CN113761667B - Empty weight estimation method for supersonic passenger plane - Google Patents

Empty weight estimation method for supersonic passenger plane Download PDF

Info

Publication number
CN113761667B
CN113761667B CN202111125590.7A CN202111125590A CN113761667B CN 113761667 B CN113761667 B CN 113761667B CN 202111125590 A CN202111125590 A CN 202111125590A CN 113761667 B CN113761667 B CN 113761667B
Authority
CN
China
Prior art keywords
weight
formula
follows
engine
supersonic
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
CN202111125590.7A
Other languages
Chinese (zh)
Other versions
CN113761667A (en
Inventor
钱丰学
刘志勇
杨洋
张兆
陶洋
郭鹏
尹刚
周波
姚丹
高荣钊
廖晓林
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
High Speed Aerodynamics Research Institute of China Aerodynamics Research and Development Center
Original Assignee
High Speed Aerodynamics Research Institute of China Aerodynamics Research and Development Center
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by High Speed Aerodynamics Research Institute of China Aerodynamics Research and Development Center filed Critical High Speed Aerodynamics Research Institute of China Aerodynamics Research and Development Center
Priority to CN202111125590.7A priority Critical patent/CN113761667B/en
Publication of CN113761667A publication Critical patent/CN113761667A/en
Application granted granted Critical
Publication of CN113761667B publication Critical patent/CN113761667B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/10—Geometric CAD
    • G06F30/15—Vehicle, aircraft or watercraft design
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/10—Geometric CAD
    • G06F30/17—Mechanical parametric or variational design
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2113/00—Details relating to the application field
    • G06F2113/28—Fuselage, exterior or interior
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
    • G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces

Landscapes

  • Physics & Mathematics (AREA)
  • Engineering & Computer Science (AREA)
  • Geometry (AREA)
  • Theoretical Computer Science (AREA)
  • General Physics & Mathematics (AREA)
  • General Engineering & Computer Science (AREA)
  • Evolutionary Computation (AREA)
  • Computer Hardware Design (AREA)
  • Pure & Applied Mathematics (AREA)
  • Mathematical Optimization (AREA)
  • Mathematical Analysis (AREA)
  • Computational Mathematics (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Automation & Control Theory (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)

Abstract

The invention discloses an empty weight estimation method for a supersonic passenger plane. The empty weight estimation method selects a statistical model of weight according to the similarity of key characteristics of components or devices, and calculates the reference weight of wings, horizontal tails, vertical tails, engines, engine installation parts, engine casings, air inlet channels, tail pipes, engine cooling systems, fuel oil cooling systems, engine control systems and engine starting systems of the supersonic airliners by adopting a Raymer fighter weight estimation system formula; calculating the reference weight of a body, a landing gear, a flight control system, an APU (auxiliary Power Unit) installation device, a measuring device, a hydraulic system, an electric system, an avionic system, a decoration system, an air conditioning system, an anti-icing and deicing system and an operating device of the supersonic passenger plane by adopting a Raymer transport plane weight estimation system formula; and introducing a technical progress weight factor to obtain the estimated weight of the component or the device and each subsystem. The method is efficient and rapid, and can accurately estimate the weight of the body structure and the weight of the propulsion system of the supersonic passenger plane.

