Novel electric retractable undercarriage mechanism and control circuit and use method thereof

Abstract

The invention relates to the technical field of aircraft landing gears, and discloses a novel electric landing gear folding and unfolding mechanism and a control circuit and using method.The mechanism comprises a shell and an aircraft wheel assembly rotationally installed in the shell, a transmission mechanism for driving the aircraft wheel assembly to rotate is installed in the shell, and a bottom plate is further installed in the shell; a mounting frame is mounted on the bottom plate, the bottom of the airplane wheel assembly is connected with an undercarriage rotating part rotationally arranged in the mounting frame, and the size of a gearbox is reduced to the maximum extent through transmission fit of a worm gear and a gear set, so that the undercarriage structure is arranged more tightly. And the undercarriage control circuit is used for controlling start and stop of the transmission mechanism and the steering engine unlocking mechanism, so that the undercarriage is in a folded state and an unfolded state.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft landing gears, and in particular to a novel electric retractable landing gear mechanism and a control circuit and a use method thereof. Background Art

[0002] With the advancement of science and technology, people's living standards are constantly improving, and the requirements for quality of life are also increasing. In order to enrich their daily lives, more and more people are willing to spend time, money and energy on their hobbies. Most of them have a deep interest in various aircraft from all over the world. However, the conditions for observing and feeling various real aircraft on site are very limited. Therefore, various simulation model aircraft have become objects of collection and appreciation, which provides a broad market for various simulation model toys. Simulation model aircraft have gradually penetrated into the lives of the majority of enthusiasts. Consumers' requirements for simulation model aircraft are also getting higher and higher. The current model aircraft are required to be as realistic as possible in both appearance and layout. The landing gear is an indispensable accessory for model aircraft. It is not an easy task to use a landing gear that can be retracted and deployed like a real aircraft on a model aircraft. At present, there are two types of retractable landing gear used in existing model airplanes. The first type is a steering gear stretching retractable landing gear, which is powered by a steering gear and achieves the retraction and extension of the landing gear by stretching a steel wire; the other type of retractable landing gear is a pneumatic retractable landing gear, which uses a gas bottle (or cylinder) to transmit power through the control of various gas valves to achieve the retraction and extension of the landing gear. The applicant has been committed to the research and development of simulation model airplanes. For the structure of the landing gear, the applicant has applied for CN210044858U and CN209984938U, but the above landing gear has the following defects: 1. The existing landing gear structure makes the overall thickness of the landing gear relatively thick. When installed on the wing, the wing needs to be made thicker, which increases the weight of the aircraft. 2. The processing accuracy of aircraft landing gear is high, and any slight dimensional deviation will cause the landing gear to loosen; 3. After the landing gear is used for a long time, a gap is easily generated between the landing gear rotating part and the limit structure, causing the landing gear to shake; Therefore, we need to propose a new type of electric retractable landing gear mechanism and its control circuit and use method, which has high structural strength, low processing precision requirements and strong stability. Summary of the invention

[0003] The purpose of the present invention is to provide a novel electric retractable landing gear mechanism and its control circuit and use method, which ensures that the size of the gear box is minimized to the maximum extent through the transmission cooperation between the turbine worm and the gear set, so that the landing gear structure is arranged more tightly and the connection is more stable, thereby enhancing the structural strength of the landing gear; through the cooperation between the locking block and the inclined surface on the landing gear rotating part, and under the tension of the reset elastic part, the two inclined surfaces are kept in close contact, ensuring that there is no gap between the landing gear rotating part and the upper cover and the locking block, the landing gear will not shake, and the landing gear will still not have a gap after long-term use, so as to solve the problems raised in the above-mentioned background technology.

[0004] To achieve the above-mentioned purpose, the present invention provides the following technical solutions: a novel electric retractable landing gear mechanism, comprising an outer shell, a wheel assembly rotatably mounted inside the outer shell, a transmission mechanism for driving the wheel assembly to rotate installed inside the outer shell, a bottom plate also installed inside the outer shell, a mounting frame installed on the bottom plate, a landing gear rotating member rotatably mounted inside the mounting frame connected to the bottom of the wheel assembly, a locking block slidably mounted on the bottom plate, the bottom of the landing gear rotating member and the top of the locking block are both provided with inclined surfaces, the two inclined surfaces are tightly fitted, and a servo unlocking mechanism for driving the locking block to move is also provided inside the outer shell.

