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1、_ SAE Technical Standards Board Rules provide that: “This report is published by SAE to advance the state of technical and engineering sciences. The use of this report is entirely voluntary, and its applicability and suitability for any particular use, including any patent infringement arising there
2、from, is the sole responsibility of the user.” SAE reviews each technical report at least every five years at which time it may be reaffirmed, revised, or cancelled. SAE invites your written comments and suggestions. Copyright 2007 SAE International All rights reserved. No part of this publication m
3、ay be reproduced, stored in a retrieval system or transmitted, in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without the prior written permission of SAE. TO PLACE A DOCUMENT ORDER: Tel: 877-606-7323 (inside USA and Canada) Tel: 724-776-4970 (outside USA)
4、 Fax: 724-776-0790 Email: CustomerServicesae.org SAE WEB ADDRESS: http:/www.sae.org AIR5682 AEROSPACE INFORMATION REPORT Issued 2007-05 Common Launch Acceptability Region Approach Interface Control Document (CLARA ICD) RATIONALE In response to a U.S. Air Force Executive Weapon Systems Review (EWSR)
5、Task Group (TG) charter, the Society of Automotive Engineers (SAE) Common Launch Acceptability Region (LAR) Approach (CLARA) TG produced this Interface Control Document (ICD). The EWSR recognized the expensive nature of the present multiple-LAR development approaches and sought help from the SAE to
6、standardize and document a new common LAR approach that is less expensive and time consuming. The EWSR TG recommended key characteristics upon which to base the new approach. This ICD is based on those key characteristics. FOREWORD Pilots, mission planners, and trainers common objective is to delive
7、r air-launched weapons within the weapons performance envelope called the LAR. The LAR is the region in space from which a released weapon could successfully guide to the target. Typically, the aircraft displays an approximation to the LAR using a mathematical model commonly referred to as the LAR A
8、lgorithm. The weapon may also run the algorithm and pass the approximation of the LAR to the aircraft. As a result of independent attempts by aircraft manufactures, weapon manufacturers, and program offices to develop and implement a LAR Algorithm, multiple LAR approaches exist that are expensive, i
9、ll-maintained, and time-consuming. In an effort to improve this business practice for future weapon integration projects, the U.S. Air Force EWSR formed a TG to study the feasibility of developing a Common LAR (CLAR) approach. The EWSR TG surveyed weapon and aircraft contractors to determine the bes
10、t solution for the CLAR approach. The EWSR TG completed the survey and presented its recommendations to the EWSR on 4 August 1998. One recommendation was to design LAR algorithms so that weapon manufacturers or aircraft offices can make performance improvements through coefficient updates. This reco
11、mmendation serves as the underlying requirement that the LAR Algorithm be coefficient-based. Another recommendation was to standardize the LAR development for all systems. The EWSR then requested the assistance of the SAE to further develop and document an approach that would standardize the develop
12、ment of a coefficient-based LAR process. In response, the SAE created the AS-1B5 CLARA TG (AS-1B is the Aircraft-Store Integration subcommittee under the SAE AS-1 Aircraft Systems and System Integration committee. The number five denotes the TG within AS-1B). The CLARA TG identified four steps to de
13、velop and implement the CLAR process: 1. Develop functional and performance specifications 2. Develop interface control documents 3. Perform algorithm trade studies 4. Implement a promising set of algorithms to demonstrate feasibility Copyright SAE International Provided by IHS under license with SA
14、ELicensee=Defense Supply Ctr/5913977001 Not for Resale, 12/04/2007 19:40:41 MSTNo reproduction or networking permitted without license from IHS -,-,- SAE AIR5682 - 2 - The four functions that the CLARA TG identified are: 1. Data Space Generator 2. Truth Data Generator 3. Coefficient Generator 4. Rec
15、onstructor External to the above four functions are the Truth Database and the LAR Algorithm which provide ancillary support to the CLARA process. This ICD addresses the functional specifications and the interfaces of those functions. Copyright SAE International Provided by IHS under license with SA
16、ELicensee=Defense Supply Ctr/5913977001 Not for Resale, 12/04/2007 19:40:41 MSTNo reproduction or networking permitted without license from IHS -,-,- SAE AIR5682 - 3 - TABLE OF CONTENTS 1. SCOPE4 1.1 Introduction .4 1.2 Purpose.4 2. REFERENCES5 2.1 Applicable Documents 5 2.1.1 SAE Publications.5 2.1