Description

Empty weight estimation method for supersonic passenger plane
Technical Field
The invention belongs to the field of weight balance and control of supersonic aircrafts, and particularly relates to an empty weight estimation method for a supersonic passenger plane.
Background
The weight of the airplane is the basic input required by cost calculation, performance calculation, sonic boom characteristic evaluation, task profile design, buffeting response analysis, flutter characteristic analysis, strength and rigidity analysis, fatigue life analysis, maneuverability, safety analysis and the like, is an important physical quantity required to be predicted and controlled in each link in the airplane research and development cycle, and is an important basis for airplane design scheme evaluation. The accuracy of the aircraft weight calculation technology determines the conformity degree of the design scheme to a great extent, and has an important influence on the economy, safety and core competitiveness of the aircraft, so the aircraft weight calculation and control technology also becomes one of the core technologies of aircraft design units. Since the 30 s of the last century, the weight balance and control of airplanes gradually become a great concern for airplane design, and various airplane companies and related research units develop weight methods based on empirical models, semi-empirical methods and theoretical analysis, so that relatively perfect weight technical systems of fighters, transporters and general airplanes are formed. The weight of the fighter plane is mainly established for an aerial combat plane and a ground attack plane, and is mainly applied to weight calculation of the fighter plane with the small aspect ratio wings. The weight of the transport plane is developed mainly for passenger planes and cargo planes, and is mainly used for calculating the weight of the transport plane with large aspect ratio and large volume body layout. The weight of the general aircraft is mainly developed for commercial aircraft and medium and small-sized transport aircraft, and is mainly applied to light general aviation aircraft.
Unlike fighters, traditional transporters, and general-purpose aircraft, supersonic airliners have the following characteristics:
(1) the main lifting surface of the supersonic airliner is a wing with a small aspect ratio and has the characteristic of the lifting surface of a typical supersonic fighter;
(2) the payload container of a supersonic passenger aircraft is a slender large-capacity fuselage with typical transport features;
(3) the stabilizing surface of the supersonic airliner is a duck wing with a small aspect ratio, a vertical wing with a small aspect ratio or a V-shaped empennage, and has the stabilizing surface characteristics of the supersonic fighter;
(4) the propulsion system of the supersonic airliner needs to meet the requirements of low-speed takeoff and supersonic cruise, and has the characteristics of the propulsion system of the supersonic fighter;
(5) the fixing device of supersonic passenger plane is to meet the requirement of load transportation and has the features of conventional fixing device of transport plane.
These features make supersonic airliners different from conventional fighters and conventional transport planes with high aspect ratio wing layouts, but integrate the typical structural features of both fighters and transport planes. Any one of the existing weight technology systems of fighters, transport planes and general airplanes cannot well embody the key characteristics of supersonic airliners. Therefore, the corresponding weight technology system is difficult to adapt to the weight requirement of the supersonic passenger plane.
In the conceptual design stage of the airplane, a large number of design schemes need to be compared and analyzed, and excellent schemes need to be screened for further research and subsequent design work. At this stage, the structural design of the airframe and each system is still insufficient, and it is difficult to perform fine calculation of the aircraft weight by using the finite element method and to bear the burden of high-intensity calculation, so that the empirical estimation method based on historical data is widely used. Raymer, Roskam, Torenbeek, Jenkinson, Howe, c.m. segel, etc. summarize the empirical methods of estimating the quality of components or devices of three types of aircraft, fighters, transporters and business machines, in the corresponding aircraft design course, by first decomposing the components or devices of the aircraft by function, such as Raymer, Roskam, Torenbeek, which divides the aircraft into wing, horizontal/duck wing, vertical tail, fuselage, etc., and engine, engine mount, engine casing, air intake duct, tail duct, engine cooling system, fuel cooling system, engine control system, engine starting system, main landing gear, nose landing gear, flight control system, APU mount, measuring device, hydraulic system, electrical system, avionic system, decoration system, air conditioning system, ice control system, and steering device, etc. And then fitting historical data of the weights of all parts or devices of the three types of airplanes to obtain a corresponding weight decomposition empirical formula. However, since supersonic aircraft history data is not much, there is no statistical formula system for estimating the components, devices, subsystem weight and empty weight. Therefore, there is a need to develop a weight fast calculation method that adapts to the characteristics of a supersonic passenger aircraft for use in the concept design and analysis of supersonic passenger aircraft.
Currently, there is a need to develop a method for estimating the empty weight for a supersonic passenger aircraft.
Disclosure of Invention
The invention aims to provide a method for estimating the empty weight of a supersonic passenger plane.
The invention relates to a method for estimating the empty weight of a supersonic passenger plane, which comprises the following steps:
s1, disassembling the supersonic passenger plane into three subsystems, namely a body structure, a propulsion system and a fixing device, according to the overall layout of the supersonic passenger plane and functions, decomposing each subsystem into a plurality of components or devices, and determining the geometric dimension, the function or the construction parameters of each component or device;
the machine body structure subsystem is divided into a machine body, wings, vertical tails, horizontal tails or canard wings and an undercarriage; the propulsion system subsystem is decomposed into an engine, an engine mounting part, an engine shell, an air inlet channel, a tail pipe, an engine cooling system, a fuel oil cooling system, an engine control system and an engine starting system; the fixing device subsystem is divided into a flight control system, an APU installation device, a measuring device, a hydraulic system, an electric system, an avionic system, a decoration system, an air conditioning system, an anti-icing and deicing system and a control device;
s2, selecting a combination from statistical models of the weights of components or devices of the existing fighter plane and the existing transport plane according to the geometric characteristics, the structural characteristics and the load characteristics of the components or the devicesCalculating reference weight of each part or device by using appropriate statistical model
Figure 100002_DEST_PATH_IMAGE002
Wherein
Figure 100002_DEST_PATH_IMAGE004
identification of each component or device;
Figure 100002_DEST_PATH_IMAGE006
s3, calculating the weight of each part or device of the supersonic passenger plane:
Figure 100002_DEST_PATH_IMAGE008
，
Figure 100002_DEST_PATH_IMAGE010
a technological progress weight factor of the era was established for the weight of each component or device corresponding to the database of statistical models,
Figure 158840DEST_PATH_IMAGE004
identification of each component or device.
S4, according to the division of the subsystems, summing the weights of the components or devices belonging to the subsystems, and calculating the weights of the three subsystems respectively;
further, in step S2, the weight models of the wings, the vertical tails, and the horizontal tails of the fighter are selected for estimation based on the reference weights of the wings, the vertical tails, and the horizontal tails of the supersonic airliner:
a. calculating a reference weight for a supersonic passenger aircraft wing
Figure 100002_DEST_PATH_IMAGE012
The formula is as follows:
Figure 100002_DEST_PATH_IMAGE014
；
whereinLayout factor
Figure 100002_DEST_PATH_IMAGE016
，
Figure 100002_DEST_PATH_IMAGE018
，
Figure 100002_DEST_PATH_IMAGE020
In order to design the weight of the vehicle,
Figure 100002_DEST_PATH_IMAGE022
in order to limit the overload, the overload is avoided,
Figure 100002_DEST_PATH_IMAGE024
the area of the wing is the area of the wing,
Figure 100002_DEST_PATH_IMAGE026
is the aspect ratio of the wing,
Figure 100002_DEST_PATH_IMAGE028
the relative thickness of the wing root is the relative thickness,
Figure 100002_DEST_PATH_IMAGE030
the ratio of the tip to the root of the wing,
Figure 100002_DEST_PATH_IMAGE032
is the sweep angle of 25 percent chord line of the wing,
Figure 100002_DEST_PATH_IMAGE034
is the control surface area on the wing;
b. calculating reference weight of horizontal tail of supersonic passenger plane
Figure 100002_DEST_PATH_IMAGE036
The formula is as follows:
Figure 100002_DEST_PATH_IMAGE038
；
wherein,
Figure 100002_DEST_PATH_IMAGE040
the width of the machine body at the horizontal tail part,
Figure 100002_DEST_PATH_IMAGE042
the tail of the tail is flat and long,
Figure 100002_DEST_PATH_IMAGE044
the area of the horizontal tail;
