Motion of a rocket Conservation of linear momentum provides appropriate analysis framework for analyzing motion of a rocket. The important difference in the approach here vis-a-vis application of Newton’s second is that we can consider “rocket” and “ejected gas mass” as components of a closed, isolated system. Though, the mass of the rocket is varying with time, but the mass of the “rocket – gas mass” system is constant. This fact eliminates the complexity resulting from varying mass. It is easy to visualize that “thrust” on the rocket should be greater than forces like gravity and air resistance, which are opposing its motion. Since rocket acquires great enough velocity and goes beyond the influence of opposing forces quickly, it is intuitive to study motion in ideal condition, when no external force other than “thrust” operates on it. This enables us to draw a base case, which can be appropriately modified by taking other external forces into account, if so required. Thus, system is closed and isolated. The net external force is zero. As such, the linear momentum of the system is conserved. For the analysis of the motion of a rocket, we shall make few simplifying assumptions : There is no external force like gravity and air resistance. The motion is taking place in one dimension. Fuel is consumed at constant rate. Gas is ejected at constant relative velocity with respect to rocket.

Reference to different velocities Conventionally, we represent velocity of rocket with respect to ground by symbol “v”, velocity of escaping gas with respect to ground by “u” and relative velocity of rocket with respect to escaping gas by “ v r ”. Also, we consider the direction of motion of rocket as the reference direction (x –direction). The absolute velocities of the rocket and ejected gas mass are shown in the figure :

Absolute velocities The velocities of rocket and ejected gas mass are shown with respect to ground. The relative velocity of rocket with respect to escaping gas is equal to difference of absolute velocities with respect to ground. It may also be emphasized here that relative velocity of rocket with respect to escaping gas and relative velocity of escaping gas with respect to rocket are equal and opposite to each other.

Time rate of change in mass The expression “ ⅆ m ⅆ t ” is time rate of change in the mass of the rocket. Since final mass of the rocket is less than initial mass during a small time interval “dt”, the time rate of change is essentially a negative quantity. We should note that mass is an unsigned scalar, which can not be negative. However, change in mass can be negative. Clearly, the mass of rocket, after a small time interval, is "m+dm" - not "m-dm". The masses of two components of system are shown in the figure.

Change in mass The change in the mass of the rocket with time is negative.

Conservation of linear momentum We analyze motion of “rocket and ejected mass” system in the inertial frame of reference of ground. There is no difficulty in the interpretation as system is a single entity without any variation in mass. At a given instant, t = t, let “m” be the mass of the rocket and “v” be the velocity of the rocket. We, now, consider the situation at a time instant t’ = t + dt, after a small time interval, “dt”. Let “m+dm” be the mass of the rocket, v+dv be the absolute velocity of the rocket with respect to ground, “-dm” be the mass of the ejected gas and “u” be the absolute velocity of the gas mass with respect to ground.

Velocities of the components of the system Velocity of rocket increases with time. Now, applying conservation of linear momentum, we have : m v = m + ⅆ m v + ⅆ v + − ⅆ m u This form of equation, however, is not very useful as it consists of absolute velocity of escaping gas, which is variable and is difficult to be measured. We need to convert this velocity in terms of relative velocity of rocket with respect to ejected mass ( v r ) and the velocity of the rocket (v). The relative velocity of rocket with respect to ejected gas is equal to the magnitude of relative velocity of ejected mass with respect to rocket. This later velocity i.e. relative velocity of ejected mass with respect to rocket is actually the velocity that can be calibrated for different time rates of mass ejection at the ground. From consideration of relative motion, we know that v r = v + ⅆ v − u In the figure, negative of the velocity of gas mass is applied to both components of the system to obtain relative velocity of the rocket with respect to ejected gas mass.

