Quick-release type self-dumping neutral position tool and using method

Abstract

The invention discloses a quick-release type self-dumping neutral position tool and a using method. The tool comprises a first half ring (1), a second half ring (3) and a binding belt (4). The first half ring (1) and the second half ring (3) are spliced to form a circular ring, a clamping groove is formed in the outer circle of the circular ring, and a ribbon (4) is arranged in the clamping groove; an annular positioning ring is arranged on the inner ring of the circular ring and arranged on the outer side of a main shaft of the main speed reducer in a sleeving mode. And the circular ring is clamped between the main speed reducer (2) and the automatic inclinator (5). The device has the advantages of simple installation, rapid fitting, rapidness, no angle requirement limitation and high positioning precision, can satisfy rapid positioning of flight control steering engine operating lever system reference adjustment, completes rapid adjustment and fixation of a flight control main paddle steering engine pull rod, and provides powerful guarantee for flight control data.

Description

Technical Field

[0001] The present invention belongs to the technical field of helicopter maintenance type, and in particular relates to a cross-medium variant unmanned rotorcraft and a use method thereof. Background Art

[0002] The current flight attitude changes of helicopters mostly rely on the angle changes of the automatic tilt mechanism, and the angle of the automatic tilt mechanism is controlled by the position of the joystick system given by the main propeller servo in the flight control system. Because each servo has a certain error in the manufacturing process, the neutral position of the automatic tilt mechanism needs to be adjusted when the servo is used. If the neutral position is inaccurate, the angle control of the automatic tilt mechanism will be inaccurate, which will cause the helicopter to have an inappropriate flight attitude, which may affect flight stability or even lose control, so the neutral position adjustment is particularly important.

[0003] With the ever-changing international situation, helicopter training will continue to increase, and the probability of serious damage to various types of helicopters will gradually increase. Among them, the probability of damage and replacement or upgrade of the main propeller servo that controls the automatic tilt device in the flight control system will also increase greatly. In order to meet the intensity requirements of training and quickly repair or upgrade helicopters, there is an urgent need for a flight control servo reference adjustment technology that is simple to operate, safe and reliable, and fast. Summary of the invention

[0004] The purpose of the present invention is to provide a cross-medium variant unmanned rotorcraft and a method of use, which can simply and efficiently perform rapid adjustment of the flight control servo control lever system benchmark.

[0005] A first aspect of the present invention provides a quick-release self-tilting neutral position tooling, comprising: a first half ring 1, a second half ring 3, and a cable tie 4;

[0006] The first half ring 1 and the second half ring 3 are spliced ​​together to form a circular ring, the outer ring of which is provided with a slot for setting a cable tie 4;

[0007] The inner ring of the circular ring is provided with an annular positioning ring, and the annular positioning ring is sleeved on the outer side of the main shaft of the main reducer;

[0008] The circular ring is clamped between the main reducer 2 and the automatic tilt device 5 .

[0009] Optionally, the height of the ring is determined according to the mechanical theoretical zero position of the main reducer 2 and the automatic inclinometer 5 .

[0010] Optionally, the parallelism of the upper and lower surfaces of the ring is not less than 0.5.

[0011] Optionally, the flatness of the upper and lower surfaces of the ring is not less than 0.5.

[0012] Optionally, a concave arc surface is provided on the lower surface of the ring to avoid the structure of the main reducer 2.

[0013] Optionally, the inner diameter of the annular locating ring is consistent with the outer diameter of the main shaft of the main reducer.

[0014] Optionally, the upper surface of the ring contacts the lower surface of the stationary ring of the automatic tilter 5;

[0015] The lower surface of the ring contacts the upper surface of the mounting screws of the final reducer 2 .

[0016] Optionally, both the first half ring 1 and the second half ring 3 are provided with handles.

