Aircraft nose wheel towbar launch pole electric actuator device

Abstract

The application discloses an electric actuator device for a front wheel towing and catapulting rod of an airplane and belongs to the technical field of airplane take-off and landing. The electric actuator device cancels a complicated hydraulic system and a connecting rod transmission in an existing mechanism, utilizes a motor to drive an extending and retracting rod, cooperates with a limiting sliding track on a fixing base, realizes the transformation of the contact position of the extending and retracting rod and the catapulting rod, thereby controls the catapulting rod to reach three positions of being laid down, being folded up and being folded in, adopts a left coil spring return mechanism to complete a hooking action, and a right coil spring energy storage mechanism can ensure that the catapulting rod is tightly close to the upper edge of a reciprocating vehicle hook during a catapulting process. When the catapulting rod is separated from the hook, the catapulting rod is rapidly rebounded to cross possible obstacles. The electric actuator device has the advantages of compact structure, low maintenance cost, high system integration, good working reliable performance, light weight and the like.

Description

Technical Field

[0001] This invention belongs to the field of aircraft takeoff and landing technology, specifically relating to an electric actuator device for an aircraft nose wheel towing catapult stick. Background Technology

[0002] This invention relates to a catapult launch device for aircraft, particularly suitable for short takeoffs. During the entire catapult launch process, the catapult rod needs to complete a complete movement of connecting with the catapult, pulling the aircraft to accelerate and taxi, automatically separating from the catapult and rebounding to the locked position of the catapult rod.

[0003] Currently, aircraft nose wheel ejection launchers are driven by hydraulic actuators and are combined using two dual rocker arms connected in series. Because the landing gear has hydraulic lines, it's convenient to use a hydraulic mechanism to operate the launcher. However, this design requires a complex hydraulic system, including a hydraulic pump, tank, and piping, increasing equipment complexity and maintenance costs. Furthermore, hydraulic mechanisms may experience hydraulic oil leaks after prolonged use.

[0004] This invention eliminates the complex hydraulic system, improving reliability and reducing costs. A catapult drive system is designed using the working principle of an electric actuator, offering advantages such as compact structure, high system integration, good operational reliability, and light weight. Summary of the Invention

[0005] The purpose of this invention is to solve the problems of existing technologies and provide an electric actuator device for an aircraft nose wheel towing catapult stick. This device eliminates the complex hydraulic system and linkage transmission found in existing mechanisms. It utilizes a motor to drive a telescopic lever, which, in conjunction with a limiting sliding rail on a fixed base, changes the contact position between the telescopic lever and the catapult stick. This controls the catapult stick to three positions: lowered, retracted, and extended. A left coil spring return mechanism completes the hooking action, while a right coil spring energy storage mechanism ensures that the catapult stick remains close to the upper edge of the reciprocating hook during launch. When the catapult stick disengages from the hook, it quickly rebounds to overcome any obstacles. This invention has advantages such as compact structure, low maintenance cost, high system integration, good operational reliability, and light weight.

[0006] This invention is achieved through the following technical solution:

[0007] An electric actuator for an aircraft nose wheel-towed ejection stick includes a landing gear with mounting lugs. A left coil spring return mechanism and a right coil spring energy storage mechanism are respectively provided on the left and right sides of the mounting lugs. An ejection stick is rotatably mounted in the middle of the mounting lugs. An electric mechanism is provided on the left coil spring return mechanism. An output gear ring is provided on the output shaft of the electric mechanism. A telescopic lever and a pin are mounted on the output gear ring. The other end of the telescopic lever contacts the ejection stick, and the pin contacts the left coil spring return mechanism.

[0008] Preferably, the output gear ring has a telescopic lever and a pin in its U-shaped groove.

[0009] Preferably, the mounting ear includes a left ear and a right ear, and a mounting cavity for mounting the ejection rod is provided between the left ear and the right ear.

[0010] Preferably, both the left and right ears are provided with perforations for the main pin to pass through, and the ejector rod is rotatably mounted on the main pin.