c. calculating a reference weight for a vertical fin of a supersonic passenger aircraft
Figure 100002_DEST_PATH_IMAGE046
The formula is as follows:
Figure 100002_DEST_PATH_IMAGE048
；
wherein,
Figure 100002_DEST_PATH_IMAGE050
the height of the horizontal tail is the height of the horizontal tail,
Figure 100002_DEST_PATH_IMAGE052
the height of the vertical tail is the height of the vertical tail,
Figure 100002_DEST_PATH_IMAGE054
the area of the vertical tail is the area of the vertical tail,
Figure 100002_DEST_PATH_IMAGE056
in order to design the mach number of the optical fiber,
Figure 100002_DEST_PATH_IMAGE058
is the length of the vertical tail arm, namely the distance from 0.25 average aerodynamic chord of the wing to 0.25 average aerodynamic chord of the vertical tail,
Figure 100002_DEST_PATH_IMAGE060
the area of the rudder is the area of the rudder,
Figure 100002_DEST_PATH_IMAGE062
is the aspect ratio of the vertical tail,
Figure 100002_DEST_PATH_IMAGE064
the ratio of the tip to the root of the vertical fin,
Figure 100002_DEST_PATH_IMAGE066
is vertical tail 25% chord line sweepback angle;
further, the reference weights of the fuselage and the landing gear of the supersonic aircraft in step S2 are estimated by selecting a statistical model of the weights of the fuselage and the landing gear of the transport aircraft, respectively:
d. calculating reference weight of supersonic passenger plane body
Figure 100002_DEST_PATH_IMAGE068
The formula is as follows:
Figure 100002_DEST_PATH_IMAGE070
；
wherein,
Figure 100002_DEST_PATH_IMAGE072
，
Figure 100002_DEST_PATH_IMAGE074
，
Figure 100002_DEST_PATH_IMAGE076
the length of the machine body is taken as the length,
Figure 100002_DEST_PATH_IMAGE078
the area of the machine body to be soaked is,
Figure 100002_DEST_PATH_IMAGE080
，
Figure 100002_DEST_PATH_IMAGE082
the depth of the structure of the machine body is,
Figure 100002_DEST_PATH_IMAGE084
extending the wing;
e. calculating a reference weight of a landing gear of a supersonic aircraft, including a reference weight of a nose landing gear and a reference weight of a main landing gear:
e1. reference weight of nose landing gear
Figure 100002_DEST_PATH_IMAGE086
The formula is as follows:
Figure 100002_DEST_PATH_IMAGE088
；
wherein
Figure 100002_DEST_PATH_IMAGE090
，
Figure 100002_DEST_PATH_IMAGE092
In order to make the landing weight heavy,
Figure 100002_DEST_PATH_IMAGE094
in order to get the overload factor to land,
Figure 100002_DEST_PATH_IMAGE096
in order to be the length of the nose landing gear,
Figure 100002_DEST_PATH_IMAGE098
the number of nose landing gear wheels;
e2. reference weight of main landing gear
Figure 100002_DEST_PATH_IMAGE100
The formula is as follows:
Figure 100002_DEST_PATH_IMAGE102
；
wherein,
Figure 100002_DEST_PATH_IMAGE104
，
Figure 100002_DEST_PATH_IMAGE106
the length of the main landing gear is taken as the length,
Figure 100002_DEST_PATH_IMAGE108
the number of the main lifting and falling frame wheels,
Figure 100002_DEST_PATH_IMAGE110
the number of shock absorbing rods for the main landing gear,
Figure 100002_DEST_PATH_IMAGE112
is the stall speed;
further, the reference weight of the propulsion system of the supersonic passenger aircraft in step S2 is selected from a weight model of the fighter aircraft for estimation, and specifically includes reference weights of an engine, an engine mounting part, an engine casing, an air inlet, a tail nozzle, an engine cooling system, a fuel cooling system, an engine control system, an engine starting system and a fuel tank;
f1. reference weight of engine
Figure 100002_DEST_PATH_IMAGE114
The formula is as follows:
Figure 100002_DEST_PATH_IMAGE116
；
wherein
Figure 100002_DEST_PATH_IMAGE118
The weight of a single engine is obtained by fitting a model through given or historical data of an engine company;
Figure 100002_DEST_PATH_IMAGE120
the number of the engines is;
f2. reference weight of engine mount
Figure 100002_DEST_PATH_IMAGE122
The formula is as follows:
Figure 100002_DEST_PATH_IMAGE124
；
wherein,
Figure 100002_DEST_PATH_IMAGE126
is the total thrust of the engine;
f3. the formula of the reference weight of the engine shell is as follows:
Figure 100002_DEST_PATH_IMAGE128
；
f4. reference weight of air intake duct
Figure 100002_DEST_PATH_IMAGE130
The formula is as follows:
Figure 100002_DEST_PATH_IMAGE132
；
wherein,
Figure 100002_DEST_PATH_IMAGE134
Figure 100002_DEST_PATH_IMAGE136
，
Figure 100002_DEST_PATH_IMAGE138
as the length of the air inlet duct,
Figure 100002_DEST_PATH_IMAGE140
the length of the double-fork air inlet combined pipe is,
Figure 100002_DEST_PATH_IMAGE142
is the engine diameter;
f5. reference weight of jet nozzle
Figure 100002_DEST_PATH_IMAGE144
The formula is as follows:
Figure 100002_DEST_PATH_IMAGE146
；
wherein,
Figure 100002_DEST_PATH_IMAGE148
is the length of the tail nozzle;
f6. reference weight of engine cooling system
Figure 100002_DEST_PATH_IMAGE150
The formula is as follows:
Figure 100002_DEST_PATH_IMAGE152
；
wherein,
Figure 100002_DEST_PATH_IMAGE154
is the engine case length;
f7. reference weight of fuel cooling system
Figure 100002_DEST_PATH_IMAGE156
The formula is as follows:
Figure 100002_DEST_PATH_IMAGE158
；
f8. reference weight of engine control system
Figure 100002_DEST_PATH_IMAGE160
The formula is as follows:
Figure 100002_DEST_PATH_IMAGE162
；
wherein,
Figure 100002_DEST_PATH_IMAGE164
the length from the front end face of the engine to the cab is equal to that of a single engineMultiplying the length from the front end surface to the cockpit by the number of engines;
f9. reference weight of engine starting system
Figure 100002_DEST_PATH_IMAGE166
The formula is as follows:
Figure 100002_DEST_PATH_IMAGE168
；
wherein,
Figure 100002_DEST_PATH_IMAGE170
the thrust of a single engine is adopted;
f10. reference weight of fuel tank
Figure 100002_DEST_PATH_IMAGE172
The formula is as follows:
Figure 100002_DEST_PATH_IMAGE174
；
Figure 100002_DEST_PATH_IMAGE176
，
Figure 100002_DEST_PATH_IMAGE178
is the total volume of the fuel,
Figure 100002_DEST_PATH_IMAGE180
the total volume of the oil tank is integrated,
Figure 100002_DEST_PATH_IMAGE182
is the total volume of the self-sealing oil tank,
Figure 100002_DEST_PATH_IMAGE184
the number of the oil tanks is the same as the number of the oil tanks,
Figure 100002_DEST_PATH_IMAGE186
fuel consumption rate at maximum thrust;
further, the reference weight of the fixing device of the supersonic passenger plane in the step S2 is selected from a weight model of the transport plane for estimation, and specifically includes reference weights of an aircraft control system, an APU installation, a measuring device, a hydraulic system, an electric system, an avionic system, a decoration system, an air conditioning system, an anti-icing system and a control device;
g1. reference weight for flight control system
Figure 100002_DEST_PATH_IMAGE188
The formula is as follows:
Figure 100002_DEST_PATH_IMAGE190
；
wherein,
Figure 100002_DEST_PATH_IMAGE192
in order to control the number of flight control system functions,
Figure 100002_DEST_PATH_IMAGE194
for the number of functions of the mechanical system,
Figure 100002_DEST_PATH_IMAGE196
in order to control the total area of the surface,
Figure 100002_DEST_PATH_IMAGE198
is the moment of inertia of the pitch axis of the aircraft,
Figure 100002_DEST_PATH_IMAGE200
in order to control the number of flight control systems,
Figure 100002_DEST_PATH_IMAGE202
the number of the crew members;
g2. reference weight for APU installation
Figure 100002_DEST_PATH_IMAGE204
The formula is as follows:
Figure 100002_DEST_PATH_IMAGE206
；
wherein,
Figure 100002_DEST_PATH_IMAGE208
is the auxiliary power supply unit weight;
g3. reference weight of measuring device
Figure 100002_DEST_PATH_IMAGE210
The formula is as follows:
Figure 100002_DEST_PATH_IMAGE212
；
wherein,
Figure 654411DEST_PATH_IMAGE084
extending the wing;
g4. reference weight of hydraulic system
Figure 100002_DEST_PATH_IMAGE214
The formula is as follows:
Figure 100002_DEST_PATH_IMAGE216
；
g5. reference weight of electric power system
Figure 100002_DEST_PATH_IMAGE218
The formula is as follows:
Figure 100002_DEST_PATH_IMAGE220
；
wherein,
Figure 100002_DEST_PATH_IMAGE222
in order to provide the rated power for the power system,
Figure 100002_DEST_PATH_IMAGE224
the total length of the cable is taken as the length,
Figure 100002_DEST_PATH_IMAGE226
the number of the generators is;
g6. reference weight of avionics system
Figure 100002_DEST_PATH_IMAGE228
The formula is as follows:
Figure 100002_DEST_PATH_IMAGE230
；
wherein,
Figure 100002_DEST_PATH_IMAGE232
avionics system weight;
g7. reference weight of decorating system
Figure 100002_DEST_PATH_IMAGE234
The formula is as follows:
Figure 100002_DEST_PATH_IMAGE236
；
wherein
Figure 100002_DEST_PATH_IMAGE238
Is the maximum payload weight;
g8. reference weight of air conditioning system
Figure 100002_DEST_PATH_IMAGE240
The formula is as follows:
Figure 100002_DEST_PATH_IMAGE242
；
wherein,
Figure 100002_DEST_PATH_IMAGE244
in order to increase the total volume of the pressure chamber,
Figure 100002_DEST_PATH_IMAGE246
designing the total number of people on the state machine, including the number of crew members and the number of passengers;
g9. reference weight of anti-icing system
Figure 100002_DEST_PATH_IMAGE248
The formula is as follows:
Figure 100002_DEST_PATH_IMAGE250
；
g10. reference weight of the operating device
Figure 100002_DEST_PATH_IMAGE252
The formula is as follows:
Figure 100002_DEST_PATH_IMAGE254
；
further, the weighting factor of the technical progress in step S3 is described
Figure 932683DEST_PATH_IMAGE010
Typical values of (a) are: the wing technical progress weight factor is 0.7, the vertical tail technical progress weight factor is 0.8, the fuselage technical progress weight factor is 0.82, the landing gear technical progress weight factor is 0.85, and the rest of the components or devices have technical progress weight factors of 1.0.