[0017] Another aspect of the present invention provides a method for using the quick-release self-tilting neutral position tooling as described above, comprising:

[0018] Step 1: Lift the first side of the automatic recliner 5 upwards, and insert the first half ring 1 between the automatic recliner 5 and the main reducer 2;

[0019] Step 2: Lift the second side of the automatic recliner 5 upwards, insert the second half ring 3 between the automatic recliner 5 and the main reducer 2, and the first half ring 1 and the second half ring 3 form a circular ring; the second side is 180° different from the first side;

[0020] Step 3: Place the cable tie 4 in the slot to fix the first half ring 1 and the second half ring 3;

[0021] Step 4: The aircraft is powered on, and the flight control computer gives the main propeller servo a zero position command;

[0022] Step 5: Adjust the length of the main propeller servo rod and connect and fix the rod to the automatic tilt device;

[0023] Step 6: Cut the cable tie 4 and take out the first half ring 1 and the second half ring 3.

[0024] The present invention provides a cross-medium variant unmanned rotorcraft and a use method, and a neutral position tooling for the flight control servo control lever system reference adjustment technology for helicopter maintenance. The tooling has the advantages of simple installation, quick fitting, speed, no angle requirement restriction, high positioning accuracy, and can meet the rapid positioning of the flight control servo control lever system reference adjustment, complete the rapid adjustment and fixation of the flight control main propeller servo pull rod, and provide strong guarantee for flight control data. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 It is a structural schematic diagram of the quick-release self-tilting neutral position tooling provided by the present invention;

[0026] Figure 2 It is a structural schematic diagram of a half ring of a quick-release self-tilting neutral position tooling provided by the present invention;

[0027] Description of reference numerals:

[0028] 1. The first half ring;

[0029] 2. Main reducer;

[0030] 3. The second half ring;

[0031] 4. Cable ties;

[0032] 5. Automatic tilt device. DETAILED DESCRIPTION

[0033] A quick-release self-tilting neutral position tooling and a method of use provided by the present invention are explained below in conjunction with the accompanying drawings.

[0034] The present invention aims to provide a quick flight control steering gear reference adjustment tool for a helicopter that needs maintenance. The present invention provides a helicopter quick-release self-tilting neutral position tool.

[0035] like Figure 1-2 As shown, the present invention provides a quick-release self-tilting neutral position tooling, comprising: a first half ring 1, a second half ring 3, and a cable tie 4;

[0036] The first half ring 1 and the second half ring 3 are spliced ​​together to form a circular ring, the outer ring of which is provided with a slot for setting a cable tie 4;

[0037] The inner ring of the circular ring is provided with an annular positioning ring, and the annular positioning ring is sleeved on the outer side of the main shaft of the main reducer;

[0038] The circular ring is clamped between the main reducer 2 and the automatic tilt device 5 .

[0039] Optionally, the height of the ring is determined according to the mechanical theoretical zero position of the main reducer 2 and the automatic inclinometer 5 .

[0040] Optionally, the parallelism of the upper and lower surfaces of the ring is not less than 0.5.

[0041] Optionally, the flatness of the upper and lower surfaces of the ring is not less than 0.5.

[0042] Optionally, a concave arc surface is provided on the lower surface of the ring to avoid the structure of the main reducer 2.

[0043] Optionally, the inner diameter of the annular locating ring is consistent with the outer diameter of the main shaft of the main reducer.

[0044] Optionally, the upper surface of the ring contacts the lower surface of the stationary ring of the automatic tilter 5;

[0045] The lower surface of the ring contacts the upper surface of the mounting screws of the final reducer 2 .

[0046] Optionally, both the first half ring 1 and the second half ring 3 are provided with handles.

[0047] Exemplarily, the first half ring 1 and the second quick-release self-tilting neutral position fixture 3 limit the neutral position of the automatic tilting device 5 and the flight control servo reference adjustment of the main reducer 2, and at the same time, the two quick-release self-tilting neutral position fixtures are reinforced with cable ties 4 to ensure the stability of the neutral position of the flight control servo reference adjustment.