[0011] Preferably, the left coil spring return mechanism includes a fixed seat, a movable seat, and a left coil spring. The fixed seat is fixedly mounted on the left ear, the inner ring of the left coil spring is mounted on the bottom of the movable seat, the outer ring of the left coil spring is mounted inside the fixed seat, and the bottom of the movable seat is rotatably mounted in the fixed seat.

[0012] Preferably, the fixed base is provided with a limiting sliding rail that matches the pin.

[0013] Preferably, the output gear ring is rotatably disposed within the movable seat.

[0014] Preferably, the right coil spring energy storage mechanism includes a right coil spring housing and a right coil spring, the right end of the main pin is connected to the inner ring of the right coil spring, the outer ring of the right coil spring is connected to the right coil spring housing, and the right coil spring housing is threadedly connected to the right ear.

[0015] Preferably, the landing gear includes a vertical rod and a mounting shaft, the vertical rod is disposed in the middle of the mounting shaft, and landing wheels are rotatably disposed on both sides of the mounting shaft.

[0016] Compared with the prior art, the present invention has the following advantages and beneficial effects:

[0017] I. This invention provides an electric actuator device for an aircraft nose wheel towing catapult stick. It eliminates the complex hydraulic system and linkage transmission found in existing mechanisms. Utilizing a motor to drive a telescopic lever, in conjunction with a limiting sliding rail on a fixed base, it changes the contact position between the telescopic lever and the catapult stick, thereby controlling the catapult stick to three positions: lowered, retracted, and extended. A left coil spring return mechanism completes the hooking action, while a right coil spring energy storage mechanism ensures the catapult stick remains close to the upper edge of the reciprocating carriage hook during catapult launch. When the catapult stick disengages from the hook, it quickly rebounds to overcome any potential obstacles. This invention has advantages such as compact structure, low maintenance cost, high system integration, good operational reliability, and light weight.

[0018] II. The present invention provides an electric actuator device for towing an aircraft nose wheel ejection stick, which is driven by an electric motor. Compared with hydraulic drive, it does not have a complicated hydraulic oil circuit, does not have oil leakage, is easy to maintain, has low cost, and is environmentally friendly.

[0019] Third, the aircraft nose wheel towing ejection stick electric actuator device provided by the present invention adopts a method of integrating the motor and controller into one unit, eliminating the complex linkage mechanism, making it lighter, more compact in structure, and more space-efficient, which is beneficial for the retraction of the landing gear.

[0020] IV. The present invention provides an electric actuator device for towing an aircraft nose wheel ejection stick. Compared with the hydraulic drive linkage mechanism, the electric actuator drives the retraction lever through the gear ring, which drives the ejection stick to rotate in both directions, resulting in higher energy conversion efficiency and control precision. Attached Figure Description

[0021] Figure 1 This is a schematic diagram of the motion angle of the ejector rod in this invention;

[0022] Figure 2 This is a schematic diagram of the structure of the present invention;

[0023] Figure 3 This is an exploded view of the left coil spring return mechanism in this invention;

[0024] Figure 4 This is a schematic diagram of the exploded structure of the right coil spring energy storage mechanism in this invention.

[0025] The components are: 1. Landing gear; 101. Vertical bar; 102. Mounting shaft; 103. Landing wheel; 2. Telescopic lever; 3. Pin; 4. Output gear ring; 5. Electric mechanism; 6. Movable seat; 7. Fixed seat; 8. Right coil spring housing; 9. Ejection rod; 10. Left coil spring; 11. Kingpin; 12. Right coil spring. Detailed Implementation

[0026] The present invention will be further described in detail below with reference to embodiments, but the implementation of the present invention is not limited thereto.

[0027] Example 1

[0028] This embodiment provides an electric actuator for an aircraft nose wheel towing ejection stick, including a landing gear 1. The landing gear 1 is provided with mounting lugs. A left coil spring return mechanism and a right coil spring energy storage mechanism are respectively provided on the left and right sides of the mounting lugs. An ejection stick 9 is rotatably mounted in the middle of the mounting lugs. An electric mechanism 5 is provided on the left coil spring return mechanism. An output gear ring 4 is provided on the output shaft of the electric mechanism 5. A telescopic lever 2 and a pin 3 are mounted on the output gear ring 4. The other end of the telescopic lever 2 is in contact with the ejection stick 9, and the pin 3 is in contact with the left coil spring return mechanism.

