Constraining slow-release device of carrier rocket and launching pad
A slow-release device and carrier rocket technology, applied in rocket launchers, offensive equipment, weapon types, etc., can solve problems such as poor slow-release effect, reduce failure rates, facilitate production and post-maintenance, and have a simple overall structure. Effect
Active Publication Date: 2021-12-03
浙江蓝箭航天空间科技有限公司
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Problems solved by technology
The structure is simple and the synchronization is good, but the slow-release effect is poor, and there are still vibration and shock loads acting on the tail structure of the rocket body
Method used
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[0028] Various exemplary embodiments of the present invention will now be described in detail. The detailed description should not be considered as a limitation of the present invention, but rather as a more detailed description of certain aspects, features and embodiments of the present invention.
[0029] It will be apparent to those skilled in the art that various modifications and changes can be made in the specific embodiments of the present invention described herein without departing from the scope or spirit of the present invention. Other embodiments will be apparent to the skilled person from the description of the present invention. The specification and examples in this application are exemplary only.
[0030] The invention provides a pinning slow release device for a launch vehicle, such as figure 1 Shown is the use state diagram of the restraint slow-release device. A plurality of restraining and slow-release devices are arranged on the launch pad 7 for restrain...
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The invention provides a restraining slow-release device of a carrier rocket and a launching pad. The restraining slow-release device comprises a telescopic rod, a pressing rod, a rotating arm and a force sensor. One end of the rotating arm is movably connected to the launching pad through a first support. The other end of the rotating arm is provided with a U-shaped groove, and the pressing rod is movably connected into the U-shaped groove. One end of the pressing rod is movably connected with one end of the telescopic rod arranged on the launching pad, and the other end of the pressing rod is connected with the tail end of the rocket and used for applying restraining force to the tail end of the rocket under the force application effect of the telescopic rod. The force sensor is arranged on the telescopic rod and used for detecting the axial force of the telescopic rod. The restraining slow-release device provided by the invention is simple in structure, few in parts, easy to produce and maintain and stable in operation. In addition, the restraining slow-release device can realize automatic control, and is high in reaction speed and good in release synchronism. When the restraining slow-release device releases the tail of the rocket, no vibration impact load is generated on the tail structure of the rocket, so that the safety and the stability of rocket launching are ensured.
Description
technical field [0001] The invention relates to the technical field of rocket pinning and slow-release devices, in particular to a pinning and slow-release device and a launch pad for a launch vehicle. Background technique [0002] At the moment of rocket launch, the engine usually delays for a few seconds before reaching full thrust. In order to improve the launch reliability and ensure the safety of the launch station, the use of pinning and slow-release devices is usually a necessary technical means for launch vehicles. [0003] At present, the pinning and slow-release devices are mainly divided into two categories: mechanism type and explosive bolt type. Mechanism-type pinning and slow-release devices are mainly driven by pneumatic or hydraulic power, and the mechanical parts move to achieve the purpose of pinning and slow-release rockets. There are many mechanical parts, which require high manufacturing and assembly precision, and the synchronization of slow release i...
Claims
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Login to View More IPC IPC(8): F41F3/052F41F3/04
CPCF41F3/052F41F3/04Y02E30/30
Inventor 王登杨俊戴政李云龙
Owner 浙江蓝箭航天空间科技有限公司