Lethargy theorem

Rockets, which lose significant amounts of mass as fuel during flight, are an example of a variable-mass system.

In mechanics, a variable-mass system is a collection of matter whose mass varies with time. Newton's second law of motion cannot directly be applied to such a system because it is valid for constant mass systems only. Instead, the time dependence of the mass m can be calculated by rearranging Newton's second law and adding a term to account for the momentum carried by mass entering or leaving the system. The general equation of variable-mass motion is written as

${𝐅}_{\mathrm{e}\mathrm{x}\mathrm{t}}+{𝐯}_{\mathrm{r}\mathrm{e}\mathrm{l}}\frac{\mathrm{d}m}{\mathrm{d}t}=m\frac{\mathrm{d}𝐯}{\mathrm{d}t}$

where F_ext is the net external force on the body, v_rel is the relative velocity of the escaping or incoming mass with respect to the center of mass of the body, and v is the velocity of the body. In astrodynamics, which deals with the mechanics of rockets, the term v_rel is often called the effective exhaust velocity and denoted v_e.

Derivation

There are different derivations for the variable-mass system motion equation, depending on whether is mass is entering or leaving a body (in other words, whether the moving body's mass is increasing or decreasing). To simplify calculations, all bodies are considered as particles.

Mass accretion

At instant 1, a mass dm with relative velocity u is about to collide with the main body of mass m and velocity v. After a time dt, at instant 2, both particles move as one body with velocity v + dv.

The following derivation is for a body that is gaining mass (accretion). Let a body of time-varying mass m moves at a velocity v at an initial time t. Meanwhile, at this instant, let a particle of mass dm moves with velocity u. The initial momentum can be written as

${𝐩}_{\mathrm{1}}=m𝐯+𝐮\mathrm{d}m$

Now at a time t + dt, let both the main body and the particle accrete into a body of velocity v + dv. Thus the new momentum of the system can be written as

${𝐩}_{\mathrm{2}}=(m+\mathrm{d}m)(𝐯+\mathrm{d}𝐯)=m𝐯+m\mathrm{d}𝐯+𝐯\mathrm{d}m+\mathrm{d}m\mathrm{d}𝐯$

Since dmdv is the product of two small values, it can be ignored, meaning during dt the momentum of the system varies for

$\mathrm{d}𝐩={𝐩}_{\mathrm{2}}-{𝐩}_{\mathrm{1}}=(m𝐯+m\mathrm{d}𝐯+𝐯\mathrm{d}m)-(m𝐯+𝐮\mathrm{d}m)=m\mathrm{d}𝐯-(𝐮-𝐯)\mathrm{d}m$

Therefore, by Newton's second law

${𝐅}_{\mathrm{n}\mathrm{e}\mathrm{t}}=\frac{\mathrm{d}𝐩}{\mathrm{d}t}=\frac{m\mathrm{d}𝐯-(𝐮-𝐯)\mathrm{d}m}{\mathrm{d}t}=m\frac{\mathrm{d}𝐯}{\mathrm{d}t}-(𝐮-𝐯)\frac{\mathrm{d}m}{\mathrm{d}t}$

Noting that u - v is the velocity of dm relative to m, symbolized as v_rel, this final equation can be arranged as

${𝐅}_{\mathrm{e}\mathrm{x}\mathrm{t}}+{𝐯}_{\mathrm{r}\mathrm{e}\mathrm{l}}\frac{\mathrm{d}m}{\mathrm{d}t}=m\frac{\mathrm{d}𝐯}{\mathrm{d}t}$

Mass ablation/ejection

In a system where mass is being ejected or ablated from a main body, the derivation is slightly different. At time t, let a mass m travel at a velocity v, meaning the initial momentum of the system is

${𝐩}_{\mathrm{1}}=m𝐯$

Since the main body will be losing mass, dm will be negative, meaning that at a time t + dt the momentum of the system becomes

${𝐩}_{\mathrm{2}}=(m+\mathrm{d}m)(𝐯+\mathrm{d}𝐯)+𝐮(-\mathrm{d}m)=m𝐯+m\mathrm{d}𝐯+𝐯\mathrm{d}m+\mathrm{d}m\mathrm{d}𝐯-𝐮\mathrm{d}m$

where u is the velocity of the ejected mass. Thus during dt the momentum of the system varies for

$\mathrm{d}𝐩={𝐩}_{\mathrm{2}}-{𝐩}_{\mathrm{1}}=(m𝐯+m\mathrm{d}𝐯+𝐯\mathrm{d}m-𝐮\mathrm{d}m)-(m𝐯)=m\mathrm{d}𝐯-(𝐮-𝐯)\mathrm{d}m$

This is the same dp as found in the mass accretion case above, meaning that the same conclusion holds.

