods are set at the bottom of the transverse beam mounting tube, and the two vertical rods are parallel to each other. The lower part of the vertical rod is provided with a lifting lug hole, and the pin can pass through the two lifting lug holes and be fixed by the locking pin.

[0022] As a further optimization of the lifting test flight platform for an electric vertical take-off and landing aircraft of this utility model: the upright is an A-shaped structure.

[0023] This invention offers the following advantages: The testing platform is suitable for both manned and unmanned compound wing aircraft, and is not limited by the specific configuration of the compound wing aircraft. The entire mobile platform adopts a modular design, facilitating installation, disassembly, maintenance, and expansion. Furthermore, the lifting fixture features a flexible design, allowing for adjustments to accommodate aircraft of different sizes. Attached Figure Description

[0024] Figure 1 This is a schematic diagram of the working state of the test platform of this utility model;

[0025] Figure 2 This is a schematic diagram of the guide rail assembly in the test platform of this utility model;

[0026] Figure 3 This is a schematic diagram of the support structure in the test platform of this utility model;

[0027] Figure 4 This is a schematic diagram of the hoisting components in the test platform of this utility model;

[0028] Figure 5 This is a schematic diagram of the hoisting fixture in the test platform of this utility model;

[0029] Figure 6 This is a schematic diagram of the lifting lugs in the test platform of this utility model;

[0030] Figure 7 This is a structural schematic diagram of the hoisting fixture (for hoisting aircraft) in the test platform of this utility model;

[0031] The diagram labels are as follows: 1. Guide rail assembly; 101. Rail; 102. Support; 1021. Support body; 1022. Main wheel assembly; 1023. Auxiliary wheel assembly; 1024. Bracket mounting base; 2. Bracket; 201. Crossbeam; 202. Upright; 3. Lifting assembly; 301. Motor; 302. Lifting lug; 303. Connector; 304. Base; 4. Lifting fixture; 401. Heading beam; 402. Transverse beam; 403. Lifting rope; 404. Heading beam mounting pipe; 405. Transverse beam mounting pipe; 406. Pin; 407. Locking pin; 408. Vertical rod; 409. Lifting lug hole; 410. Lifting lug. Detailed Implementation

[0032] To better understand this utility model, the following embodiments further illustrate the content of this utility model, but the content of this utility model is not limited to the following embodiments.

[0033] like Figure 1 The diagram shows the overall working state of an electric vertical takeoff and landing (eVTOL) aircraft lifting and flight test platform. The platform includes a guide rail assembly 1, a support frame 2, a lifting assembly 3, and a lifting and flight tooling 4. Each component is modularly designed and can be disassembled and assembled. The guide rail assembly enables overall movement, and the lifting assembly and lifting and flight tooling work together to lift and adjust the attitude of the aircraft, adapting to the flight test requirements of compound wing aircraft of different sizes.

[0034] like Figure 2 As shown, the track assembly 1 provides a foundation for the movement of the test platform, enabling the overall translation of the support 2, and includes the track 101 and the support 102.

[0035] Track 101 consists of an I-beam and a slide rail set on top of the I-beam. The I-beam is made of high-strength steel, and its high structural strength allows it to withstand large loads. The slide rail design ensures smooth movement of the support and is suitable for adjusting the platform position during test flights.

[0036] The support 102 includes a support body 1021, a main moving wheel assembly 1022, an auxiliary wheel assembly 1023, and a support mounting base 1024. The main moving wheel assembly 1022 includes two main moving wheels located at the front and rear ends of the support body, mounted on slide rails to drive the support to move along the rails. The auxiliary wheel assemblies 1023 are located at the front, middle, and rear of the support body, each assembly including two auxiliary wheels on both sides of the support body, traveling along the lower surface of the upper flange of the I-beam. The main wheel assembly and the auxiliary wheel assembly work together to ensure both mobility and stability, preventing platform swaying during flight tests and ensuring test safety.

[0037] like Figure 3 As shown, bracket 2 provides installation support for the hoisting components and adopts a gantry structure, including a crossbeam 201 and two uprights 202.

[0038] The crossbeam 201 is composed of several beam segments connected in series along its length, with adjacent beams being detachably fixed together by bolts. The modular splicing design facilitates transportation, installation, and subsequent maintenance. The length of the crossbeam can be extended by increasing or decreasing the number of beams to adapt to different flight test sites and aircraft sizes.