17、.2 NOAA Publications5 2.2 Definitions .5 2.2.1 LAR and Footprint.5 2.2.2 Training and Verification Truth Data Sets.5 2.2.3 Coordinate Systems5 2.2.4 Units7 2.2.5 Atmospheric Model .7 2.2.6 Wind Model.7 2.3 CLAR Acronyms and Terminology Definitions7 3. INTERFACES .10 3.1 Process Description11 3.1.1 D
18、ata Space Generator11 3.1.2 Truth DataGenerator.12 3.1.3 Coefficient Generator13 3.1.4 Reconstructor14 3.2 Interface Requirements.15 FIGURE 1 CLARA SIMPLIFIED DIAGRAM.4 FIGURE 2 WEAPON IMPACT RELATIVE TO TARGET .6 FIGURE 3 CLAR FUNCTIONAL FLOW BLOCK DIAGRAM10 FIGURE 4 NOTIONAL DATA SPACE GENERATOR B
19、LOCK DIAGRAM.11 FIGURE 5 NOTIONAL WEAPON TRUTH MODEL BLOCK DIAGRAM12 FIGURE 6 NOTIONAL COEFFICIENT GENERATION PROCESS.14 FIGURE 7 NOTIONAL RECONSTRUCTOR BLOCK DIAGRAM 15 TABLE 1 INTERFACE TABLES.16 TABLE 2 CLAR DATA SPACE GENERATOR INPUT REQUIREMENTS.17 TABLE 3 DATA SPACE GENERATOR OUTPUT DATA.18 TA
20、BLE 4 TRUTH DATA GENERATOR OUTPUT DATA.19 TABLE 5 RECONSTRUCTOR INPUT CONDITIONS .20 TABLE 6 RECONSTRUCTOR OUTPUT DATA 21 Copyright SAE International Provided by IHS under license with SAELicensee=Defense Supply Ctr/5913977001 Not for Resale, 12/04/2007 19:40:41 MSTNo reproduction or networking perm
21、itted without license from IHS -,-,- SAE AIR5682 - 4 - 1. SCOPE 1.1 Introduction CLARA identifies four functions: Data Space Generator, Truth Data Generator, Coefficient Generator, and Reconstructor. Together these four functions standardize the solution to the LAR problem. This ICD defines the logi
22、cal interfaces of the four functions. 1.2 Purpose This document specifies the CLARA interfaces of the Data Space Generator, Truth Data Generator, Coefficient Generator, and Reconstructor functions as shown in Figure 1. The weapon and delivery platform developers define the details of each function.
23、Data Space Generator Coefficient Generator Reconstructor Truth Data Generator Truth Database FIGURE 1 - CLARA SIMPLIFIED DIAGRAM The Data Space Generator selects a representative set of discrete release conditions, (such as altitude, wind, speed, and release flight path angle) from a continuum of re
24、lease-condition possibilities. For each set of release conditions, the Data Space Generator defines a corresponding grid of target points. The subset from the multi-dimensional space of discrete release conditions, along with their corresponding grid of target points, wind constraints, and impact an
25、gle constraints serve as the input to the Truth Data Generator. The Truth Data Generator uses the Data Space Generator output to calculate the achieved impact parameters (velocity, angles, and miss distance). The Truth Database stores the release conditions and the achieved impact parameters for eac
26、h target point. The Truth Data Generator generates impact data sets for the Coefficient Generator. The Truth Data Generator uses a model of the weapon system that predicts weapon delivery performance to a predefined accuracy. The weapon model may use Six-Degrees-Of-Freedom (6DOF) or another mathemat
27、ical representation that meets the objective for the weapon system LAR. The Coefficient Generator generates coefficients for a mathematical fitting model. This mathematical fitting model is commonly referred to as the LAR Algorithm. The output of the Reconstructor is an approximation of the original
28、 weapon footprint data based on flight and environment conditions. The Mission Planning, Trainer Systems, and weapon delivery aircraft use this approximation. Copyright SAE International Provided by IHS under license with SAELicensee=Defense Supply Ctr/5913977001 Not for Resale, 12/04/2007 19:40:41
29、MSTNo reproduction or networking permitted without license from IHS -,-,- SAE AIR5682 - 5 - 2. REFERENCES 2.1 Applicable Documents The following publications form a part of this document to the extent specified herein. The latest issue of SAE publications shall apply. The applicable issue of other p
30、ublications shall be the issue in effect on the date of the purchase order. In the event of conflict between the text of this document and references cited herein, the text of this document takes precedence. Nothing in this document, however, supersedes applicable laws and regulations unless a speci
31、fic exemption has been obtained. 2.1.1 SAE Publications Available from SAE International, 400 Commonwealth Drive, Warrendale, PA 15096-0001, Tel: 877-606-7323 (inside USA and Canada) or 724-776-4970 (outside USA), www.sae.org. SAE ACE Paper 2001-01-2953 titled “Common Launch Acceptability Region Tas
32、k Group” AIR5712 Common Launch Acceptability Region Approach (CLARA) Rationale Document TSB 003 Rules for SAE Use of SI (Metric) Units (as issued 1965-06 and revised 1999-05)+ 2.1.2 NOAA Publications Available from U.S. Government Printing Office, 732 North Capitol Street, NW, Washington, DC 20401,