Further, the reference weight of the fuselage in step S2 is as follows:
Figure DEST_PATH_IMAGE255
with respect to a conventional passenger aircraft layout,
Figure 100002_DEST_PATH_IMAGE257
(ii) a For the modern supersonic low-speed passenger blasting machine layout,
Figure 100002_DEST_PATH_IMAGE259
，
Figure 100002_DEST_PATH_IMAGE261
。
further, the single engine weight of f1 in the step S2
Figure 100002_DEST_PATH_IMAGE263
The formula of the historical data fitting model is as follows:
Figure 100002_DEST_PATH_IMAGE265
。
further, the weight calculation formulas of the three subsystems in step S4 are as follows:
h1. weight of the body structure
Figure 100002_DEST_PATH_IMAGE267
The formula is as follows:
Figure 100002_DEST_PATH_IMAGE269
；
h2. weight of propulsion system
Figure 100002_DEST_PATH_IMAGE271
The formula is as follows:
Figure 100002_DEST_PATH_IMAGE273
；
if it is not
Figure 100002_DEST_PATH_IMAGE275
Is the weight of the engine including the accessories, the weight of the propulsion system is reduced to:
Figure 100002_DEST_PATH_IMAGE277
。
h3. weight of the fixing device
Figure 100002_DEST_PATH_IMAGE279
The formula is as follows:
Figure 100002_DEST_PATH_IMAGE281
；
empty weight of supersonic passenger plane
Figure 100002_DEST_PATH_IMAGE283
Is of the formula
Figure 100002_DEST_PATH_IMAGE285
。
Further, when the supersonic passenger aircraft is provided with a canard, the weight of the horizontal tail of the supersonic passenger aircraft in step S2 is adopted
Figure 100002_DEST_PATH_IMAGE287
The formula performs the canard weight calculation and adds the canard weight to the body structure weight calculation formula of h1 in step S4.
The method for estimating the empty weight of the supersonic passenger plane is based on the decomposition of an airplane system, a component or a device, selects a weight statistical model of each component or device from weight estimation statistical models of a fighter and a transport plane of Raymer according to a characteristic similarity principle to calculate the reference weight, and multiplies a correction factor reflecting the technical progress to obtain the weight of each component or device.
The wings, the vertical tails and the horizontal tails of the supersonic airliner all belong to thin lifting surfaces with small aspect ratio, the geometrical shape (including sweepback angle, aspect ratio, relative thickness and tip-root ratio), the structural form (including a beam-rib wing box and front and rear edge lift-increasing devices) and the aerodynamic load distribution characteristics born in the whole flight process are all similar to those of the supersonic fighter, and are far away from the traditional airliner, and the reference weights of the wings, the vertical tails and the horizontal tails of the supersonic airliner are respectively estimated by selecting a statistical model of the weights of the wings, the vertical tails and the horizontal tails of the Raymer fighter. Meanwhile, the design points of the propulsion system of the supersonic passenger plane comprise a supersonic cruise point, the geometric characteristics, the structural form, the load characteristics and the working mode of an air inlet channel, a spray pipe, a turbofan engine and a duct of the supersonic passenger plane, and the characteristics of other parts or devices of the propulsion system are similar to those of the supersonic fighter, and a statistical model of the weight of the propulsion system of the Raymer fighter is selected by referring to weight estimation. Therefore, in order to adapt to the supersonic layout characteristics of wings, horizontal tails, vertical tails and propulsion systems of supersonic airliners, the wings, horizontal tails, vertical tails, engines, engine mounting parts, engine casings, air inlet channels, tail pipes, engine cooling systems, fuel cooling systems, engine control systems and engine starting systems in steps a, b, c and f, weight calculation adopts a fighter component or device weight model given by Raymer. Of course, the formula for the components or devices in steps a, b, c and f can be any other weight system for the corresponding components of the fighter class and the propulsion system, such as the weight system of the fighters of Roskam, Howe, C.M. and Legel.
The airframe and the undercarriage of the supersonic passenger plane are subjected to small aerodynamic loads, the weight of the airframe and the undercarriage of the supersonic passenger plane is mainly determined by the similar geometrical characteristics and structural form of the traditional passenger plane, and the reference weight of the airframe and the undercarriage of the supersonic passenger plane is estimated by respectively selecting a statistical model of the weight of the airframe and the undercarriage of a Raymer transport plane. The function and characteristics of the fixture are the same as in a conventional passenger aircraft, and a statistical model of the weight of the transport aircraft is selected for estimation on the reference weight of the components or devices in the fixture. Therefore, in order to adapt to the loading, use and characteristics of the running parts or devices of the supersonic airliner, the weight calculation of the fuselage, main landing gear, nose landing gear, flight control system, APU installation, measuring device, hydraulic system, electric system, avionic system, decoration system, air conditioning system, ice control system and control device in steps d, e and g uses the model of the weight of the parts or devices of the transport aircraft given by Raymer. Of course, the formula for the components or devices in steps d, e and g can also be the formula for the corresponding components or devices of the class of conveyors in any other weight system, such as the weight system of conveyors in Roskam, Eger, Jenkinson, Howe, c.m. hagell.
Statistical modeling of the weight of the components or devices of the method for estimating the empty weight of a supersonic passenger aircraft according to the inventionTypes were based on fighter and transporter weight databases before the 1990's. The technical progress weighting factors of the current components or devices are respectively determined according to the development progress situation of materials, design methods and manufacturing processes and by considering related technical reports and practices of NASA. In particular, modern supersonic low-sonic-velocity passenger aircraft are divided into three sections of fuselage forebody, passenger cabin and afterbody, in order to reduce sonic boom, the slenderness ratio of the fuselage is increased, the cross-section distribution of forebody and afterbody is smoother, and the relative length of the cabin section of the fuselage is (
Figure 888745DEST_PATH_IMAGE261
) With the reduction, the weight estimation of the machine body can be carried out
Figure 703117DEST_PATH_IMAGE068
Is multiplied by a factor
Figure 525579DEST_PATH_IMAGE259
To correct for the effects of changes in the forebody, aft body shape and volume.
In summary, the method for estimating the empty weight of a supersonic passenger aircraft according to the present invention is divided into the following steps: calculating the reference weight of wings, horizontal tails, vertical tails, engines, engine mounting parts, engine shells, air inlet channels, tail pipes, engine cooling systems, fuel oil cooling systems, engine control systems and engine starting systems of the supersonic airliners by adopting a Raymer fighter weight estimation formula; secondly, calculating the reference weight of the body, the undercarriage, the flight control system, the APU installation, the measuring device, the hydraulic system, the electric system, the avionic system, the decoration system, the air-conditioning system, the ice prevention and deicing system and the operating device of the supersonic passenger plane by adopting a Raymer's formula of a weight estimation system of the transport plane; and thirdly, introducing a technical progress weight factor, multiplying the weight of each part or device by the corresponding technical progress weight factor, and then respectively obtaining the weight of each subsystem and the empty weight of the whole machine.
The method for estimating the empty weight of the supersonic passenger plane is based on an airplane weight decomposition statistical model, comprehensively utilizes weight formulas of parts or devices of fighters and transport planes, and combines the parts or devices of the supersonic passenger plane and a complete method for quickly estimating the weight of a subsystem, overcomes the problem that the existing weight estimation formula system of the fighters and the transport planes cannot adapt to the parts or devices of the supersonic passenger plane, has the characteristics of high efficiency and high speed, and can accurately estimate the body structure weight and the propulsion system weight of the supersonic passenger plane.
Drawings
FIG. 1 is a flow chart of calculating the weight and empty weight of each subsystem of a supersonic aircraft in the method for estimating empty weight of a supersonic aircraft according to the present invention;
FIG. 2a is a schematic view (top view) of the locked Engineering & Sciences Company M1.6 SST layout and its propulsion system of example 1;
FIG. 2b is a schematic view (side view) of the locked Engineering & Sciences Company M1.6 SST layout and its propulsion system of example 1;
FIG. 2c is a schematic view (front view) of the locked Engineering & Sciences Company M1.6 SST layout and its propulsion system of embodiment 1;
FIG. 2d is a schematic view of a locked Engineering & Sciences Company M1.6 SST layout and its propulsion system of embodiment 1 (engine main view);
