Report On Design Of An Innovative Heavy-Lift Transport Aircraft

Introduction of Design of an innovative heavy-lift transport aircraft

In this assessment, there is comprehensive detail on the design of heavy-lift transport aircraft. This aircraft is able to lift up heavy weights like ship parts, tanks, and other heavy materials. According to the information, the cargo aircraft is able to carry 800 minor segments for the EELT Company. The aircraft will travel from the UK to Chile. In this report, there is complete information about the concept generation of the aircraft. Then after this, there is complete information on the trust to weight analysis of the craft with wing loading analysis.

Then estimate the real mass of the aircraft. Moreover, there is complete information on the choice of the power plant for the manufacturing of the craft; also, the choice of Aerofoil for the aircraft. There is also some information on the geometry of its wings. The next thing is that there is a proper analysis of the weight and balance of the craft. Furthermore, in the next part, there is complete information on the cruise design of the craft. Then in the last part of the paper, there is complete information on the off-design points of the aircraft. It includes two important points that are take-off and landing analysis and also the stability and control analysis of the craft (Gudmundsson, 2013).

Concept generation of Design of an innovative heavy-lift transport aircraft

According to the given information about the manufacturing of the innovative design of the aircraft. This plan is able to handle any kind of weight in an effective manner. Moreover, according to the condition, the aircraft must be a cargo plane. On the other hand, it is able to handle more than 800 minor segments in a proper way for the company.

Trust to weight analysis of Design of an innovative heavy-lift transport aircraft

For that analysis, there is a need to apply some assumptions that will help to analyze the thrust to weight of the aircraft. This will help to identify the real power of the plane on such weight. The thrust will help the plane to take-off and maintain height in the air in a perfect way. For that case, the thrust of this craft will be taken as T, the air resistance is given by B, the lift of the plane is given as L, and according to that the take-off ground roll can be calculated through

S_ROG=1/2 (m_ro.〖(V_LOF- V_w)〗^2)/(T_ro- B_ro-u.(m×g-L_ro )-m_ro×g×sin⁡γ )

In the above equation V_LOF is considered as the lift-off speed. On the other hand, V_w is the speed of the wind, ‘u’ is considered as the rolling friction, and γ this shows the runway slope. But for the design of this aircraft make this equation simpler and calculate the speed with the help of this formula

m_(ro )×g=L=ρ/2 V_LOF^2 ×C_(L,LOF )×S_w

Then according to this formula, the lift-off speed of the aircraft can be found easily through this

V_LOF=√(2g/ρ ×m_ro/S_w ×1/C_(L,LOF) )

From the given information, there are some assumption can be made. The first one is related to the take-off speed is just lower. On the other hand, the next assumption is that there will be no wind on the runway. The last one is that the Trust of the aircraft is extremely greater than the rolling friction. Due to these assumptions, the take-off ground roll will be minimized as

s_ROG=(g×m_MTO^2)/(ρ×C_(L,LOF)×S_w×T)=g/(ρ×C_(L,LOF) )×(m_MTO/S_w )/(T_ro/(m_MTO×g))

Due to this equation, it will be easy to calculate the value of maximum lift and the ratio from thrust to weight of the aircraft will be

(T_RO/m_MTO ×g)/(m_MTO/S_w )=k_RO/(s_ROFL×σ〖×C〗_(L.max,RO) )

Wing loading analysis of Design of an innovative heavy-lift transport aircraft

It can be noted that the aircraft has to handle huge weight; for that case, there is a need to analyze the wing loading factor of the plane for achieving the lifting power. This will give proper information about the aerodynamic load that is acting on the wing of the aircraft. This will help to analyze the main structure of the craft. For that case, LAPAN surveillance method is used for the analysis of the aerodynamics of the craft. This will be done through the help of the Schrenk method. This will give comprehensive information on the span-wise lift distribution. This method will give information about the wingspan of the craft (Sadraey, 2012).

