Báo Cáo Thiết Kế Máy Bay UAV Aero Elearning UAV Group 2

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Report of Aircraft Design – UAV2

Members:

Lê Hoài Tâm – G1002841

Tống Công Danh – G1000403

Nguyễn Viết Khải – G1001509

Văng Hoàng Nam – G1002062

Trần Đức Minh – G1001977

HCM University of Technology Department of Aeronautics

III Customer survey and requirement

IV Advantage of QFD method

V Basic theory about application development of QFD

VI Specify a configuration of UAV:

1 Main wing selection

2 Tail selection

3 Landing gear selection

4 Material of fuselage

5 Engine selection

VII Static stability

1 Static longitudinal stability

2 Static directional stability

VIII Dynamic stability

1 Drag of wing

2 Drag of fuselage

3 Drag of horizontal tail

4 Drag of vertical tail

IX Performance

1 Pilot’s Operating Handbook (POH)

2 Characteristics of aircraft when take-off

a Calculate the running momentum distance sg

b Calculate the distance over obstacles sa

3 Characteristics of aircraft when landing

a Calculate the approach distance sa

b Calculate flare distance sf

c Calculate the running distance on runway sg

4 Cruise Flight

5 Crosswinds

X References

I Quality Function Deployment QFD

1 Introduction

Quality function deployment (QFD) is a “method to transform user demands into design quality, to deploy the functions forming quality, and to deploy methods for achieving the design quality into subsystems and component parts, and ultimately to specific elements of the manufacturing process To test the quality surely the need’s customer and the satisfy is put into the product before it’s created”, as described by Dr Yoji Akao, who originally developed QFD in Japan in the last 1960, when the author combined his work in quality assurance and quality control points with function deployment used in value engineering

QFD is designed to help planners focus on characteristics of a new or existing product or service from the viewpoints of market segments, company, or technology-development needs The technique yields charts and matrices

QFD helps transform customer needs (the voice of the customer [VOC]) into engineering characteristics (and appropriate test methods) for a product

or service, prioritizing each product or service characteristic while simultaneously setting development targets for product or service

QFD consists of two components which are deployed into the design process: quality and function The "quality deployment" component brings the costumer’s voice into the design process The "function deployment" component links different organizational functions and units into to the design-to-manufacturing transition via the formation of design teams

QFD was invented in Japan by Yoji Akao in 1966, but was first implemented in the Mitsubishi’s Kobe shipyard in 1972, possibly out of the teaching of Deming Then later it was adopted and developed by other Japanese companies, notably Toyota and its suppliers [1]

QFD has reached to top when Toyota company apply and develop into a quality table with a “roof” on the top and it’s called “House Of Quality” HOQ has become popular in America since 1998

2 Assumption statement:

- The most important feature of UAV are easy to flight and control

- Purpose of use will be the survey about weather…

- It is considered as non-human aircraft.

II Planning

- This part, we will use the Gantt chart:

Figure III.1: Plan of design process

III Customer survey and requirement

- We will create a form to survey the customer requirements:

Figure IV.1: Survey form

Table IV.1: Summary of responses from customer survey for UAV

Survey base on 100 customers

Figure IV.2: Chart of survey

The question has over 50% will be customer requirement (QFD)

IV Advantage of QFD method

To increase customer satisfaction: Product/Service development base on the need of customers

To decrease the sunk cost during product development process To minimize the fix times because it isn’t determined clearly and fully about the customers requirement To shorten the product design time

To avoid the risk during product development process: Define and analyze the mistakes which can happen to reduce the complaints To increase customer satisfaction

To build a active working environment, enhance collaboration and teamwork between the team members

V Basic theory about application development of QFD

Generally, QFD deploy follow the rule: The customers who propose the a lot of criteria of product quality and the manufacturers must satisfy

to the maximum with these principles Only satisfy the criteria of product quality was proposed by customers then the manufacturer has customers’ trust and this is a prerequisite for the development of production