FIG. 3 is a comparison of the parts, equipment, subsystem weights and empty weight estimation errors for a supersonic aircraft layout of the locked Engineering & Sciences Company M1.6 SST of example 1.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and examples.
As shown in fig. 1, the method for estimating empty weight for supersonic passenger aircraft of the present invention comprises the following steps:
s1, disassembling the supersonic passenger plane into three subsystems, namely a body structure, a propulsion system and a fixing device, according to the overall layout of the supersonic passenger plane and functions, decomposing each subsystem into a plurality of components or devices, and determining the geometric dimension, the function or the construction parameters of each component or device;
the machine body structure subsystem is divided into a machine body, wings, vertical tails, horizontal tails or canard wings and an undercarriage; the propulsion system subsystem is decomposed into an engine, an engine mounting part, an engine shell, an air inlet channel, a tail pipe, an engine cooling system, a fuel oil cooling system, an engine control system and an engine starting system; the fixing device subsystem is divided into a flight control system, an APU installation device, a measuring device, a hydraulic system, an electric system, an avionic system, a decoration system, an air conditioning system, an anti-icing and deicing system and a control device;
s2, according to the geometric characteristics, the structural characteristics and the load characteristics of each part or device, selecting a proper statistical model from statistical models of the weights of the parts or devices of the existing fighter plane and the existing transport plane, and calculating to obtain the reference weight of each part or device
Figure 730296DEST_PATH_IMAGE002
Wherein
Figure 929196DEST_PATH_IMAGE004
identification of each component or device;
Figure DEST_PATH_IMAGE288
s3, calculating the weight of each part or device of the supersonic passenger plane:
Figure 270178DEST_PATH_IMAGE008
，
Figure 263542DEST_PATH_IMAGE010
a technological progress weight factor of the era was established for the weight of each component or device corresponding to the database of statistical models,
Figure 221134DEST_PATH_IMAGE004
identification of each component or device.
S4, according to the division of the subsystems, summing the weights of the components or devices belonging to the subsystems, and calculating the weights of the three subsystems respectively;
further, in step S2, the weight models of the wings, the vertical tails, and the horizontal tails of the fighter are selected for estimation based on the reference weights of the wings, the vertical tails, and the horizontal tails of the supersonic airliner:
a. calculating a reference weight for a supersonic passenger aircraft wing
Figure 958146DEST_PATH_IMAGE012
The formula is as follows:
Figure 481531DEST_PATH_IMAGE014
；
wherein the layout factor
Figure 82014DEST_PATH_IMAGE016
，
Figure DEST_PATH_IMAGE290
，
Figure 323640DEST_PATH_IMAGE020
In order to design the weight of the vehicle,
Figure 536447DEST_PATH_IMAGE022
in order to limit the overload, the overload is avoided,
Figure 179918DEST_PATH_IMAGE024
the area of the wing is the area of the wing,
Figure 718346DEST_PATH_IMAGE026
is the aspect ratio of the wing,
Figure 447268DEST_PATH_IMAGE028
the relative thickness of the wing root is the relative thickness,
Figure 526082DEST_PATH_IMAGE030
the ratio of the tip to the root of the wing,
Figure 696164DEST_PATH_IMAGE032
is the sweep angle of 25 percent chord line of the wing,
Figure 467811DEST_PATH_IMAGE034
is the control surface area on the wing;
b. calculating reference weight of horizontal tail of supersonic passenger plane
Figure 418449DEST_PATH_IMAGE036
The formula is as follows:
Figure 2752DEST_PATH_IMAGE038
；
wherein,
Figure 355236DEST_PATH_IMAGE040
the width of the machine body at the horizontal tail part,
Figure 969888DEST_PATH_IMAGE042
the tail of the tail is flat and long,
Figure 407822DEST_PATH_IMAGE044
the area of the horizontal tail;
c. calculating a reference weight for a vertical fin of a supersonic passenger aircraft
Figure 828439DEST_PATH_IMAGE046
The formula is as follows:
Figure 238692DEST_PATH_IMAGE048
；
wherein,
Figure 352142DEST_PATH_IMAGE050
the height of the horizontal tail is the height of the horizontal tail,
Figure 277372DEST_PATH_IMAGE052
the height of the vertical tail is the height of the vertical tail,
Figure 704943DEST_PATH_IMAGE054
the area of the vertical tail is the area of the vertical tail,
Figure 766440DEST_PATH_IMAGE056
in order to design the mach number of the optical fiber,
Figure 221429DEST_PATH_IMAGE058
is the length of the vertical tail arm, namely the distance from 0.25 average aerodynamic chord of the wing to 0.25 average aerodynamic chord of the vertical tail,
Figure 633956DEST_PATH_IMAGE060
the area of the rudder is the area of the rudder,
Figure 661955DEST_PATH_IMAGE062
is the aspect ratio of the vertical tail,
Figure 781221DEST_PATH_IMAGE064
the ratio of the tip to the root of the vertical fin,
Figure 970894DEST_PATH_IMAGE066
is vertical tail 25% chord line sweepback angle;
further, the reference weights of the fuselage and the landing gear of the supersonic aircraft in step S2 are estimated by selecting a statistical model of the weights of the fuselage and the landing gear of the transport aircraft, respectively:
d. calculating reference weight of supersonic passenger plane body
Figure 870717DEST_PATH_IMAGE068
The formula is as follows:
Figure 374510DEST_PATH_IMAGE070
；
wherein,
Figure 676179DEST_PATH_IMAGE072
，
Figure DEST_PATH_IMAGE292
，
Figure 974436DEST_PATH_IMAGE076
is the length of the fuselageThe degree of the magnetic field is measured,
Figure 63352DEST_PATH_IMAGE078
the area of the machine body to be soaked is,
Figure 433154DEST_PATH_IMAGE080
，
Figure 995853DEST_PATH_IMAGE082
the depth of the structure of the machine body is,
Figure 792908DEST_PATH_IMAGE084
extending the wing;
e. calculating a reference weight of a landing gear of a supersonic aircraft, including a reference weight of a nose landing gear and a reference weight of a main landing gear:
e1. reference weight of nose landing gear
Figure 401744DEST_PATH_IMAGE086
The formula is as follows:
Figure 512919DEST_PATH_IMAGE088
；
wherein
Figure 523601DEST_PATH_IMAGE090
，
Figure 429240DEST_PATH_IMAGE092
In order to make the landing weight heavy,
Figure 525372DEST_PATH_IMAGE094
in order to get the overload factor to land,
Figure 236976DEST_PATH_IMAGE096
in order to be the length of the nose landing gear,
Figure 538382DEST_PATH_IMAGE098
the number of nose landing gear wheels;
e2. reference weight of main landing gear
Figure 677239DEST_PATH_IMAGE100
The formula is as follows:
Figure 198350DEST_PATH_IMAGE102
；
wherein,
Figure 448066DEST_PATH_IMAGE104
，
Figure 371023DEST_PATH_IMAGE106
the length of the main landing gear is taken as the length,
Figure 680781DEST_PATH_IMAGE108
the number of the main lifting and falling frame wheels,
Figure 689189DEST_PATH_IMAGE110
the number of shock absorbing rods for the main landing gear,
Figure 742595DEST_PATH_IMAGE112
is the stall speed;
further, the reference weight of the propulsion system of the supersonic passenger aircraft in step S2 is selected from a weight model of the fighter aircraft for estimation, and specifically includes reference weights of an engine, an engine mounting part, an engine casing, an air inlet, a tail nozzle, an engine cooling system, a fuel cooling system, an engine control system, an engine starting system and a fuel tank;
f1. reference weight of engine
Figure 582375DEST_PATH_IMAGE114
The formula is as follows:
Figure 499254DEST_PATH_IMAGE116
；
wherein
Figure 791695DEST_PATH_IMAGE118
The weight of a single engine is obtained by fitting a model through given or historical data of an engine company;
Figure 586475DEST_PATH_IMAGE120
the number of the engines is;
f2. reference weight of engine mount
Figure 280762DEST_PATH_IMAGE122
The formula is as follows:
Figure 870006DEST_PATH_IMAGE124
；
wherein,
Figure 915323DEST_PATH_IMAGE126
is the total thrust of the engine;
f3. reference weight of engine casing
Figure DEST_PATH_IMAGE294
The formula is as follows:
Figure 248215DEST_PATH_IMAGE128
；
f4. reference weight of air intake duct
Figure 797008DEST_PATH_IMAGE130
The formula is as follows:
Figure 321268DEST_PATH_IMAGE132
；
wherein,
Figure 588301DEST_PATH_IMAGE134
Figure 724885DEST_PATH_IMAGE136
，
Figure 128184DEST_PATH_IMAGE138
as the length of the air inlet duct,
Figure 324810DEST_PATH_IMAGE140
the length of the double-fork air inlet combined pipe is,
Figure 79140DEST_PATH_IMAGE142
is the engine diameter;
f5. reference weight of jet nozzle
Figure 816151DEST_PATH_IMAGE144
The formula is as follows:
Figure 277220DEST_PATH_IMAGE146
；
wherein,
Figure 707064DEST_PATH_IMAGE148
is the length of the tail nozzle;
f6. reference weight of engine cooling system
Figure 142766DEST_PATH_IMAGE150
The formula is as follows:
Figure 683469DEST_PATH_IMAGE152
；
wherein,
Figure 264623DEST_PATH_IMAGE154
is the engine case length;
f7. reference weight of fuel cooling system
Figure 599789DEST_PATH_IMAGE156
The formula is as follows:
Figure 266394DEST_PATH_IMAGE158
；
f8. reference weight of engine control system
Figure 345208DEST_PATH_IMAGE160
The formula is as follows:
Figure 780869DEST_PATH_IMAGE162
；
wherein,
Figure 286937DEST_PATH_IMAGE164
the length from the front end face of the engine to the cockpit is equal to the length from the front end face of a single engine to the cockpit multiplied by the number of the engines;
f9. reference weight of engine starting system
Figure 503154DEST_PATH_IMAGE166
The formula is as follows:
Figure 821878DEST_PATH_IMAGE168
；
wherein,
Figure 174362DEST_PATH_IMAGE170
the thrust of a single engine is adopted;
f10. reference weight of fuel tank
Figure 54593DEST_PATH_IMAGE172