L^'=4L/πb √(1-(2y/b)^2 )

L_planform^'=2L/(1+γ)b (1+2y/b×(λ-1))

L_schrenk^'=(L^'-L_planform^')/2

In the above equation, L is the total lift force of the craft. On the other hand, λ is the taper ratio, b is the wingspan of the aircraft, and the last parameter is the spanwise distance of the plan.

Mass estimation of Design of an innovative heavy-lift transport aircraft

For the deigning of the aircraft, it's ground-based mass is estimated. It can be noted that the mass is one of the important parameters for the climb prediction. According to the given information, the aircraft is able to carry 800 minor segments. There are two different methods for the estimation of the mass of the aircraft. The first one is to dynamically adjust the weight parameter of the craft through the use of the adaptive sensitivity parameter. The next one is related to estimating the mass by analyzing the power of the craft (Torenbeek, 2013).

For that case, the P and Q can be defined easily

P=Power-m ×[d/dt (Energy/m+((W ⃗ . (V_a ) ⃗ ) ̇ ))]

Q=V_a ×〖dV〗_a/dt+(T/(T- ∆T))×(dH_p)/dt+ (d W ⃗)/dt.V ⃗_a

In this equation, the Q is the main sum of the wind effect and energy rate. That can be found on any part on the radar track. Due to this, the total energy will become

(P_(i ) (m_i ))/m_i =0

On the other hand, in the adaptive method, there is a dynamical arrangement in the weight of the aircraft. According to that method, the weight is adjusted automatically as the height of the craft changes

m_i=(〖Power〗_i (m_(i-1)))/Q_i

m_i=m_(i-1) (1-(P_i (m_(i-1) ))/(〖Power〗_i (m_(i-1) ) ))^(-1)

According to some reason, the is another factor of sensitivity is added, and that is β_i then the estimated mass will be

m_i=m_(i-1) (1+ β_i (P_i (m_(i-1) ))/(〖Power〗_i (m_(i-1) ) ))^(-1)

The value of β_i will be about 0.005, and this is its maximum value.

Power plant choice of Design of an innovative heavy-lift transport aircraft

In the modern world, there are different power plants that are used for the manufacturing of the aircraft. For that case, the most important thing is the choice of plant is perfect for air craft manufacturing. It can be seen that there is a need for some type of engines in the powered aircraft that will help them to stay aloft. These powered aircraft engines contain the horse power of about 350 to 400 horsepower. Such engine contains huge power for lifting up. There are about two main models for the power plant. The first one is the gas turbine, and the second one is related to the piston engine. On the other hand, all of these models are subdivided into different categories. It is important before choosing the best power plant for the manufacturing of the aircraft to make sure it must have some specialization in the prime movers in Aviation (Ajoy Kumar Kundu, 2019).

Aerofoil selection of Design of an innovative heavy-lift transport aircraft

           The first thing is that the aircraft must be light for achieving the high speed and carry out the load in an effective way. According to our case, the aircraft must be perfect at high-speed cruise. This aircraft has to maintain high quality C_L and also favourable flight for increasing the safety level of the flight. This will help the aircraft to land safely on the surface of the water. Due to such reasons, there is a need to design perfect supercritical airfoil. That will help to minimize the wing sweep for the requirement of high speed during the landing and turning. This type of design is applied and used in different advance cargo aircraft.

Wing geometry of Design of an innovative heavy-lift transport aircraft

In this part, there is complete information about the main geometry of its wing. This can be calculated through the use of historical data approach. This is because it will give complete information about the different geometries of the wing. In that case, the main thing is to find the value of the initial wing geometry. For this, there are some calculations that will be done on Excel for determining the parameters required to obtain the real geometry.

