Aircraft Design最新文献_第6页

Rotary cockpit compartment—design concept and control strategy 旋转座舱舱室设计概念与控制策略

Aircraft Design Pub Date : 1999-06-01 DOI: 10.1016/S1369-8869(99)00010-5

S.M Malaek, K Hodjat, M Dorri

引用次数: 0

Intake-engine matching for high-speed civil transport powerplant design and analysis 高速民用运输动力装置进气发动机匹配设计与分析

Aircraft Design Pub Date : 1999-06-01 DOI: 10.1016/S1369-8869(99)00009-9

Adolf H.W Bos

{"title":"Intake-engine matching for high-speed civil transport powerplant design and analysis","authors":"Adolf H.W Bos","doi":"10.1016/S1369-8869(99)00009-9","DOIUrl":"10.1016/S1369-8869(99)00009-9","url":null,"abstract":"<div><p><span><span>This paper addresses the necessity to incorporate an intake-engine matching procedure in any procedure to analyze the off-design performance of engines designed to power high-speed civil transport aircraft. Most methods known to the author that are useable in the </span>conceptual design phase of the aircraft (a phase characterized by the fact that very few design variables are known) only analyze the performance of the engine, without taking into account the design and performance of the intake. It will be shown in this paper, that the intake and the design exhibit a strong mutual influence, that cannot be neglected. An alternative method of analysis is presented. Particular reference will be made to the phenomenon of excess air and the resulting spillage drag. It will be shown that spillage air can be quite large in case of an HSCT design, especially in case the engine is designed for a high cruise Mach number. Assuming the presence of a sophisticated </span>intake system<span> generating multiple shocks in order to optimize the intake efficiency at the cruise condition, excess air at lower Mach numbers can amount to more than 60%.</span></p></div>","PeriodicalId":100070,"journal":{"name":"Aircraft Design","volume":"2 2","pages":"Pages 95-104"},"PeriodicalIF":0.0,"publicationDate":"1999-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://sci-hub-pdf.com/10.1016/S1369-8869(99)00009-9","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"80186402","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Mission and concept evaluation for a multirole, mission-adaptable air vehicle 多用途、任务适应性飞行器的任务和概念评估

Aircraft Design Pub Date : 1999-06-01 DOI: 10.1016/S1369-8869(99)00003-8

V.L. Wells , J.W. Rutherford , A.M. Corgiat

{"title":"Mission and concept evaluation for a multirole, mission-adaptable air vehicle","authors":"V.L. Wells , J.W. Rutherford , A.M. Corgiat","doi":"10.1016/S1369-8869(99)00003-8","DOIUrl":"10.1016/S1369-8869(99)00003-8","url":null,"abstract":"<div><p>The paper describes the results from a concept exploration study to assess the feasibility of a modular/reconfigurable rotorcraft<span><span> designated the “multirole, mission-adaptable air vehicle (MRMAAV)”. The initial phase of the study consisted of developing mission and operational requirements<span> for the vehicle. This phase resulted in the assessment that the aircraft should be considered primarily an attack vehicle but with the capability, through reconfiguration, for performing several alternate missions. Evaluation of several high-speed rotorcraft concepts led to the selection of two platform configurations for further study. These included the variable-diameter compound helicopter (VDCH) and the joined-wing tilt rotor (JWTR). Detailed sizing efforts focused on the VDCH as the more feasible of the two concepts. Innovative aspects of the air vehicle include variable-diameter main rotor, turboshaft/turbofan </span></span>convertible engine, virtual-canopy cockpit, and reconfigurable payload bay. The mission-equipment package is highlighted by an autonomous remote sensor platform. The study identifies areas which best lend themselves to a modular or reconfigurable design approach and describes in detail a candidate vehicle meeting the MRMAAV objectives.</span></p></div>","PeriodicalId":100070,"journal":{"name":"Aircraft Design","volume":"2 2","pages":"Pages 65-80"},"PeriodicalIF":0.0,"publicationDate":"1999-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://sci-hub-pdf.com/10.1016/S1369-8869(99)00003-8","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"76422183","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 6

An air-launched, self-recovering autonomous vehicle concept 一种空中发射、自我回收的自动驾驶概念车

Aircraft Design Pub Date : 1999-06-01 DOI: 10.1016/S1369-8869(99)00005-1

J.W. Rutherford , V.L. Wells

引用次数: 2

Design concept of a high-altitude long-endurance unmanned aerial vehicle 高空长航时无人机的设计概念

Aircraft Design Pub Date : 1999-03-01 DOI: 10.1016/S1369-8869(99)00004-X

Zdobysław Goraj , Andrzej Frydrychiewicz , Jacek Winiecki

{"title":"Design concept of a high-altitude long-endurance unmanned aerial vehicle","authors":"Zdobysław Goraj , Andrzej Frydrychiewicz , Jacek Winiecki","doi":"10.1016/S1369-8869(99)00004-X","DOIUrl":"10.1016/S1369-8869(99)00004-X","url":null,"abstract":"<div><p><span>This paper presents a conceptual project of a high-altitude long-endurance unmanned aerial vehicle. It describes a number of historical, current and prospective HALE aircraft and considers existing four serious obstacles, to overcome them can mean the successful building of HALE aircraft. Among these obstacles there are very special aerodynamic (low Reynolds numbers together with transonic speeds), very light structures usually of </span>high aspect ratio<span>, propulsion technology (usually propeller driven by turbocharged piston engines) and flight control system (usually combining the best features of preprogrammed and hand-flown modes). Four aerodynamic design concepts are presented and their performances are compared. Among them is a biplane, considered mainly because of its moderate wing span, which can be obtained for a relatively big wing area and a high effective wing aspect ratio, a relatively stiff wing structure, and lower induced drag being possible to be obtained at the same lift and wing area as for the equivalent monoplane. It is shown that an attentively designed biplane can be efficient aerodynamically for high altitude patrol missions having almost the same endurance, using the same fuel to reach a service ceiling and having the take-off mass (and the payload) considerably bigger than a corresponding, equivalent monoplane. The paper is completed with selected considerations about dynamic stability.</span></p></div>","PeriodicalId":100070,"journal":{"name":"Aircraft Design","volume":"2 1","pages":"Pages 19-44"},"PeriodicalIF":0.0,"publicationDate":"1999-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://sci-hub-pdf.com/10.1016/S1369-8869(99)00004-X","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"90526964","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 28

