Rocket projectile tail electric connector pulling-out mechanism
By designing a rocket tail electrical connector unplugging mechanism and using a steel cable assembly and a forced unplugging mechanism, the problem of reliable unplugging of the electrical connector in a high-temperature environment is solved, and reliable communication separation is achieved under high temperatures.
Patent Information
- Application Number
- CN202510904367.4
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-07-01
- Publication Date
- 2025-10-17
AI Technical Summary
The electrical connector at the tail of the rocket is difficult to disconnect reliably under the high temperature environment of the engine, resulting in communication interruption.
A rocket tail electrical connector unplugging mechanism is designed, which includes a rocket tail electrical connector, a steel cable assembly, a forced unplugging mechanism, a fixing bracket and an adjusting screw. The mechanism is connected by pins and threads, and a U-shaped pull ring and a pull ring structure are used to eliminate the misalignment problem. The slack can be adjusted to ensure reliable unplugging.
Ensure reliable disconnection of the rocket tail electrical connector in a high-temperature environment to avoid accidental disconnection during transportation, and reliably unlock it after the engine is ignited to ensure the normal separation of the communication system.
Smart Images
Figure CN120810312A_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The application belongs to the technical field of rocket projectiles, and particularly relates to a rocket projectile tail electric connector pulling-off mechanism. BACKGROUND
[0002] The rocket projectile launching process is an important link of rocket projectile flight test, and the rocket projectile needs to realize communication with the ground launching system through the tail electric connector during the launching process; when the rocket projectile works and the engine is ignited, the ground launching communication system works and completes, and the rocket projectile is displaced under the action of the engine thrust, at which time the tail electric connector for communication with the ground launching system needs to be pulled off and separated from the rocket projectile. SUMMARY
[0003] In order to overcome the defects of the prior art, the application provides a rocket projectile tail electric connector pulling-off mechanism, which comprises a tail electric connector, a steel cable assembly, a forced pulling-off mechanism, a fixing support and an adjusting screw; the steel cable assembly is connected with the tail electric connector through a pin, and the adjusting screw is connected with the steel cable assembly through a pin; the adjusting screw is constrained on the fixing support; one end of the forced pulling-off mechanism is connected with the electric connector, and the other end is connected with the adjusting screw; the steel cable assembly is composed of a U-shaped pull ring and a pull ring; the adjusting screw is in the shape of a fork, one end of which is connected with the steel cable assembly through a pin, and the other end is designed with threads and constrained on the fixing support through a nut, and the loosening amount of the steel cable assembly can be controlled by adjusting the adjusting screw; one end of the forced pulling-off mechanism is connected with the electric connector, and the other end is connected with the adjusting screw. The application solves the problem of reliable pulling-off of the rocket projectile tail electric connector in the high-temperature environment of the engine working.
[0004] The application solves the technical problems by adopting the following technical scheme:
[0005] The rocket projectile tail electric connector pulling-off mechanism comprises a tail electric connector, a steel cable assembly, a forced pulling-off mechanism, a fixing support and an adjusting screw.
[0006] The steel cable assembly is connected with the tail electric connector through a pin, and the adjusting screw is connected with the steel cable assembly through a pin; the adjusting screw is constrained on the fixing support; one end of the forced pulling-off mechanism is connected with the electric connector, and the other end is connected with the adjusting screw.
[0007] The steel cable assembly is composed of a U-shaped pull ring and a pull ring.
[0008] The adjusting screw is in the shape of a fork, one end of which is connected with the steel cable assembly through a pin, and the other end is designed with threads and constrained on the fixing support through a nut, and the loosening amount of the steel cable assembly can be controlled by adjusting the adjusting screw.
[0009] One end of the forced pulling-off mechanism is connected with the electric connector, and the other end is connected with the adjusting screw.
[0010] Preferably, the steel cable assembly does not unlock the electrical connector due to an accident, and the rocket projectile can reliably pull out the tail electrical connector under the action of the forced pulling-out mechanism after moving a certain distance.
[0011] Preferably, the U-shaped pull ring and the pull ring structure of the steel cable assembly can eliminate the problem of misalignment of the electrical connector and the adjusting screw due to position error of the fixed support.
[0012] Preferably, the slack amount can avoid accidental pulling out of the tail electrical connector of the rocket projectile caused by small displacement during transportation, and can reliably unlock the tail electrical connector of the rocket projectile after a certain displacement of the engine after ignition.
[0013] The beneficial effects of the present application are as follows:
[0014] The present application solves the problem of reliable pulling out of the tail electrical connector of the rocket projectile in a high-temperature environment of the engine in operation. BRIEF DESCRIPTION OF DRAWINGS
[0015] Figure 1 is a schematic diagram of the mechanism of the present application.
[0016] Reference signs: 1: tail electrical connector 2: steel cable assembly 3: forced pulling-out mechanism 4: adjusting screw 5: fixed support. DETAILED DESCRIPTION
[0017] The present application will be further described below in combination with the drawings and examples.