QFD is a structured technique to solve the combining problem about the product development and product improvement It is often combined a system of matrix with relationship one other, consist of 4 stages:

i The stage of Product Planning, given the basic parameters from the mission, set the performance parameters

ii The stage of Part Deployment

iii The stage of Process Planning

iv The stage of Production Planning

Figure I.3.1: 4 stages of QFD

Figure I.3.2: House Of Quality (HOQ)

(3) Engineering characteristics

This section presents the engineering characteristics or “the voice of the engineering”, it describes the product features that the designer will design This information will be determined by QFD team based

on quantitative characteristics which QFD team see that they have the relation to the requirements of customers

The same way as the first part, here the customer's requirements will

be analyzied and structured, relational diagrams and tree diagrams will be applied to clarify the product characteristics

In the process of the voice of engineer must always ask the question

"how” (way), such as how to catch the customer's requirements, we can control something that customers need

(4) Correlation relationship

This section is the main body of the house of quality and we can spend a lot of time to complete Its purpose is transform customer requirements into engineering characteristics of the product

Its structure is a matrix with 2 standard size include the cell to link the individual requirements of the customer and engineering requirements QFD team's mission must identify the relationship or correlation, the most important After it will be arranged, assess about important level and scoring before completing

To rate about the correlation between the customer and the engineer then we will score and evaluate the correlation between each pair as follows:

Θ = 9 Strong relationship

Ο = 3 Medium relationship

▲ = 1 Weak relationship

(5) Matrix of correlation (Roof of Quality)

A triangular matrix "roof form" will determine the technical requirements for design features, it supports or prevent the other part The same in the relationship matrix, one technical requirement will

be compared with the next technical requirement For each cell, the question posed is "improvement requirements can reduce or increase the value of other requirements or not?" If the answer is devalued,

we will tick in the box with the symbol (eg -) and contra for the symbol (+)

To assess the correlation between the different technical requirements

we will use this system symbols as follows:

┼┼ Strong positive correlation

┼ Positive correlation

▬ Negative correlation

▼ Strong negative correlation

v First we will calculate values of absolute importance by multiplying the values in each cell of the relationship matrix by the the value of importance rating Then, take the sum of these number in each row and each column The total value of this important show absolute value of every engineer in the encounter with the customer requirements

vi Second, we will calculate in the relative importance value by taking the sum of the absolute values important Then, take each of the values of absolute importance value in each cell and then divide by the sum of the absolute importance value, and finally multiplied by 100 Typically the value from 1 to

100

vii Finally,we use QFD method to apply for UAV design process:

We have 3 House Of Quality:

House Of Quality 1

House Of Quality 2

House Of Quality 3

VI Specify a configuration of UAV

1 Main wing selection

a Select the shape

The wing has a wide variety Depending on the purpose that is made of different way For small aircraft, people often make a rectangular wing As for military aircraft, people often make delta wing to reduce drag Hence the choice depends on the kind of purposes but also consider the influence of the geometrical characteristics of the wing

Figure II.1.1: The popular main wing

The wing shape in figure II.1.1 above is a popular for the conventional aircraft, in addition to the other special forms but with a simple UAV design,

we only consider the wing shapes above

Figure II.1.2: Straight and Swept wing selection

From the table of comparison above we can choose for UAV wing configuration is:

i Straight wing

ii Shape of rectangular

iii The wing hasn’t swept angle, not be twisted from inside to outside The geometric characteristics of the wing consists of the following components:

iv Wing swept

v Taper ratio cr/ct.

vi Geometric twist and Dihedral

Considering the effect of swept angle, geometric twist, dihedral angle:

vii For aircraft has speed greater than the speed of sound, we should made oblique wing with the purpose to reduce the drag As for small aircraft has a small speed so it has the small drag, so no need to manufacture the wing has swept angle

viii On the other hand, to have a simple manufacturing process, the wing should not have geometric twist angles, dihedral angles

ix Conclusion: The group’s aircraft will use the wing hasn’t swept angle

and geometric twist

b Position to set up the wing

We have 3 position to set up the wing: on the top of fuselage (high wing), middle of fuselage (mid wing) and bottom of fuselage (low wing)

(1) Set up on the top of fuselage (high wing):