Forms

When released, this rocket balloon ejects a significant amount of its mass as air, causing a large acceleration.

By the definition of acceleration, a = dv/dt, so the variable-mass system motion equation can be written as

${𝐅}_{\mathrm{e}\mathrm{x}\mathrm{t}}+{𝐯}_{\mathrm{r}\mathrm{e}\mathrm{l}}\frac{\mathrm{d}m}{\mathrm{d}t}=m𝐚$

In bodies that are not treated as particles a must be replaced by a_cm, the acceleration of the center of mass of the system, meaning

${𝐅}_{\mathrm{e}\mathrm{x}\mathrm{t}}+{𝐯}_{\mathrm{r}\mathrm{e}\mathrm{l}}\frac{\mathrm{d}m}{\mathrm{d}t}=m{𝐚}_{\mathrm{c}\mathrm{m}}$

Often the force due to thrust is defined as ${𝐅}_{\mathrm{t}\mathrm{h}\mathrm{r}\mathrm{u}\mathrm{s}\mathrm{t}}={𝐯}_{\mathrm{r}\mathrm{e}\mathrm{l}}\frac{\mathrm{d}m}{\mathrm{d}t}$ so that

${𝐅}_{\mathrm{e}\mathrm{x}\mathrm{t}}+{𝐅}_{\mathrm{t}\mathrm{h}\mathrm{r}\mathrm{u}\mathrm{s}\mathrm{t}}=m{𝐚}_{\mathrm{c}\mathrm{m}}$

This form shows that a body can have acceleration due to thrust even if no external forces act on it (F_ext = 0). Note finally that if one lets F_net be the sum of F_ext and F_thrust then the equation regains the usual form of Newton's second law:

${𝐅}_{\mathrm{n}\mathrm{e}\mathrm{t}}=m{𝐚}_{\mathrm{c}\mathrm{m}}$

Ideal rocket equation

Rocket mass ratios versus final velocity calculated from the rocket equation

Mining Engineer (Excluding Oil ) Truman from Alma, loves to spend time knotting, largest property developers in singapore developers in singapore and stamp collecting. Recently had a family visit to Urnes Stave Church. The ideal rocket equation, or the Tsiolkovsky rocket equation, can be used to study the motion of vehicles that behave like a rocket (where a body accelerates itself by ejecting part of its mass, a propellant, with high speed). It can be derived from the general equation of motion for variable-mass systems as follows: when no external forces act on a body (F_ext = 0) the variable-mass system motion equation reduces to

${𝐯}_{\mathrm{r}\mathrm{e}\mathrm{l}}\frac{\mathrm{d}m}{\mathrm{d}t}=m\frac{\mathrm{d}𝐯}{\mathrm{d}t}$

If the velocity of the ejected propellant, v_rel, is assumed have the opposite direction as the rocket's acceleration, dv/dt, the scalar equivalent of this equation can be written as

$-v_{\mathrm{r}\mathrm{e}\mathrm{l}}\frac{\mathrm{d}m}{\mathrm{d}t}=m\frac{\mathrm{d}v}{\mathrm{d}t}$

from which dt can be canceled out to give

$-v_{\mathrm{r}\mathrm{e}\mathrm{l}}\mathrm{d}m=m\mathrm{d}v$

Integration by separation of variables gives

$-v_{\mathrm{r}\mathrm{e}\mathrm{l}}{\int }_{m_0}^{m_1}\frac{\mathrm{d}m}{m}={\int }_{v_0}^{v_1}\mathrm{d}v$

$v_{\mathrm{r}\mathrm{e}\mathrm{l}}\ln \frac{m_0}{m_1}=v_1-v_0$

By rearranging and letting Δv = v₁ - v₀, one arrives at the standard form of the ideal rocket equation:

$\Delta v=v_{\mathrm{r}\mathrm{e}\mathrm{l}}\ln \frac{m_0}{m_1}$

where m₀ is the initial total mass, including propellant, m₁ is the final total mass, v_rel is the effective exhaust velocity (often denoted as v_e), and Δv is the maximum change of speed of the vehicle (when no external forces are acting).

References

43 year old Petroleum Engineer Harry from Deep River, usually spends time with hobbies and interests like renting movies, property developers in singapore new condominium and vehicle racing. Constantly enjoys going to destinations like Camino Real de Tierra Adentro.