Computational investigation of slot blowing for fuselage forebody flow control 机身前体气流控制的狭缝吹气计算研究

Aircraft Design Pub Date : 1999-03-01 DOI: 10.1016/S1369-8869(99)00006-3

Scott M. Murman , Yehia M. Rizk , Russell M. Cummings , Lewis B. Schiff

引用次数: 15

Multidisciplinary design optimization of an electric-powered unmanned air vehicle 电动无人飞行器多学科设计优化

Aircraft Design Pub Date : 1999-03-01 DOI: 10.1016/S1369-8869(99)00002-6

Stephen M. Batill , Marc A. Stelmack , Xiong Qing Yu

引用次数: 20

Derivation of perturbed equations of motion of aircraft 飞行器摄动方程的推导

Aircraft Design Pub Date : 1998-12-01 DOI: 10.1016/S1369-8869(98)00017-2

S. Pradeep

引用次数: 3

Advanced configurations for very large transport airplanes 大型运输机的先进配置

Aircraft Design Pub Date : 1998-12-01 DOI: 10.1016/S1369-8869(98)00018-4

John H. McMasters , Ilan M. Kroo

{"title":"Advanced configurations for very large transport airplanes","authors":"John H. McMasters , Ilan M. Kroo","doi":"10.1016/S1369-8869(98)00018-4","DOIUrl":"10.1016/S1369-8869(98)00018-4","url":null,"abstract":"<div><p>Recent aerospace industry interest in developing subsonic commercial transport airplanes with at least 50% greater passenger capacity than the largest existing aircraft in this category (e.g. the Boeing 747-400 with approximately 400–450 seats) has generated a number of proposals based primarily on the configuration paradigm established 50 years ago with the Boeing B-47 bomber. While this classic configuration has come to dominate subsonic commercial airplane development since the advent of the Boeing 707/Douglas DC-8 in the mid-1950s, its extrapolation to the size required to carry more than 600–700 passengers raises a number of questions, including:</p><ul><li><span>1. </span><span><p>How large can an airplane of 707/747 configuration be built and still remain economically and operationally viable?</p></span></li><li><span>2. </span><span><p>What configuration alternatives might allow circumvention of practical size limitations inherent in the basic 707/747 configuration?</p></span></li><li><span>3. </span><span><p>What new and/or dormant technology elements might be brought together in synergistic ways to resolve or ameliorate very large subsonic airplane problems?</p></span></li></ul>\u0000<p>To explore these and a number of related issues, a team of Boeing, university and NASA engineers was formed under the auspices of the NASA Advanced Concepts Program during 1994. The results of a Research Analysis contract (NAS1-20269) focused on a large, unconventional (C-wing) transport configuration for which Boeing and the authors were granted a design patent in 1995 is the subject of this paper which is based on information contained in McMasters et al. (NASA CR 198351, October 1996).</p></div>","PeriodicalId":100070,"journal":{"name":"Aircraft Design","volume":"1 4","pages":"Pages 217-242"},"PeriodicalIF":0.0,"publicationDate":"1998-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://sci-hub-pdf.com/10.1016/S1369-8869(98)00018-4","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"79356716","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 63

“Starting mass”—a complex criterion of quality for aircraft on-board systems “启动质量”是飞机机载系统的一个复杂的质量标准

Aircraft Design Pub Date : 1998-12-01 DOI: 10.1016/S1369-8869(98)00016-0

Yury M. Shustrov

{"title":"“Starting mass”—a complex criterion of quality for aircraft on-board systems","authors":"Yury M. Shustrov","doi":"10.1016/S1369-8869(98)00016-0","DOIUrl":"10.1016/S1369-8869(98)00016-0","url":null,"abstract":"<div><p>It is very important to have minimum weight of aircraft equipment. It allows to increase the payload or flight range or to improve some other aircraft characteristics. For the systems that are consuming energy during the flight it is not less important to save the power spent on their functioning. “Starting mass” gives the opportunity to combine these two heterogeneous sides of the equipment properties into one complex characteristic, which depends on the flight duration and on the aircraft engine parameters. The main idea in solving the problem of combining mass and energy in one complex parameter arises from the fact that practically the only on-board source of energy is the fuel stored in the aircraft tanks. Therefore, the energy consumed by the system may be substituted by the equivalent mass of fuel. Another component of the “starting mass” is the fuel spent on the transportation of the first two parts. The necessity of this third part arises from the differences in fuel expenditure on transportation of unchangeable and changeable loads during the flight. The summation of these weight components is called “starting mass” because all of them should be present in the aircraft before take-off.</p><p>The core of the method was developed by Bulaevsky and myself. It is refined and partially corrected in this paper.</p></div>","PeriodicalId":100070,"journal":{"name":"Aircraft Design","volume":"1 4","pages":"Pages 193-203"},"PeriodicalIF":0.0,"publicationDate":"1998-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://sci-hub-pdf.com/10.1016/S1369-8869(98)00016-0","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"85210042","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 5