ADVANTAGES:

x Increase the distance from wing to the ground  easy to install the

engine on the wing

xi Easy to install the struts

xii When the aircraft diheral is increased the lateral stability more

Create more lift than the mid wing and low wing

DISADVANTAGES:

xiii Frontal area large

xiv Ground effect low

xv Landing gear will be longer

xvi Create more induce drag

xvii The structure weighs more 20% than the low wing

(2) Set up on the bottom of fuselage (low wing):

ADVANTAGES:

xviii Landing gear short

xix Take off performance better than high wing

xx Lighter than the high wing structure

xxi Frontal area small

xxii Downwash low impact to the tail

DISADVANTAGES:

xxiii Create less lift than high wing

xxiv Stall speed high

xxv Lower landing performance

xxvi Stable horizontal lower than high wing

(3) Set up on the middle of fuselage (mid wing):

ADVANTAGES:

xxvii Combination of high wing and low wing

DISADVANTAGES:

xxviii The weight of structure is stronger

xxix High cost

From the comparison table above you can see the high wing has higher strengths than the other two positions, so, we choose this (high wing)

ii T-tail configuration help the flow through the tail more stability ,reduce drag and increase climb performance of the aircraft Therefore, the T-tail configuration is especially popular on gliders iii The control surface of the horizontal tailplane is mounted separate from the hindquarters, and this space will be used to install the engine of the aircraft

vi T-tail configuration has a problems maintenance

vii Due to lack of air flow through the elevator from the front engine, the control and operate on low-speed becomes more difficult

iii Avoid placing the tail behind the engine exhaust stream, not interrupting reduce runoff and increase the thrust stability

DISADVANTAGES:

iv Size larger than normal type

v The combination of pitch and yaw control is very difficult and requires a control system more complex

vi Create pressure on the fuselage than when pitching and yawing

c Twin tail

ADVANTAGES:

i No need to have large vertical tailplane

ii Improve control, aircraft control at low airspeed, and the taxi run iii Aircraft using double tail can also simplify the requirements for the hangar

iv Reduce the weight of the aircraft

v This is one form of redundancy, if one side is damaged, the other

categories can remain fully functional

Also from a table comparison between the tail rotor configuration, we can see that the tail shape convnetional dominant than the remaining tail

configuration when applied to UAVs are designing Therefore we choose

the shape of “conventional tail configuration” in our design (UAV)

3 Landing Gear selection

a Conventional Landing Gear

- ADVANTAGES:

- Due to its smaller size the tailwheel has less parasite drag than

a nosewheel

- Without cumulative airframe damage occurring

- Save a buy and maintenance cost

b Trycycle gear

ADVANTAGES:

- Difficulty get "nose-over" when pilots slam on the brakes

- Landing easier, safer and less affected by wind blowing the horizontal

- Easy to control DISADVANTAGES:

- Not good when there is activity on the surface of many stones

- The structure must certainly more => more complex, larger weight

4 Material of fuselage

a Composites

ADVANTAGES:

- Lighter than metal

- Module (stiffness density ratio) from 3.5 to 5 times higher than steel or aluminum

- Life greater than metal

- High against corrosion

- Tensile strength higher from 4 to 6 times than steel or aluminum

- Greater design flexibility

- Contributing to remove the joints and fasteners

- The variety of materials, processes and techniques

- General lack of knowledge between expertise and repair

- Products often are a toxic

- Lack of standard method for building and repairing

b Metal

Material usually is a metal alloy of other metal and it usually is an alloys of aluminum, steel and titanium (For example, Sr-71 the main component is titanium, while the MiG-27 and MiG-31 made of steel and titanium)

ADVANTAGES:

- High stability and easy to control

- Create more strength and rigidity

- It can relative withstand damage and still strong enough to maintain the

relative structure

- A material commonly Hence, the way to made it is simple

- Price and cost is cheaper than other materials

- Recyclable

DISADVANTAGES:

- Structural vibration is large

- The large weight and lead to have a high fuel consumption

- Restrictions on performance

- Noise level is large

Table shows the comparison of materials to produce UAV and the group's UAV will be designed with hybrid material

• Payload is low