The formula is as follows:
Figure 492528DEST_PATH_IMAGE174
；
Figure 913145DEST_PATH_IMAGE176
，
Figure 323398DEST_PATH_IMAGE178
is the total volume of the fuel,
Figure 171268DEST_PATH_IMAGE180
the total volume of the oil tank is integrated,
Figure 34182DEST_PATH_IMAGE182
is the total volume of the self-sealing oil tank,
Figure 258490DEST_PATH_IMAGE184
the number of the oil tanks is the same as the number of the oil tanks,
Figure 21784DEST_PATH_IMAGE186
fuel consumption rate at maximum thrust;
further, the reference weight of the fixing device of the supersonic passenger plane in the step S2 is selected from a weight model of the transport plane for estimation, and specifically includes reference weights of an aircraft control system, an APU installation, a measuring device, a hydraulic system, an electric system, an avionic system, a decoration system, an air conditioning system, an anti-icing system and a control device;
g1. reference weight for flight control system
Figure 306135DEST_PATH_IMAGE188
The formula is as follows:
Figure 656345DEST_PATH_IMAGE190
；
wherein,
Figure 418764DEST_PATH_IMAGE192
in order to control the number of flight control system functions,
Figure 600347DEST_PATH_IMAGE194
for the number of functions of the mechanical system,
Figure 993282DEST_PATH_IMAGE196
in order to control the total area of the surface,
Figure 893105DEST_PATH_IMAGE198
is the moment of inertia of the pitch axis of the aircraft,
Figure 396899DEST_PATH_IMAGE200
in order to control the number of flight control systems,
Figure 432988DEST_PATH_IMAGE202
the number of the crew members;
g2. reference weight for APU installation
Figure 59141DEST_PATH_IMAGE204
The formula is as follows:
Figure 882479DEST_PATH_IMAGE206
；
wherein,
Figure 986701DEST_PATH_IMAGE208
is the auxiliary power supply unit weight;
g3. reference weight of measuring device
Figure 80559DEST_PATH_IMAGE210
The formula is as follows:
Figure 877613DEST_PATH_IMAGE212
；
wherein,
Figure 424132DEST_PATH_IMAGE084
extending the wing;
g4. reference weight of hydraulic system
Figure 597625DEST_PATH_IMAGE214
The formula is as follows:
Figure 608306DEST_PATH_IMAGE216
；
g5. reference weight of electric power system
Figure 513945DEST_PATH_IMAGE218
The formula is as follows:
Figure 610077DEST_PATH_IMAGE220
；
wherein,
Figure 492320DEST_PATH_IMAGE222
in order to provide the rated power for the power system,
Figure 623087DEST_PATH_IMAGE224
the total length of the cable is taken as the length,
Figure 761945DEST_PATH_IMAGE226
the number of the generators is;
g6. reference weight of avionics system
Figure 283056DEST_PATH_IMAGE228
The formula is as follows:
Figure 532772DEST_PATH_IMAGE230
；
wherein,
Figure 455728DEST_PATH_IMAGE232
avionics system weight;
g7. reference weight of decorating system
Figure 765487DEST_PATH_IMAGE234
The formula is as follows:
Figure 836211DEST_PATH_IMAGE236
；
wherein
Figure 827301DEST_PATH_IMAGE238
Is the maximum payload weight;
g8. reference weight of air conditioning system
Figure 667081DEST_PATH_IMAGE240
The formula is as follows:
Figure 583959DEST_PATH_IMAGE242
；
wherein,
Figure 876400DEST_PATH_IMAGE244
in order to increase the total volume of the pressure chamber,
Figure 671181DEST_PATH_IMAGE246
designing the total number of people on the state machine, including the number of crew members and the number of passengers;
g9. reference weight of anti-icing system
Figure 365467DEST_PATH_IMAGE248
The formula is as follows:
Figure 17028DEST_PATH_IMAGE250
；
g10. reference weight of the operating device
Figure 28DEST_PATH_IMAGE252
The formula is as follows:
Figure 395237DEST_PATH_IMAGE254
；
further, the weighting factor of the technical progress in step S3 is described
Figure 881713DEST_PATH_IMAGE010
Typical values of (a) are: the wing technical progress weight factor is 0.7, the vertical tail technical progress weight factor is 0.8, the fuselage technical progress weight factor is 0.82, the landing gear technical progress weight factor is 0.85, and the rest of the components or devices have technical progress weight factors of 1.0.
Further, the reference weight of the fuselage in step S2 is as follows:
Figure 969755DEST_PATH_IMAGE255
with respect to a conventional passenger aircraft layout,
Figure 236788DEST_PATH_IMAGE257
(ii) a For the modern supersonic low-speed passenger blasting machine layout,
Figure 606328DEST_PATH_IMAGE259
，
Figure 275206DEST_PATH_IMAGE261
。
further, the single engine weight of f1 in the step S2
Figure 471832DEST_PATH_IMAGE263
The formula of the historical data fitting model is as follows:
Figure 960583DEST_PATH_IMAGE265
。
further, the weight calculation formulas of the three subsystems in step S4 are as follows:
h1. weight of the body structure
Figure 900857DEST_PATH_IMAGE267
The formula is as follows:
Figure 424242DEST_PATH_IMAGE269
；
h2. weight of propulsion system
Figure 526190DEST_PATH_IMAGE271
The formula is as follows:
Figure 767816DEST_PATH_IMAGE273
；
if it is not
Figure 308518DEST_PATH_IMAGE275
Is the weight of the engine including the accessories, the weight of the propulsion system is reduced to:
Figure 122628DEST_PATH_IMAGE277
。
h3. weight of the fixing device
Figure 723374DEST_PATH_IMAGE279
The formula is as follows:
Figure 124399DEST_PATH_IMAGE281
；
empty weight of supersonic passenger plane
Figure 468793DEST_PATH_IMAGE283
Is of the formula
Figure 966771DEST_PATH_IMAGE285
。
Further, when the supersonic passenger aircraft is provided with a canard, the weight of the horizontal tail of the supersonic passenger aircraft in step S2 is adopted
Figure 410521DEST_PATH_IMAGE287
The formula performs the canard weight calculation and adds the canard weight to the body structure weight calculation formula of h1 in step S4.
Example 1
In this embodiment, the empty weight calculation of the component or device and subsystem is performed on the locked Engineering and Sciences Company M1.6 SST in the NASA HSR project, i.e., the 250-seat supersonic passenger aircraft (SST) designed by rockschid Engineering technology corporation and the lanley center, and compared with the FLOPS weight result adopted by NASA TP-1999-9697.
Cruise Mach of SSTNumber 1.6, voyage 6500 haili. Wing reference area 8732.9ft of SST2Wing load 67.74lb/ft24 conceptual engines with thrust 41000lb and weight 8146lb are arranged, and the layout and the propulsion system of the conceptual engines are shown in figures 2 a-2 d. According to the parameters reported from NASA TP-1999-.
The result shows that the air weight estimation method for the supersonic passenger plane of the embodiment is lighter than the air weight of the whole plane obtained by the FLOPS method of NASA, and the total difference is about-10.8%. From the calculation result of the weight of the aircraft component or device, the method for estimating the empty weight of the supersonic passenger plane according to the embodiment grasps the main characteristics of the supersonic passenger plane for the weight of the significant component or device of the aircraft, and in the aspect of the body structure, although the vertical tail error is large, the absolute value of the error between the wing and the body is less than 2%, so that the absolute value of the error between the weight of the body structure is less than 3%. In the aspect of a propulsion system, although the error of the oil tank system is large, the weight error of the whole propulsion system is about 4% because the oil tank system occupies a small proportion of the propulsion system. The dead weight estimation method for the supersonic passenger plane has the advantages that the weight error of the fixed equipment is large on the whole, particularly, the weight of the decoration system is seriously underestimated, the direct relation between the weight of the control system, the weight of the hydraulic system and the weight of the decoration system and the weight of the basic database and the system division are increased when comfort and safety are more emphasized by modern airplanes, and the basic database and the system division are possibly related.
In order to compare with the traditional weight systems of fighters and transport planes, the results of the SST weight comparison table obtained by the method of two weight systems of the Raymer transport plane and the fighter plane are shown in table 1, and the results show that the empty weight obtained by the weight system of the transport plane is larger, and the empty weight obtained by the weight system of the fighter plane is smaller, but are closer to the results obtained by the empty weight estimation method for the supersonic airliner in the embodiment. Fig. 3 shows relative errors between the empty weight estimation method for the supersonic passenger plane according to the embodiment and the estimation results of the conventional fighter plane weight model and the conventional transport plane weight model with respect to the estimation results of the reference FLOPS method. For this embodiment, although the Raymer fighter aircraft weight model estimates the smallest absolute value of the own dead weight error, it estimates the weight of the fuselage significantly higher, while the weight of the fixture system is too low. The absolute value of the error of the local weight estimated by the traditional transporter weight model is only slightly larger than that of the method, but the weight of the wing and the vertical tail is seriously overestimated. Therefore, in general, the weight of each part or device obtained by the method for estimating the empty weight of the supersonic passenger plane of the embodiment is very close to that of the FLOPS method, and the obtained result is relatively credible and can be used for quickly estimating the parts, devices, subsystems and the empty weight of the plane in the conceptual design and analysis stage of the supersonic passenger plane.
Figure DEST_PATH_IMAGE296