[0005] Preferably, the transmission mechanism includes a gear box fixed inside the outer shell, a second motor is fixedly arranged inside the gear box, a worm gear is connected to the output shaft of the second motor, a rotatable turbine and a gear transmission assembly for driving the landing gear rotating parts to rotate are also installed inside the gear box, and the turbine and the gear transmission assembly are arranged in coordination.

[0006] Preferably, the landing gear rotating member includes a rotating seat, a rotating shaft penetrating through and connected to the rotating seat, an inner ring of one of the gears in the gear transmission assembly is plugged with a connecting member, and one end of the rotating shaft is plugged and fixed inside the connecting member.

[0007] Preferably, an upper cover is fixed to the mounting frame by bolts, a bearing is installed in the circular gap between the mounting frame and the upper cover, and the outer wall of the rotating shaft is inserted and fixed to the inner ring of the bearing.

[0008] Preferably, a limiting groove is provided at the lower end of the inner wall of the mounting frame, and stepped grooves are provided at both ends of the locking block, and both ends of the locking block are slidably arranged inside the limiting groove.

[0009] Preferably, one end of the mounting frame is connected to a hook, the hook is connected to a reset elastic member, and one end of the reset elastic member is connected to one end of the locking block.

[0010] Preferably, a through hole is provided on the shell, and the servo unlocking mechanism is installed inside the through hole. The servo unlocking mechanism includes a rotating block rotatably arranged inside the through hole, and a steel wire rope is connected between the rotating block and the other end of the locking block.

[0011] Preferably, the servo unlocking mechanism further comprises a plastic plate installed inside the housing and used to press the servo, and a first motor installed at the bottom of the housing, wherein the output shaft of the first motor is connected to the rotating block.

[0012] The present invention also provides a control circuit for a novel electric retractable landing gear mechanism, which is used to control the novel electric retractable landing gear mechanism described above, including a landing gear control circuit, the landing gear control circuit is used to control the start and stop of the transmission mechanism and the servo unlocking mechanism, and the landing gear control circuit includes: a signal input interface, an input signal processing circuit, a power supply voltage stabilizing circuit, an electric gear box control circuit, an unlocking servo control circuit, and a signal output interface; The input signal processing circuit is electrically connected to the power supply voltage stabilizing circuit, the signal input interface, input signal processing circuit, electric gear box control circuit, unlocking servo control circuit, and signal output interface are all electrically connected to the power supply voltage stabilizing circuit, and the electric gear box control circuit is electrically connected to the signal output interface.

[0013] The present invention also provides a method for using a novel electric retractable landing gear mechanism, which uses the novel electric retractable landing gear mechanism described above and specifically includes the following steps: When the landing gear is retracted, the first motor is operated, the first motor drives the rotating block to rotate, the rotating block pulls the wire rope to move, and then drives the locking block to move in the direction away from the landing gear rotating member, so that the locking block is separated from the two inclined surfaces on the landing gear rotating member, and the limit on the landing gear rotating member can be cancelled; then the second motor is operated, the second motor drives the worm rod to rotate, the worm rod drives the turbine to rotate, and the turbine drives the landing gear rotating member to rotate clockwise through the gear transmission assembly and the connecting member, and then drives the rotation of the wheel assembly to retract the wheel assembly. After the landing gear reaches the storage position, the transmission mechanism stops rotating; When the landing gear is in the open state, the second motor runs and reverses, and with the cooperation of the worm gear, turbine, gear transmission assembly and connecting parts, the landing gear rotating part is driven to rotate, driving the wheel assembly to move out of the housing, and the landing gear rotating part abuts against the upper cover. After the landing gear reaches the open position, the transmission mechanism stops rotating, and under the elastic force of the reset elastic part, the locking block automatically bounces into the locking position, so that the locking block is tightly fitted with the two inclined surfaces on the landing gear rotating part, thereby realizing the positioning of the landing gear rotating part.

[0014] Compared with the prior art, the present invention has the following beneficial effects: 1. The present invention ensures that the size of the gear box is minimized through the transmission cooperation between the turbine worm and the gear set, so that the landing gear structure is arranged more closely, the connection is more stable, the landing gear is more stable, and the structural strength of the landing gear is enhanced; 2. The present invention cooperates with the inclined surface on the landing gear rotating part through the locking block, and under the tension of the resetting elastic part, the two inclined surfaces remain in close contact, ensuring that there is no gap between the landing gear rotating part and the upper cover and the locking block, the landing gear will not shake, and there will be no gap in the landing gear after long-term use. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 This is a schematic diagram of the landing gear of the present invention in a retracted state; Figure 2 This is a schematic diagram of the landing gear of the present invention in an open state; Figure 3 A bottom view of the internal structure of the present invention; Figure 4 It is a top view of the internal structure of the present invention; Figure 5 It is a schematic diagram of the unlocking mechanism, transmission mechanism, locking block and resetting elastic member of the steering gear of the present invention; Figure 6 It is a structural schematic diagram of the servo unlocking mechanism, transmission mechanism, landing gear and locking block of the present invention; Figure 7 It is a schematic diagram of the assembly of the transmission mechanism and the landing gear rotating part of the present invention.