[0039] The upright 202 adopts an A-shaped structure, with its lower end fixed to the bracket mounting seat 1024 of the support 102, and its upper end detachably connected to the crossbeam 201. The upright 202 is used to support the weight of the crossbeam and the hoisting assembly, and to transfer the load to the guide rail assembly. Compared with the traditional straight rod structure, the A-shaped structure has stronger stability and outstanding anti-rollover and anti-overturning capabilities, which can effectively disperse the lateral forces generated by the aircraft during flight testing and ensure the overall rigidity of the support.

[0040] like Figure 4 As shown, the lifting assembly 3 is used to realize the lifting and adjustment of the aircraft, including motor 301, lifting lug 302, connector 303 and base 304.

[0041] The base 304 is equipped with wheels on top, which are compatible with the track of the crossbeam 201, allowing the motor 301 to slide along the length of the crossbeam. A locking mechanism is provided on the side of the base, which can be fixed after sliding to the target position, thus allowing for horizontal adjustment of the motor and the lifting lug.

[0042] The motor 301 is fixedly mounted on the base 304, and its output end is connected to the lifting lug 302 through a transmission cable (such as a high-strength steel wire rope) to drive the lifting lug 302 to move up and down and adjust the lifting height of the aircraft.

[0043] Lifting lug 302 and connector 303: The lifting lug 302 is a ring structure used to connect the transmission cable and the connector 303. The connector 303 adopts a universal joint structure and is located at the lower part of the lifting lug 302 for connecting with the lifting tool 4.

[0044] like Figure 5 and 6 As shown, the hoisting tool 4 is used to connect the hoisting components to the aircraft, including a heading beam 401, two transverse beams 402 and two hoisting ropes 403.

[0045] The transverse beams 402 are distributed along the length of the directional beams 401, with directional beam mounting tubes 404 located on their lower ends. The directional beams 401 pass through the directional beam mounting tubes 404 of the two transverse beams in sequence. The side walls of the directional beam mounting tubes 404 have locking holes; locking bolts are screwed into these holes to secure the directional beams 401 to the mounting tubes. By adjusting the spacing of the transverse beams on the directional beams, the system can accommodate aircraft with different wingspans. The locking bolts ensure that the transverse beams remain in place during flight testing, preventing loosening.

[0046] The transverse beam 402 is connected to the lifting rope 403 via lifting lugs 410. The lifting lug 410 includes a transverse beam mounting tube 405, a pin 406, a locking pin 407, and two vertical rods 408. The transverse beam mounting tube 405 is fitted onto the transverse beam 402, and the vertical rods 408 are fixed to the bottom of the transverse beam mounting tube 405. The lower part has lifting lug holes 409. The pin 406 passes through the two lifting lug holes 409 and is fixed by the locking pin 407. The lifting rope 403 is connected to the pin 406. The cooperation between the pin and the locking pin ensures a secure connection and easy disassembly. The lifting rope is made of high-strength, flexible material, which can buffer vibrations and impacts during aircraft test flights. Simultaneously, the two lifting ropes are connected to both ends of the same transverse beam, forming a symmetrical lifting system to ensure the aircraft's stable posture during lifting.

[0047] Flight test process:

[0048] Connect the two lifting ropes 403 of the hoisting tool 4 to the aircraft's preset lifting points (e.g., Figure 7 (As shown), ensure a secure connection; start motor 301, and slowly lift lug 302 via transmission cable to lift the aircraft to the preset test flight altitude (ensuring the aircraft is off the ground and there is no risk of free fall), then turn off the motor and lock the transmission cable.

[0049] If the aircraft's horizontal position needs to be adjusted, loosen the locking mechanism of the base 304, push the base to slide along the crossbeam 201 to the target position, and then lock it again; if the aircraft's front and rear position needs to be adjusted, push the support 102 to move along the track 101 to achieve overall position adjustment.

[0050] The aircraft initiates hovering or small-range attitude adjustment tests using the multi-rotor system. During the test flight, the flexibility of the suspending rope 403 and the universal adjustment function of the connector 303 can adapt to the slight attitude changes of the aircraft, avoiding the impact of rigid constraints on the test results. The stable structure of the guide rail assembly and the support ensures that the platform does not shake, guaranteeing test safety.

[0051] Turn off the aircraft's multi-rotor system, start motor 301 to slowly lower the lifting lug 302, land the aircraft smoothly, disconnect the lifting rope from the aircraft, and complete the test flight.