Claims (6)

1. A method for estimating empty weight for a supersonic aircraft, comprising the steps of:
s1, disassembling the supersonic passenger plane into three subsystems, namely a body structure, a propulsion system and a fixing device, according to the overall layout of the supersonic passenger plane and functions, decomposing each subsystem into a plurality of components or devices, and determining the geometric dimension, the function or the construction parameters of each component or device;
the machine body structure subsystem is divided into a machine body, wings, vertical tails, horizontal tails or canard wings and an undercarriage; the propulsion system subsystem is decomposed into an engine, an engine mounting part, an engine shell, an air inlet channel, a tail pipe, an engine cooling system, a fuel oil cooling system, an engine control system and an engine starting system; the fixing device subsystem is divided into a flight control system, an APU installation device, a measuring device, a hydraulic system, an electric system, an avionic system, a decoration system, an air conditioning system, an anti-icing and deicing system and a control device;
s2, selecting the weight statistical model of the components or the devices of the existing fighter plane and the existing transport plane according to the geometric characteristics, the structural characteristics and the load characteristics of the components or the devicesCalculating reference weight of each part or device by using appropriate statistical model
Figure DEST_PATH_IMAGE002
Wherein
Figure DEST_PATH_IMAGE004
identification of each component or device;
Figure DEST_PATH_IMAGE006
s3, calculating the weight of each part or device of the supersonic passenger plane:
Figure DEST_PATH_IMAGE008
，
Figure DEST_PATH_IMAGE010
a technological progress weight factor of the era was established for the weight of each component or device corresponding to the database of statistical models,
Figure 311321DEST_PATH_IMAGE004
identification of each component or device;
s4, according to the division of the subsystems, summing the weights of the components or devices belonging to the subsystems, and calculating the weights of the three subsystems respectively;
the reference weights of the wings, the vertical tails and the horizontal tails of the supersonic airliners are respectively estimated by selecting weight models of the wings, the vertical tails and the horizontal tails of the fighter:
a. calculating a reference weight for a supersonic passenger aircraft wing
Figure DEST_PATH_IMAGE012
The formula is as follows:
Figure DEST_PATH_IMAGE014
；
wherein the layout factor
Figure DEST_PATH_IMAGE016
，
Figure DEST_PATH_IMAGE018
，
Figure DEST_PATH_IMAGE020
In order to design the weight of the vehicle,
Figure DEST_PATH_IMAGE022
in order to limit the overload, the overload is avoided,
Figure DEST_PATH_IMAGE024
the area of the wing is the area of the wing,
Figure DEST_PATH_IMAGE026
is the aspect ratio of the wing,
Figure DEST_PATH_IMAGE028
the relative thickness of the wing root is the relative thickness,
Figure DEST_PATH_IMAGE030
the ratio of the tip to the root of the wing,
Figure DEST_PATH_IMAGE032
is the sweep angle of 25 percent chord line of the wing,
Figure DEST_PATH_IMAGE034
is the control surface area on the wing;
b. calculating reference weight of horizontal tail of supersonic passenger plane
Figure DEST_PATH_IMAGE036
The formula is as follows:
Figure DEST_PATH_IMAGE038
；
wherein,
Figure DEST_PATH_IMAGE040
the width of the machine body at the horizontal tail part,
Figure DEST_PATH_IMAGE042
the tail of the tail is flat and long,
Figure DEST_PATH_IMAGE044
the area of the horizontal tail;
c. calculating a reference weight for a vertical fin of a supersonic passenger aircraft
Figure DEST_PATH_IMAGE046
The formula is as follows:
Figure DEST_PATH_IMAGE048
；
wherein,
Figure DEST_PATH_IMAGE050
the height of the horizontal tail is the height of the horizontal tail,
Figure DEST_PATH_IMAGE052
the height of the vertical tail is the height of the vertical tail,
Figure DEST_PATH_IMAGE054
the area of the vertical tail is the area of the vertical tail,
Figure DEST_PATH_IMAGE056
in order to design the mach number of the optical fiber,
Figure DEST_PATH_IMAGE058
the length of the vertical tail arm, namely the distance from the average aerodynamic chord of 0.25 of the wing to the average aerodynamic chord of 0.25 of the vertical tail,
Figure DEST_PATH_IMAGE060
the area of the rudder is the area of the rudder,
Figure DEST_PATH_IMAGE062
is the aspect ratio of the vertical tail,
Figure DEST_PATH_IMAGE064
the ratio of the tip to the root of the vertical fin,
Figure DEST_PATH_IMAGE066
is vertical tail 25% chord line sweepback angle;
the reference weight of the body and the undercarriage of the supersonic passenger plane is estimated by selecting a statistical model of the weight of the body and the undercarriage of the transport plane respectively:
d. calculating reference weight of supersonic passenger plane body
Figure DEST_PATH_IMAGE068
The formula is as follows:
Figure DEST_PATH_IMAGE070
；
wherein,
Figure DEST_PATH_IMAGE072
，
Figure DEST_PATH_IMAGE074
，
Figure DEST_PATH_IMAGE076
the length of the machine body is taken as the length,
Figure DEST_PATH_IMAGE078
the area of the machine body to be soaked is,
Figure DEST_PATH_IMAGE080
，
Figure DEST_PATH_IMAGE082
the depth of the structure of the machine body is,
Figure DEST_PATH_IMAGE084
extending the wing;
e. calculating a reference weight of a landing gear of a supersonic aircraft, including a reference weight of a nose landing gear and a reference weight of a main landing gear:
e1. reference weight of nose landing gear
Figure DEST_PATH_IMAGE086
The formula is as follows:
Figure DEST_PATH_IMAGE088
；
wherein
Figure DEST_PATH_IMAGE090
，
Figure DEST_PATH_IMAGE092
In order to make the landing weight heavy,
Figure DEST_PATH_IMAGE094
in order to get the overload factor to land,
Figure DEST_PATH_IMAGE096
in order to be the length of the nose landing gear,
Figure DEST_PATH_IMAGE098
the number of nose landing gear wheels;
e2. reference weight of main landing gear
Figure DEST_PATH_IMAGE100
The formula is as follows:
Figure DEST_PATH_IMAGE102
；
wherein,
Figure DEST_PATH_IMAGE104
，
Figure DEST_PATH_IMAGE106
the length of the main landing gear is taken as the length,
Figure DEST_PATH_IMAGE108
the number of the main lifting and falling frame wheels,
Figure DEST_PATH_IMAGE110
the number of shock absorbing rods for the main landing gear,
Figure DEST_PATH_IMAGE112
is the stall speed;
the method for estimating the reference weight of the propulsion system of the supersonic passenger plane by selecting the weight model of the fighter plane specifically comprises the following steps:
f. reference weights of an engine, an engine mounting part, an engine shell, an air inlet channel, a tail nozzle, an engine cooling system, a fuel oil cooling system, an engine control system, an engine starting system and an oil tank;
f1. reference weight of engine
Figure DEST_PATH_IMAGE114
The formula is as follows:
Figure DEST_PATH_IMAGE116
；
wherein
Figure DEST_PATH_IMAGE118
The weight of a single engine is obtained by fitting a model through given or historical data of an engine company;
Figure DEST_PATH_IMAGE120
the number of the engines is;
f2. reference weight of engine mount
Figure DEST_PATH_IMAGE122
The formula is as follows:
Figure DEST_PATH_IMAGE124
；
wherein,
Figure DEST_PATH_IMAGE126
is the total thrust of the engine;
f3. reference weight of engine casing
Figure DEST_PATH_IMAGE128
The formula is as follows:
Figure DEST_PATH_IMAGE130
；
f4. reference weight of air intake duct
Figure DEST_PATH_IMAGE132
The formula is as follows:
Figure DEST_PATH_IMAGE134
；
wherein,
Figure DEST_PATH_IMAGE136
Figure DEST_PATH_IMAGE138
，
Figure DEST_PATH_IMAGE140
as the length of the air inlet duct,
Figure DEST_PATH_IMAGE142
the length of the double-fork air inlet combined pipe is,
Figure DEST_PATH_IMAGE144
is the engine diameter;
f5. reference weight of jet nozzle
Figure DEST_PATH_IMAGE146
The formula is as follows:
Figure DEST_PATH_IMAGE148
；
wherein,
Figure DEST_PATH_IMAGE150
is the length of the tail nozzle;
f6. reference weight of engine cooling system
Figure DEST_PATH_IMAGE152
The formula is as follows:
Figure DEST_PATH_IMAGE154
；
wherein,
Figure DEST_PATH_IMAGE156
is the engine case length;
f7. reference weight of fuel cooling system
Figure DEST_PATH_IMAGE158
The formula is as follows:
Figure DEST_PATH_IMAGE160
；
f8. reference weight of engine control system
Figure DEST_PATH_IMAGE162
The formula is as follows:
Figure DEST_PATH_IMAGE164
；
wherein,
Figure DEST_PATH_IMAGE166
the length from the front end face of the engine to the cockpit is equal to the length from the front end face of a single engine to the cockpit multiplied by the number of the engines;
f9. reference weight of engine starting system
Figure DEST_PATH_IMAGE168
The formula is as follows:
Figure DEST_PATH_IMAGE170
；
wherein,
Figure DEST_PATH_IMAGE172
the thrust of a single engine is adopted;
f10. reference weight of fuel tank
Figure DEST_PATH_IMAGE174
The formula is as follows:
Figure DEST_PATH_IMAGE176
Figure DEST_PATH_IMAGE178
；
wherein,
Figure DEST_PATH_IMAGE180
is the total volume of the fuel,
Figure DEST_PATH_IMAGE182
the total volume of the oil tank is integrated,
Figure DEST_PATH_IMAGE184
is the total volume of the self-sealing oil tank,
Figure DEST_PATH_IMAGE186
the number of the oil tanks is the same as the number of the oil tanks,
Figure DEST_PATH_IMAGE188
fuel consumption rate at maximum thrust;
the method for estimating the weight model of the selected transport plane by the reference weight of the fixing device of the supersonic passenger plane specifically comprises the following steps:
g. flight control system, APU installation, measuring device, hydraulic system, electric power system, avionics system, decoration system, air conditioning system, anti-icing system and reference weight of the operating device;
g1. reference weight for flight control system
Figure DEST_PATH_IMAGE190
The formula is as follows:
Figure DEST_PATH_IMAGE192
；
wherein,
Figure DEST_PATH_IMAGE194
in order to control the number of flight control system functions,
Figure DEST_PATH_IMAGE196
for the number of functions of the mechanical system,
Figure DEST_PATH_IMAGE198
in order to control the total area of the surface,
Figure DEST_PATH_IMAGE200
is the moment of inertia of the pitch axis of the aircraft,
Figure DEST_PATH_IMAGE202
in order to control the number of flight control systems,
Figure DEST_PATH_IMAGE204
the number of the crew members;
g2. reference weight for APU installation
Figure DEST_PATH_IMAGE206
The formula is as follows:
Figure DEST_PATH_IMAGE208
；
wherein,
Figure DEST_PATH_IMAGE210
is the auxiliary power supply unit weight;
g3. reference weight of measuring device
Figure DEST_PATH_IMAGE212
The formula is as follows:
Figure DEST_PATH_IMAGE214
；
wherein,
Figure 711952DEST_PATH_IMAGE084
extending the wing;
g4. reference weight of hydraulic system
Figure DEST_PATH_IMAGE216
The formula is as follows:
Figure DEST_PATH_IMAGE218
；
g5. reference weight of electric power system
Figure DEST_PATH_IMAGE220
The formula is as follows:
Figure DEST_PATH_IMAGE222
；
wherein,
Figure DEST_PATH_IMAGE224
in order to provide the rated power for the power system,
Figure DEST_PATH_IMAGE226
the total length of the cable is taken as the length,
Figure DEST_PATH_IMAGE228
the number of the generators is;
g6. reference weight of avionics system
Figure DEST_PATH_IMAGE230
The formula is as follows:
Figure DEST_PATH_IMAGE232
；
wherein,
Figure DEST_PATH_IMAGE234
avionics system weight;
g7. reference weight of decorating system
Figure DEST_PATH_IMAGE236
The formula is as follows:
Figure DEST_PATH_IMAGE238
；
wherein
Figure DEST_PATH_IMAGE240
Is the maximum payload weight;
g8. reference weight of air conditioning system
Figure DEST_PATH_IMAGE242
The formula is as follows:
Figure DEST_PATH_IMAGE244
；
wherein,
Figure DEST_PATH_IMAGE246
in order to increase the total volume of the pressure chamber,
Figure DEST_PATH_IMAGE248
designing the total number of people on the state machine, including the number of crew members and the number of passengers;
g9. reference weight of anti-icing system
Figure DEST_PATH_IMAGE250
The formula is as follows:
Figure DEST_PATH_IMAGE252
；
g10. reference weight of the operating device
Figure DEST_PATH_IMAGE254
The formula is as follows:
Figure DEST_PATH_IMAGE256
。
2. the empty weight estimation method for supersonic passenger aircraft as defined in claim 1, wherein said technological advancement weight factor in step S3
Figure 862661DEST_PATH_IMAGE010
Typical values of (a) are: the wing technical progress weight factor is 0.7, the vertical tail technical progress weight factor is 0.8, the fuselage technical progress weight factor is 0.82, the landing gear technical progress weight factor is 0.85, and the rest of the components or devices have technical progress weight factors of 1.0.
3. The method of claim 1, wherein the reference weight of the fuselage of step d is:
Figure DEST_PATH_IMAGE257
with respect to a conventional passenger aircraft layout,
Figure DEST_PATH_IMAGE259
(ii) a For the modern supersonic low-speed passenger blasting machine layout,
Figure DEST_PATH_IMAGE261
，
Figure DEST_PATH_IMAGE263
。
4. method for estimating the empty weight of a supersonic passenger aircraft as defined in claim 1, wherein the weight of the single engine of f1 in step f
Figure DEST_PATH_IMAGE265
The formula of the historical data fitting model is as follows:
Figure DEST_PATH_IMAGE267
。
5. the method of claim 1, wherein the weight calculation formula for the three subsystems of step S4 is as follows:
h1. weight of the body structure
Figure DEST_PATH_IMAGE269
The formula is as follows:
Figure DEST_PATH_IMAGE271
；
h2. weight of propulsion system
Figure DEST_PATH_IMAGE273
The formula is as follows:
Figure DEST_PATH_IMAGE275
；
if it is not
Figure DEST_PATH_IMAGE277
Is the weight of the engine including the accessories, the weight of the propulsion system is reduced to:
Figure DEST_PATH_IMAGE279
；
h3. weight of the fixing device
Figure DEST_PATH_IMAGE281
The formula is as follows:
Figure DEST_PATH_IMAGE283
；
empty weight of supersonic passenger plane
Figure DEST_PATH_IMAGE285
Is of the formula
Figure DEST_PATH_IMAGE287
。
6. Method for estimating the empty weight of a supersonic aircraft according to claim 5, wherein the weight of the horizontal tail of the supersonic aircraft of step b is used when the supersonic aircraft is provided with canards
Figure DEST_PATH_IMAGE289
The canard weight is calculated according to the formula, and the canard weight is added to the body structure weight calculation formula of step h1.
CN202111125590.7A 2021-09-26 2021-09-26 Empty weight estimation method for supersonic passenger plane Active CN113761667B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202111125590.7A CN113761667B (en) 2021-09-26 2021-09-26 Empty weight estimation method for supersonic passenger plane

