1、BRITISH STANDARD OBSOLESCENT MARCH 1987 BS 185-6:1970 Incorporating Amendment No. 1 Glossary of Aeronautical and astronautical terms Section 6: Ballistic and guided missiles UDC 001.4:629.7.035.5BS185-6:1970 This British Standard, having been approved by the AerospaceIndustry StandardsCommittee, was
2、 published under the authorityofthe Executive Boardof the Institution on 21July1970 BSI 12-1999 The following BSI references relate to the work on this standard: Committee reference ACE/1 Draft for comment 67/24301 ISBN 580 06431 X A British Standard does not purport to include all the necessary pro
3、visions of a contract. Users of British Standards are responsible for their correct application. Compliance with a British Standard does not of itself confer immunity from legal obligations. Summary of pages This document comprises a front cover, an inside front cover, pages i and ii, pages 1 to 6 a
4、nd a back cover. This standard has been updated (see copyright date) and may have had amendments incorporated. This will be indicated in the amendment table on the inside front cover. Amendments issued since publication Amd. No. Date of issue Comments 1035 November 1972 Indicated by a sideline in th
5、e marginBS185-6:1970 BSI 12-1999 i Contents Page Section 6. Ballistic and guided missiles 1 Subsection 61. General 1 Subsection 62. Propulsion 2 Subsection 63. Launching 3 Subsection 64. Control 4 Subsection 65. Guidance 5ii blankBS185-6:1970 BSI 12-1999 1 (Notes on the arrangement and scope of the
6、glossary are contained in the Foreword to Section 1.) Section 6. Ballistic and guided missiles Subsection 61. General No. Term Definition 6101 ballistic missile A missile which follows a ballistic trajectory when thrust is terminated. 6102 ballistic trajectory The path followed by a projected body u
7、nder gravitational and aerodynamic forces only. 6103 ballistic wind That uniform wind which would produce the same effect upon the trajectory of a projectile as the actual wind encountered in flight. 6104 break-up The intentional breaking up of a missile structure by means which may be pre-set, self
8、-detecting or subject to remote control. 6105 characteristic velocity 1. Of a rocket propelled vehicle. The speed that a rocket propelled vehicle would attain in free field conditions (i.e. no gravitational or drag forces) by full utilization of the propellants. Also known as stage characteristic ve
9、locity. 2. Of a propellant. The ratio of the product of the chamber pressure and the throat area to the mass flow rate. 6106 control round A missile which is launched with the specific task of verifying control characteristics. 6107 dart That part of a missile which continues the mission beyond boos
10、ter separation or burnout. 6108 drone An unmanned aircraft with pre-set or remotely operated controls. separation or burnout. 6109 guidance round A missile which is hunched with the specific task of verifying guidance characteristics. 6110 guided missile A missile whose flight path can be controlled
11、 during part or all of its flight. 6111 manacle ring A circumferential clamp ring, able to transfer loads in an axial direction, providing a ready means of joining, end-to-end, two cylindrical structural sections. 6112 panoramic camera A camera using multiple exposure on the same plate to record the
12、 motion of a body. 6113 ballistic camera A panoramic camera used to record the trajectory of a high-speed body, usually a rocket. ranges 6114 all-burnt range The range of a missile to the all-burnt state. 6115 operating range The range over which a missile is capable of carrying out its function. 61
13、16 slant range The straight line distance from a specified point to a remote object. 6117 rocket A missile propelled by a rocket motor (8107). 6118 separation 1. The detachment of a missile from its launcher, or of one part of a missile from another, or the moment in time at which such detachment oc
14、curs. 2. In ground launched missile systems, the distance of the launcher from the controllers sightline. 6119 skirt An aerodynamic fairing to influence the airflow in the vicinity of the propelling nozzles.BS185-6:1970 2 BSI 12-1999 No. Term Definition Subsection 62. Propulsion 6201 afterburning Th
15、e burning of residual solid propellant in a rocket motor after the main burning and thrust have ceased. (Cf. 8464.) 6202 all-burnt The stage in the operation of a rocket motor when the propellant is effectively consumed and ceases to provide thrust. 6203 burn-out velocity The velocity attained by a
16、rocket-propelled vehicle at the all-burnt state. 6204 boost rocket motor A rocket motor, additional to the main motor, for accelerating a missile. BOOSTER MOTOR 6205 integral boost A boost rocket motor assembly which does not separate from the missile. 6206 tandem boost A boost rocket motor assembly
17、 which is located at the rear of the missile and co-axially with it. 6207 wrap-round boosts STRAP-ON BOOSTERS A number of boost rocket motor assemblies located externally along the sides of the missile body. 6208 zero stage Boost rocket motors lighting up before the integral first stage and effectiv
18、ely providing a preliminary stage in a multi-stage vehicle. burning (of solid propellants) 6209 end burning CIGARETTE BURNING Axial burning of a rocket charge, burning on all other surfaces being prevented by inhibitory coating or case-bonding. 6210 plateau burning Burning at a rate approximately in
19、dependent of pressure. 6211 progressive burning Burning of a solid propellant so shaped that the burning surface area and combustion chamber pressure steadily increase. 6212 radial burning Burning of a solid propellant so shaped that the burning surface recedes in an approximately radial direction.