For that case, the initial value of the wing loading is about 120. Then according to this value, the wing area can be calculated easily through this

S_wing=W_0/(W_0/S_wing )=1351.25 feet square

Also, the wing size can be calculated easily

C_root=2S/b(1+λ)

C_tip=C_(root )×λ

tan⁡█(α/4=tan⁡(α_LE-((1-λ)/AR(1+λ) )) @)

Loading and unloading of Cargo

It can be noted that the cargo aircraft are involved in carrying the load that contains different types of freight. That may include mail, perishable items and other packages. During the loading, the aircraft must able to maintain the load in a perfect way. For that case, the loading base has to give proper information. There are different types of loading in cargo aircraft. The first one is related to the bulk loading and the next one is related to the loading of special items. Also, the next factor is that during unloading, it must have enough space to carry to load in a perfect way.

Weight and balance of the aircraft

The next important point is that the weight and balance control of the aircraft. The main reason is that the aircraft has to carry a huge load during the flight, so it must be balance. Otherwise, it will become difficult for the pilot to handle the plane. The most important point is that excessive weight may involve in reducing the efficiency of the aircraft also affect safety in an emergency condition. Also, the next thing is that the weight of the aircraft is increased than its rotors will produce additional lift and then it will be difficult for the plane to move in the air. This means that the main wings of the 2500 kg then it must support 2500 kgs to level the flight of the craft. Furthermore, the bank angle must be about 60 degrees for smooth turning.

Cruise design of Design of an innovative heavy-lift transport aircraft

This design will be perfect, and this is because it is a cargo plane, and it has to carry a heavy load in a perfect way. For that case, the cruise design must be according to the historical parameters. The design of the craft must be according to the two main parameters. The first parameter is climbed and the next one is the turn. The cruise design must be perfect that is able to handle the climb and turn in a perfect way. By holding the weight in plane, it will be quite easy to climb and turn at a fast speed (Rudinskas, Goraj, & Stankūnas, 2009).

Off design point situations

For that, there is complete information on the two important points that are given below

Take-off and landing analysis

Stability and control analysis

For this analysis, there are two main points that are extremely important for analysis. The first one is related to the center of gravity of the aircraft and the next one is related to the neutral point and most forward point of the plane. Both of these points are extremely important for calculating the stability and control of the design.

The center of gravity can be calculated through the help of this formula

X_cg=(∑▒〖W_i X_cgi 〗)/W_(total )

On the other hand, neutral points can be summarized through this equation

A=n_H (S_H/S_w )(C_LaH/C_LaW )(d_aH/d_a )

Conclusion of Design of an innovative heavy-lift transport aircraft

Summing up all the discussion from above, it is concluded that for designing any ,aircraft it is extremely important to discuss these parameters in a perfect way. According to the information, the cargo aircraft is able to carry 800 minor segments for the EELT Company. The aircraft will travel from the UK to Chile. In this report, there is complete information about the concept generation of the aircraft.

Moreover, according to the condition, the aircraft must be a cargo plane. The thrust will help the plane to take-off and maintain height in the air in a perfect way. This will give proper information about the aerodynamic load that is acting on the wing of the aircraft. There are two different methods for the estimation of the mass of the aircraft. The first one is to dynamically adjust the weight parameter of the craft through the use of the adaptive sensitivity parameter. It can be seen that there is a need for some type of engines in the powered aircraft that will help them to stay aloft. There are about two main models for the power plant.

References of Design of an innovative heavy-lift transport aircraft

Ajoy Kumar Kundu, M. A. (2019). Conceptual Aircraft Design: An Industrial Approach. John Wiley & Sons.

Gudmundsson, S. (2013). General Aviation Aircraft Design: Applied Methods and Procedures. Butterworth-Heinemann.

Sadraey, M. H. (2012). Aircraft Design: A Systems Engineering Approach. John Wiley & Sons.

Torenbeek, E. (2013). Advanced Aircraft Design: Conceptual Design, Analysis and Optimization of Subsonic Civil Airplanes. John Wiley & Sons, .