[0018] The present application discloses a rocket projectile tail electrical connector pulling-out mechanism and method. The main functions of the mechanism are as follows:
[0019] A rocket projectile tail electrical connector pulling-out mechanism, characterized by a tail electrical connector, a steel cable assembly, a forced pulling-out mechanism, a fixed support, an adjusting screw, etc.
[0020] The steel cable assembly is connected to the tail electrical connector through a pin, the adjusting screw is connected to the steel cable assembly through a pin, the adjusting screw is constrained on the fixed support, one end of the forced pulling-out mechanism is connected to the electrical connector, and the other end is connected to the adjusting screw.
[0021] The steel cable assembly is composed of a U-shaped pull ring and a pull ring. This structure has the advantage of eliminating the problem of misalignment of the electrical connector and the adjusting screw due to position error of the fixed support.
[0022] The adjusting screw is in the shape of a fork, one end is connected to the steel cable assembly through a pin, and the other end is designed with threads, which is constrained on the fixed support through a nut. By adjusting the adjusting screw, the slack amount of the steel cable assembly can be controlled. This slack amount can avoid accidental pulling out of the tail electrical connector of the rocket projectile caused by small displacement during transportation, and can reliably unlock the tail electrical connector of the rocket projectile after a certain displacement of the engine after ignition.
[0023] The one end of the forced pulling-off mechanism is connected with the electric connector, and the other end is connected with the adjusting screw. When the steel cable assembly does not unlock the electric connector accidentally, the rocket projectile can be reliably pulled off from the tail electric connector under the action of the forced pulling-off mechanism after moving a certain distance.
[0024] Embodiment:
[0025] 1. The steel cable assembly is connected with the tail electric connector through a pin, the adjusting screw is connected with the steel cable assembly through a pin, the adjusting screw is constrained on the fixed support, the one end of the forced pulling-off mechanism is connected with the electric connector, and the other end is connected with the adjusting screw.
[0026] 2. The steel cable assembly is composed of a U-shaped pull ring and a pull ring. The advantage of this structure is that it can eliminate the problem of misalignment of the electric connector and the adjusting screw caused by the position error of the fixed support.
[0027] 3. The adjusting screw is in the shape of a fork, one end of which is connected with the steel cable assembly through a pin, and the other end is designed with a thread, which is constrained on the fixed support through a nut. The relaxation amount of the steel cable assembly can be controlled by adjusting the adjusting screw, which can avoid the accidental pulling-off of the tail electric connector caused by small displacement of the rocket projectile during transportation, and can reliably unlock the tail electric connector under a certain displacement of the rocket projectile after the engine is ignited.
[0028] 4. The one end of the forced pulling-off mechanism is connected with the electric connector, and the other end is connected with the adjusting screw. When the steel cable assembly does not unlock the electric connector accidentally, the rocket projectile can be reliably pulled off from the tail electric connector under the action of the forced pulling-off mechanism after moving a certain distance.
[0029] 5. When the rocket projectile works, the ground launch communication system works after the engine is ignited, the rocket projectile moves under the action of the engine thrust, and the tail electric connector is separated from the rocket projectile under the action of the pulling-off mechanism.
Claims
1. A rocket tail electrical connector removal mechanism, characterized in that: It includes a tail electric connector, a steel cable assembly, a forced removal mechanism, a fixing bracket and an adjusting screw; The steel cable assembly is connected to the spring-tail electrical connector via a pin, and the adjusting screw is connected to the steel cable assembly via a pin; the adjusting screw is constrained on the fixed bracket; one end of the forced removal mechanism is connected to the electrical connector, and the other end is connected to the adjusting screw; The steel cable assembly consists of a U-shaped pull ring and a pull ring; The adjusting screw is fork-shaped, one end of which is connected to the cable assembly via a pin, and the other end is designed with a thread and constrained to the fixed bracket via a nut. The slack of the cable assembly can be controlled by adjusting the adjusting screw. One end of the forced pull-out mechanism is connected to the electrical connector, and the other end is connected to the adjusting screw.
2. The rocket tail electrical connector removal mechanism according to claim 1, characterized in that: If the steel cable assembly fails to unlock the electrical connector due to an accident, the rocket can reliably unplug the tail electrical connector under the action of the forced unplugging mechanism after the rocket moves a certain distance.
3. The rocket tail electrical connector removal mechanism according to claim 1, characterized in that: The U-shaped pull ring and the pull ring structure of the steel cable assembly can eliminate the problem of the electric connector and the adjusting screw being out of alignment due to the position error of the fixing bracket.
4. The rocket tail electrical connector removal mechanism according to claim 1, characterized in that: The slack can prevent the tail electrical connector from being accidentally disconnected due to a small displacement during the transportation of the rocket, and can also reliably unlock the tail electrical connector when the rocket is displaced to a certain extent after the engine is ignited.