[0029] Example 2

[0030] like Figures 1-4As shown, this embodiment provides an electric actuator device for an aircraft nose wheel towing ejection stick, including a landing gear 1. The landing gear 1 is provided with mounting ears. A left coil spring return mechanism and a right coil spring energy storage mechanism are respectively provided on the left and right sides of the mounting ears. An ejection stick 9 is rotatably mounted in the middle of the mounting ears. An electric mechanism 5 is provided on the left coil spring return mechanism. An output gear ring 4 is provided on the output shaft of the electric mechanism 5. A telescopic lever 2 and a pin 3 are mounted on the output gear ring 4. The other end of the telescopic lever 2 is in contact with the ejection stick 9, and the pin 3 is in contact with the left coil spring return mechanism.

[0031] The output gear ring 4 has a telescopic lever 2 and a pin 3 installed in its U-shaped groove.

[0032] The mounting ear includes a left ear and a right ear, and a mounting cavity for mounting the ejection rod 9 is provided between the left ear and the right ear.

[0033] The left and right ears are each provided with a through hole for the main pin 11 to pass through, and the ejector rod 9 is rotatably mounted on the main pin 11.

[0034] The left coil spring return mechanism includes a fixed seat 7, a movable seat 6, and a left coil spring 10. The fixed seat 7 is fixedly mounted on the left ear. The inner ring of the left coil spring 10 is mounted on the bottom of the movable seat 6, and the outer ring of the left coil spring 10 is mounted inside the fixed seat 7. The bottom of the movable seat 6 is rotatably mounted in the fixed seat 7.

[0035] The fixed base 7 is provided with a limiting sliding rail that matches the pin 3.

[0036] The output gear ring 4 is rotatably mounted within the movable seat 6.

[0037] The right coil spring energy storage mechanism includes a right coil spring housing 8 and a right coil spring 12. The right end of the main pin 11 is connected to the inner ring of the right coil spring 12, the outer ring of the right coil spring 12 is connected to the right coil spring housing 8, and the right coil spring housing 8 is threadedly connected to the right ear.

[0038] The landing gear 1 includes a vertical rod 101 and a mounting shaft 102. The vertical rod 101 is located in the middle of the mounting shaft 102, and landing wheels 103 are rotatably arranged on both sides of the mounting shaft 102.

[0039] Compared with the prior art, the present invention has the following advantages and beneficial effects:

[0040] I. This invention provides an electric actuator device for an aircraft nose wheel towing ejection rod 9. It eliminates the complex hydraulic system and linkage transmission found in existing mechanisms. Using a motor to drive a telescopic lever 2, in conjunction with a limiting sliding rail on a fixed base 7, it changes the contact position between the telescopic lever 2 and the ejection rod 9, thereby controlling the ejection rod 9 to reach three positions: lowered, retracted, and extended. A left coil spring 10 return mechanism completes the hooking action, while a right coil spring 12 energy storage mechanism ensures that the ejection rod 9 remains close to the upper edge of the reciprocating vehicle hook during ejection. When the ejection rod 9 disengages from the hook, it quickly rebounds to overcome any potential obstacles. This invention has advantages such as compact structure, low maintenance cost, high system integration, good operational reliability, and light weight.

[0041] II. The present invention provides an electric actuator device for towing an aircraft nose wheel ejection stick 9, which is driven by an electric motor. Compared with hydraulic drive, it does not have a complicated hydraulic oil circuit, does not have oil leakage, is easy to maintain, has low cost, and is environmentally friendly.

[0042] Third, the present invention provides an electric actuator device for the aircraft nose wheel towing ejection stick 9, which integrates the motor and controller into one unit, eliminating the complex linkage mechanism, making it lighter, more compact, and with higher space utilization, which is beneficial for the retraction of the landing gear 1.

[0043] IV. The present invention provides an electric actuator device for towing the aircraft nose wheel ejection rod 9. Compared with the hydraulic drive linkage mechanism, the electric actuator drives the retraction lever through the gear ring, which drives the ejection rod 9 to rotate in both directions, resulting in higher energy conversion efficiency and control precision.