[0016] Figure 8 It is a schematic diagram of the structure of the mounting frame, the hook and the limiting groove of the present invention; Fig. 9 It is a schematic diagram of the landing gear rotating member and the locking block when the landing gear of the present invention is opened.

[0017] Fig.10 It is a schematic diagram of the landing gear rotating member and the locking block when the landing gear of the present invention is retracted.

[0018] Fig.11 A circuit diagram of the signal input interface of the present invention; Fig.12 A circuit diagram of an input signal processing circuit of the present invention; Fig.13 A circuit diagram of a power supply voltage stabilizing circuit of the present invention; Fig.14 A circuit diagram of the electric gear box control circuit of the present invention; Fig.15 A circuit diagram of an unlocking steering gear control circuit of the present invention; Fig.16 A circuit diagram of the signal output interface of the present invention; Fig.17 A circuit diagram of a body mainboard in the circuit board of the present invention; Fig.18 It is a front view schematic diagram of the main wing adapter board in the circuit board of the present invention; Fig.19 It is a side view of the main wing adapter board in the circuit board of the present invention; Fig. 20 It is a schematic diagram of the back side of the main wing adapter board in the circuit board of the present invention.

[0019] In the figure: 1. casing; 2. servo unlocking mechanism; 21. plastic plate; 22. first motor; 23. rotating block; 24. wire rope; 3. transmission mechanism; 31. gear box; 32. second motor; 33. worm gear; 34. turbine; 35. gear transmission assembly; 36. connecting piece; 4. wheel assembly; 41. landing gear rotating piece; 411. rotating seat; 412. rotating shaft; 5. upper cover; 6. locking block; 7. bottom plate; 70. mounting frame; 71. hook; 72. limit groove; 8. reset elastic piece. DETAILED DESCRIPTION

[0020] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0021] See also Figure 1-20 The present invention provides a technical solution: a novel electric retractable landing gear mechanism, comprising a housing 1, and a wheel assembly 4 rotatably mounted inside the housing 1, wherein the landing gear is retracted and extended by rotating the wheel assembly 4, and the wheel assembly 4 comprises a wheel and a shock-absorbing cylinder for controlling the extension and retraction of the wheel.

[0022] A transmission mechanism 3 for driving the wheel assembly 4 to rotate is installed inside the shell 1. A base plate 7 is also installed inside the shell 1, and a mounting frame 70 is installed on the base plate 7. The bottom of the wheel assembly 4 is connected to a landing gear rotating member 41 rotatably arranged inside the mounting frame 70. A locking block 6 is slidably installed on the base plate 7. Inclined surfaces 9 are provided at the bottom of the landing gear rotating member 41 and the top of the locking block 6. The two inclined surfaces 9 fit tightly to ensure that the landing gear rotating member 41 will not rotate clockwise after being lowered. A servo unlocking mechanism 2 for driving the locking block 6 to move is also provided inside the shell 1.

[0023] When the landing gear is retracted, the servo unlocking mechanism 2 pulls the locking block 6 to move rightward (away from the landing gear rotating member 41), cancels the limit on the landing gear rotating member 41, and then drives the landing gear rotating member 41 to rotate through the transmission mechanism 3, thereby completing the retraction of the landing gear; Similarly, when the landing gear is lowered, the transmission mechanism 3 drives the landing gear rotating member 41 to reverse and make the landing gear rotating member 41 contact the upper cover 5, which can ensure that the landing gear rotating member 41 does not rotate counterclockwise after being lowered. The locking block 6 cooperates with the upper cover 5 to achieve the positioning of the landing gear rotating member 41 so that it does not shake. Under the pulling force of the reset elastic member 8, the locking block 6 rebounds to the locked position, so that the landing gear rotating member 41 and the inclined surface 9 on the locking block 6 are pressed tightly, thereby achieving the positioning of the landing gear.