[0052] The test platform of this utility model is mainly used in the lifting test flight scenarios of manned or unmanned compound-wing electric vertical take-off and landing aircraft. It solves the problems of poor adaptability, cumbersome installation and maintenance, and difficulty in flexible adjustment of traditional test flight platforms, and realizes the test flight requirements of safe and controllable, modular assembly and adaptability to aircraft of multiple sizes.

[0053] The specific embodiments of this utility model have been described above. It should be understood that this utility model is not limited to the specific embodiments described above, and those skilled in the art can make various modifications or variations within the scope of the claims, which do not affect the substantive content of this utility model.

Claims

1. A lifting test flight platform for an electric vertical takeoff and landing aircraft, characterized in that, include: The guide rail assembly (1) includes two parallel rails (101) and a support (102) slidably mounted on the rails (101); and The support frame (2) is a gantry structure, consisting of a crossbeam (201) and two uprights (202), with the two uprights (202) respectively mounted on the supports (102) of the two tracks (101); and The lifting assembly (3) includes a motor (301), a lifting lug (302), and a connector (303). The motor (301) is mounted on the crossbeam (201) via a base (304) and is capable of moving along the length of the crossbeam (201). The motor (301) drives the lifting lug (302) to move up and down. The connector (303) is located at the lower part of the lifting lug (302). The hoisting fixture (4) includes a heading beam (401), two transverse beams (402) and two hoisting ropes (403). The two transverse beams (402) are distributed along the length of the heading beam (401). The middle part of the transverse beams (402) is fixedly connected to the heading beam (401). The hoisting ropes (403) are set between the two ends of the same transverse beam (402).

2. The lifting test flight platform for an electric vertical takeoff and landing aircraft as described in claim 1, characterized in that, The base (304) is provided with a traveling wheel that can slide along the length of the crossbeam (201) at its top. The motor (301) is fixedly installed on the base (304), and the output end of the motor (301) is connected to the lifting lug (302) via a transmission cable.

3. The lifting test flight platform for an electric vertical takeoff and landing aircraft as described in claim 1, characterized in that, The crossbeam (201) includes several beams, which are connected in series along the length direction, and adjacent beams can be detachably fixed together.

4. The lifting test flight platform for an electric vertical takeoff and landing aircraft as described in claim 1, characterized in that, The track (101) consists of an I-beam and a slide rail set on top of the I-beam.

5. The lifting test flight platform for an electric vertical takeoff and landing aircraft as described in claim 4, characterized in that, The support (102) includes a support body (1021), a set of main moving wheels (1022), an auxiliary wheel set (1023), and a bracket mounting seat (1024). The bracket mounting seat (1024) is located on the upper surface of the support body (1021). The set of main moving wheels (1022) includes two main moving wheels located at the front and rear ends of the support body (1021), and the main moving wheels are mounted on the slide rail. The support body (1021) is provided with auxiliary wheel sets (1023) at the front, middle, and rear. Each auxiliary wheel set (1023) includes two auxiliary wheels located on both sides of the support body (1021), and the auxiliary wheels travel along the lower surface of the upper flange plate of the I-beam.

6. The lifting test flight platform for an electric vertical takeoff and landing aircraft as described in claim 1, characterized in that, The lower end face of the middle part of the transverse beam (402) is provided with a heading beam mounting pipe (404), and the heading beam (401) passes through the heading beam mounting pipes (404) of the two transverse beams (402) in sequence.

7. The lifting test flight platform for an electric vertical takeoff and landing aircraft as described in claim 6, characterized in that, The side wall of the heading beam mounting tube (404) is provided with a locking hole, into which a locking bolt can be screwed to fasten the heading beam (401) and the heading beam mounting tube (404) together.

8. The lifting test flight platform for an electric vertical takeoff and landing aircraft as described in claim 1, characterized in that, The transverse beam (402) is connected to the lifting rope (403) via lifting lugs.

9. The lifting test flight platform for an electric vertical takeoff and landing aircraft as described in claim 8, characterized in that, The lifting lugs include a transverse beam mounting tube (405), a pin (406), a locking pin (407), and two vertical rods (408). The vertical rods (408) are located at the bottom of the transverse beam mounting tube (405), and the two vertical rods (408) are parallel to each other. The lower part of the vertical rods (408) is provided with lifting lug holes (409). The pin (406) can pass through the two lifting lug holes (409) and be fixed by the locking pin (407).

10. The lifting test flight platform for an electric vertical takeoff and landing aircraft as described in claim 1, characterized in that, The upright (202) has an A-shaped structure.

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