33、http:/catalog.gpo.gov. NOAA-S/T 76-1562 US Standard Atmosphere, 1976 2.2 Definitions 2.2.1 LAR and Footprint Given a set of release, environmental, target, and mission conditions, a footprint is the area on the ground within which the weapon can impact and a LAR is the geometric region where if the
34、weapon is released, the weapon can impact the target. A footprint is referenced to the release platform and it moves along with the release platform. A LAR is the footprint transposed to the launch plane and is referenced to the target position. The CLAR process uses footprints; however, the impleme
35、ntor may choose to transpose the footprint into a LAR. 2.2.2 Training and Verification Truth Data Sets Training Data Sets are used to develop or train the CLAR Coefficients. Verification Data Sets are used to verify that footprints generated using the CLAR Coefficients meet the defined criteria. Bot
36、h Verification and Training data sets come from the same release envelope (the optimization envelope input space over which the coefficients are hypothesized to apply), but from different points within. 2.2.3 Coordinate Systems 2.2.3.1 Launch Coordinate Frame The launch coordinate frame for launch s
37、tates and aimpoint locations is an aircraft-centered, local level, right-handed coordinate system with X-axis positive forward along the horizontal component of the velocity vector, and Z-axis positive down. The origin (0,0,0) is the position of the weapon at launch. Copyright SAE International Prov
38、ided by IHS under license with SAELicensee=Defense Supply Ctr/5913977001 Not for Resale, 12/04/2007 19:40:41 MSTNo reproduction or networking permitted without license from IHS -,-,- SAE AIR5682 - 6 - 2.2.3.2 Impact State Coordinates The Impact State coordinate system is defined as the launch coordi
39、nate frame with the origin translated to the aimpoint (Desired Impact). Impact azimuth is positive from the X-axis toward the Y-axis and is the angle between the X-axis and the weapon velocity component in the X-Y plane at impact. Impact Angle is measured from the horizontal plane toward the Z-axis
40、in the plane that includes the weapon velocity vector at impact. 2.2.3.3 Wind Coordinates Wind shall be defined as a velocity vector in the launch coordinate frame, i.e., tail wind is defined as positive (Wind Vx). 2.2.3.4 Weapon Coordinates Figure 2 illustrates the weapons coordinate system. The we
41、apons body axis system consists of an orthogonal triad of axis, Xw, Yw, and Zw with origin (0,0,0) at the fixed location determined to be the optimum for that weapon (for example, at the center of mass). The Xw axis is positive in the forward direction of the weapon. The Yw axis is positive to the r
42、ight of the forward direction of the weapon. The Zw axis is positive down through the lower side of the weapon. FIGURE 2 - WEAPON IMPACT RELATIVE TO TARGET The weapons attitude relative to the inertial velocity vector is defined by the inertial Angle of Attack (iAOA) in the weapon (X, Z) plane and t
43、he inertial Angle of Sideslip (iAOSS). The order of rotation is: iAOA and then iAOSS. The weapon impact point (or function point - in the case of a store that does not impact) is a point some miss distance from the target point on the same horizontal plane. For consistency, this document uses target
44、 point to represent desired impact point, function point, or aimpoint. Figure 2 demonstrates weapon impact angles, velocity, and angles of attack and sideslip. Data files contain these impact parameters along with miss distance for the CLAR process to use to construct the weapons footprint. Copyrigh
45、t SAE International Provided by IHS under license with SAELicensee=Defense Supply Ctr/5913977001 Not for Resale, 12/04/2007 19:40:41 MSTNo reproduction or networking permitted without license from IHS -,-,- SAE AIR5682 - 7 - 2.2.4 Units All units shall be metric conforming to the Society of Automoti
46、ve Engineering Technical Standards Board Standard, TSB 003 as issued 1965-06 and revised 1999-05. 2.2.5 Atmospheric Model A Standard Atmospheric Model defined in NOAA-S/T 76-1562 U.S. Standard Atmosphere, 1976 shall be used. The Standard Day is default, however it is recognized that multiple conditi
47、ons may be used to model conditions at a particular location, region, or season. 2.2.6 Wind Model A single wind model shall be used. The model shall be defined as a given wind speed at the weapon release that is linearly decayed to 0 at -1219.2m Height Above Ellipsoid (HAE) with a constant direction
48、 throughout the profile. 2.3 CLAR Acronyms and Terminology Definitions 6DOF Six Degrees of Freedom. A mathematical model that uses the translational and rotational equations of motion, which are based upon the physical characteristics of a weapon as it interacts with the environment to estimate an impact point or approximate the LAR. AFMSS Air Force Mission Support System. Primary system utilized by the United States Air Force to plan missions. Aircraft G