[0024] The transmission mechanism 3 includes a gear box 31 fixed inside the housing 1 , a second motor 32 is fixedly disposed inside the gear box 31 , and a worm 33 is connected to the output shaft of the second motor 32 .

[0025] A rotatable turbine 34 and a gear transmission assembly 35 for driving the landing gear rotating member 41 to rotate are also installed inside the gear box 31. The turbine 34 and the gear transmission assembly 35 are arranged in coordination.

[0026] like Figure 3-4 As shown, the gear transmission assembly 35 includes a plurality of gears, and a plurality of rotating rods are rotatably arranged inside the gear box 31, and one or two gears are sleeved on the outer wall of each rotating rod, and the two gears on the same rotating rod have different diameters (i.e., one large gear and one small gear); A turbine 34 and a small gear are sleeved on one of the rotating rods, and a large gear in the gear transmission assembly 35 is meshed with the small gear.

[0027] The landing gear rotating member 41 includes a rotating seat 411, a rotating shaft 412 penetrating and connected to the rotating seat 411, a connecting member 36 is inserted into the inner ring of one of the gears in the gear transmission assembly 35, and one end of the rotating shaft is inserted and fixed inside the connecting member 36. The transmission mechanism 3 drives the rotating shaft 412 to rotate, thereby driving the rotating seat 411 fixed to the rotating shaft 412 to rotate.

[0028] Specifically, the connecting member 36 is mounted on a large gear farthest from the second motor 32 .

[0029] like Figure 5 As shown, the upper cover 5 is fixed to the mounting frame 70 by bolts, a bearing is installed in the circular gap between the mounting frame 70 and the upper cover 5, and the outer wall of the rotating shaft is inserted and fixed to the inner ring of the bearing.

[0030] A limiting groove 72 is provided at the lower end of the inner wall of the mounting frame 70 , and stepped grooves are provided at both ends of the locking block 6 . Both ends of the locking block 6 are slidably disposed inside the limiting groove 72 .

[0031] One end of the mounting frame 70 is connected to a hook 71 , the hook 71 is connected to a reset elastic member 8 , and one end of the reset elastic member 8 is connected to one end of the locking block 6 .

[0032] A through hole is provided on the housing 1 , and the servo unlocking mechanism 2 is installed inside the through hole. The servo unlocking mechanism 2 includes a rotating block 23 rotatably arranged inside the through hole, and a steel wire rope 24 is connected between the rotating block 23 and the other end of the locking block 6 .

[0033] One end of the locking block 6 is provided with a hanging ear, one end of the resetting elastic member 8 is connected to the hanging ear, and the other end of the locking block 6 is provided with a hanging ring, one end of the steel wire rope 24 is connected to the hanging ring.

[0034] The first motor 22 drives the rotating block 23 to rotate, and the rotating block 23 pulls the steel wire rope 24 to move, thereby driving the locking block 6 to move in a direction away from the landing gear rotating member 41 .

[0035] The servo unlocking mechanism 2 further includes a plastic plate 21 installed inside the housing 1 and used to press the servo, and a first motor 22 installed at the bottom of the housing 1 , wherein the output shaft of the first motor 22 is connected to a rotating block 23 .

[0036] The present invention also provides a control circuit for a novel electric retractable landing gear mechanism, which is used to control the novel electric retractable landing gear mechanism described above, including a landing gear control circuit, the landing gear control circuit is used to control the start and stop of the transmission mechanism and the servo unlocking mechanism, and the landing gear control circuit includes: a signal input interface, an input signal processing circuit, a power supply voltage stabilizing circuit, an electric gear box control circuit, an unlocking servo control circuit, and a signal output interface; The input signal processing circuit is electrically connected to the power supply voltage stabilizing circuit, the signal input interface, the input signal processing circuit, the electric gear box control circuit, the unlocking servo control circuit, and the signal output interface are all electrically connected to the power supply voltage stabilizing circuit, and the electric gear box control circuit is electrically connected to the signal output interface; The schematic diagram of the circuit board is shown in Figure 17-Figure 20 Because the main landing gear locking mechanism is driven by the servo, the fuselage mainboard needs to design a main landing gear electric gear box and locking servo linkage control system.

[0037] Working principle: When the main landing gear gear box 31 drives the wheel assembly 4 to be in the raised state, the locking servo does not work, and the locking mechanism is physically locked automatically.

[0038] When the main landing gear needs to be retracted, the locking servo is first powered on to unlock, and then the gear box 31 drives the wheel assembly 4 to be retracted.

[0039] The input signal processing circuit includes a chip U3 and a MOS tube Q1. A resistor R3 is connected between the G pole and the S pole of the MOS tube Q1. A resistor R4 is also connected to the S pole of the MOS tube Q1. The signal input interface includes a terminal block J1 and a terminal block J3. Pin 1 of the terminal block J1 is connected to the D pole of the MOS tube Q1. Pin 1 of the terminal block J3 is connected to the G pole of the MOS tube Q1, pin 3 of the terminal block J3 is connected to pin 5 of the chip U3, and pin 4 of the terminal block J3 is connected to pin 15 of the chip U3.

[0040] The power supply voltage stabilizing circuit includes a chip U1, capacitors C2 and C3 are connected in parallel between pins 1 and 3 of the chip U1, capacitors C4 and C5 are connected in parallel between pins 1 and 2 of the chip U1, and pin 1 of the chip U1 inputs a 5V voltage, pin 2 of the chip U1 outputs a 3.3V voltage, and pin 2 of the chip U1 is connected to pin 6 of the chip U3.

[0041] The electric gear box control circuit includes a chip U2, wherein pin 2 of the chip U2 is connected to pin 9 of the chip U3, pin 3 of the chip U2 is connected to pin 2 of the chip U3, and pins 6 and 7 of the chip U2 are connected to a resistor R1, a resistor R2, and a capacitor C1 forming a closed loop, and the connection terminals of the resistor R1 and the capacitor C1 are connected to pin 16 of the chip U3.

[0042] The unlocking servo control circuit includes a MOS tube Q5, a resistor R18 is connected between the S pole and the G pole of the MOS tube Q5, the G pole of the MOS tube Q5 is connected to 3.3V, the S pole of the MOS tube Q5 is connected to the 10th pin of the chip U3, the D pole of the MOS tube Q5 is respectively connected to the resistor R21 and the resistor R22, and one end of the resistor R21 is connected to the 3rd pin of the chip U1.

[0043] The signal output interface includes terminal block J2 and terminal block J6. Terminal block J2 outputs the landing gear electric gearbox control signal, and terminal block J6 outputs the unlocking servo signal. Pin 5 of chip U2 is connected to pin 4 of terminal block J2, and pin 8 of chip U2 is connected to pin 1 of terminal block J2; one end of resistor R22 is connected to pin 1 of terminal block J6.

[0044] The present invention also provides a method for using a novel electric retractable landing gear mechanism, which uses the novel electric retractable landing gear mechanism described above and specifically includes the following steps: In the state of the landing gear being retracted, the first motor 22 is operated, the first motor 22 drives the rotating block 23 to rotate, the rotating block 23 pulls the wire rope 24 to move, and then drives the locking block 6 to move in the direction away from the landing gear rotating member 41, so that the locking block 6 is separated from the two inclined surfaces on the landing gear rotating member 41, and the limit on the landing gear rotating member 41 can be cancelled; then the second motor 32 is operated, the second motor 32 drives the worm rod 33 to rotate, the worm rod 33 drives the turbine 34 to rotate, and the turbine 34 drives the landing gear rotating member 41 to rotate clockwise through the gear transmission assembly 35 and the connecting member 36, and then drives the rotation of the wheel assembly 4, and the wheel assembly 4 is retracted. After the landing gear reaches the storage position, the transmission mechanism 3 stops rotating; When the landing gear is in the open state, the second motor 32 runs and reverses, and with the cooperation of the worm rod 33, the turbine 34, the gear transmission assembly 35, and the connecting member 36, the landing gear rotating member 41 is driven to rotate, and the wheel assembly 4 is driven to move out of the housing 1, and the landing gear rotating member 41 abuts against the upper cover 5. After the landing gear reaches the open position, the transmission mechanism 3 stops rotating, and under the elastic force of the reset elastic member, the locking block 6 automatically bounces into the locking position, so that the locking block 6 is tightly fitted with the two inclined surfaces on the landing gear rotating member 41, so as to realize the positioning of the landing gear rotating member 41.

[0045] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A novel electric retractable landing gear mechanism, characterized in that: It includes an outer shell, a wheel assembly rotatably mounted inside the outer shell, a transmission mechanism for driving the wheel assembly to rotate is mounted inside the outer shell, a base plate is also mounted inside the outer shell, a mounting frame is mounted on the base plate, the bottom of the wheel assembly is connected to a landing gear rotating member rotatably mounted inside the mounting frame, a locking block is slidably mounted on the base plate, the bottom of the landing gear rotating member and the top of the locking block are both provided with inclined surfaces, the two inclined surfaces are tightly fitted, and a steering gear unlocking mechanism for driving the locking block to move is also provided inside the outer shell.

2. The novel electric retractable landing gear mechanism according to claim 1 is characterized in that: The transmission mechanism includes a gear box fixed inside the outer shell, a second motor is fixedly arranged inside the gear box, a worm gear is connected to the output shaft of the second motor, a rotatable turbine and a gear transmission assembly for driving the landing gear rotating part to rotate are also installed inside the gear box, and the turbine and the gear transmission assembly are arranged in coordination.

3. The novel electric retractable landing gear mechanism according to claim 2 is characterized in that: The landing gear rotating member includes a rotating seat, a rotating shaft penetrating and connected to the rotating seat, a connecting member is inserted into the inner ring of one of the gears in the gear transmission assembly, and one end of the rotating shaft is inserted and fixed inside the connecting member.

4. The novel electric retractable landing gear mechanism according to claim 3 is characterized in that: An upper cover is fixed on the mounting frame by bolts, a bearing is installed in the circular gap between the mounting frame and the upper cover, and the outer wall of the rotating shaft is inserted and fixed on the inner ring of the bearing.

5. The novel electric retractable landing gear mechanism according to claim 1 is characterized in that: A limiting groove is provided at the lower end of the inner wall of the mounting frame, and stepped grooves are provided at both ends of the locking block. Both ends of the locking block are slidably arranged inside the limiting groove.

6. The novel electric retractable landing gear mechanism according to claim 1 is characterized in that: One end of the mounting frame is connected with a hook, the hook is connected with a reset elastic member, and one end of the reset elastic member is connected to one end of the locking block.

7. The novel electric retractable landing gear mechanism according to claim 1 is characterized in that: A through hole is provided on the shell, and the servo unlocking mechanism is installed inside the through hole. The servo unlocking mechanism includes a rotating block rotatably arranged inside the through hole, and a steel wire rope is connected between the rotating block and the other end of the locking block.

8. The novel electric retractable landing gear mechanism according to claim 7 is characterized in that: The steering gear unlocking mechanism also includes a plastic plate installed inside the shell and used to press the steering gear, and a first motor installed at the bottom of the shell, wherein the output shaft of the first motor is connected to the rotating block.

9. A control circuit for a novel electric retractable landing gear mechanism, used to control a novel electric retractable landing gear mechanism according to any one of claims 1 to 8, characterized in that: It includes a landing gear control circuit, which is used to control the start and stop of the transmission mechanism and the servo unlocking mechanism. The landing gear control circuit includes: a signal input interface, an input signal processing circuit, a power supply voltage stabilizing circuit, an electric gear box control circuit, an unlocking servo control circuit, and a signal output interface; The input signal processing circuit is electrically connected to the power supply voltage stabilizing circuit, the signal input interface, input signal processing circuit, electric gear box control circuit, unlocking servo control circuit, and signal output interface are all electrically connected to the power supply voltage stabilizing circuit, and the electric gear box control circuit is electrically connected to the signal output interface.

10. A method for using a novel electric retractable landing gear mechanism, using the novel electric retractable landing gear mechanism according to any one of claims 1 to 8, characterized in that: The specific steps include: When the landing gear is retracted, the first motor is operated, the first motor drives the rotating block to rotate, the rotating block pulls the wire rope to move, and then drives the locking block to move in the direction away from the landing gear rotating member, so that the locking block is separated from the two inclined surfaces on the landing gear rotating member, and the limit on the landing gear rotating member can be cancelled; then the second motor is operated, the second motor drives the worm rod to rotate, the worm rod drives the turbine to rotate, and the turbine drives the landing gear rotating member to rotate clockwise through the gear transmission assembly and the connecting member, and then drives the rotation of the wheel assembly to retract the wheel assembly. After the landing gear reaches the storage position, the transmission mechanism stops rotating; When the landing gear is in the open state, the second motor runs and reverses, and with the cooperation of the worm gear, turbine, gear transmission assembly and connecting parts, the landing gear rotating part is driven to rotate, driving the wheel assembly to move out of the housing, and the landing gear rotating part abuts against the upper cover. After the landing gear reaches the open position, the transmission mechanism stops rotating, and under the elastic force of the reset elastic part, the locking block automatically bounces into the locking position, so that the locking block is tightly fitted with the two inclined surfaces on the landing gear rotating part, thereby realizing the positioning of the landing gear rotating part.

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