20、6213 regressive burning Burning of a solid propellant so shaped that the burning surface area and combustion chamber pressure steadily decrease. 6214 chemical pressurization The pressurization of propellant tanks in a rocket by exhaust gases or by gases generated for the purpose. 6215 chuffing Inter
21、mittent burning of a rocket motor, producing an irregular noise. CHUGGING 6216 critical velocity The speed of sound in the conditions prevailing at the nozzle where the flow has a minimum cross section. 6217 delayer A substance mixed with solid rocket propellants to decrease the rate of combustion.
22、6218 equilibrium flow Gas flow in which energy is constant along streamlines and the composition of the gas at any point corresponds to that of the steady state at the temperature and pressure there prevailing. 6219 expansion ratio Of a rocket motor. The ratio of the nozzle outlet area to the nozzle
23、 throat area. 6220 expulsion system The mechanical or other means by which liquid (e.g. a liquid propellant) is expelled from its container. 6221 fuel A substance requiring oxidation for the release of its energy. 6222 grain An elongated moulding or extrusion of solid propellant for a rocket, regard
24、less of size.BS185-6:1970 BSI 12-1999 3 6223 cruciform grain Grain of cruciform cross section. 6224 star-perforated grain Grain having an axial hole, star-shape, in cross section, passing through it. impulses 6225 total impulse The time-integral of the thrust for its duration, i.e. the product of th
25、e mean thrust and the duration. 6226 specific impulse 1. Total impulse divided by the initial propellant mass. 2. The thrust per unit mass-flow rate of propellant. 6227 overall specific impulse Total impulse divided by the gross weight of the filled propulsion system. 6228 inhibitor A coating (usual
26、ly in the form of a plastics or rubber, sheath) the application of which delays or gives direction to the burning of part of a propellant charge. 6229 moderator A substance added or applied to a propellant to moderate the burning rate in the early stages of burning. 6230 modifier (ballistic) A subst
27、ance, small amounts of which can considerably alter the burning rate of a propellant. In particular, it may reduce the effects of pressure and temperature on the burning rate. 6231 propellant One or more substances used for the chemical generation of gas at the controlled rates required to provide t
28、hrust. 6232 bipropellant A liquid propellant in the form of two substances, a fuel and an oxidant, which are kept separate until their mutual chemical reaction is required. 6233 composite propellant A solid propellant containing both fuel and oxidant. 6234 double-base propellant A solid propellant i
29、n which two active components, e.g. cellulose nitrate and nitroglycerin, are blended. 6235 monopropellant Propellant in the form of a single substance requiring no additional chemical component for the production of thrust. 6236 platinized propellant A propellant whose rate of burning remains approx
30、imately constant over certain ranges of combustion chamber pressure. (See also 6210.) 6237 oxidant An oxidizing agent which promotes combustion of fuel. OXIDIZER 6238 sloshing See 8261. 6239 sustainer A motor which provides thrust after the boosts, if any, are all-burnt. 6240 sustainer motor A rocke
31、t motor that maintains the velocity of a rocket once it has achieved its initial programmed velocity. 6241 vernier engine/motor A rocket motor of small thrust used primarily to obtain free adjustment of a missiles motion. Subsection 63. Launching 6301 count-down The procedure whereby a programmed se
32、ries of pre-launch systems checks is carried out, timed in reverse numerical order, culminating in the launching of a missile or space vehicle. 6302 erector A vehicle used to support a rocket for transportation and for placing the rocket in an upright position within a gantry. No. Term DefinitionBS1
33、85-6:1970 4 BSI 12-1999 No. Term Definition 6303 launch pad The loadbearing base or platform from which a rocket vehicle is launched. PAD 6304 launcher A structure which supports a missile before and during launching. 6305 rail launcher A launcher which constrains the initial travel of a missile to
34、the line of rails. 6306 zero-length launcher A launcher which supports a missile in position at a number of discrete points from which it can be released simultaneously when the build-up of thrust is sufficient to ensure an effective launch. 6307 launching shoe SHOE 1. A launcher which carries a mis