Relative velocity of the rocket Relative velocity is obtained by subtracting velocities. Rearranging, we have : ⇒ u = v + ⅆ v − v r Substituting this expression for “u” in the equation of conservation of linear momentum, we have : ⇒ m v = m + ⅆ m v + ⅆ v + − ⅆ m v + ⅆ v − v r ⇒ m v = m v + v ⅆ m + m ⅆ v + ⅆ m ⅆ v − v ⅆ m − ⅆ m ⅆ v + v r ⅆ m ⇒ m ⅆ v + v r ⅆ m = 0 ⇒ m ⅆ v = − v r ⅆ m Dividing both sides by “dt”, we have : m ⅆ v ⅆ t = − v r ⅆ m ⅆ t ⇒ m a = − v r ⅆ m ⅆ t We have discussed the expression on the right hand side of the equation in the module named “Force and invariant mass”. This term was found to be the “cause” element in Newton’s second law of motion known as “thrust”. The thrust, “T”, is a force that results from exchange of mass between rocket and its surrounding. It acts on the rocket in the direction opposite to the direction in which gas escapes from the rocket i.e. in the direction of motion of the rocket. ⇒ T = m a = − v r ⅆ m ⅆ t This equation is the governing expression for the motion of a rocket in the absence of other external forces.

Rocket parameters A rocket is usually designed for different uniform time rates of change in mass ( ⅆ m ⅆ t ). by This rate, in turn, determines (i) fuel consumption rate (ii) velocity with which gas is ejected for given nozzle size (iii) thrust on the rocket and (iv) velocity of the rocket.

Fuel consumption rate We have seen that time rate of change in mass is a negative quantity. On the other hand, we report fuel consumption with a positive number like 1 kg/s or so. Negative number, as we can see, does not make sense in reporting fuel consumption rate. It is, therefore, imperative that we define fuel consumption rate, “r”, as negative of time rate of change in mass i.e. r = − ⅆ m ⅆ t The equation of rocket can be written in terms of fuel consumption rate as : ⇒ T = m a = r v r

Velocity of a rocket We have established relation for thrust in terms of relative velocity of rocket and time rate of change in mass. Yet another interesting aspect to know about rocket would be the velocity of rocket for a given set of design parameters. In order to find the same, we need to have another close look at the governing expression of the rocket, m a = − v r ⅆ m ⅆ t The important thing to emphasize here is that acceleration “a” is the acceleration of the rocket and as such is equal to the time rate of change of velocity of the rocket – not the time rate of change of relative velocity. Rewriting the equation, ⇒ m ⅆ v ⅆ t = − v r ⅆ m ⅆ t Rearranging, ⇒ ⅆ v = − v r ⅆ m m Integrating both sides of the equation, ⇒ ∫ ⅆ v = − ∫ v r ⅆ m m As pointed out, rocket design considers uniform ejection rate and relative velocity. Hence, we can take “ v r ” term out of the integral. Now, integrating both sides between initial and final values, we have : ⇒ v f − v i = − v r ∫ m f m i ⅆ m m ⇒ v f − v i = − v r ln m f m i ⇒ v f − v i = v r ln m i m f Converting natural logarithm to the base “10”, we have : ⇒ v f − v i = 2.303 v r log m i m f If initial velocity is zero and final velocity, v f = v , then velocity of rocket, “v”, is given as : ⇒ v = 2.303 v r log m i m f We should note here that m f < m i . Hence, ratio “ m i m f ” is greater than "1". Its logarithm is positive.

Multistage rocket system The expression of velocity of a rocket as derived is : v = 2.303 v r log m i m f This expression is indicative of one important aspect about the motion of rocket. The motion of the rocket can be increased in two ways (i) by increasing gas ejection velocity, “ v r ” and (ii) by reducing mass of the rocket, “ m f ”. The first factor is the primary cause of motion. We can not impart acceleration and velocity to a standstill rocket by removing a part of it. However, if the rocket has acquired certain velocity, then it is possible to increase velocity of the rocket by merely dislodging unnecessary part (mass), therefore reducing final mass at any time. This is what is achieved in the multi – stage rocket system. Fuel load is divided in different segments. Once the fuel is exhausted, then that segment is dislodged successively.

Other external force(s) We are now equipped to analyze motion of a rocket with external force other than thrust. Analyzing air resistance is complicated as it depends on many factors including velocity of the rocket. This aspect is beyond the scope of this module. The effect of force due to gravity, in the range in which acceleration due to gravity is considered constant, is relatively easy to assess. As pointed out earlier in the module named "Force and invariant mass", F + T = m a Gravity acts downward – opposite to the direction of motion of a vertically moving rocket. Hence, ⇒ m a = T − m g ⇒ a = T m − g We should be careful in using this relation. This relation is valid for a given instant, when mass of the rocket is “m”. Generally, we know the initial mass and as such this relation can be used to determine acceleration of the rocket in the beginning of motion of rocket fired from the ground or from near the ground.