[0048] Furthermore, the present invention designs a helicopter quick-release self-tilting neutral position tooling, and the implementation steps are as follows:

[0049] Step 1: Slightly lift the automatic recliner 5 upward until the first half ring 1 fits with the main reducer 2;

[0050] Step 2: Slightly lift the automatic tilter 5 upward until the second half ring 3 fits with the main reducer 2;

[0051] Step 3: Use a cable tie 4 to fix the first half ring 1 and the second half ring 3 to ensure that the quick-release self-tilting neutral position tooling does not fall off when the self-tilting rotates;

[0052] Step 4: The aircraft is powered on, and the flight control computer gives the main propeller servo a zero position command;

[0053] Step 5: Adjust the length of the main propeller servo rod and connect and fix the rod to the automatic tilt device;

[0054] Step 6: Use tools to cut the cable tie 4 and clean up the excess;

[0055] Step 7: Use the handles of the first half ring 1 and the second half ring 3 to quickly disassemble the neutral position tooling.

[0056] The invention has a quick fitting design, and the tooling can be directly fitted to the main reducer to achieve quick positioning; the angle-free design, and the tooling can fit the main reducer at any angle; the quick disassembly design, after the flight control servo base adjustment and positioning are achieved and the main propeller servo pull rod is fixedly connected, the tooling is designed with a quick disassembly handle.

Claims

1. A quick-release self-tilting neutral position tooling, characterized in that: include: A first half ring (1), a second half ring (3), and a cable tie (4); The first half ring (1) and the second half ring (3) are spliced ​​together to form a circular ring, the outer ring of which is provided with a slot, and the slot is used to set a cable tie (4); The inner ring of the circular ring is provided with an annular positioning ring, and the annular positioning ring is sleeved on the outer side of the main shaft of the main reducer; The circular ring is clamped between the main reducer (2) and the automatic tilting device (5).

2. The quick-release self-tilting neutral position tooling according to claim 1 is characterized in that: The height of the ring is determined according to the mechanical theoretical zero position of the main reducer (2) and the automatic tilting device (5).

3. The quick-release self-tilting neutral position tooling according to claim 1 is characterized in that: The parallelism of the upper and lower surfaces of the ring shall not be less than 0.

5.

4. The quick-release self-tilting neutral position tooling according to claim 1 is characterized in that: The flatness of the upper and lower surfaces of the ring shall not be less than 0.

5.

5. The quick-release self-tilting neutral position tooling according to claim 1, characterized in that: The lower surface of the circular ring is provided with an inner concave arc surface for avoiding the structure of the main reducer (2).

6. The quick-release self-tilting neutral position tooling according to claim 1, characterized in that: The inner diameter of the annular locating ring is consistent with the outer diameter of the main shaft of the main reducer.

7. The quick-release self-tilting neutral position tooling according to claim 1, characterized in that: The upper surface of the circular ring contacts the lower surface of the stationary ring of the automatic tilting device (5); The lower surface of the ring contacts the upper surface of the mounting screw of the main reducer (2).

8. The quick-release self-tilting neutral position tooling according to claim 1, characterized in that: The first half ring (1) and the second half ring (3) are both provided with handles.

9. A method for using the quick-release self-tilting neutral position tooling according to any one of claims 1 to 8, characterized in that: include: Step 1: Lift the first side of the automatic recliner (5) upwards and insert the first half ring (1) between the automatic recliner (5) and the main reducer (2); Step 2: Lift the second side of the automatic tilt mechanism (5) upwards, insert the second half ring (3) between the automatic tilt mechanism (5) and the main reducer (2), the first half ring (1) and the second half ring (3) forming a circular ring; the second side is 180° different from the first side; Step 3: Place the cable tie (4) in the slot to fix the first half ring (1) and the second half ring (3); Step 4: The aircraft is powered on, and the flight control computer gives the main propeller servo a zero position command; Step 5: Adjust the length of the main propeller servo rod and connect and fix the rod to the automatic tilt device; Step 6: Cut the cable tie (4) and take out the first half ring (1) and the second half ring (3).

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