35、sile in its launching position and may provide electrical and other services prior to launch. 2. That part of a missile support foot which makes sliding contact with the launcher rail. 6308 lift-off The initial motion of a rocket vehicle as it rises from the launch pad in a vertical ascent. 6309 pyl
36、on The structure on an aircraft which carries a launching shoe. 6310 sequence unit A device which determines the sequence of operations to effect a particular purpose, e.g. launching or separation. 6311 umbilical connector A unit through which electrical, pneumatic, hydraulic and other supplies are
37、conveyed to a rocket vehicle before it is launched. Subsection 64. Control 6401 adaptive control A form of control in which the performance is monitored and used to vary the control characteristics in such a manner that the behaviour is optimized in a changing environment. 6402 bangbang control FLIC
38、KER CONTROL A control system wherein the control, when applied, is applied to its full extent in either direction. 6403 canard controls Control surfaces which are forward of the centre of lift. 6404 cartesian control A system providing directional control about the pitch and yaw axes, generally exer
39、cised by cruciform control devices. 6405 control loop A representation of the elements in the control of a missile, including sensing elements, actuators for control surfaces, missile aerodynamic characteristics, etc. 6406 lateral control Control of the motion about the axes of a missile normal to t
40、he longitudinal axis. 6407 moving-wing control A system of control in flight in which the wings act as the principal control surfaces. 6408 polar control A system providing control about the pitch and roll axes only. TWIST AND STEER 6409 proportional control Control in which the action to correct an
41、 error is made proportional to that error. 6410 reinjection The bleeding of hot gas from the combustion chamber and its reinjection into the efflux, thus providing thrust vector control. 6411 roll-rate control A system of control which maintains the rate of roll within specified limits. 6412 roll st
42、abilization A system of control in which roll position is maintained within specified limits.BS185-6:1970 BSI 12-1999 5 No. Term Definition 6413 shaping The design procedure for modifying the system response characteristics by alterations in circuitry or other network adjustment. 6414 side thrust co
43、efficient The ratio of the side force, in a thrust vector control system, to unmodified axial thrust. 6415 thrust vector control (TVC) A system of control in which the direction of motor thrust is altered relative to the missile axes. Subsection 65. Guidance 6501 beam riding guidance A system of gui
44、dance in which a missile steers itself along the axis of a beam of radiation. 6501A capture The acquisition (14502) of a guided missile for the purpose of providing beam riding guidance. 6502 celestial guidance The guidance of a missile or spacecraft by reference to celestial bodies. 6503 command gu
45、idance A system wherein computed intelligence transmitted to a missile causes it to follow a directed path. 6504 command to line of sight A command guidance in which a missile is commanded to maintain itself on the line of sight to the target. 6505 error signal A voltage related to the difference be
46、tween the actual and desired response to a command. 6506 error wave An alternating signal produced by a guidance receiver when a missile has become displaced from its assigned course. 6507 external loop A representation of the complete sequence of events (guidance, control, target motion, etc.) in d
47、irecting a missile towards its target. 6508 field guidance Guidance of a missile to a point within a field by means of the properties of that field; the field may be either natural (e.g. gravitational) or artificial (e.g. radio). 6509 gathering phase The phase in the flight of a missile in which it
48、is brought under the influence of guidance after an unguided initial launching phase. 6510 guidance loop A representation of the guidance system of a missile. 6511 guidance receiver The receiving set in a missile which converts the received intelligence into a form suitable for feeding to the contro
49、l system. 6512 homing guidance A system wherein devices built into a missile enable it to detect and steer itself towards, or to intercept, a target. 6513 active guidance A homing guidance system wherein the missile carries both the source of radiation for illuminating the target and the receiver of the radiation reflected from the target. 6514 passive guidance A homing guidance system wherein the receiver in a missile utilizes radiations from the target. 6515 semi-active guidance A homing guidance system wherein a receiver in the missile utilizes radiations which are reflect