[0044] In use of this embodiment, the fixed seat 7 of the left coil spring return mechanism is installed on the left ear of the landing gear 1. The inner ring of the left coil spring 10 is installed at the bottom of the movable seat 6, and the outer ring of the left coil spring 10 is installed in the fixed seat 7. At the same time, the bottom of the movable seat 6 is installed in the fixed seat 7 and can rotate relatively. When installed, the left coil spring 10 has an initial pre-tightening torque N1, which causes the movable seat 6 to rotate clockwise. There is a limit between the movable seat 6 and the fixed seat 7 to restrict the spring back and maintain the pre-tightening torque N1 of the left coil spring 10, where N2 < N1 (rated output torque of the electric mechanism 5). The electric mechanism 5 is fixedly installed on the movable seat 6. The electric mechanism 5 and the control box are designed as a whole. An output gear ring 4 is installed on the output shaft of the electric mechanism 5. The output gear ring 4 is installed inside the movable seat 6 and can rotate inside the movable seat 6. A spring and a telescopic lever 2 are sequentially installed in the U-shaped groove of the output gear ring 4. A spring and a pin shaft 3 are sequentially installed in the telescopic lever 2, so that the pin shaft 3 contacts the limit sliding track of the fixed seat 7. The telescopic lever 2 can contact the ejection lever 9. The ejection lever 9 is installed between the double ears of the landing gear 1 through the main pin 11. The right end of the main pin 11 is connected to the inner ring of the right coil spring 12 in the right coil spring energy storage mechanism. The outer ring of the right coil spring 12 is connected to the right coil spring housing 8. The right coil spring housing 8 is threadedly connected to the right ear of the landing gear 1. The right coil spring 12 energy storage mechanism has an initial pre-tightening torque N3, where N3 < N2 (rated output torque of the electric mechanism 5). The initial pre-tightening torque N3 can lift the ejection lever 9 upward, overcome its own weight, and keep it in the retracted position.

[0045] When preparing for catapult takeoff, the ejection lever 9 needs to move from the retracted position to the lowered position. The electric mechanism 5 drives the output gear ring 4 to rotate, presses the ejection lever 9 to rotate clockwise through the telescopic lever 2. The ejection lever 9 starts to store energy through the main pin 11 with the right coil spring energy storage mechanism. When the ejection lever 9 moves to the lowered position, it receives the switch position signal, and the electric mechanism 5 stops moving and locks in the current position through the brake.

[0046] During the hooking process, when the aircraft moves forward, a counterclockwise torque N4 is applied to the ejection lever 9. When N4 is greater than the installed energy storage N1 of the left coil spring return mechanism, due to the brake locking, the output gear ring 4, the electric mechanism 5 and the movable seat 6 can be driven to rotate counterclockwise together through the rope lever. This function can ensure that the ejection lever 9 crosses the reciprocating vehicle on the aircraft carrier deck. After crossing, under the action of the left coil spring return mechanism, the movable seat ⑥, the electric mechanism 5, the output gear ring 4 and the telescopic lever 2 drive the ejection lever 9 to rotate clockwise until the limit position, and the ejection lever 9 is hooked with the reciprocating vehicle hook head.

[0047] When the ejector rod 9 is engaged with the reciprocating car, after confirmation by the operator, the control electric mechanism 5 continues to rotate clockwise. Under the action of the limiting sliding track of the fixed seat 7, the telescopic lever 2 will retract into the U-shaped groove of the output gear ring 4. After disengaging from the ejector rod 9, the ejector rod 9 will be tightly attached to the lower edge of the reciprocating car hook head under the force of the right coil spring energy storage mechanism, while the telescopic lever 2 will extend under the action of the internal spring force. At this time, the contact position between the telescopic lever 2 and the ejector rod 9 changes, and it is located below the ejector rod 9, thus closing the electric mechanism 5.

[0048] Once the catapult launch is complete and the aircraft leaves the ship, the catapult lever 9 separates from the reciprocating carriage. Under the action of the right-hand coil spring energy storage mechanism, the catapult lever 9 rotates counterclockwise. The electric mechanism 5 is activated, and the telescopic lever 2 rotates counterclockwise. After contacting the catapult lever 9, it drives the catapult lever 9 to continue rotating counterclockwise. When the catapult lever 9 reaches the retracted position, it receives a switch position signal, and the electric mechanism 5 stops moving and locks itself in the neutral position via the brake.