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202111125590.7A CN113761667B (en) 2021-09-26 2021-09-26 Empty weight estimation method for supersonic passenger plane

Publications (2)

Publication Number Publication Date
CN113761667A CN113761667A (en) 2021-12-07
CN113761667B true CN113761667B (en) 2022-04-26

Family

ID=78797425

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202111125590.7A Active CN113761667B (en) 2021-09-26 2021-09-26 Empty weight estimation method for supersonic passenger plane

Country Status (1)

Country Link
CN (1) CN113761667B (en)

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112660410A (en) * 2020-12-29 2021-04-16 中国航空工业集团公司西安飞机设计研究所 Estimation method for weight of high-aspect-ratio wing

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2883967B1 (en) * 2005-04-04 2007-06-29 Messier Bugatti Sa DEVICE AND METHOD FOR DETERMINING THE WEIGHT AND / OR CHARACTERISTIC SIZE OF THE CENTERING OF AN AIRCRAFT
US10232937B2 (en) * 2012-12-07 2019-03-19 Hypermach Aerospace Industries, Inc. Hypersonic aircraft
US20190087531A1 (en) * 2016-05-18 2019-03-21 Airbus Group Hq Inc Dba A3 By Airbus Group Systems, devices, and methods for a modular passenger aircraft cabin and design thereof
JP6768348B2 (en) * 2016-05-26 2020-10-14 三菱重工業株式会社 Fuselage cross-sectional shape design method, design equipment and design program
CN112434380A (en) * 2020-12-12 2021-03-02 江西洪都航空工业股份有限公司 Aircraft wing weight estimation method
CN113221251B (en) * 2021-05-28 2023-01-03 西北工业大学 Whole structure design method and system of hypersonic aircraft

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112660410A (en) * 2020-12-29 2021-04-16 中国航空工业集团公司西安飞机设计研究所 Estimation method for weight of high-aspect-ratio wing

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
基于并联协作混合遗传算法的高超声速巡航飞行器一体化优化设计研究;罗世彬等;《宇航学报》;20040130(第01期);第29-35页 *

Also Published As

Publication number Publication date
CN113761667A (en) 2021-12-07

Similar Documents

Publication Publication Date Title
Wiart et al. Development of NOVA aircraft configurations for large engine integration studies
Yutko et al. Conceptual design of a D8 commercial aircraft
Nickol Hybrid wing body configuration scaling study
Fujino et al. Wave-drag characteristics of an over-the-wing nacelle business-jet configuration
Iwanizki et al. Conceptual design studies of short range aircraft configurations with hybrid electric propulsion
Vos et al. System-level assessment of tail-mounted propellers for regional aircraft
Sóbester et al. Conceptual design of UAV airframes using a generic geometry service
CN113761667B (en) Empty weight estimation method for supersonic passenger plane
Gern Finite element based HWB centerbody structural optimization and weight prediction
Sadraey et al. Drag force and drag coefficient
Aronstein et al. Two supersonic business aircraft conceptual designs with and without sonic boom constraint
Andrews et al. Multidisciplinary analysis of a box-wing aircraft designed for a regional-jet mission
Gauvrit-Ledogar et al. Blended wing body design
Becker et al. Numerical aerodynamics in transport aircraft design
Kornev et al. Aerodynamic design method of integrated aircraft with submerged intake devices and power plant included into airframe carrying system
Wood et al. Status review of a supersonically biased fighter wing design study
Kirkman et al. Design Study for a Highly Fuel Efficient Regional Transport
Badis Subsonic aircraft wing conceptual design synthesis and analysis
Aronstein et al. Conceptual design of a sonic boom constrained supersonic business aircraft
Lange et al. Wing Shape Improvement in the Presence of an Over-the-Wing Mounted UHBR Engine for a Short Range Transport Aircraft
Matsuno et al. Multidisciplinary design optimization of long or short range hypersonic aircraft
Bliamis et al. Parametric investigation of the aerodynamic and acoustic performance of a low-boom supersonic airliner
Aulnette Design Synthesis of a Hybrid Wing Body Transport Aircraft
Mason Comparison of Structural Concepts for Transport Aircraft with an Aft Tail Cone Turbine
Graziano et al. High efficiency regional aircraft conceptual design and on-board systems preliminary study

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant