CN204258158U - Electric aircraft unwrapping wire tripping gear - Google Patents

Abstract

An electric aircraft release and decoupling device, comprising a base, and a lock shaft, a lock ring and a motor installed on the base, the lock shaft can reciprocate along the port of the lock ring driven by the motor, It is characterized in that: a drive nut is fixed on the shaft body of the lock shaft, and the drive nut is matched with a screw rod fixed on the motor shaft of the motor. After the utility model adopts the structure of the screw rod and the transmission nut, the motor shaft directly drives the lock shaft to reciprocate through the screw rod and the transmission nut, which not only has a simple structure, but also greatly improves the reliability.

Description

Uncoupling device for uncoupling of electric aircraft

technical field

The utility model relates to an uncoupling device used by electric power departments for field operations, in particular to a decoupling device installed on an electric rotorcraft and controlled by a driving device to serve as a fixed-point uncoupling device.

Background technique

At present, the use of rotorcraft to release wires is quietly emerging in power systems. It completes flight tasks through satellite positioning, video tracking, and manual remote control. It has the advantages of stability, precision, and safety. During operation, the aircraft is equipped with a high-strength, high-light nylon lead wire, which is brought from No. A iron tower to B No. iron tower for precise delivery, thus completing the lead-off work between the two towers. This method avoids the need to open up construction channels and other work links in the past, which can not only effectively improve the construction progress, but also avoid damage and pollution to the ecology. Before the utility model was made, the decoupling device installed on the rotorcraft and used to carry the lead wire had the problems of complex structure, high production cost and poor stability, which affected the popularization and application of this wire releasing method to a certain extent.

Contents of the invention

In order to overcome the above-mentioned problems existing in the prior art, the utility model aims to provide a new structure electric aircraft release and decoupling device, which has the advantages of simple structure and high reliability.

In order to achieve the above object, the utility model adopts the following technical scheme: the uncoupling device for electric aircraft includes a base, and a lock shaft, a lock ring and a motor installed on the base, and the lock shaft is mounted on the base of the motor. Driven to move back and forth along the port of the lock ring, it is characterized in that: a drive nut is fixed on the shaft body of the lock shaft, and the drive nut is connected with a drive nut fixed on the motor shaft of the motor The screws are matched.

During specific implementation, a travel switch is respectively provided at both ends of the reciprocating movement track of the lock shaft.

Beneficial effects: Compared with the prior art, the utility model adopts the structure of the screw rod and the transmission nut, so that the motor shaft directly drives the lock shaft to reciprocate through the screw rod and the transmission nut, which not only has a simple structure, but also greatly improves the reliability .

Below in conjunction with accompanying drawing, the utility model is described further through embodiment.

Description of drawings

Fig. 1 is a top view structural diagram of an embodiment of the utility model.

Among the figure: base 1, lock shaft 2, motor 3, drive nut 4, drive screw 5, screw seat 6, lock ring 7, travel switch 8, travel switch 9.

Detailed ways

See Figure 1. This electric aircraft uncoupling device includes a base 1, and a lock shaft 2 installed on the base 1, a motor 3, a drive nut 4, a drive screw 5, a screw seat 6, a lock ring 7, a travel switch 8 and a travel switch 9. The rear axle body of lock shaft 2 is fixed with transmission nut 4, and transmission nut 4 is matched with the transmission screw rod 5 that is fixed on the motor shaft again. Therefore, when the motor 3 drives the transmission screw 5 to rotate, the transmission nut 4 and the lock shaft 2 are displaced, that is, reciprocating along the port of the lock ring 7 . Stroke switches 8 and 9 are respectively located at the two ends of the reciprocating movement track of the lock shaft 2 to control the motor 3 to act.

During operation, the motor 3 acts under the control of the control system, and the rotation of the transmission screw 5 causes the displacement of the transmission nut 4, thereby driving the movement of the lock shaft 2 to realize the opening and closing action. The lead wire is wound on the lock shaft 2, and the travel switches 8 and 9 control the motor 3 to stop.

The above-mentioned embodiments are only used to explain the idea of the invention, and should not be used as a limitation to the present invention. All simple deformation structures inspired by the embodiments should be considered as falling within the scope of protection of the present invention.

Claims (2)

1. an electric aircraft unwrapping wire tripping gear, comprise base (1), and the lock shaft (2), lock ring (7) and the motor (3) that are arranged on this base (1), described lock shaft (2) can move back and forth along the port of described lock ring (7) under the driving of this motor (3), it is characterized in that: the axle body of described lock shaft (2) is fixed with a transmission nut (4), the screw rod (5) that this transmission nut (4) is fixed on on the motor shaft of described motor (3) is again matched.

2. unwrapping wire tripping gear as claimed in claim 1, is characterized in that: be respectively equipped with a travel switch (8,9) at the two ends moving back and forth track of described lock shaft (2).