[0049] Before retracting landing gear 1, the aircraft can only retract landing gear 1 when the ejection lever 9 is in the retracted position. The motor mechanism 5 is started to control the telescopic lever 2 to continue to rotate counterclockwise, which drives the ejection lever 9 to the retracted position. The electric mechanism 5 is then turned off and locked in the current position by the brake.

[0050] After the landing gear 1 is lowered, the electric mechanism 5 drives the telescopic lever 2 to rotate counterclockwise. Under the action of the limiting sliding track of the fixed seat 7, the telescopic lever 2 will retract into the U-shaped groove of the output gear ring 4. After disengaging from the ejection rod 9, the ejection rod 9 will rotate clockwise under the action of gravity, while the telescopic lever 2 will extend under the action of the internal spring force. At this time, the contact position between the telescopic lever 2 and the ejection rod 9 changes again. Subsequently, the electric mechanism 5 drives the telescopic lever 2 to rotate clockwise, driving the ejection rod 9 to the retracted position. After that, the electric mechanism 5 stops moving and locks in the current position through the brake. At this time, the ejection rod 9 returns to the retracted position.

[0051] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention in any way. Any simple modifications or equivalent changes made to the above embodiments based on the technical essence of the present invention shall fall within the protection scope of the present invention.

Claims

1. An electrically operated aircraft nose wheel towbar launch pole actuator apparatus, characterised in that: The landing gear (1) is provided with mounting ears, and the left and right sides of the mounting ears are respectively provided with a left coil spring return mechanism and a right coil spring energy storage mechanism.

2. An electrically operated aircraft nose wheel towbar launch pole actuator device as claimed in claim 1 wherein: The output gear ring (4) is provided with a telescopic lever (2) and a pin shaft (3) in the U-shaped groove.

3. An electrically operated aircraft nose wheel towbar launch pole actuator device as claimed in claim 2, characterised in that: The mounting ears include left and right ears, and the left and right ears are provided with a mounting cavity for mounting the ejector rod (9).

4. An electrically operated aircraft nose wheel towbar launch pole actuator device as claimed in claim 3, characterised in that: The left and right ears are provided with a through hole for passing through the kingpin (11), and the ejector rod (9) is rotatably arranged on the kingpin (11).

5. An electrically operated aircraft nose wheel towbar launch pole actuator device as claimed in claim 4, characterised in that: The left coil spring return mechanism further includes a fixed seat (7) and a movable seat (6), the fixed seat (7) is fixedly arranged on the left ear, the inner ring of the left coil spring (10) is arranged at the bottom of the movable seat (6), the outer ring of the left coil spring (10) is arranged in the fixed seat (7), and the bottom of the movable seat (6) is rotatably arranged in the fixed seat (7).

6. An electrically operated aircraft nose wheel towbar launch pole actuator device as claimed in claim 5 wherein: The fixed seat (7) is provided with a limiting sliding track matched with the pin shaft (3).

7. An electrically operated aircraft nose wheel towbar launch pole actuator device as claimed in claim 6, characterised in that: The output gear ring (4) is rotatably arranged in the movable seat (6).

8. An electrically operated aircraft nose wheel towbar launch pole actuator device as claimed in claim 7, characterised in that: The right coil spring energy storage mechanism includes a right coil spring shell (8) and a right coil spring (12), the right end of the kingpin (11) is connected with the inner ring of the right coil spring (12), the outer ring of the right coil spring (12) is connected with the right coil spring shell (8), and the right coil spring shell (8) is threadedly connected with the right ear.

9. An electrically operated aircraft nose wheel towbar launch pole actuator device as claimed in claim 8, characterised in that: The landing gear (1) includes a vertical rod (101) and a mounting shaft (102), the vertical rod (101) is arranged in the middle of the mounting shaft (102), and the landing wheels (103) are rotatably arranged on the two sides of the mounting shaft (102).

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