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Rocket Propulsion in Empty Space - I01:13

Rocket Propulsion in Empty Space - I

3.8K
The driving force for the motion of any vehicle is friction, but in the case of rocket propulsion in space, the friction force is not present. The motion of a rocket changes its velocity (and hence its momentum) by ejecting burned fuel gases, thus causing it to accelerate in the direction opposite to the velocity of the ejected fuel. In this situation, the mass and velocity of the rocket constantly change along with the total mass of ejected gases. Due to conservation of momentum, the...
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Rocket Propulsion In Empty Space - II01:12

Rocket Propulsion In Empty Space - II

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The motion of a rocket is governed by the conservation of momentum principle. A rocket's momentum changes by the same amount (with the opposite sign) as the ejected gases. As time goes by, the rocket's mass (which includes the mass of the remaining fuel) continuously decreases, and its velocity increases. Therefore, the principle of conservation of momentum is used to explain the dynamics of a rocket's motion. The ideal rocket equation gives the change in velocity that a rocket...
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Rocket Propulsion in Gravitational Field - I01:20

Rocket Propulsion in Gravitational Field - I

3.3K
Rockets range in size from small fireworks that ordinary people use to the enormous Saturn V that once propelled massive payloads toward the Moon. The propulsion of all rockets, jet engines, deflating balloons, and even squids and octopuses are explained by the same physical principle: Newton's third law of motion. The matter is forcefully ejected from a system, producing an equal and opposite reaction on what remains.
The motion of a rocket in space changes its velocity (and hence its...
3.3K
Rocket Propulsion in Gravitational Field - II01:03

Rocket Propulsion in Gravitational Field - II

2.8K
A rocket's velocity in the presence of a gravitational field is decreased by the amount of force exerted by Earth's gravitational field, which opposes the motion of the rocket. If we consider thrust, that is, the force exerted on a rocket by the exhaust gases, then a rocket's thrust is greater in outer space than in the atmosphere or on a launch pad. In fact, gases are easier to expel in a vacuum.
A rocket's acceleration depends on three major factors, consistent with the...
2.8K
Inductively Coupled Plasma Atomic Emission Spectroscopy: Instrumentation01:26

Inductively Coupled Plasma Atomic Emission Spectroscopy: Instrumentation

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Inductively coupled plasma (ICP) is the common plasma source used in atomic emission spectroscopy (AES), a technique that detects and analyzes various elements in a sample. This method is often called inductively coupled plasma atomic emission spectroscopy (ICP-AES).
There are three main types of inductively coupled plasma atomic emission spectroscopy  (ICP-AES) instruments: sequential, simultaneous multichannel, and Fourier transform instruments, with the latter being less commonly used....
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Electro-mechanical Systems01:19

Electro-mechanical Systems

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Electromechanical systems are intricate configurations that effectively combine electrical and mechanical elements to achieve a desired outcome. Central to many of these systems is the DC motor, a device that converts electrical energy into mechanical motion, enabling various applications ranging from simple fans to complex robotic mechanisms.
A key component of the DC motor is the armature, a rotating circuit positioned within a magnetic field. As an electric current passes through the...
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Design of an onboard computer for small experimental rockets with an integrated hardware-in-the-loop validation framework.

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相关实验视频

Updated: Jan 16, 2026

Laboratory Scale Slow Cook-Off Testing of Rocket Propellants: The Combustion Rate Analysis of a Slowly Heated Propellant CRASH-P Test
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Laboratory Scale Slow Cook-Off Testing of Rocket Propellants: The Combustion Rate Analysis of a Slowly Heated Propellant CRASH-P Test

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适用于小型火箭发动机测试台的多功能低成本数据采集系统.

Nathan Andreani Netzel1, Daniel Strufaldi Batista1, Francisco Granziera1

  • 1State University of Londrina, Department of Electrical Engineering, Rod. Celso Garcia Cid- PR-445, 86057-970, Londrina, PR, Brazil.

HardwareX
|October 1, 2025
PubMed
概括
此摘要是机器生成的。

为小型火箭发动机测试开发了一种新的,负担得起的数据采集系统. 这个系统准确地测量推力和压力,提高安全性,并使学生有效研究.

关键词:
数据采集系统 (DAQ) 是一个数据采集系统.负载细胞的负载细胞.压力传感器 压力传感器导弹发动机的火箭发动机.静态点火试验 静态点火试验系统校准系统的校准

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Optimization, Test and Diagnostics of Miniaturized Hall Thrusters
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Improving the Combustion Performance of a Hybrid Rocket Engine using a Novel Fuel Grain with a Nested Helical Structure
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相关实验视频

Last Updated: Jan 16, 2026

Laboratory Scale Slow Cook-Off Testing of Rocket Propellants: The Combustion Rate Analysis of a Slowly Heated Propellant CRASH-P Test
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Laboratory Scale Slow Cook-Off Testing of Rocket Propellants: The Combustion Rate Analysis of a Slowly Heated Propellant CRASH-P Test

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Optimization, Test and Diagnostics of Miniaturized Hall Thrusters
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科学领域:

  • 航空航天工程 航空航天工程
  • 教育技术的教育技术
  • 仪器化 仪器化 仪器化

背景情况:

  • 小型探测火箭对于大气数据收集至关重要,并在大学研究中提供实践学习体验.
  • 发动机测试和验证对于探测火箭实验的安全性和可靠性至关重要,需要专门的测试台.

研究的目的:

  • 为小型火箭发动机试验台设计和实施一个多功能,低成本的数据采集 (DAQ) 系统.
  • 为教育和研究目的提供一个负担得起但功能性的替代商业DAQ系统.

主要方法:

  • 开发了一个模块化DAQ系统,使用成本效益高的硬件和软件.
  • 集成的负载电池传感器和压力传感器用于测量推力和压力.
  • 优先考虑允许未来扩展和适应各种发动机配置的设计.

主要成果:

  • 实施的DAQ系统成功地以准确和可靠的方式测量了推力和压力.
  • 实验测试显示,噪声水平与商业DAQ系统相美.
  • 该系统在可负担性和功能性之间取得了平衡.

结论:

  • 开发的低成本DAQ系统适合在学术环境中进行小型火箭发动机测试.
  • 该系统增强了实验安全,并为学生和研究人员提供了有效的数据采集.
  • 模块化设计支持未来的适应性和整合到更广泛的研究项目.